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
2006051200028	20060512	00028	CE  	2006	5	12	000              	1	20060331	G	3213	51410051	BOLT            	CESSNA      		CESSNA	421   	421A        	2076012	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					RT MLG	DEPARTED        	P				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	19	849JB	2000 	2000 		NA	421A0075				WHILE TAXING TO PARK THE RT MLG LINK ASSEMBLY BOLT CAME OUT CAUSING THE UPPER AND LOWER LINKS TO SEPERATE. THE RT LANDIN	G GEAR TURNED 90 DEGREES BENDING THE GEAR DOOR COVER.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006060800442	20060608	00442	GL  	2006	6	8	000000002        	1	20060530	G	3222	2032200800	FORK            	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  										NOSE WHEEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	857PA	1544 				C0218				DISCOVERED 8 CRACKS, 4 PER SIDE APPROXIMATELY 1 INCH FORWARD OF NOSE GEAR AXLE ADJACENT TO FAIRING ATTACH POINT HOLES.						1	L	7	1 	3O			NT	TA4CH   					 
2006061300196	20060613	00196	GL  	2006	6	13	0079965A         	3	20060404	G	6114	E71693	HUB             			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										PROPELLER HUB HAS INTERNAL AND EXTERNAL CORROSION						1	L	7	2 	3O				A23CE   		5	C	P36EA	 
2007061300161	20070613	00161	NE  	2007	6	13	0089756          	3	20060203	G	6111	94LMA4	BLADE           			CESSNA	425   	425         	2076018	CE  						MCAULY	4HFR34	4HFR34C762  	NE  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								951649		CORROSION IN BLADE SHANK, NOT REPAIRABLE.						1	L	7	2 	3T			RT	A7CE    		6	C	3PNE	 
2007061300160	20070613	00160	GL  	2007	6	13	0093855          	3	20061103	G	6114	D2011	HUB             	HARTZL      		BEECH 	58    	58          	1152740	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN737		HUB CORRODED BEYOND SPEC.						1	L	7	2 	3O				3A16    		5	C	P920	 
2006062700332	20060627	00332	CE  	2006	6	27	01676201         	1	20060621	G	3213	NAS464414	BOLT            	CESSNA      		CESSNA	421   	421A        	2076012	CE  										ZONE 700	FAILED          	B			DYCR	E				ENGINE SHUTDOWN         				G			MULTIPLE FAILURE          			TX	TAXI/GRND HDL  	1			GL	07	216WA	3463 				421A0032				LANDING GEAR COLLAPSED DURING ROLLOUT AFTER LANDING. UPON INSPECTION IT WAS NOTED THAT A BOLT CONNECTING THE DOWNLOCK BE	LLCRANK TO THE UPPER STRUT ASSEMBLY HAD FAILED. THE BOLT HEAD WAS MISSING ALLOWING ALL OF THE FORCE FROM THE BELLCRANK T	O BE APPLIED DIRECTLY AND ENTIRELY TO THE FORWARD ATTACH LUG ON THE UPPER STRUT CAUSING THE LUG TO BREAK AND THE GEAR TO	 COLLAPSE. MAINTENANCE RECOMMENDS TIME CHANGE ON BOLT AND AN NDT INSPECTION OF LUGS AND SURROUNDING AREA AT THE SAME TIM	E.		1	L	7	2 	3O				A7CE    					 
2006051200038	20060512	00038	SO  	2006	5	12	0600710          	1	20060331	G	7810	89366003	EXHAUST RISER   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  	HARTZL	HCC3Y	HCC3Y*      	GL  	RT ENGINE	BROKEN          	B			BF8X	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			WP	07	572ER	2449 				4496148	L74571A	AU10894B		PILOT'S REPORTED VIBRATION IN RT ENGINE, ALSO STATED SOMETHING SEEMED LOOSE AND RATTLING. LEANED AT DIFFERENT POWER SETT	INGS WHILE IN FLIGHT WITH NO CHANGES. RETURNED TO AIRPORT WITHOUT INCIDENT. UNCOWLED RT ENGINE AND FOUND NR 2 CYLINDER E	XHAUST RISER BROKEN OFF AT MOUNT FLANGE. REPLACED WITH NEW RISER AND GASKET, OPERATIONAL CHECK GOOD.				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P25EA	 
2006091300235	20060913	00235	NM  	2006	9	13	060602           	1	20060909	G	5310	13017R	RIB             			UNIVAR	415   	415C        	0420302	NM  										CENTER SECTION	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	99325					1948				THE DEFECT WAS DISCOVERED DURING THE INITIAL COMPLIANCE WITH AD 2002-26-02 ON AN AIRCRAFT THAT HAD BEEN IN STORAGE FOR A	 NUMBER OF YEARS. AN APPROXIMATE 0.5 INCH BY 0.25 INCH AREA AT THE BOTTOM EDGE OF A LIGHTENING HOLE WAS CORRODED AND FLA	KING. A COLLECTION OF NUT SHELLS AND DEBRIS WERE FOUND NEARBY, INDICATING THAT THE CORROSION WAS PROBABLY STARTED DUE TO	 THE PRESENCE OF ANIMAL WASTE PRODUCTS AND THE BLOCKAGE OF DRAINAGE PATHS. STORAGE IN A RODENT-CONTROLLED AREA, COMBINED	 WITH PERIODIC USE OF INSPECTION HOLES (WHICH WERE INSTALLED TO COMPLY WITH THE AFOREMENTIONED AD) TO APPLY CLEANING FLU	IDS AND CORROSION PREVENTIVE COMPOUND SHOULD HELP PREVENT FUTURE RECURRENCE.	1	L	7	1 	3O				A718    					 
2006071800163	20060718	00163	CE  	2006	7	18	071106KTR        	1	20060410	G	3210	AN501A105	SCREW           			BEECH 	MU300 	400A        	1155402	CE  										LANDING GEAR	SHEARED         	B			NV2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07										UPON REMOVAL OF THE PLUNGER TUBE ASSEMBLY FROM THE LANDING GEAR CYLINDER, FOUND THE2 AN501A10-5 SCREWS THAT SECURE THE P	LUNGER TUBE HEAD TO THE PLUNGER TUBE HAD SHEARED. THE CONDITION RESULTED IN LOOSE PARTS, WHICH CAUSED ONLY MINIMAL INTER	NAL STRUT DAMAGE, AND AFFECTED THE SHOCK CHARACTERISTICS OF THE AFFECTED LANDING GEAR STUT.				2	H	7	2 	4F			RT	A16SW   					 
2006081400146	20060814	00146	CE  	2006	8	14	080106           	1	20060801	G	2910	1015802181	TUBE            			BEECH 	200   	B200        	1152922	CE  										HYD SYSTEM	DAMAGED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	6300F	538  				BB1865				DURING ROUTINE INSPECTION IT WAS DISCOVERED THAT THE PILOT SIDE RUDDER CABLE HAD BEEN RUBBING ON THE PILOTS SIDE RT BRAK	E TUBE ASSY P/N 101-580218-1 NEAR THE FORWARD END OF THE TUBE ASSY CAUSING IT TO BECOME NOTCHED.  THE DAMAGE IS TO THE E	XTENT THAT REPLACEMENT WAS REQUIRED. THIS DAMAGE WAS FOUND UNDER THE PILOTS SEAT FLOOR INSPECTION PANEL ADJACENT TO THE 	BUSS FEEDER DIODE ASSY.  THE CAUSE APPEARS TO BE IMPROPER TUBE ASSY ROUTING BY NOT ALLOWING FOR PROPER CONTROL CABLE CLE	ARANCE.  RECOMMEND INSPECTION OF THE AFFECTED AREA AND REROUTING AND OR REPLACEMENT OF BRAKE TUBE ASSY.		1	L	7	2 	4T				A24CE   					 
2006082500027	20060825	00027	GL  	2006	8	25	0823061          	3	20060823	G	6114	D2A34C98NO	HUB             	MCAULY      	D2A34C98NO  											MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	F-GAP				739321			739321		CRACKED IN BLADE SOCKET.																5	C	P3EA	 
2006061400188	20060614	00188	CE  	2006	6	14	0MKR20064        	1	20060525	G	5511	45A21104641	RIB             	BEECH       		BEECH 	MU300 	400A        	1155402	CE  										HORIZ STAB	CRACKED         	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	793TA				RK224	RK244				LT IB ROLLER SUPPORT RIB FOUND CRACKED.  P/N 45A21104-641 WAS REMOVED AND REPLACED WITH NEW.  DUE TO THE NUMBER OF THESE	 WE ARE SEEING, IT IS LIKELY THE ENTIRE 400A FLEET HAS A PROBLEM IN THIS AREA.					2	H	7	2 	4F			RT	A16SW   					 
2006012300228	20060123	00228	CE  	2006	1	23	1054822          	1	20060110	G	5341		FRAME           			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					WING ROOT	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4358N					35065	74505			FOUND CRACKS ON THE FUSELAGE SIDE OF FRAME 20 ON BOTH LT AND RT SIDE. FRAME 20 IS THE WING ATTACH POINT.  ON THE LT SIDE	 THE LENGTH OF THE CRACK WAS 1.25 INCH IN LENGTH AND ON THE RT SIDE, 1.50 INCH.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006012300229	20060123	00229	CE  	2006	1	23	10548226         	1	20060110	G	5341		FRAME           			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					WING ROOT	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4358N					35065	74505			FOUND CRACKS ON THE FUSELAGE SIDE OF FRAME 20 ON BOTH LT AND RT SIDE.  FRAME 20 IS THE WING ATTACH POINT.  ON THE LT SID	E THE LENGTH OF THE CRACK WAS 1.25 INCH IN LENGTH AND ON THE RT SIDE, 1.5 INCH.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006021400214	20060214	00214	SO  	2006	2	14	10943282         	1	20060120	G	5310		FRAME           			MAULE 	M5    	M5210C      	5460134	SO  	CONT  	IO360 	IO360*      	17025	CE  					FUSELAGE	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	314X					6134C				FOUND CRACK APPROXIMATELY .3750 INCH IN LENGTH ON RT FRAME 20 WING ATTACH POINT.						1	H	7	1 	3O	3	O		3A23    	E1CE				 
2006032300057	20060323	00057	CE  	2006	3	23	11143            	1	20060223	G	5341	251120015	FITTING         			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	81FR					081				LT AND RT WING ATTACH POINT FITTING AT FRAME 20 IS CRACKED. LT IS CRACKED APPROX. 1.0 INCHES IN LENGTH.  RT IS CRACKED A	PPROX. 1.25 INCHES IN LENGTH.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006051800253	20060518	00253	CE  	2006	5	18	11221            	1	20060414	G	5311		FRAME           			LEAR  	35    	35A         	5170602	CE  										FUSELAGE	CRACKED         	E			WTXR	K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			NM	07	98LC					077				RH FUSELAGE FRAME 20 CRACKED APPROX. 11/8 IN LENGTH AT THE AFT WING ATTACH POINT.						2	L	7	2 	4F				A10CE   					 
2006101800060	20061018	00060	CE  	2006	10	18	1538T092806      	1	20060928	G	2120	CM321110B335	DUCT            			CESSNA	421   	421B        	2076014	CE  										RIGHT	BLOWN           	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	11	1538T	1764 	176  			421B0308				CABIN BEGAN TO CLIMB AT 2000 FPM DURING CRUISE AT 12,500 FT.  DESCENT TO 10,500 FT.  CABIN WOULD ONLY MAINTAIN 2.5 PSID.	  CHECKED OUTFLOW AND SAFETY VALVES, MOISTURE DRAINS, LANDING GEAR BOOTS, FAILEADS ALL FOUND OK.  PERFORM GROUND CHECK O	F SYSTEM FOUND NO AUDIBLE LEAKS ELSEWHERE IN CABIN AND DIFFERENTIAL CHECKED OK. PERFORMED SECOND GROUND CHECK AND PULLED	 CABIN AIR VALVES ONE AT A TIME ISOLATED PROBLEM TO RIGHT SOURCE.  FOUND DUCT PARTIALLY BLOWN OFF OF SONIC VENTURI.  REM	OVED DUCT AND FOUND .7500 INCH TEAR WHERE IT PASSES THROUGH WING RIB.  MFG NO LONGER STOCKS A 33.5 DUCT, ONLY 38 INCH. -	38 CUT DOWN IN THE FIELD AND INSTALLED BOTH WINGS.  LT DUCTING REPLACED MARCH 2006.  RT DUCTING WAS FOUND AIRWORTHY AT T	1	L	7	2 	3O				A7CE    					 
2006072500184	20060725	00184	CE  	2006	7	25	15462006H1       	1	20060710	G	8010	6041H190	RELAY           			BEECH 	200   	A200        	1152921	CE  										NR 2 STARTER	BURNED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	1546					BC58				NR 2 START RELAY SHORTED TO GROUND DURING ENGINE START, APPARENTLY DUE TO WATER INCURSION OR CONTACT CORROSION. RELAY BU	RNED BUT START WAS SECURED BEFORE ADJACENT WIRE BUNDLE WAS DAMAGED. RELAY REPLACED. NEW RELAYS APPEAR TO HAVE ADDITIONAL	 SEALANT TO PREVENT THIS PROBLEM. MAY BE RELATED TO CORROSIVE ATMOSPHERE AS 2 OTHER IDENTICAL AIRCRAFT HAVE HAD SIMILAR 	FAILURES CAUSING MORE SEVERE DAMAGE AT THIS SITE.			1	L	7	2 	4T				A24CE   					 
2006051200148	20060512	00148	EU  	2006	5	12	1MAC06           	1	20060410	G	2731	T700A2740085002	CABLE           			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  	HARTZL	HCE4N	HCE4N3      	NE  	ELEV TRIM SYS	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	930MA	201  	100  			340	PM0222	HH2276		FRAYED ELEVATOR TRIM CABLE FOUND DURING 100 HR INSPECTION IN AFT FUSELAGE ACCESS PANEL.						1	L	7	1 	3T	4	T	RT	A60EU   	E4EA	5	C	P10NE	 
2006051800245	20060518	00245	NM  	2006	5	18	200600005        	1	20060427	G	5730	9006031	PANEL           			LKHEED	P3A   	P3A         	5260103	NM  										LT WING	CRACKED         	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	925AU	16997				151361				NR 2 FUEL CELL LOWER WING SKIN, PLANK NR 2 CRACKED RISER. NO SRM STANDARD REPAIR FOR THIS DAMAGE. REPAIR WILL BE ACCOMPL	ISHED IAW  EO 462557001.					2	L	7	4 	4T			RT	A32NM   					 
2006092100124	20060921	00124	WP  	2006	9	21	200600077        	1	20060919	G	2730	78213008	HINGE           			FRCHLD	C82   	C82ASTWDAVIS	3372004	WP  	PWA   	R2800 	R2800*      	52026	NE  					ZONE 300	FRACTURED       	B			KGBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	9701F					4557814				LT AND RT FURTHEST OB ELEVATOR HINGE BRACKET ON THE STABILIZER WERE BROKEN.  IT APPEARS TO BE FROM WIND GUSTS.  THE CENT	ER 3 HINGES WERE UNAFFECTED.					2	H	7	3 	4R	4	R	J	AR15    	5E8				 
2006051800254	20060518	00254	EU  	2006	5	18	20060502D        	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA					029007				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCRE	WS.		1	K	0	0 	  			RC	G24EU   					 
2006041100035	20060411	00035	SO  	2006	4	11	2006ADP001       	2	20060224	G	8530	655470A3	CYLINDER        			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21		301  				U20606365	532260			ALL SIX CYLINDERS HAVE CRACKS IN THE SAME AREA JUST ABOVE THE TOP SPARK PLUG HOLE.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2006081500012	20060815	00012		2006	8	15	2006ADP08001     	4	20060804	G	2300		ELEC CONNECTOR  			DIAMON	DA40  	DA40        	2990002	GL  											SHORTED         	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	05	38CF					40567				ADJACENT MIC AND PHONE JACKS SHORTED TOGETHER CAUSING SQUEAL IN AUDIO SYSTEM.						1	L	7	1 	3O			NT	A47CE   					 
2006092600031	20060926	00031	SO  	2006	9	26	2006ADP09001     	2	20060901	G	7497	108326841	WIRE HARNESS    			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					IGNITION SYS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	PKMAR	94   	94   			U20606231	532296			DURING INSPECTION ON A NEW, LOW TIME ENGINE, THE MT NOTICED A RATHER LARGE CRACK IN THE RT IGNITION HARNESS COVER, WHERE	 THE HARNESS ATTACHES TO THE MAGNETO.  AFTER LOOKING A LITTLE CLOSER, IT IS CLEAR THAT THE CRACK WAS THERE PRIOR TO OVER	HAUL AND PAINTING.  THIS HARNESS WAS SUPPLIED WITH THE NEW ENGINE NOTED BELOW.				1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2006041100039	20060411	00039	NE  	2006	4	11	2006F00011       	2	20060223	G	8530	327628	CYLINDER        			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  					NR 2 ENGINE	CRACKED         	I				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AL	05	444CE		2269 			45478	NK510061			NR 2 ENGINE SHUT DOWN DUE ROUGH RUNNING						2	L	7	4 	4R	4	R		6A4     	E264				 
2006080400011	20060804	00011	CE  	2006	8	4	2006F00024       	1	20060505	G	5100		CANISTER        			BEECH 	300   	300BEECH    	1152930	CE  										COWL	OPEN            	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	52LP					FA8				SMOKING ON SHUT DOWN.  OPENED RIGHT SIDE COWLING AND FOUND THE END OF THE EPA CAN COMPLETELY OPEN.  END PLATE FOUND IN B	OTTOM OF COWLING.  TT PRESUMED TO BE ORIGINAL.					2	L	7	2 	4T				A24CE   					 
2006101200119	20061012	00119		2006	10	12	2006F00042       	1	20060930	G	2612	2158	SMOKE DETECTOR  								PWA   	PT6   	PT6A42      	52043	NE  						FALSE INDICATION	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			GL	07	200E	6819 					PCE93694			LT ENGINE FIRE INDICATION IN DECENT DURING APPROACH PHASE OF FLIGHT. SHUT ENGINE DOWN.INSPECTION OF THE FIRE DETECTION S	YSTEM AND DETECTORS PROVED TO HAVE NO ISSUES, COULD NOT DUPLICATE ON GROUND RUN.										4	T			E4EA				 
2006102300076	20061023	00076	EU  	2006	10	23	2006F00048       	1	20060925	G	2841	6653505509	PROBE           			ISRAEL	1124  	1124A       	4500103	EU  										FUEL SYSTEM	MALFUNCTIONED   	E				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	09	211ST	8445 				303				PRIOR TO REFUELING AIRCRAFT, CREW NOTICED LEFT FUEL QUANTITY GAUGE WAS 1400 LBS HEAVIER THAN RIGHT.  SUBMITTED SPECIAL F	LIGHT PERMIT AND RETURNED TO BASE.  FOUND LEFT MAIN FUEL PROBE BAD.  REMOVED AND REPLACED FUEL PROBE, CALIBRATED FUEL QU	ANTITY SYSTEM.  PERFORMED FUNCTIONAL CHECK FLIGHT, NO DEFECTS NOTED.				2	M	7	2 	4F				A2SW    					 
2006010500211	20060105	00211	CE  	2006	1	5	2006FA0000002    	1	20060104	G	2497	593240101	CIRCUIT BREAKER 			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					MASTER	CORRODED        	D				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			NR	NOT REPORTED   	1			EA	01	678DB	4950 				421B0876				AVIONICS MASTER CIRCUIT BREAKER SWITCH FOUND INTERMITTENT DURING COMPLIANCE WITH AD 2005-20-05, MEB05-1.  PN 593-240-101	 NOT FOUND IN MFG PARTS MANUAL BUT THIS WAS CLEARLY THE ORIGINAL FACTORY INSTALLED CB.  PROBLEM NR1,  INTERNAL COMPONENT	S OF CB HAD SEVERE CORROSION AND WAS CONTAMINATED WITH DUST, DIRT AND SMALL INSECTS.  AIRCRAFT HAS ALWAYS BEEN HANGARED 	EXCEPT ON TRIPS.  PROBLEM NR2  MEB 05-1 AND AD 2005-20-05 DO NOT INCLUDE THIS PART NUMBER.  THE AD AND MEB REFERENCE 539	-250-101 (50 AMP BREAKER) NOT THE 40 AMP BREAKER FOUND ON ALL 421B AIRCRAFT (IAW THE MFG PARTS MANUAL).		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006010600011	20060106	00011	SO  	2006	1	6	2006FA0000003    	2	20060104	G	8550		DIPSTICK        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					OIL CAP	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5175L	168  				1542				DURING PREFLIGHT WHILE CHECKING OIL LEVEL ON DIPSTICK, ENTIRE ROD PORTION OF DIPSTICK CAME APART IN MY HANDS UPON LIFTIN	G IT OUT OF OIL FILLER TUBE.  BARELY CAUGHT IT WITH MY HAND BEFORE IT WOULD'VE FALLEN DOWN INSIDE THE ENGINE CRANKCASE W	ITH POTENTIALLY CATASTROPHIC RESULTS.  ROD IS SWAGED IN 2 PLACES ONTO A LOWER CALIBRATED AREA FOR DETERMINING OIL LEVEL 	AS WELL AS AT TOP WHERE IT AFFIXES TO DIPSTICK COVER.  IT HAS COME UNSWAGED IN BOTH UPPER AND LOWER PLACES.  IF THIS OCC	URRED IN FLIGHT, IT APPEARS A CATASTROPHIC ENGINE FAILURE COULD OCCUR AS METAL ROD PARTS FELL DOWN INTO ENG CRANKCASE/SU	MP REGION.  BELIEVE THIS DESERVES AN EMERGENCY AD.  THIS PLANE IS A 2005 - JUST A FEW MONTHS OLD!	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006011000141	20060110	00141	SO  	2006	1	10	2006FA0000004    	2	20060104	G	8550		DIPSTICK        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ENGINE	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	5175L	168  				1542				DURING PREFLIGHT WHILE CHECKING OIL LEVEL ON DIPSTICK, THE ENTIRE ROD PORTION OF THE DIPSTICK CAME APART IN MY HANDS UPO	N LIFTING IT OUT OF THE OIL FILLER TUBE. BARELY CAUGHT IT WITH MY HAND BEFORE IT WOULD'VE FALLEN DOWN INSIDE THE ENGINE 	CRANK CASE WITH POTENTIALLY CATASTROPHIC RESULTS.  ROD IS SWAGED IN 2 PLACES ONTO A LOWER CALIBRATED AREA FOR DETERMININ	G OIL LEVEL AS WELL AS AT THE TOP WHERE IT AFFIXES TO THE DIPSTICK COVER.  IT HAS COME UNSWAGED IN BOTH UPPER AND LOWER 	PLACES.  IF THIS OCCURRED IN FLIGHT, IT APPEARS A CATASTROPHIC ENGINE FAILURE COULD OCCUR AS THE METAL ROD PARTS FELL DO	WN INTO THE ENGINE CRANK CASE / SUMP REGION.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006012300226	20060123	00226	CE  	2006	1	23	2006FA0000015    	1	20060104	G	5210		DOOR            			AYRES 	S2    	S2R         	7630202	CE  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	RT CABIN DOOR	BULGED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AG	AGRICULTURE    	1			SW	15	4914X					2105R				CARBON MONOXIDE ENTRANCE INTO CABIN AREA.  INCREASED AIRSPEED RESULTING FROM THIS COMBINATION CAUSED THE RT CABIN DOOR T	O BULGE SLIGHTLY.  PILOT CONCERNS ABOUT CARBON MONOXIDE ENTRANCE INTO THE CABIN WERE CONFIRMED WITH THE USE OF CO DETECT	ORS.  RT CABIN DOOR WAS REMOVED AND SENT TO SERVICE CENTER TO BE MODIFIED TO THE 2-LATCH CONFIGURATION FOUND ON TURBINE 	AIRCRAFT.  ADDITIONAL MONITORING FOR CARBON MONOXIDE SHOWED NO FURTHER PROBLEMS.			1	L	7	1 	3R	3	R	NC	A4SW    	5E2	6	C	P719	 
2006012000107	20060120	00107	CE  	2006	1	20	2006FA0000018    	1	20060111	G	2820	12161074	SEAL            			CESSNA	182   	182M        	2072728	CE  										SELECTOR VALVE	DEFORMED        	D				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CE	07					7069					RESEALED FUEL SELECTOR VALVE PN 0716613-1 AND DURING A LEAK TEST LEAKAGE WAS FOUND FROM ONE OF THE PN 1216107-4 SEALS. I	NVESTIGATION FOUND THAT THE SEAL FACE WAS DEFORMED AND THAT MOLD LINES FROM THE INJECTION MOLDING PROCESS CAUSED VOIDS I	N THE SEALING SURFACE.				1	H	7	1 	3O			NT	3A13    					 
2006012400150	20060124	00150	GL  	2006	1	24	2006FA0000019    	1	20060109	G	3220		ROLL PIN        			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					NLG STRUT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	917AF					C0172				ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01)	 HAD WORKED OUT UNLOCKING THE ASSY.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006012400198	20060124	00198	CE  	2006	1	24	2006FA0000021    	1	20060104	G	3242	952891	BRAKE ASSY      			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					WHEEL	CORRODED        	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	07	1528D	3075 				7750				DISASSEMBLED BRAKE AND FOUND THAT THE BRAKE CYLINDER WAS CORRODED FROM WHERE THE O-RING MAKES A SEAL TO THE IB STOP. THE	 O-RING WAS HARD AND HAD TAKEN A SET.  MFG P/N 0341015.					1	H	7	1 	3R	3	R		A790    	TC121				 
2006012400118	20060124	00118		2006	1	24	2006FA0000030    	1	20060112	G	3242	244688	KEYWAY          	BFGOODRICH  																STATOR/CARRIER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										HAVE RECENTLY SEEN (4) BRAKE ASSY'S COME IN WITH THE CARRIER LINING/STATOR COMPLETELY BROKEN WITH MULTIPLE CRACKS AND DI	SCOLORED FROM WHAT APPEARS TO BE (OVERHEATED).  THESE PARTS ARE NOT LIFE LIMITED AND ARE ON CONDITION ONLY.  THEY ARE ND	I AT THE TIME OF OVERHAUL BUT WITH THE AGING FACTOR AND OVERHEAT CONDITIONS, THESE PARTS WILL CONTINUE TO FAIL AND CRACK	.  THE TABS ARE COMPLETELY SHEARING OFF AND COULD CAUSE SEVERE BRAKING FAILURE OF THE AIRCRAFT.  RE: W122086, W122087, W	121926															 
2006012400120	20060124	00120		2006	1	24	2006FA0000031    	1	20060112	G	2120		SMOKE           																	COCKPIT	DETECTED        	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	15										SMOKE IN COCKPIT FROM AUXILIARY GENERATOR OIL SPILL.  2ND TIME FOR AA MD80 IN LAST 30 DAYS.  FLIGHTS:  AA1160 12/14/05 S	FO TO DFWAA552 1/12/2006 SFO TO ORD.																		 
2006011800186	20060118	00186	CE  	2006	1	18	2006FA0000032    	1	20060112	G	2822	LW15473	PUMP            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SW	09	79LU	1821 				17281163	L3087351A			AIRCRAFT WAS PARKED FOR 3 WEEKS. FOUND FUEL/OIL MIX LEAKING FROM MUFFLER EXHAUST PIPE. FUEL LEAKED VIA GRAVITY FROM TANK	S THROUGH PUMP, INTO PUMP DRIVE LEVER AREA, THEN, VIA THE ACCESSORY SECTION INTO ENGINE . FOUND ENGINE CRANK CASE FILLED	 WITH AVGAS.  CYLINDERS WERE ALSO FULL OF GAS/OIL MIX AND WERE HYDRAULICALLY LOCKED. FUEL/OIL MIX WAS DRAINING OUT EXHAU	ST VALVES INTO MUFFLER. NOTE: FUEL DID NOT DRAIN OUT OF DRAIN PORT ON FUEL PUMP. DISASSEMBLED PUMP. DRAIN PORT WAS NOT O	BSTRUCTED.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006011800187	20060118	00187	CE  	2006	1	18	2006FA0000033    	1	20060112	G	2822	LW15473	PUMP            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SW	09	79LU	1821 				17281163	L3087351A			AIRCRAFT WAS PARKED FOR 3 WEEKS. FOUND FUEL/OIL MIX LEAKING FROM MUFFLER EXHAUST PIPE. FUEL LEAKED VIA GRAVITY FROM TANK	S THROUGH PUMP, INTO PUMP DRIVE LEVER AREA, THEN, VIA THE ACCESSORY SECTION INTO ENGINE . FOUND ENGINE CRANK CASE FILLED	 WITH AVGAS.  CYLINDERS WERE ALSO FULL OF GAS/OIL MIX AND WERE HYDRAULICALLY LOCKED. FUEL/OIL MIX WAS DRAINING OUT EXHAU	ST VALVES INTO MUFFLER.  NOTE: FUEL DID NOT DRAIN OUT OF DRAIN PORT ON FUEL PUMP. DISASSEMBLED PUMP. DRAIN PORT WAS NOT 	OBSTRUCTED.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006011700341	20060117	00341	CE  	2006	1	17	2006FA0000034    	1	20060112	G	7331	MS3126F1065	CONNECTOR       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ZONE 400	MISMARKED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07										REPLACEMENT CONNECTOR FOR RT ENGINE FUEL FLOW TRANSDUCER.  INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLO	W INDICATOR NOW OPERATES BACKWARDS.  FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROP	ERLY MARKED.  IN FACT THE MARKINGS ON THE FRONT END OF CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR.	  TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR.  PR	OBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE	 CORRECT.  NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR.	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006011700343	20060117	00343	CE  	2006	1	17	2006FA0000035    	1	20060112	G	7810	20M911	MUFFLER         			ZINAIR	CH2000	CH2000      	9950100	CE  										ENGINE	CRACKED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	15	9229	80   								TAILPIPE CRACKED WHERE WELDED TO CAN, CRACKED .7500 OF WAY AROUND TAILPIPE LETTING EXHUAST INTO CABIN HEAT SHROUD.  PART	 TOTAL TIME IN SERVE OF 80 HRS.  FOUND DURING 50 HR OIL CHANGE.					1	L	7	1 	3O			NT	TA5CH   					 
2006011700342	20060117	00342	CE  	2006	1	17	2006FA0000036    	1	20060112	G	7810	20M911	MUFFLER         			ZINAIR	CH2000	CH2000      	9950100	CE  										ENGINE	CRACKED         	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	15	9229	80   								TAILPIPE CRACKED WHERE WELDED TO CAN, CRACKED .7500 OF WAY AROUND TAILPIPE LETTING EXHAUST INTO CABIN HEAT SHROUD.  PART	 TOTAL TIME IN SERVICE OF 80 HRS.  FOUND DURING 50 HR OIL CHANGE.					1	L	7	1 	3O			NT	TA5CH   					 
2006011700347	20060117	00347	CE  	2006	1	17	2006FA0000037    	1	20060112	G	7331	MS3126F1065	CONNECTOR       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					FUEL FLOW INDICA	MISMARKED       	B				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07										PURCHASED A REPLACEMENT CONNECTOR FOR THE RT ENGINE FUEL FLOW TRANSDUCER.  INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOU	ND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS.  FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HO	LES ARE NOT PROPERLY MARKED.  IN FACT THE MARKINGS ON THE FRONT END OF THE CONNECTOR DO NOT MATCH THE MARKINGS AT THE BA	CK OF THE CONNECTOR.  TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL	 FLOW INDICATOR.  PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LO	CATION MARKINGS WERE CORRECT.  NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR.	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006011700332	20060117	00332	CE  	2006	1	17	2006FA0000038    	1	20060105	G	3230	45A3951141	UPLOCK          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					NOSE GEAR UPLOCK	INTERMITTENT    	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	21	674SF	2132 				RK232				AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND GEAR CAME UP TOO BUT RED WARNING LIGHT IN GEAR HANDLE STAYED ON AND YOU C	OULD HEAR THE DOORS WERE STILL OPEN.  SELECTED GEAR DOWN AND RETURNED TO BASE.  FOUND NOSE GEAR UPLOCK WAS INTERMITTENT.	  RIGGED UPLOCK AND OPS CHECK.				2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2006011700331	20060117	00331	CE  	2006	1	17	2006FA0000039    	1	20060105	G	3230	45A3951141	UPLOCK          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					NOSE GEAR	OUT OF RIG      	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	21	674SF	2132 				RK232				AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND GEAR CAME UP TO BUT RED WARNING LIGHT IN GEAR HANDLE STAYED ON AND YOU CO	ULD HEAR THE DOORS WERE STILL OPEN.  SELECTED GEAR DOWN AND RETURNED TO BASE.  FOUND NOSE GEAR UPLOCK WAS INTERMITTENT. 	 RIGGED UP LOCK AND OPS CHECK GEAR.				2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2006021400247	20060214	00247		2006	2	14	2006FA0000040    	4	20060113	G	3416		ALTIMETER       			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					INSTRUMENT PANEL	ERRATIC         	G				K				NONE                    				S	E		AFFECT SYSTEMS            	VIBRATION/BUFFET          		CR	CRUISE         	1			WP	23	1836U	65   				T20608548				AT TAKEOFF POWER (2500 RPM) AND CRUISE OVER 2390 RPM, THE STANDBY ALTIMETER MAY OSCILLATE 20 FT TO 100 FT (3500 FT CRUIS	E ALTITUDE).AT CRUISE, THE AUTOPILOT UNCOUPLED ITSELF THREE TIMES.DESCENT AND APPROACH (BELOW 2390 RPM) OSC. WAS 20 TO 4	0 FEET. BELOW 2300 RPM THE ALT. WAS STEADY.GARMIN 1000 EFIS INSTALLATION HAS THE STNBY ALTIMETER HARD MOUNTED TO A LARGE	 INSTRUMENT PANEL WITH NO VIBRATION DAMPENING MECHANISM. DURING CRUISE, WHEN THE ALTIMETER WAS OSCILLATING THE GREATEST,	 APPLYING MODERATE HAND PRESSURE (APPX. 10 LBS.) TO THE INSTRUMENT PANEL LESSENED THE AMOUNT OF OSCILLATION.THE AUTOPILO	T CONTROL PANEL (HARD MOUNTED BELOW THE STANDBY ALTIMETER) CONTAINS AN ANEROID SIMILAR TO ONE IN THE STANDBY ALTIMETER.	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2006011700340	20060117	00340	CE  	2006	1	17	2006FA0000041    	1	20060112	G	7331	MS3126F1065	CONNECTOR       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ZONE 400	MISMARKED       	B				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07										WE PURCHASED A REPLACEMENT CONNECTOR FOR THE RT ENGINE FUEL FLOW TRANSDUCER.  INSTALLED NEW CONNECTOR AND UPON CHECKOUT 	FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS.  FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN	 HOLES ARE NOT PROPERLY MARKED.  IN FACT THE MARKINGS ON THE FRONT END OF THE CONNECTOR DO NOT MATCH THE MARKINGS AT THE	 BACK OF THE CONNECTOR.  TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE F	UEL FLOW INDICATOR.  PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN	 LOCATION MARKINGS WERE CORRECT.  NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR.	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2006021400229	20060214	00229		2006	2	14	2006FA0000042    	4	20060117	G	2350	0110040110	AUDIO PANEL     			DIAMON	DA20  	DA20C1      	2990001	GL  										RADIO PANEL	BURNED          	B				K				NONE                    				B	W		SMOKE/FUMES/ODORS/SPARKS  	INADEQUATE Q C            		IN	INSP/MAINT     	1			NE	03	176MA	18   				C0345				AIRCRAFT HEADSET MICROPHONE JACKS ARE UNIQUILY WIRED FOR SENNHIESER ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE M	ICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERANTLY THAN SHOWN IN MFG GMA-340 INSTALLATION MANUAL. USE OF STANDARD AI	RCRAFT HANDHELD MIC IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OF GMA-340 UNIT	 RESULTING IN A COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFGR AS (HEADSET MI	CROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE 	IN A STANDARD AIRCRAFT JACK, SHOULD NOT CAUSE TOTAL LOSS OF AC COMMUNICATIONS.	1	L	7	1 	3O			NT	TA4CH   					 
2006021400230	20060214	00230		2006	2	14	2006FA0000043    	4	20060117	G	2350	0110040110	AUDIO PANEL     			DIAMON	DA20  	DA20C1      	2990001	GL  										RADIO PANEL	BURNED          	B				K				NONE                    				B	W		SMOKE/FUMES/ODORS/SPARKS  	INADEQUATE Q C            		IN	INSP/MAINT     	1			NE	03	176MA	18   				C0345				AC HEADSET MICROPHONE JACKS ARE UNIQUELY WIRED FOR SENNHIESER ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPH	ONE JACK KEY TERMINAL. THIS IS WIRED DIFFERENTLY THAN SHOWN IN GARMIN'S GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIR	CRAFT HANDHELD MIC. IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OFN GMA-340 UNI	T RESULTING IN COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFGR AS (HEADSET MIC	ROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE I	N A STANDARD AC JACK, SHOULD NOT CAUSE TOTAL LOSS OF AC COMMUNICATIONS.	1	L	7	1 	3O			NT	TA4CH   					 
2006021400245	20060214	00245		2006	2	14	2006FA0000044    	4	20060117	G	2350	0110040110	AUDIO PANEL     			DIAMON	DA20  	DA20C1      	2990001	GL  										RADIO PANEL	BURNED          	B				K				NONE                    				B	W		SMOKE/FUMES/ODORS/SPARKS  	INADEQUATE Q C            		UK	UNKNOWN        	1			NE	03	176MA	18   				C0345				AIRCRAFT HEADSET MICROPHONE JACKS ARE UNIQUILY WIRED FOR ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE J	ACK KEY TERMINAL. THIS IS WIRED DIFFERANTLY THAN SHOWN IN MFG GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HAND	HELD MIC IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OFN GMA-340 UNIT RESULTING	 IN COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFG AS (HEADSET MICROPHONE ONLY	), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD	 AIRCRAFT JACK, SHOULD NOT CAUSE TOTAL LOSS OF AIRCRAFT COMMUNICATIONS.	1	L	7	1 	3O			NT	TA4CH   					 
2006012600032	20060126	00032	SO  	2006	1	26	2006FA0000045    	2	20060118	G	7414	10357586	DISTRIBUTOR GEAR	TELEDYNESYST	S6LSC25     	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  					MAGNETO	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	4718K	175  			D04HA269R	R1722017	288769			ELEVEN GEAR TEETH FAILED ON NYLON DISTRIBUTOR GEAR.						1	H	7	1 	3O	3	O		3A17    	E1CE				 
2006012600091	20060126	00091	SO  	2006	1	26	2006FA0000046    	1	20060111	G	5310	12034535003	WINDOW FRAME    			EMB   	120   	EMB120RT    	3260202	SO  	PWA   	118   	PW118       	 	NE  					RT COCKPIT	CRACKED         	B			OWFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	200CD	26579				120200				COPILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT RT WINDSHIELD AFT BEAM.  NORMAL OPS.  (K)						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2006012400192	20060124	00192	SO  	2006	1	24	2006FA0000047    	1	20060111	G	5310	12034535001	WINDOW FRAME    			EMB   	120   	EMB120RT    	3260202	SO  	PWA   	118   	PW118       	 	NE  					LT COCKPIT	CRACKED         	B			OWFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	196CA	28588				120196				PILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LEFT WINDSHIELD AFT BEAM.  NORMAL OPS.  (K)						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2006012000102	20060120	00102	SO  	2006	1	20	2006FA0000050    	2	20060110	G	8530	1864321	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	8195R					TH529	299141R			ENGINE CYLINDER CRACKED AND BARREL AND HEAD.						1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006012600099	20060126	00099	SO  	2006	1	26	2006FA0000051    	2	20060110	G	8530	1847312	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	8195R	611  				TH529	299141R			ENGINE CYLINDER CRACKED AT BARREL AND HEAD.  (K)						1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006012600096	20060126	00096	NE  	2006	1	26	2006FA0000053    	2	20060107	G	8520	LW13923	PISTON          			MAULE 	M7    	M7235       	5460170	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	9234N	1078 				4119C	L2492048A			INSPECTION OF THE OIL FILTER DURING ROUTINE OIL CHANGE FOUND 2 EA (.1250 INCH) DIAMETER PIECES OF ALUMINUM.  FURTHER DIS	ASSEMBLY OF THE ENGINE/ CYLINDERS FOUND THE NR 1 CYLINDER PISTON SKIRT WAS MISSING A SECTION (.5 INCH X 1.1250 INCH LONG	).  PERFORMED A DY PENETRANT INSP TO THE OTHER PISTONS.  3 WERE CRACKED AT THE SAME LOCATION.  1 HAD INDICATION OF POSSI	BLE CRACK AND 1 WAS IN SERVICEABLE CONDITION.  NO OTHER DAMAGE TO THE PISTON WAS DIAMETER WAS WITHIN SERVICE LIMITS.  CY	LINDER DIAMETER WAS WITHIN SERVICE LIMITS.  (K)		1	H	7	1 	3O	3	O	NC	3A23    	1E4				 
2006012600086	20060126	00086	WP  	2006	1	26	2006FA0000055    	2	20060109	G	7261	30745732	CARBON SEAL     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	411AJ	747  				2011	P116515			PERFORMED SOAP SAMPLE DUE TO FILTER BYPASSED.  SAMPLE CAME BACK NORMAL.  PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AN	D FILTER FAILED DELTA P-CHECK.  RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) INSTALLED LOANER ENGINE.  ORIGINAL E	NGINE HAD NR 1, NR 3, NR 4 AND NR 5 CARBON SEALS REPLACED.  RE-INSTALLED ORIGINAL ENGINE AFTER REPAIRE.  25 HOUR SOAP SA	MPLE RESULTS ARE NORMAL.  PROBABLE CAUSE IS PREMATURE WEAR/FAILURE OF CARBON SEALS.  RECOMMEND IMPROVING CARBON SEAL MAT	ERIAL AND QUALITY. (K)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006012600102	20060126	00102	WP  	2006	1	26	2006FA0000056    	2	20060109	G	7261	30745742	CARBON SEAL     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	411AJ	747  				2011	P116515			PERFORMED SOAP SAMBLE DUE TO FILTER BYPASSED.  SAMPLE CAME BACK NORMAL.  PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AN	D FILTER FAILED DELTA P-CHECK.  RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY).  INSTALLED LOANER ENGINE.  ORIGINAL	 ENGINE HAD NR1, NR3, NR4 AND NR5 CARBON SEALS REPLACED.  REINSTALLED ORIGINAL ENGINE AFTER REPAIR.  25 HOUR SOAP SAMPLE	 RESULTS ARE NORMAL.  PROBABLE CAUSE IS PREMATURE WEAR/FAILURE OF CARBON SEALS.  RECOMMEND IMPROVING CARBON SEAL MATERIA	L AND QUALITY.  (K)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006012600103	20060126	00103	SO  	2006	1	26	2006FA0000057    	1	20060112	G	5751	6538834	BALANCE WEIGHT  			PIPER 	PA28  	PA28150     	7102804	SO  	LYC   	O320  	O320*       	41508	EA  					LT AILERON	BROKEN          	D			V36R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	5105W					28122				REMOVED EXISTING BALANCE WEIGHT ASSEMBLY, PN 65388-34 ON THE LT AILERON AND REPLACED WITH A SERVICEABLE BALANCE WEIGHT A	SSEMBLY OF THE SAME PN AND WEIGHT.  AT ANNUAL INSPECTION, THE WEIGHT WAS FOUND BROKEN OFF AT THE ATTACHMENT TUBE.  THE E	XISTING RIVET PATTERN WAS REUSED.  SINCE THE WEIGHT AND ATTACHMENT POINTS WERE IDENTICAL BETWEEN THE ASSEMBLIES, THERE W	AS NO CHANGE TO THE WEIGHT AND BALANCE.  THE PILOT DID NOT NOTICE ANY DIFFERENCE IN THE HANDLING OF THE RESPONSE OF THE 	AC PRIOR TO THE REPAIR.  THE BROKEN OFF WEIGHT WAS FOUND IN THE WING BETWEEN THE OUTER RIB AND THE ADJACENT IB RIB.  (K)		1	L	7	1 	3O	3	O		2A13    	E274				 
2006012600089	20060126	00089	NM  	2006	1	26	2006FA0000058    	1	20060102	G	2910		VENT LINE       			CHRIS 	HUSKY 	A1          	221020X	NM  	LYC   	O360  	O360*       	41514	EA  					FUEL VENT	BLOCKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	9622V					1154				BOTH LT FUEL VENT LINES BLOCKED BY ICE.  ENGINE STOPPED DURING TAXI TO RUNWAY.  ALTHOUGH PREFLIGHT LISTS CHECKING FUEL V	ENT LINES ARE CLEAR, THIS NEEDS TO BE EMPHASIZED MORE.  (K)					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2006012600087	20060126	00087	CE  	2006	1	26	2006FA0000060    	1	20060105	G	5752	AA50723	BUSHING         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					AILERON TRIM	WORN            	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	376W	517  				TH1970				AILERON TRIM MADE POPPING NOISE AS CONTROL WAS ROTATED.  FOUND BUSHING FOR CONTROL SHAFT IN PEDESTAL SEVERELY WORN ALLOW	ING U-JOINT TO CONTACT STRUCTURE AS CONTROL WAS ROTATED.  TRIM CABLE TENSION WAS WITHIN LIMITS, NO REASON FOR ACCELERATE	D WEAR NOTED.  BUSHING IS OILITE TYPE AND NO LUBRICATION IS CALLED FOR. (K)				1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006013100211	20060131	00211		2006	1	31	2006FA0000064    	1	20060112	G	5100		CASE            																	UNKNOWN	LEAKING         	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09										IVSI WAS RECEIVED FOR REPAIR OF A CASE LEAK EXCEEDING MFG TOLERANCES.  (RC-60-VIL1) MFG ACCEPTABLE SEALANT FOR DASHPOT C	YL ENDS AND FOR FEED-IN-FLANGE MNTG SCREW HEADS IS RED GLYPTAL.  5-MIN EXPOXY WAS APPLIED TO END CAPS AND FITTING FLANGE	.  5-MIN EXPOXY HAS BEEN APPLIED OVER SCREW HEADS AND AROUND FITTING FLANGE THAT ATTACHES FEED-IN TUBE FROM DASHPOT ASSY	 TO REAR OF THE INSTRMT CASE, ALSO PACKED AROUND FEED-IN TUBE ITSELF. THIS METHOD OF SEALING WITH EXPOXY RATHER GYPTAL M	AKES IT DIFFICULT TO FURTHER REPAIR THIS IVSI W/O DESTROYING DASHPOT FEED-IN TUBE.  NATURE OF EPOXY, IT DOES NOT ALLOW F	LEXING AT JOINT, NOT RESPONSIVE TO CHANGE IN TEMP.  OVER TIME IT MAY PULL AWAY FROM ONE SURFACE AND ALLOW LEAKAGE.  (K)														 
2006012400176	20060124	00176	SO  	2006	1	24	2006FA0000065    	1	20060111	G	5310	12034535001	WINDOW FRAME    			EMB   	120   	EMB120RT    	3260202	SO  	PWA   	118   	PW118       	 	NE  					WINDSHIELD	CRACKED         	B			OWFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	200CD	26579				120200				PILOT`S SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LT WINDSHIELD AFT BEAM.  NORMAL OPERATIONS.  (K)						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2006013100220	20060131	00220	SW  	2006	1	31	2006FA0000066    	1	20060111	G	5320	K660000	ANGLE           			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					FUSELAGE	MISLOCATED      	D			MV5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	7895G					96070				JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENE	R.  (K)					1	H	7	2 	4T	3	T		2A4     	E2WE				 
2006013100215	20060131	00215	SW  	2006	1	31	2006FA0000067    	1	20060111	G	5320	K6600006	ANGLE           			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					FUSELAGE	MISLOCATED      	D			MV5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	7896G					96070				JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENE	R.  (K)					1	H	7	2 	4T	3	T		2A4     	E2WE				 
2006012600106	20060126	00106	SW  	2006	1	26	2006FA0000068    	1	20060111	G	5320	K6600005	ANGLE           			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					FUSELAGE	MISLOCATED      	D			MV5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	7896G					96070				JOGGLE IN PRAT NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENE	R.  (K)					1	H	7	2 	4T	3	T		2A4     	E2WE				 
2006012600107	20060126	00107	SW  	2006	1	26	2006FA0000069    	1	20060111	G	5320	K6600004	ANGLE           			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					FUSELAGE	MISLOCATED      	D			MV5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	7896G					96070				JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENE	R.  (K)					1	H	7	2 	4T	3	T		2A4     	E2WE				 
2006012400186	20060124	00186	NM  	2006	1	24	2006FA0000071    	1	20060102	G	3213	40005401	CYLINDER        			PIPER 	PA60  	PA60601P    	7106012	NM  										MLG STRUT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	91VK	4148 				61P06157963				COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BRAZED OR SILVER SOLDERED TOGETHER 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 WHERE PART IS MACHINED FOR CLEARANCE ON TORQUE LINKS.  	(K)			1	M	7	2 	3O			RT	A17WE   					 
2006012600082	20060126	00082	NE  	2006	1	26	2006FA0000076    	2	20060116	G	7230	2292260060	TURBINE WHEEL   			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					GAS GENERATOR	MIGRATED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	352SA				01018	3348	22396			DURING A ROUTINE 600 HR BORESCOPE INSP OF THE GAS GENERATOR TURBINE BLADES, 2 BLADES WERE FOUND TO HAVE MOVED AFT IN THE	IR (FIR-TREE) TYPE MOUNTS IN THE TURBINE DISK.  1 BLADE WAS FOUND TO HAVE MOVED .1250-.2500 INCH, AND THE OTHER LESS THA	N .1250 INCH.  THE BLADES HAD TO MOVE PAST A RETAINING CLIP TO ACHIEVE THE AMOUNT OF MOVEMENT OBSERVED.  THIS TYPE OF DE	FECT IS NOT LISTED AS A POSSIBLE DEFECT IN THE ENGINE MM AND SMALL AMOUNTS OF INSP REGIME.  DUE TO THE POTENTIAL EFFECTS	 OF THE RECOMMEND A BORESCOPE INSP OF THE BLADE ALIGNMENT BEFORE FURTHER FLIGHT AND AT AN INTERVAL OF 300 HOURS ENGINE I	S BEING RETURNED TO MFG.  (K)	1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006012600078	20060126	00078	SO  	2006	1	26	2006FA0000077    	2	20060116	G	8530	SA52000	CYLINDER HEAD   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE	SEPARATED       	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	7209B	992  				TH1428	280384R			APPEAR THAT THERE WAS A CRACK IN THE CYLINDER HEAD AT THE EXHAUST VALVE SEAT, WHICH PROPOGATED DURING OPERATION UNTIL TH	E CYLINDER HEAD FAILED AND SEPARATED FROM THE CYLINDER.  (K)					1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006012600009	20060126	00009	CE  	2006	1	26	2006FA0000078    	1	20060103	G	2823	25CX1123AC	LEVER           			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL TRANSFER	CORRODED        	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	71MT	8865 				258230				FOUND WING FUEL TRANSFER LEVER ASSY CORRODED AT FORKED END.  THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A	 DIRECT LUBE ITEM.  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006013000071	20060130	00071	CE  	2006	1	30	2006FA0000079    	1	20060105	G	2823		LEVER           			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL TRANSFER	CORRODED        	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	75MT	8527 				258231				FOUND WING FUEL TRANSFER LEVER ASSY CORRODED AT THE FORK END.  THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT	 A DIRECT LUBE ITEM.  (CE09200602408)  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006013000072	20060130	00072	CE  	2006	1	30	2006FA0000080    	1	20060105	G	2823	25CX1123AC	LEVER           			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL TRANSFER	CORRODED        	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	954H	5819 				258259				FOUND WING FUEL TRANSFER LEVER CORRODED AT BOTH ENDS.  THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIREC	T LUBE ITEM.  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006012600079	20060126	00079	CE  	2006	1	26	2006FA0000081    	1	20060108	G	3250	0543022	ROD             			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300*       	17022	SO  					LT STEERING	RUSTED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	9852T					47652				ROD END FAILED.  AIRCRAFT TURNED LT AND IMPACTED AN EMBANKMENT.  SMALL AMOUNT OF RUST ON ROD END AT THE THREADED AREA. (	K)					1	H	7	1 	3O	3	O		3A12    	E253				 
2006013000074	20060130	00074	EU  	2006	1	30	2006FA0000082    	1	20060109	G	4940		SWITCH          			HWKSLY	DH125 	BH125400A   	4230138	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					APU START PANEL	PILOT ERROR     	H				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	03	125CK					25266				PILOT MISTAKENLY TRIPPED THE APU FIRE EXTINGUISHER SWITCH INSTEAD OF THE APU START SWITCH.  BOTH SWITCHES ARE OF THE SAM	E STYLE, ARE LOCATED CLOSE TOGETHER AND BOTH HAVE THE SAME STYLE OF RED GUARDED SWITCHES.  (K)					2	L	7	2 	4J	4	F		A3EU    	E6WE				 
2006013100175	20060131	00175	SW  	2006	1	31	2006FA0000083    	1	20060102	G	5751	250000225	SKIN            			GULSTM	690TP 	690B        	7630516	SW  										RT WING AILERON	CORRODED        	B			MV5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	690LL					11544				CORROSION BEYOND 10 PERCENT LIMITS IN LEADING EDGE SKIN UNDER BALANCE WEIGHTS.  FOUND DURING SB238. (K)						1	H	7	2 	3T				2A4     					 
2006013000075	20060130	00075	SO  	2006	1	30	2006FA0000084    	2	20060110	G	8530	196279	CYLINDER HEAD   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	8195R	611  				TH529				ENGINE CYLINDER CRACKED AT BARREL AND HEAD.  (K)						1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006012600047	20060126	00047	SO  	2006	1	26	2006FA0000086    	1	20060112	G	3244	304K632	TIRE            			EMB   	135   	EMB135BJ    	3260306	SO  										MLG	LEAKING         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25										AFTER INSTALLING NEW TIRE ON WHEEL ASSEMBLY AND INFLATING, THE TIRE WAS DISCOVERED TO BE LEAKING AT ALL SIDEWALL WEEP HO	LES.  THIS CONDITION CONTINUED EVEN AFTER THE 12 HOUR LEAK CHECK TIME HAD EXPIRED.  (K)					2	L	7	2 	4F			RT	        					 
2006020700205	20060207	00205	EA  	2006	2	7	2006FA0000087    	2	20060120	G	7324		POPPET VALVE    	LYC         	63323440ASY 	CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	STICKING        	B				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	07	575TW	33   	33   		0A10933	172S10078	L3241851E			AIRCRAFT WOULD NOT START. ENGINE & FUEL COLD SOAKED (JUST AT BELOW 32 DEG. F). THE FLOW DIVIDER POPPET VALVE WOULD STICK	 CLOSED AND PREVENT FUEL FLOW.  AFTER TROUBLSHOOTING DETERMINED THAT UNIT WOULD STICK IN  CLOSED AND OPEN POS. THE CLOSE	D POS. PREVENTS FUEL FLOW TO NOZZLES. FOUND IF UNIT WAS COOLED ON THE BENCH WITHOUT FUEL IN THE DIVIDER THE POPPET VALVE	 WOULD STILL STICK. SUSPECT MFG TOLERANCES BAD ON POPPET ASSY. TRIED DUPLICATING ON AN AIRCRAFT  1 1/2 YEARS OLDER. COUL	D NOT DUPLICATE. HOWEVER, COULD DUPLICATE ON AN AIRCRAFT WHO'S SERIAL NUMBER IS IN CLOSE TO THE SQUAWKED AIRCRAFT. APPEA	RS TO BE A SPECIFIC LOT NUMBER OF EFFECTED PARTS.  HEAT FROM RUNNING ENGINE RUNNING KEEPS VALVE MOVING FREELY.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006022400186	20060224	00186	CE  	2006	2	24	2006FA0000088    	1	20060124	G	5610	45AS3101011	WINDOW          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					COCKPIT	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	674SF	2141 				RK232				DURING INSPECTION, THE PILOTS SIDE WINDOW WAS FOUND TO BE CRACKED THROUGH THE OUTER PANE CONNECTING 5 BOLT HOLES ALONG T	HE TOP OF WINDOW.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006013100199	20060131	00199	CE  	2006	1	31	2006FA0000090    	1	20060106	G	3240	07515500	PLATE           			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A27      	52043	EA  					BRAKE CYLINDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	200RE	8273 				LW164				DURING A PHASE I AND II INSPECTION A CRACK WAS FOUND IN THIS PART ATTACHED TO THE RT GEAR ASSY.  THE CRACK IS ON THE TOR	QUE PLATE UPPER FORWARD BRAKE CYLINDER PIN ATTACH HOLE.  A BUSHING INSTALLED IN THIS HOLE HAS NO SIGN OF DAMAGE.  PROBAB	LE CAUSE OF CRACKING WOULD BE STRESS RELATED.  (K)				1	L	7	2 	3T	4	T		3A20    	E4EA				 
2006013100164	20060131	00164	SW  	2006	1	31	2006FA0000092    	1	20060113	G	7810		RISER           			GULSTM	112   	114         	7630314	SW  										EXHAUST	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	4775W	207  				14105				TURBO SYSTEM INSTALLED IAW STL, BOTH LT AND RT EXHAUST RISERS HAD MANY CRACKS AND DEEMED UNSERVICEABLE.  207.8 HRS SINCE	 NEW, REPLACED UNITS FAILED IN 140.0 MORE.  (K)					1	L	7	1 	3O				A12SO   					 
2006012700069	20060127	00069	NM  	2006	1	27	2006FA0000093    	1	20060126	G	3231		SHEAR PIN       	DORNER      		DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  						BROKEN          	E				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	25	328GT					3183				CREW REPORTED DURING GEAR RETRACTION THEY HEARD AND FELT A VIBRATION FROM NOSE GEAR DOOR NOT CLOSING FULLY.  DURING INSP	ECTION THE RIGHT HAND FORWARD GEAR DOOR BREAKING ROD ASSEMBLY WAS FOUND TO HAVE A BROKEN SHEAR PIN.					2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006013100206	20060131	00206		2006	1	31	2006FA0000094    	4	20060129	G	2562	AK450	TRANSMITTER     			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ELT	DETERIORATED    	B			NT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	201CD					240063				ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING. UNIT HAD BATTERIES REPLACED.  DURING TEST	ING THE UNIT MADE A WEAK SIGNAL OUTPUT AND HAS NO RANGE.  USED DIFFERENT SET OF BATTERIES FOR RETESTING, SAME RESULTS.  	HOOKED BACK IN AIRCRAFT TO AIRCRAFT ANTENNA, TEST RESULTS THE SAME.  ARMED UNIT AND TESTED THROUGH REMOTE MOUNTED SWITCH	 WITH SAME UNSATISFACTORY RESULTS.  UNIT IS APPROXIMATELY 2 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				 
2006013100173	20060131	00173		2006	1	31	2006FA0000096    	4	20060117	G	2562		TRANSMITTER     			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					ELT	INTERMITTENT    	B			NT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	2164K	532  			455647	290172				ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING.  UPON TEST WITH BATTERIES REPLACED.  THE 	UNIT ON/OFF WAS INTERMITTENT AND THE REMOTE OPERATION WAS INTERMITTENT.  UNIT IS APPROXIMATELY 7 YEARS OLD.   TREND OF F	AILURES ON THIS MAKE AND MODEL OF ELT.  SUSPECT INTERNAL DETERIORATION OF COMPONENT SECURITY.  (K)				1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2006013100176	20060131	00176	CE  	2006	1	31	2006FA0000098    	1	20060124	G	3340	RN24885023	LENS            			LEAR  	35    	36LEAR      	5170601	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					TAIL STROBELIGHT	SPLIT           	B			BHKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	83FN					007				FAA/PMA APPROVED REPLACEMENT SPLITS/CRACKS ON INSTALL.  SHAPE IS SLIGHTLY DIFFERENT FROM PN 248850237.  (K)						2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006013100191	20060131	00191		2006	1	31	2006FA0000099    	2	20060123	G	7414	BL3492901	MAGNETO         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										SHOWER OF SPARKS DOESN`T WORK IAW TEST CELL.  (K)																			 
2006013100167	20060131	00167		2006	1	31	2006FA0000100    	1	20060123	G	7921	G05448292	OIL COOLER      																		CRACKED         	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										CRACKED FOOT ON OIL COOLER.  (K)																			 
2006013100192	20060131	00192	CE  	2006	1	31	2006FA0000101    	1	20060107	G	3210	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T					CE1350				MECHANIC REMOVED NEW RELAY FROM STOCK AND INSTALLED ON AIRCRAFT AND GEAR FAILED TO EXTEND, AFTER TAPPING ON THE TOP OF R	ELAY GEAR WENT DOWN.  MECHANIC THEN INSTALLS ANOTHER NEW RELAY FROM STOCK AND SYSTEM OPERATED NORMAL.  PROBABLE CAUSE AT	 THIS TIME UNKNOWN.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006020200122	20060202	00122	SO  	2006	2	2	2006FA0000102    	1	20060124	G	3210	40288000	TRUNNION        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					RT MLG	CRACKED         	E			IPMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	111KV	10500				31T7920035				DURING 100 HOUR INSPECTION FOUND CRACK IN WEB OF AFT MLG TRUNNION ASSY AIRCRAFT.  (K)						1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2006020200108	20060202	00108		2006	2	2	2006FA0000103    	4	20060109	G	6113	C30031	PLATE           													HARTZL	HCB3T	HCB3TN3     	GL  	SPINNER	FAILED          	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19								BUA26690		SPINNER SUPPORT PLATES RECEIVED BROKEN WITH BOLTS STILL INSTALLED ON HUB, NO OTHER BROKEN PARTS OF THIS SUPPORT PLATE AS	SY WERE FOUND ON THIS PROPELLER. (K)															6	C	P15EA	 
2006020200105	20060202	00105	SO  	2006	2	2	2006FA0000104    	1	20060121	G	3610	J301300AR	COUPLING        			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					BLEED AIR DUCT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	327TL					1339				WITH APU RUNNING AND BLEED AIR SELECTED ON, COUPLING FAILED CAUSING DUCT TO SEPARATE.  PROBABLE CAUSE UNKNOWN.  SUGGEST 	MORE AGGRESSIVE LOCKING MECHANISM.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006020200143	20060202	00143	EA  	2006	2	2	2006FA0000106    	2	20060123	G	7314		SEAL            			AMTR  	SKYSMI	SMITHMINIPLA	05625N3	GL  	LYC   	O540  	TIO540J2BD  	41532	EA  					PUMP SHAFT	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	11NS	43   			HKN023FP	61P0343102	L829261A			WITH THE ENGINE OFF AND THE FUEL BOOST PUMP ON , A STEADY STREAM OF FUEL CAME OUT THE ENGINE DRIVEN FUEL PUMP SHAFT SEAL	 DRAIN HOSE.  THE FUEL CONTINUED TO FLOW OUT THE DRAIN HOSE AFTER THE ENGINE WAS STARTED.  THIS IS NOT THE FIRST INSTANC	E OF LEAKS WITH THIS MODEL PUMP.  THIS IS A RELATIVELY NEW DESIGN PUMP.  PUMP WAS RETURNED TO THE MFG FOR WARRANTY.  (K)				1	B	7	1 	3O	3	O	NC	EXPA1B71	E14EA				 
2006020200144	20060202	00144	EU  	2006	2	2	2006FA0000107    	1	20060120	G	2822	568127202	PUMP            			AIRBUS	320   	A320*       	       	EU  										FUEL SYS	INOPERATIVE     	B			G7EY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35										ONE FUEL PUMP WAS RETURNED FOR INSPECTION/REPAIR DUE TO A FAULT AND ASSOCIATED CB TRIP FOR LT WING TANK PUMP 2.  ONE OF 	TWO NUTS HOLDING THE HOUSING BERING ASSY TO THE STATOR CAP BECAME LOOSE.  THE ASSOCIATED SCREW DROPPED INTO THE STATOR W	INDING, CAUSING ARCING.  THE FLAME TRAP WAS BREACHED.  DUE TO THE HOLE LEFT IN THE STATOR HOUSING BY THE MIGRATION OF TH	E SCREW.  THIS LEFT A DIRECT PATH TO THE FUEL.  THE MFG HAS ALSO BEEN INFORMED.  (K)			2	L	7	2 	4F			RT	A46NM   					 
2006020200128	20060202	00128	CE  	2006	2	2	2006FA0000108    	1	20060116	G	2823		CONTROL CABLE   			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					AFT FUEL SELECT	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	38US					18281173	L2858348			AT AC STA 22 LWS 3 INCHES, 3.75 INCHES BELOW CABIN FLOOR, ELEVATOR TRIM CONTROL CABLES CHAFING HARD ON BOTTOM SURFACE OF	 .2500 DIA FUEL TUBE AT LEFT AND AFT OF AIRCRAFT FUEL SELECTOR.  IF LEFT CONTROL CABLE WILL CUT THRU FUEL TUBE  (CAUSE) 	NOT SEEN AT FACTORY.  REPOSITIONED FUEL TUBE UP AWAY FROM CONTROLS.  (NE03200606762) (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2006020200103	20060202	00103	CE  	2006	2	2	2006FA0000109    	1	20060118	G	8011	642087A64	ADAPTER         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					STARTER ADAPTER	WRONG PART      	B			MQ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	268EA	4    				E3473	685983			AIRCRAFT CAME TO OUR SHOP WITH SMOKE AND OIL COMING OUT OF TAIL PIPE.  4 HOURS PRIOR, THE AIRCRAFT ANNUAL INSP WAS COMPL	ETED AND AT THAT TIME THE STARTER ADAPTOR WAS REPLACED WITH THE WRONG PART.  THIS AC HAD BEEN MODIFIED BY  STC WITH TORN	ADO ALLEY TURBO CHARGER SYS.  THE STC REQUIRED THAT STARTER ADAPTER ASSEMBLY BE CHANGED TO PN 642087A63 THAT INCLUDES A 	OIL SCAVENGE PUMP.  PN A2087A64 DOES NOT HAVE A SCAVENGE PUMP INSTALLED.  THE REPLACEMENT PART WAS ORDERED BY ENGINE SN 	NOT BY STC MODIFIED PARTS LIST.  IT WOULD BE RECOMMENDED THAT WHEN ORDERING PARTS FOR STC MODIFIED AIRCRAFT THAT THE STC	C HOLDER BE CONTACTED FOR PARTS.	1	L	7	1 	3O	3	O		3A15    	E3SO				 
2006020200129	20060202	00129		2006	2	2	2006FA0000110    	2	20060123	G	7414	BL6006061	MAGNETO         																	ENGINE	INOPERATIVE     	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										METAL IN MAGNETO.  (K)																			 
2006020200106	20060202	00106	CE  	2006	2	2	2006FA0000111    	1	20060119	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5582X	510  				CE1353				PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE DOWN POSITION THE GEAR WOULDN`T EXTEND, AFTER CYCLING GEAR SELECTO	R GEAR WENT DOWN, AIRCRAFT RETURNED TO BASE.  ON TROUBLESHOOTING THE MECHANIC SELECTED DOWN AND IT FAILED TO EXTEND, AFT	ER TAPPING ON TOP OF RELAY THE GEAR WENT DOWN.  PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY I	AW DATE CODE.  (K)			1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006020300085	20060203	00085	EA  	2006	2	3	2006FA0000117    	2	20060120	G	8520		FLANGE          			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	263ND					2842064	L1016739A	A58041		BOTH FORWARD BOLT ATTACHMENT FLANGES WERE CRACKED OFF OF STARTER ATTACHMENT FLANGE ASSEMBLY. THIS CAUSED THE STARTER TO 	DROOP DOWNWARD WITH ONLY THE AFT BOLTS SUPPORTING THE STARTER. AS A RESULT, THE STARTER RING GEAR AND STARTER BENDIX WOU	LD NOT PROPERLY ENGAGE. THIS RESULTED IN THE TEETH OF THE BENDIX TO BREAK APART. THE STARTER FLANGE WAS CRACKED OFF ON B	OTH THE FWD LT SIDE AND FWD RT SIDE AT A 45 DEGREE ANGLE.			1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006020300096	20060203	00096	EA  	2006	2	3	2006FA0000118    	2	20060130	G	7414	4302	MAGNETO         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  						INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	295ND	861  				4496030	RL74671A			ON ENGINE INSPECTION RUN-UP MAGNETO RPM DROP NORMAL.  WHEN MECHANIC ATTEMPTED TO CHECK TIMING, FOUND TIMING 20 DEGREES L	ATE.  REMOVED AND DISASSEMBLED MAGNETO.  FOUND DISTRIBUTOR CARBON BRUSH MISSING AND ROTOR SHAFT BROKEN AT BASE OF SLOT F	OR POINT CAM.  ALSO FOUND EXTENSIVE BURNING DAMAGE TO DISTRIBUTOR BLOCK CROSSBEAM AND ARCING DAMAGE TO COIL AND DISTRIBU	TOR GEAR SHAFT.			1	L	7	2 	3O	3	O		A19S0   	E286				 
2006021400154	20060214	00154	CE  	2006	2	14	2006FA0000119    	1	20060130	G	5270	631221160	SUPPORT BRACKET 			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					DOOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	345MG	1501 				5250372				DURING INSPECTION FOUND THE RT ATTENUATOR PIVOT SUPPORT BRACKET CRACKED.  THERE IS A SB (SB525-78-03 R1) THAT ADDRESSES 	THIS PROBLEM HOWEVER IT IS ONLY FOR SN PRIOR TO AND INCLUDING -0135.  HAVE BEEN FINDING THIS CONDITION ON ALL 525S EVEN 	IF THE SB HAS BEEN ACCOMPLISHED.  RECOMMEND THAT THE OEM REEVALUATES THIS AREA AND RE-ISSUE A SB TO CORRECT THE CONDITIO	N.			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006020200148	20060202	00148	CE  	2006	2	2	2006FA0000121    	1	20060110	G	2720	0025240121	ARM             			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					RUDDER PEDAL	WORN            	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	3224G	1719 				E2924				TROUBLESHOT STIFF RUDDER PEDAL STEERING AND REPLACED PILOTS RT ARM ASSY.  PN 002-524012-1 WITH NEW IAW MM.  APPEARS ARM 	ASSY ROLLER BEARING WAS NEVER LUBED DURING BUILD OF AIRCRAFT.  THE ROLLER BEARING WEAR CAUSED THE ARM TO SEIZE ON THE RU	DDER PEDAL TORQUE TUBE AT RANDOM TRAVEL POSITIONS. (K)				1	L	7	1 	3O	3	O		3A15    	E3SO				 
2006021400235	20060214	00235	CE  	2006	2	14	2006FA0000123    	1	20060113	G	2800	543003	MOUNT           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550*      	 	SO  					POWERPLANT	CRACKED         	B			HJBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8419Q	246  				U20603279				DURING SCHEDULED INSPECTION FOUND THE FUEL FLOW TRANSDUCER MOUNT CRACKED COMPLETELY ACROSS ON ONE END.  (K)						1	H	7	1 	3O	3	O		A4CE    	E3SO				 
2006021400215	20060214	00215	EU  	2006	2	14	2006FA0000125    	1	20060111	G	5751	25W181001502	AILERON         			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					UPPER SURFACE	DELAMINATED     	B			T77R	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	03	918MJ	6061 				073				RT AILERON UPPER SKIN FOUND DELAMINATED FROM HONEYCOMB CORE.  DELAMINATION COVERS MORE THAN 50 PERCENT OF UPPER SURFACE.	  AILERON REPLACED WITH SERVICEABLE UNIT.  (K)					2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2006021400246	20060214	00246	EU  	2006	2	14	2006FA0000126    	1	20060126	G	5753	T700A5755001000	FLAP            			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  					IB FLAP END RIB	EXCESS PLAY     	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	05	704QD	1752 				188				FLAP SN SC279 WAS REMOVED FROM SERVICE FOR LOOSE ATTACHMENT INSERTS ON THE IB END RIB.  THE FLAP ATTACH CARRIAGE WAS DIS	COVERED LOOSE DURING A ROUTINE DAILY PPOST FLIGHT INSPECTION, WHERE PLAY WAS NOTED BETWEEN THE FLAP ATTACH CARRIAGE AND 	THE IB FLAP END RIB.  IT SHOULD BE NOTED THAT ALL OPERATORS SHOULD PERFORM AN INSP IN FLAP ATTACH AREA BEFORE OPERATING 	AC.  (K)			1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2006021400223	20060214	00223	EU  	2006	2	14	2006FA0000127    	1	20060110	G	5754	F50B134000191B3	PLATE           			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					OB SLATS	CRACKED         	B			M2MR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	03	5731					008				SEAL CLAMPING PLATE IS CRACKING AND BREAKING OFF AT THE 6TH AND 7TH SCREWS, (FROM IB TO OB) ON THE INSIDE OF THE OB SLAT	S.  SUBSEQUENT FOD DAMAGE TO THE NUT AND SAFETY WIRE OF THE BLEED AIR TUBE, AND ALSO THE LEADING EDGE OF THE WING BEHIND	 THE SLAT IS OCCURING DURING SLAT RETRACTION.  (K)				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2006021400224	20060214	00224	EU  	2006	2	14	2006FA0000128    	1	20060110	G	5754	F50B144000191B3	PLATE           			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					OB SLOTS	CRACKED         	B			M2MR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	03	5731					008				SEAL CLAMPING PLATE IS CRACKING AND BREAKING OFF AT THE 6TH AND 7TH SCREWS, (FROM IB TO OB) ON THE INSIDE OF THE OB SLOT	S.  SUBSEQUENT FOD DAMAGE TO THE NUT AND SAFETY WIRE OF THE BLEED AIR TUBE, AND ALSO THE LEADING EDGE OF THE WING BEHIND	 THE SLAT IS OCCURRING DURING SLAT RETRACTION.  (K)				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2006021400204	20060214	00204	SO  	2006	2	14	2006FA0000129    	1	20060125	G	5600	1159SCB51021	WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					LT	CRACKED         	B			BTVR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	23	49SL					1167				AIRCRAFT WAS FLYING AT 41,000 FT WHEN WINDSHIELD FAILED BY OVERHEATING AND CRACKING.  PROBABLE CAUSE, HEATING ELEMENT FA	ILED THEN WINDSHIELD OUTER PLY FAILED.  NO RECOMMENDATION TO PREVENT FAILURE.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006021400213	20060214	00213	CE  	2006	2	14	2006FA0000132    	1	20060130	G	5610	5111604200	WINDSHIELD      			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520F   	17032	SO  					COCKPIT	BLEW OUT        	B				B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SW	01		6622 				421C0426				DURING PRESSURIZED FLIGHT, AT 17000 FEET, THE RT SIDE WINDSHIELD CRACKED AND A MAJOR PORTION BLEW OUT.  THE GLARESHIELD 	IS A ONE PIECE ASSY AND STAYED INTACT; THE RT SIDE REMAINED ATTACHED TO THE INSTRUMENT PANEL WHILE THE FASTENERS ON THE 	RT SIDE FAILED AND ALLOWED THE THAT HALF OF THE GLARESHIELD TO BE PULLED OUTSIDE.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006021400236	20060214	00236	EA  	2006	2	14	2006FA0000133    	2	20060120	G	8510		CRANKCASE       	LYC         	0320D3G     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	BROKEN          	B				K				NONE                    				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			GL	21	263ND	703  	703  		L1016739A	2842064	L1016739A	A58041		BOTH FORWARD BOLT ATTACHMENT FLANGES WERE CRACKED OFF OF STARTER ATTACHMENT FLANGE ASSEMBLY. THIS CAUSED THE STARTER TO 	DROOP DOWNWARD WITH ONLY THE AFT BOLTS SUPPORTING THE STARTER. AS A RESULT, THE STARTER RING GEAR AND STARTER BENDIX WOU	LD NOT PROPERLY ENGAGE. THIS RESULTED IN THE TEETH OF THE BENDIX TO BREAK APART. THE STARTER FLANGE WAS CRACKED OFF ON B	OTH THE FWD. LT SIDE AND FWD RT SIDE AT A 45 DEGREE ANGLE.			1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006021400158	20060214	00158	CE  	2006	2	14	2006FA0000134    	1	20060131	G	7120	051313211	ATTACH BRACKET  			CESSNA	175   	175         	2072502	CE  	CONT  	IO360 	IO360*      	17025	CE  	MCAULY	2A34C	D2A34C*     	GL  	ENGINE MOUNT	BROKEN          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	15	6612E					56112				THE AC EXPERIENCED A HARD LANDING.  DURING THE LANDING THE 2 TOP ENGINE MOUNT ATTACH BRACKETS FAILED BEHIND THE FIREWALL	, ALLOWING THE TOP HALF OF THE FIREWALL TO FAIL, PULLING FORWARD AND DOWN ABOUT 18 INCHES.  PN 051313211 ENGINE MOUNT AT	TACH BRACKET FITS ONTO THE FRONT OF HAT CHANNELS ITEM 6 AND 7.  PN 051213211 WHICH HAS A HOLE IN IT FOR THE ENGINE MOUNT	 BOLT TO GO THROUGH, HAD FAILED (BROKEN IN 2 PIECES) SOME TIME AGO ON THE PILOTS TOP SIDE WITH RUST ON BOTH BRAKES.  THE	 BRACKET ON THE CO-PILOTS TOP SIDE HAD AN EXISTING CRACK IN THE CENTER THIRD OF IT AT THE BOLT HOLE, RUST WAS ALSO ON TH	IS CRACK.  (K)	1	H	7	1 	3O	3	O	NT	3A17    	E1CE	5	C	P3EA	 
2006021700100	20060217	00100	NM  	2006	2	17	2006FA0000135    	1	20060130	G	3210	NAS14635	BOLT            			UNIVAR	415   	A2ALON      	0540102	NM  	CONT  	C90   	C90*        	17009	SO  					MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5616F	1515 				A216				BOLT LOCATED TOP OF SPRING OF LANDING GEAR, 3 OF THESE BOLTS HOLD THE SPRING GEAR ON.  ALL 3 BOLTS FAILED, RECOMMEND ALL	 3 BOLTS IN BOTH MAIN GEAR REPLACED EACH, 1000 HRS TIME IN SERVICE.  (EA13200602813) (K)					1	L	7	1 	3O	3	O		A787    	E252				 
2006021700101	20060217	00101	SO  	2006	2	17	2006FA0000136    	1	20060120	G	3610	1159SB42000044	LINE            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					PNEUMATIC SYS	CHAFED          	B			CW1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	11	780E					1165				DURING A ENGINE CHANGE A PYLON INSPECTION WAS BEING PERFORMED.  SPIRAL WRAP WAS NOTICED WORN.  FURTHER INVESTIGATION REV	EALED CHAFF ON HIGH TEMPERATURE BLEED AIR LINE MORE THAN 50 PERCENT THROUGH.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006020800159	20060208	00159	CE  	2006	2	8	2006FA0000138    	1	20060202	G	2750	99100554	MOTOR           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAPS	FAILED          	B			OJ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	550VW					5500307				THE FLAP MOTOR EXPERIENCED AN OUT OF BOX FAILURE IMMEDIATELY AFTER INSTALL.  THE MOTOR`S INTERNAL BRAKE MECHANISM MALFUN	CTIONED IN A WAY TO NOT ALLOW IT TO RELEASE.  THE PART WAS IN NO WAY AIRWORTHY AND MALFUNCTION SHOULD HAVE BEEN NOTICED 	AT THE REPAIR STATION DURNING THE FUNCTIONAL CHECK WHICH WAS SIGNED OFF BY THEM .				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006021400226	20060214	00226	SO  	2006	2	14	2006FA0000139    	1	20060119	G	5740	402915	BOLT            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					LT WING	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	803ND	11642				2837003				DURING PHASE INSPECTION LT AFT WING ATTACH BOLT WAS FOUND LOOSE. UPON FURTHER INSP IAW MFG SL 1087 THE HOLE WAS FOUND TO	 BE ELONGATED AND BOLT SHANK WORN.  SL 1087 DOES NOT COVER THIS SN BUT DOES COVER MODEL.					1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041100029	20060411	00029	SO  	2006	4	11	2006FA0000140    	1	20060119	G	5740	402915	ATTACH FITTING  			PIPER 	PA28  	PA28R201    	7102816	SO  										LT WING	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	803ND	11642				2837003				DURING PHASE INSPECTION LT AFT WING ATTACH BOLT WAS FOUND LOOSE. UPON FURTHER INSP AS PER PIPER SL 1087 THE HOLE WAS FOU	ND TO BE ELONGATED AND BOLT SHANK WORN. SL 1087 DOES NOT COVER THIS S/N BUT DOES COVER MODEL.					1	L	7	1 	3O				2A13    					 
2006021700080	20060217	00080	SO  	2006	2	17	2006FA0000141    	2	20060126	G	7314	6467672A1	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					FUEL SYS	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	3214H	1373 				TH1731	824463R			FUEL PUMP FAILED AFTER LANDING.  ENGINE QUIT ON ROLL OUT.  PUMP WOULD NOT PRODUCE ENOUGH PRESSURE TO SUSTAIN AN ENGINE R	PM ABOVE IDLE. (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006021400244	20060214	00244	CE  	2006	2	14	2006FA0000142    	1	20060106	G	2800	05160167	VENT LINE       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					IB RT/LT RIB	CHAFED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	73813					17267693				DEFECT WAS NOTED DURING SEB04-4, WHICH REQUIRED INSP OF FUEL HOSES IN OLDER PRODUCTION AC.  IN ORDER TO INSPECT ALL LINE	S, HEADLINER IS REQUIRED TO BE PULLED.  LINES IN QUESTION ARE LOCATED ABOVE DOORS IB OF LT AND RT FUSELAGE RIB.  PROBLEM	 WAS CHAFING OF FUEL VENT LINE AGAINST REAR CABIN VENT HOSE.  METAL IN CABIN HOSE RUBBED SURFACE OF FUEL VENT LINE TO PR	ODUCE 2 WEAR SPOTS, WHICH WHEN GENTLY PROBED WITH A SCRIBE PIERCED TUBING.  POTENTIAL FOR THIS PROBLEM TO OCCUR IS ONLY 	ON AC THAT HAVE DUCTING FOR REAR VENTILATION.  WEAR OF LINE COULD CAUSE FUMES TO ENTER CABIN AREA.  ACCOMPLISHMENT OF SE	B04-4 TO INCLUDE CHECKING FOR POSSIBLE CHAFING OF FUEL VENT LINE AGAINST REAR CABIN VENT HOSE OR OTHER COMPONENTS.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006021400200	20060214	00200	SO  	2006	2	14	2006FA0000143    	1	20060206	G	3220		CABLE           	AYRES       	S2RGHT65    	AYRES 	S2    	S2RHGT65    	0970110	SO  										TAIL WHEEL	BINDING         	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19						013DC				AIRCRAFT TAIL WHEEL LOCKING / UNLOCKING MECHANISM NOT SATISFACTORY IAW PILOT'S REPORT. ANGLE OF CABLE AT POINT WHERE IT 	ATTACHES TO THE TAILWHEEL INTRODUCES BINDING. CABLE CLAMP USED DURING MANUFACTURE PINCHES END OF TELEFLEX CABLE AT MOUNT	ING POINT AND RESTRICTS MOVEMENT OF THE LOCK PIN ASSY. ATTENTION SHOULD BE PAID IN THE ASSEMBLY OF THE CABLE TO THE TAIL	WHEEL AS WELL AS IN THE DESIGN OF THE ATTACHING BRACKET ANGLES FOR PROPER CABLE RUN W/O BINDING.			1	L	7	1 	3T			NC	        					 
2006032100037	20060321	00037	SO  	2006	3	21	2006FA0000144    	1	20060206	G	3220		PIN             			AYRES 	S2    	S2RHGT65    	0970110	SO  										TAILWHEEL LOCK	MISMANUFACTURED 	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19						013DC				AIRCRAFT TAIL WHEEL LOCKING / UNLOCKING MECHANISH NOT SATISFACTORY PER PILOT'S REPORT.  FOUND TAIL WHEEL LOCKING PIN OUT	SIDE DIAMETER WAS NOT SUFFICIENT TO ALLOW THE LOCK PIN TO SLIDE WITHIN ITS HOUSING.  A 1/4 TURN EITHER WAY FREED THE PIN	.  FURTHER, THE PART OF THE PIN THAT PROTRUDES INTO THE TAIL WHEEL CENTERING CAM WAS NOT SUFFICIENTLY ROUNDED OR TAPERED	 TO ALLOW A RAPID AND POSITIVE ENGAGEMENT.  THE LOCK PIN IS CRITICAL TO THE SAFE LANDING OF THE AIRCRAFT IN GUSTY WIND C	ONDITIONS.		1	L	7	1 	3T			NC	        					 
2006021600235	20060216	00235	CE  	2006	2	16	2006FA0000145    	1	20060202	G	2597	SPS321135	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					CABIN VIP SEAT	OVERTEMP        	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	119QS					RK394				CREW SMELLED SMOKE/ODOR IN THE CABIN DURING FLIGHT.  FOUND SLIGHT DISCOLORATION OF DUCT DUE TO AN OVERTEMP.  NO DELAMINA	TION NOTED AND NO OTHER SIGN OF WIRING OR COMPONENT DAMAGE.  WHILE TROUBLESHOOTING FOUND RELAY INSIDE OF VIP CABIN TEMP 	SWITCH PANEL THAT WAS DEFECTIVE, NOT ALLOWING COCKPIT CONTROL OF CABIN TEMP IN THE AUTO POSITION.  PILOTS HAD TO SWITCH 	TO MANUAL MODE TO OVERRIDE VIP TEMP SWITCH PANEL.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006021700010	20060217	00010	SO  	2006	2	17	2006FA0000146    	1	20060119	G	5512		SKIN            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					HORIZONTAL STAB	BENT            	G			A5OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	7368Y	3234 				30419				DURING INSP OF HORIZ STAB, FWD SPAR AND CTR SECTION SKIN WAS FOUND BENT,  DISTORTED AT CENTER LIGHTENING HOLE.  SKIN AND	 SPAR BOTH SHOWED SIGNS OF WRINKLING AND DEFORMATION.  CLOSE INSP OF PARTS DID NOT SHOW ANY CRACKS. SPAR HAD BEEN REINFO	RCED WITH SPAR REINFORCEMENT AS REQUIRED BY SEB.  STAB WAS REPAIRED USING A NEW FWD SPAR ASSY WITH REINFORCEMENT NEW CTR	 SECTION SKIN AND COMPLYING WITH SEB.  PROBABLE CAUSE IS OVER STRESSING STAB BY FORCING TAIL DOWN TO MOVE AC ON GROUND. 	 RECOMMEND PERSONNEL BE BRIEFED ON PROPER PROCEDURES FOR MOVING AC, MECHANICS CLOSELY INSPECT THIS AREA FOR DAMAGE.  ALS	O, RECOMMEND THAT SEB INSP OF FWD SPAR LIGHTENING HOLE AND SB INSP OF BOLT HOLES BE COMPLIED WITH AT NEXT ANNUAL INSP.	1	L	7	2 	3O	3	O		A1EA    	1E12				 
2006021600197	20060216	00197	CE  	2006	2	16	2006FA0000156    	1	20060213	G	5346	051313211	ATTACH BRACKET  	CESSNA      		CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9456B	2417 				55256				FOUND THE LT UPPER ENGINE MOUNT ATTACHMENT BRACKET CRACKED THROUGH ON THE IB SIDE. CRACK APPEARS TO HAVE ORIGINATED AT O	UTER RADIUS OF WASHER THEN PROGRESSED UP AND DOWN THROUGH BRACKET. THIS INSPECTION WAS PROMPTED AFTER REPORTED FAILURE O	F SAME BRACKET, SAME MAKE AND MODEL OF AIRCRAFT, THAT SUFFERED A PARTIAL ENGINE/FIREWALL SEPARATION DURING LANDING.				1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2006022800065	20060228	00065	CE  	2006	2	28	2006FA0000157    	1	20060222	G	5346	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENGINE MOUNT	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9456B					55256				A REPLACEMENT 0513132-11 ENGINE MOUNT BRACKET WAS ORDERED TO REPLACE ONE FOUND CRACKED. THE JOGGLED FLANGE WAS INCORRECT	LY FORMED. THE FLANGE WAS BENT OUTWARD TO THE POINT THAT IT WOULD NOT FIT IN THE AIRCRAFT.					1	H	7	1 	3O			NT	3A17    					 
2006022400180	20060224	00180	CE  	2006	2	24	2006FA0000159    	1	20060130	G	2170	728802	WATER SEPARATOR 			CESSNA	650   	650         	2076802	CE  										A/C BAY	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	766MH					6500015				EXPERIENCED AN ABRUPT CABIN PRESS FLUCTUATION DURING FLT.  FLT CREW REPORTED, ABLE TO MAINTAIN CABIN ALT WITHIN LIMITS A	FTER NOTICED PROBLEM.  AFTER THIS A/C LANDED MX PERSONNEL DISCOVERED ONE OF THE ENVIRONMENTAL CONTROL SYS WATER SEPARATO	R UNITS HAD SEPARATED DURING FLT.  AFFECTED WATER SEPARATOR IS MANUF WITH A CLAMP FLANGE (WHERE THE MAIN V-BAND THAT ALL	OWS DISASSEMBLY OF THE UNIT FOR SERVICING IS INSTALLED) THAT IS BONDED TO FWD AND AFT SECTIONS OF UNIT.  BONDING MAT`L H	AD APPARENTLY LOST ABILITY TO KEEP FLANGE ADHERED TO BODY OF UNIT ALLOWING UNIT TO SEPARATE AND CAUSE LOSS OF PRESS..		2	L	7	2 	4F				A9NM    					 
2006022800008	20060228	00008	NM  	2006	2	28	2006FA0000160    	1	20060201	G	2782		GREASE FITTING  	ISRAEL      		ISRAEL	1125  	1125        	       	NM  										LE SLAT ACTUATOR	LEAKING         	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99					1820	080				DURING NORMAL GREASING OPERATION, THE GREASE BALL DID NOT RESET TO THE CLOSED POSITION, ALLOWING GREASE TO FLOW OUT OF T	HE ACTUATOR.					2	L	7	2 	4F			RT	A16NM   					 
2006022700254	20060227	00254	EA  	2006	2	27	2006FA0000161    	2	20060209	G	7310		FUEL            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					FUEL TANK	CONTAMINATED    	B				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			GL	21	384ND					2844095	L3081251A			BROWNISH FUEL WAS DETECTED FROM THE FUEL GASCOLATOR.  AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE BROWNISH FUEL COL	OR PRESENT IN THE FUEL SYSTEM.					1	L	7	1 	3O	3	O		2A13    	1E10				 
2006022700147	20060227	00147	GL  	2006	2	27	2006FA0000162    	1	20060207	G	3210		PIN             			DIAMON	DA20  	DA20C1      	2990001	GL  										MLG	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	915AF					C0149				ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01)	 HAD WORKED OUT UNLOCKING THE ASSY.					1	L	7	1 	3O			NT	TA4CH   					 
2006022800032	20060228	00032	EA  	2006	2	28	2006FA0000164    	2	20060207	G	7421	UREM40E	SPARK PLUG      			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	DEFECTIVE       	B			A5OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	6372D					17272758				DURING THE INSTALLATION AND OPS CHECK OF 2 NEW MAGNETOS, HARNESS AND 8 SPARK PLUGS TO CORRECT A HARD STARTING DISCREPANC	Y, THE ENGINE HAD A 200 TO 300 RPM MAGNETO DROP O THE LT MAGNETO.  TROBLESHOT THE IGNITION SYSTEM USING A COLD CYLINDER 	TESTER AND DETERMINED THAT 1 OF 8 SPARK PLUGS WAS DEFECTIVE.  SEEMS TO BE A TREND OF BAD SPARK PLUGS BEING SHIPPED BY MF	G. REMOVED DEFECTIVE SPARK PLUG AND REPLACED WITH A KNOWN GOOD SPARK PLUG AND ENGINE OPS CHECKED GOOD.  SPARK PLUGS WERE	 REPLACED AT TIME OF MAGNETO AND HARNESS CHANGE.  ALL OF THIS BECAUSE OF POOR QUALITY CONTROL.  (K)		1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2006022800006	20060228	00006	GL  	2006	2	28	2006FA0000165    	1	20060214	G	3220	PAF18220P11	BUSHING         			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					NLG STRUT	MISALIGNED      	B			UV6S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	100UV	454  				40405				THIS ADDRESSES A CONDITION OF EXCESSIVE (0.085 INCHES) CLEARANCE BETWEEN A BUSHING AT THE BOTTOM OF THE NLG SHOCK STRUT 	(ITEM NR 290, PN PAF18220P11, FIG .01, CH 32-20-02, IPC) AND THE SHOCK STRUT CENTER ROD (ITEM NR 210, PN D41-3223-20-33B	).  THIS CLEARANCE ALLOWS THE END FITTING (ITEM NR 310) TO SLOPE APPROX.  10 DEGREES TO ONE SIDE.  THIS RESULTS IN THE B	OTTOM ELASTOMERIC DONUT TAKING ON A WEDGE SHAPE AND THE SHOCK LOADS BEING TRANSMITTED OFF THE CENTERLINE OF THE NLG SHOC	K STRUT.  (K)		1	L	7	1 	3O	3	O	NT	A47CE   	1E10				 
2006022800050	20060228	00050	GL  	2006	2	28	2006FA0000166    	1	20060214	G	3220	PAF18220P11	BUSHING         			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					NLG STRUT	WORN            	B			UV6S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	834DS	1963 				40034				REPORT ADDRESSES A CONDITION OF EXCESSIVE (0.085 INCHES) CLEARANCE BETWEEN A BUSHING AT THE BOTTOM OF THE NLG SHOCK STRU	T (ITEM NR 290, PN PAF18220P11, FIG 01, CH 32-20-02, IPC) AND THE SHOCK STRUT CENTER ROD (ITEM NR 210, PN D41-3223-20-33	B).  THIS CLEARANCE ALLOWS THE END FITTING  (ITEM NR 310) TO SLOPE APPROX.  10 DEGREES TO ONE SIDE.  THIS RESULTS IN THE	 BOTTOM ELASTOMERIC DONUT TAKING ON A WEDGE SHAPE AND THE SHOCK LOADS BEING TRANSMITTED OFF THE CENTERLINE OF THE NLG SH	OCK STUT.  (K)		1	L	7	1 	3O	3	O	NT	A47CE   	1E10				 
2006022800033	20060228	00033	EA  	2006	2	28	2006FA0000167    	2	20060203	G	8530	751868	CYLINDER HEAD   			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NR 2 CYLINDER	SEPARATED       	E			GB7A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	62BA	8566 	1752 			274859				CYLINDER HEAD SEPARATED FROM CYLINDER FOR REASONS UNKNOWN.  (K)						1	L	7	2 	3O	3	O		1A10    	1E4				 
2006022800004	20060228	00004	CE  	2006	2	28	2006FA0000168    	1	20060216	G	3233	26900127	ACTUATOR        			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					NLG	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	502BE					5000195				HYDRAULIC LEAK AT SWITCH ACTUATOR ENTRY INTO NLG ACTUATOR AT 231 CYCLES INSTALLED AND 4224 CYCLES SOH/NEW.  DEPELETED HY	DRAULIC SYSTEM ON LANDING.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006022800022	20060228	00022	EU  	2006	2	28	2006FA0000169    	1	20060210	G	8097	Z00NN6024017227	ELECTRICAL BOX  			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  	HARTZL	HCE4N	HCE4N3      	NE  	STARTER	OVERHEATED      	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			EA	17	704QD		1280 			188	PCEPM0073	HH463		DURING THE START SEQUENCE WHEN THE PILOT SELECTED THE START POSITION THE STARTER WOULD NOT RESPOND.  THE PILOT COULD HEA	R THE SOUND OF RELAY CONTACTS BUT THE STARTER WOULD NOT RESPOND.  THE AIRCRAFT WAS EXAMINED BY A LINE TECHNICIAN WHO REP	ORTED THE ELECTRICAL MASTER SMELLED OVERHEATED AND BURNED.  THE UNIT WAS REMOVED, OVERHEATING.  REPLACEMENT UNIT OF THE 	SAME PN WAS INSTALLED AND THE STARTER AND ELECTRICAL SYSTEM FUNCTIONED NORMALLY.  (K)			1	L	7	1 	3T	4	T	RT	A60EU   	E4EA	5	C	P10NE	 
2006022800005	20060228	00005		2006	2	28	2006FA0000170    	1	20060217	G	8011	MZ4212	STARTER         																	ENGINE	SEIZED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER SEIZED DURING START UP.  (K)																			 
2006022800052	20060228	00052		2006	2	28	2006FA0000171    	1	20060217	G	8011	ES6462382	STARTER         																	ENGINE	CONTAMINATED    	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		10   								WAX FROM ELECTRICAL WINDING IS SEEPING THROUGH THE PLATE.  (K)																			 
2006022800044	20060228	00044		2006	2	28	2006FA0000172    	1	20060210	G	2420	ALX9525B	ALTERNATOR      																	ENGINE	MISMANUFACTURED 	B			KC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03										THIS ALTERNATOR HAS 0-HOURS TIME IN SERVICE SINCE OVERHAUL ON W/O M039030.  IN PREPARING THIS UNIT FOR INSTALLATION ON A	IRCRAFT, EXCESSIVE SIDE PLAY OF ROTOR SHAFT WAS NOTED.  DISASSEMBLY OF THE UNIT REVEALED THAT THE DRIVE-END BEARING BORE	 WAS .015 INCH OVERSIZE AND THE BEARING WAS VERY LOOSE IN THE BORE.  THIS END FRAME SHOULD HAVE BEEN REJECTED DURING THE	 OVERHAUL PROCESS DUE TO THE EXCESSIVE WEAR OF THE BEARING BORE.  RECOMMENDATIONS WOULD INCLUDE CLOSER INSPECTION OF THE	 BEARING BORE DIMENSIONS DURING THE OVERHAUL PROCESS.  THIS UNIT WILL BE RETURNED TO BE INSPECTED AND WARRANTY REPLACED 	BY OVERHAULER.  (K)														 
2006022800041	20060228	00041	CE  	2006	2	28	2006FA0000173    	1	20060213	G	2820	0020200005A	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	FUEL SYS	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	202P	3255 				TH1875				THE CROSS FEED LINE PN 002-92000-51 WAS IMPROPERLY MANUFACTURED WHICH CAUSED THE RT LANDING GEAR DRIVE TUBE TO CONTACT, 	AND ABRADE THE LINE DURING LANDING GEAR RETRACTION.  THE ABRASION HAD PROGRESSED TO THE POINT THAT ONLY 10 PERCENT OF TH	E WALL THICKNESS REMAINED.  THE REPLACEMENT LINE PN HAS BEEN MANUFACTURED TO ALLOW GREATER CLEARANCE WITH THE LANDING GE	AR DRIVE TUBE.  IT IS RECOMMENDED THAT THE CLEARANCE BETWEEN THE CROSS FEED LINE AND THE DRIVE TUBE BE CHECKED.  (K)			1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
2006022800031	20060228	00031		2006	2	28	2006FA0000174    	4	20060216	G	3100	70265421901	COMPUTER        			GULSTM	GV    	GV          	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  						FAILED          	B			VU2R	O				OTHER                   				G			MULTIPLE FAILURE          			NR	NOT REPORTED   	1			GL	05	5PG	340  				5046				DURING A RECENT FLIGHT DISPLAY UNITS 1,2, AND 3 BLINKED ON AND OFF.  DISPLAY UNITS 1, 2 CYCLED ON AND OFF DISPLAY UNIT 3	 WAS RED X`D.  DURING THAT TIME AN AMBER (MAU 3A FAIL) MESSAGE DISPLAYED AND A BLUE (DATABASE CONFIG) MESSAGE ALSO DISPL	AYED.  AFTER 5-8 SECOUNDS, ALL DISPLAY UNITS RETURNED TO NORMAL.  AFTER 10 SECONDS THE MESSAGES WENT AWAY.  THE FAULT HI	STORY WAS DOWNLOADED AND SENT TO MFG.  THE NIC/PROC NR5 MODULE WAS REPLACED IAW MFG DIRECTION.  CERT CHARLIE (ASC 904) W	AS INSTALLED WHICH ADDED THE AUTO REVERSION OF THE DISPLAY UNITS IN CASE OF A FAILURE OPERATOR FEELS THIS IN CONJUNCTION	 WITH A BAD NIC/PROC NR5 CAUSED THE BLINKING OF THE DISPLAYS.	2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2006022800009	20060228	00009		2006	2	28	2006FA0000175    	1	20060206	G	3246		WHEEL           																	MLG	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										MAIN WHEEL FAILURE.																			 
2006022800063	20060228	00063	SW  	2006	2	28	2006FA0000176    	1	20060215	G	7810	PFS16201	EXHAUST PORT    			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					NR 4	BROKEN          	B			ZKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	799EC	121  				240920				INSTALLED POWER FLOW SYSTEMS EXHAUST STC NR SA02871AT AT TACH TIME 4646.93, AT TACH TIME 4768.70 THE NR 4 EXHAUST PORT H	AD BROKE FREE OF MUFFLER.  (K)					1	L	7	1 	3O	3	O		2A3     	1E10				 
2006022800021	20060228	00021	SO  	2006	2	28	2006FA0000183    	2	20060203	G	8520	AEC631475	PISTON          			BEECH 	33    	E33A        	1151424	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	DAMAGED         	B			MW2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	1069F					CE230	1218098BA			ALL 6 PISTON SKIRTS HITTING CASE.  ALL PISTON DAMAGE BEYOND REPAIR.  (K)						1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006022800077	20060228	00077	GL  	2006	2	28	2006FA0000185    	1	20060215	G	2700	11169002	TORQUE TUBE     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	FLT CONTROLS	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	150X	315  				0813	917119	030521		INSPECTED THE FLIGHT CONTROL SYS IAW SB AND FOUND FREE PLAY AT THE TORQUE TUBE/ END FITTING INTERFACE ON BOTH SIDES.  TH	E RT SIDE WAS MOR PRONOUNCED THAN THE LT.  MFG CONSIDERS THIS SB TO BE OPTIONAL, HOWEVER THE CONTINUED USE WITH THIS DEF	ECT WILL RESULT IN THE BOLT HOLWS IN THE TORQUE TUBES CONTINUING TO ELONGATE AND EXACERBATING THE PROBLEM.  AS LONG AS T	HIS IS CONSIDERED OPTIONAL, CUSTOMERS WON`T PAY FOR REPAIRS UNTIL IT IS DETERMINED TO BE AN AIRWORTHINESS ISSUE.  (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P47GL	 
2006022800078	20060228	00078	GL  	2006	2	28	2006FA0000186    	1	20060215	G	2700	11168002	TORQUE TUBE     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	FLT CONTROLS	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	150X	315  				0813	917119	030521		INSPECTED THE FLIGHT CONTROL SYSTEM IAW SB AND FOUND FREE PLAY AT THE TORQUE TUBE/ END FITTING INTERFACE ON BOTH SIDES. 	 THE RIGHT SIDE WAS MORE PORNOUNCED THAN THE LEFT.  MFG CONSIDERS THIS SB TO BE OPTIONAL, HOWEVER THE CONTINUED USE WITH	 THIS DEFECT WILL RESULT IN THE BOLT HOLES IN THE TORQUE TUBES CONTINUING TO ELONGATE AND EXACERGBATING THE PROBLEM.  AS	 LONG AS THIS IS CONSIDERED OPTIONAL, CUSTOMER WON`T PAY FOR REPAIRS UNTIL IT IS DETERMINED TO BE AN AIRWORTHINESS ISSUE	.  (K)		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P47GL	 
2006022800038	20060228	00038	EU  	2006	2	28	2006FA0000187    	1	20060221	G	2741		COVER           			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					ACTUATOR	MISSING         	B			GSPR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	05	411HB				02834AA	419				WHILE PERFORMING A 200 HOUR INSPECTION ON THIS AIRCRAFT, THE TAIL SECTION FAIRINGS AND PANELS WERE REMOVED.  THE PITCH T	RIM ACTUATOR WAS FOUND WITH THE DUST SHIELD DOWN AGAINS THE MOTOR HOUSING.  IT WAS OBVIOUS THAT THE TIE BOLT HAD BEEN RE	MOVED, DUST SHIELD LOWERED AND THE TIE BOLT REINSTALLED WITHOUT THE DUST SHIELD IN PLACE.  A PREVIOUS FATALITY CRASH HAS	 OCCURED DUE TO THE SAME INSPECTION BEING PERFORMED AND THE TIE BOLT INCORRECTLY INSTALLED.  THIS INSPECTION AND PROCEDU	RE SHOULD BE REMOVED FROM  GUIDE AND BEFORE SOME CAUSES THE SAME PROBLEM AGAIN.  THIS INSPECTION SHOULD ONLY BE PERFORME	D BY OEM, TOO CRITICAL FOR THE FIELD.  (K)	2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2006022800042	20060228	00042	NE  	2006	2	28	2006FA0000188    	1	20060216	G	2820		O-RING          			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL DIST	CORRODED        	B			Y3AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO	 LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE.  (K)					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006022800043	20060228	00043	NE  	2006	2	28	2006FA0000189    	1	20060216	G	2820		O-RING          			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL DIST	CORRODED        	B			Y3AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO 	LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE. (K)					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006022800040	20060228	00040	NE  	2006	2	28	2006FA0000190    	1	20060216	G	2820		O-RING          			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL DIST	CORRODED        	B			Y3AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO	 LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE.  (K)					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006022800039	20060228	00039	NE  	2006	2	28	2006FA0000191    	1	20060216	G	2820		O-RING          			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL SYSTEM	CORRODED        	D			Y3AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO	 LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE.  (K)					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006022800010	20060228	00010	CE  	2006	2	28	2006FA0000192    	1	20060209	G	5710	S3461111	BOLT            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	WING	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	410BS	49   				172S9966	23016	3220351E		DURING FIRST PHASE INSPECTION (49 HOURS SINCE NEW)FOUND LEFT WING TO UPPER STRUT BOLT HEAD DAMAGED FROM FACTORY, APPAREN	TLY INSTALLED WITH VISE-GRIP TYPE TOOL. NO TORQUE SEAL FOUND ON NUT. DAMAGE EXTENSIVE ENOUGH THAT TORQUE COULD NOT BE CH	ECKED WITH SOCKET. PHOTOS AVAILABLE. (S3461-111 REPLACES AN8-25A.)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006022800011	20060228	00011	CE  	2006	2	28	2006FA0000193    	1	20060209	G	5710	S3461111	BOLT            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ZONE 500	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	410BS	49   				172S9966	23016	3220351E		DURING FIRST PHASE INSPECTION (49 HOURS SINCE NEW)FOUND LEFT WING TO UPPER STRUT BOLT HEAD DAMAGED FROM FACTORY, APPAREN	TLY INSTALLED WITH VISE-GRIP TYPE TOOL. NO TORQUE SEAL FOUND ON NUT. DAMAGE EXTENSIVE ENOUGH THAT TORQUE COULD NOT BE CH	ECKED WITH SOCKET. PHOTOS AVAILABLE. (S3461-111 REPLACES AN8-25A.)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006022700299	20060227	00299		2006	2	27	2006FA0000194    	4	20060205	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	13	402FJ	9021 			00077031	3147				HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.						2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006022700257	20060227	00257		2006	2	27	2006FA0000195    	4	20060205	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	13	402FJ	9021 			00077031	3147				HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.						2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006022700258	20060227	00258		2006	2	27	2006FA0000196    	4	20060205	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	13	402FJ	9021 			00077031	3147				HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.						2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006022700300	20060227	00300		2006	2	27	2006FA0000197    	4	20060205	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	13	402FJ	9021 			00077031	3147				HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.						2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006022700301	20060227	00301	GL  	2006	2	27	2006FA0000198    	1	20060210	G	2460		ELECTRICAL BOX  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ELECTRICAL SYS	FAULTY          	G				O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			EA	25										OPERATOR REPORTS THREE CASES OF UNCOMMANDED ENGINE STARTER ENGAGEMENT.  IN TWO CASES, STARTER ENGAGED WHEN THE BATTERY M	ASTER WAS TURNED ON.  IN THE THIRD CASE, OPERATOR STATES THAT THE SHIP'S BATTERY CAME ON LINE UNCOMMANDED AND THAT START	ER CONCURRENTLY ENGAGED UNCOMMANDED.  IN ALL THREE CASES, REPLACEMENT OF THE AIRCRAFT POWER DISTRIBUTION BOX RECTIFIED T	HE PROBLEM.			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006022800014	20060228	00014		2006	2	28	2006FA0000199    	4	20060205	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   		DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY	FAILED          	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	13	402FJ				00077031	3147				DU-870 DISPLAY UNIT REFERENCE FAILED DURING FLIGHT.  THE COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY.						2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006022800067	20060228	00067	SO  	2006	2	28	2006FA0000201    	1	20060220	G	5610		WINDOW          			PIPER 	PA24  	PA24250     	7102404	SO  										COCKPIT	INFLT SEPARATION	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	04	456P					243276				PILOTS SIDE WINDOW PARTIALLY POPPED OUT AT 19,000 FEET. PRESSURIZATION ISSUES RESULTED IN EMERGECY DECENT.  OPERATOR NOT	IFIED KIT MANUFACTURER.					1	L	7	1 	3O				1A15    					 
2006031700048	20060317	00048	CE  	2006	3	17	2006FA0000202    	1	20060221	G	8120	20591	TURBOCHARGER    			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	DISINTEGRATED   	B			J7BR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4243C					4140539	R20836872J			TURBOCHARGER CAME APART INTERNALLY RESULTING IN LOSS OF MANIFOLD PRESSURE AND ENGINE METAL CONTAMINATION.  ENGINE REMOVE	D FROM SERVICE.  (K)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2006031700060	20060317	00060	CE  	2006	3	17	2006FA0000203    	1	20060131	G	7120	SB997102	TUBE            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE MOUNT	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5273U					172S9193	L3050951A			DURING 100 HOUR/ANNUAL INSPECTION FOUND THE ENGINE OIL DIPSTICK CHAFING SLIGHTLY ON THE ENGINE MOUNT.  INSPECTED FOR DAM	AGE, ONLY PROBLEM NOTED WAS PAINT WAS CHAFED.  THIS PROBLEM WAS SUPPOSED TO HAVE BEEN TAKEN CARE OF BY THE FACTORY PRIOR	 TO THIS SN AIRCRAFT.  ENGINE OIL FILLER TUBE TO ENGINE MOUNT CLEARANCE, WAS ISSUED TO TAKE CARE OF EARLIER SN AIRCRAFT.	  THIS AIRCRAFT EVIDENTLY DID NOT GET THE CORRECT HARDWARE AT MANUFACTURER.  INSTALLED CORRECT PARTS IAW TE IPC FOR THIS	 SN AIRCRAFT.  (K)		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006031700058	20060317	00058	CE  	2006	3	17	2006FA0000204    	1	20060121	G	5710	1019800387	COVER           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					WINGS	CHAFED          	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	6812W	5952 				FA38				COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH PORT SPART CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION. 	 RECOMMEND RUBBER EDGE SEAL OR FAY SEALED EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006040600212	20060406	00212	CE  	2006	4	6	2006FA0000205    	1	20060221	G	3000	1019800388	COVER           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					WINGS	CHAFED          	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	6812W					FA38				COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT, SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.	  RECOMMEND RUBBER EDGE SEAL OR FAY SEALED EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006040600178	20060406	00178	CE  	2006	4	6	2006FA0000206    	1	20060221	G	5720	1019800387	COVER           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					WINGS	CHAFED          	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	79TE	5991 				FA67				COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT, SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.	  RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006032300205	20060323	00205	CE  	2006	3	23	2006FA0000207    	1	20060221	G	3000	1019800388	COVER           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					WING	CHAFED          	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	79TE	5991 				FA67				COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING  SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.	  RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006040600185	20060406	00185	CE  	2006	4	6	2006FA0000208    	1	20060221	G	5720	1019800387	COVER           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6*        	52043	EA  					WINGS	CHAFED          	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	103CW	4080 				FA64				COVER IS CHAFING LWR FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  R	ECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR WING SKIN.  (K)					2	L	7	2 	4T	3	T		A24CE   	E2NE				 
2006031700051	20060317	00051	CE  	2006	3	17	2006FA0000209    	1	20060221	G	3000	1019800388	COVER           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6*        	52043	EA  					WINGS	CHAFED          	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	103CW	4082 				FA64				COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION. 	 RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)					2	L	7	2 	4T	3	T		A24CE   	E2NE				 
2006031600117	20060316	00117	SO  	2006	3	16	2006FA0000210    	1	20060228	G	3520	P24029	SWITCH          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					FUSELAGE	FAILED          	D				O				OTHER                   				J	N		WARNING INDICATION        	FALSE WARNING             		TX	TAXI/GRND HDL  	1			NM	09	941AM	1179 				1499				PILOTS RECEIVED PAX OXY OFF MESSAGE BEFORE TAXI OUT, INDICATING LESS THAN 50 PSI IN PASSENGER OXYGEN BOTTLE SYSTEM. VERI	FIED PAX BOTTLES WERE TURNED ON AND PRESSURES WERE READING NORMAL AT BOTTLES AND COCKPIT INDICATORS. VERIFIED FLOW FROM 	THERAPEUTIC OXYGEN PORT AS THIS UTILIZES PASSENGER BOTTLES.  TROUBLESHOT INDICATION SYSTEM AND FOUND FAILED SWITCH, IDEN	TIFIER 95S4. WIRING WAS OK. SWITCH WAS REPLACED WITH NEW UNIT. INDICATION THEN NORMAL.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006040400175	20060404	00175	SO  	2006	4	4	2006FA0000211    	1	20060211	G	3210	1159H5020085	LINE            			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										HYDRAULIC SYS	FRAYED          	C				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	07	405LM	4569 	30   			541				DUE TO IMPROPERLY POSITIONED ELBOW DURING AIRCRAFT PRODUCTION ON RT MAIN LANDING GEAR DOOR ACTUATOR, FLEX LINE WAS CONTA	CTING LINE DURING DOOR RETRACTION.  THE FLEX LINE DEVELOPED A HYDRAULIC LEAK WHICH IN TURN DEPLETED THE LT AIRCRAFT HYDR	AULIC SYSTEM.				2	L	7	2 	4F			RT	A12EA   					 
2006040400180	20060404	00180		2006	4	4	2006FA0000213    	4	20060217	G	2562		BATTERY         	ACK         		RYAN  	ST3   	ST3KR       	7830502	WP  										ELT	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	170P				032988	1566				DURING REPLACEMENT OF BATTERIES FROM ELT CASE, MODERATE FORCE WAS NEEDED TO REMOVE THE BOTTOM 4 BATTERIES.  THE FIT OF T	HE NEW BATTERIES INTO THE CASE WAS  VERY TIGHT.  AFTER CLOSING THE ELT CASE, THE ELT BECAME HOT TO THE TOUCH.  SUSPECTIN	G  AN ELECTRICAL SHORT CIRCUIT, THE NEW BATTERIES WERE REMOVED.  UPON EXAMINING THE NEW BATTERIES JUST REMOVED, IT WAS F	OUND THAT THE PROTECTIVE COVERING ON THE TERMINAL END OF THE BATTERIES WAS SCRAPED AWAY.  THIS MUST HAVE HAPPENED BY SLI	DING THE BATTERIES INTO THE TIGHT CASE.  THE RELATIVE BARE SPOTS ON THE BATTERIES WOULD ACCOUNT FOR A SHORT CIRCUITING O	F THE BATTERIES THAT CAUSED THE ELT TO OVERHEAT.  IT IS BELIEVED THAT THE TECHNIQUE USED TO INSERT THE BATTERIES INTO TH	1	L	7	1 	3R				A749    					 
2006032300053	20060323	00053	CE  	2006	3	23	2006FA0000214    	1	20060308	G	5610	99143809	WINDSHIELD      			CESSNA	650   	650         	2076802	CE  										COCKPIT	CRACKED         	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	09	430SA	6269 				6507041				PILOT'S GLASS WINDSHIELD SHOWED SIGNS OF OVERHEATING AT UPPER CENTER EDGE CAUSING COMPLETE CRACKING OF WINDSHIELD IN A S	PIDER WEB FASHION.  THE WINDSHIELD REMAINED STRUCTURALLY SOUND AND THE AIRCRAFT WAS ABLE TO LAND WITHOUT INCIDENT.					2	L	7	2 	4F				A9NM    					 
2006032100036	20060321	00036		2006	3	21	2006FA0000215    	1	20060228	G	2761	120611	PISTON          	BOEING      																ACTUATOR	CRACKED         	D			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1292					SUBJECT PISTON WAS RECEIVED WITH THE 2 KENY SLOTS CRACKED ON ID RADIUS.  CAUSE UNKNOWN.  (K)																			 
2006041300264	20060413	00264	NM  	2006	4	13	2006FA0000216    	1	20060228	G	2761	656952211	HOUSING         			BOEING	737   	737*        	       	NM  										SPOILER ACTUATOR	SPLIT           	D			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										HOUSING RECEIVED SPLIT OPEN IN A RADIAL DIRECTION NEAR LARGE ID, CAUSING TOTAL FAILURE OF ASSY, CAUSE UNKNOWN.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006032000030	20060320	00030	SO  	2006	3	20	2006FA0000217    	1	20060206	G	5610	1159SCB310212	WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					COPILOT WNDSHLD	CRACKED         	B			UO2R	O				OTHER                   				G			MULTIPLE FAILURE          			CR	CRUISE         	1			GL	19	181CW		6058 			1001				OUTER PLY OF CO-PILOT WINDSHIELD CRACKED IN FLIGHT.  NO LOSS OF PRESSURIZATION OCCURRED.  APPEARS HEATING ELEMENT SHORTE	D.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006040500253	20060405	00253	GL  	2006	4	5	2006FA0000219    	1	20060210	G	7800	DA403	RISER           			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	164DS					40467				ORDERED A NEW EXHAUST RISER FOR THE NR 2 CYLINDER.  INSPECTING THE RISER BEFORE INSTALLATION WE FOUND A CRACK AT THE WEL	D RADIUS OF THE MOUNT FLANGE AND THE EXHAUST PIPE.  THIS MAY HAVE ACCURED FROM EXCESS HEAT DURING MANUFACTUR.  THIS THE 	FIRST CRACK SEEN ON NEW RISERS SEAT TO US, BUT WE HAVE HAD 2 IN SERVICE RISERS CRACKED AT 780.4 HOURS AND 2 IN SERVICE R	ISERS CRACKED.  (K)			1	L	7	1 	3O	3	O	NT	A47CE   	1E10				 
2006032100237	20060321	00237		2006	3	21	2006FA0000220    	4	20060301	G	3452	SSD12030A	ENCODER         			BEECH 	33    	35A33       	1151404	CE  	CONT  	O470  	IO470*      	17026	SO  					COCKPIT	OUT OF ADJUST   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	1329Z					CD354				CHECKED ENCODER SYSTEM AND COULD NOT VERIFIED REPORT OF ATTITUDE ERROR.  REPLACED TRANS CAL BLIND ENCODER AS PRECAUTIONA	RY MEASURE.  RECERTIFY TRANSPONDER AND ENCODER IAW FAR.  (K)					1	L	7	1 	3O	3	O		3A15    	E1CE				 
2006032200140	20060322	00140	SO  	2006	3	22	2006FA0000221    	1	20060216	G	3230	8627503	DOWNLOCK        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NOSE GEAR	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	09	2163N					447995222				NOSE GEAR COLLAPSE DURING ROLLOUT AFTER BRAKE APPLICATION.  PILOT HAD 3 GREEN LIGHTS.  HOOK PORTION OF DOWNLOCK PN 86275	-03 FOUND CRACKED, BROKEN OFF.  FOUND BROKEN NAS 464P4-27 ALSO FOUND FAILED.  BOLT FRACTURED MID SHANK.  HEAD PORTION OF	 BOLT NEVER FOUND.  REMAINDER OF BOLT WITH NUT AND COTTER PIN INSTALLED FOUND STILL INSTALLED IN DRAGLINK ASSY.  UNCLEAR	 AS TO WHAT FAILED FIRST.  DOWNLOCK TT 8258 HRS, BOLT TT UNKNOWN.			1	L	7	2 	3O	3	O		A19S0   	E286				 
2006032200145	20060322	00145	SO  	2006	3	22	2006FA0000222    	1	20060216	G	3230	NAS464P427	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NLG	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	09	2163N					447995222				NOSE GEAR COLLAPSED DURING ROLL OUT, AFTER BRAKE APPLICATION.  PILOT HAD 3 GREEN LIGHTS.  HOOK PORTIONOF DOWNLOCK PN 862	75-03 FOUND CRACKED, BROKEN OFF.  FOUND BROKEN PIECE ON RUNWAY.  DRAGLINK BOLT PN NAS 464P4-27 ALSO FOUND FAILED.   BOLT	 FRACTURED MID SHANK.  HEAD PORTION OF BOLT NEVER FOUND.  REMAINDER OF BOLT WITH NUT AND COTTER PIN INSTALLED FUND STILL	 INSTALLED IN DRAGLINK ASSY.  UNCLEAR AS TO WHAT FAILED FIRST.  AD WAS PREVIOUSLY COMPLIED WITH.  DOWN LOCK TT 8258 HRS,	 BOLT TT UNKNOWN.  (K)		1	L	7	2 	3O	3	O		A19S0   	E286				 
2006032000080	20060320	00080	CE  	2006	3	20	2006FA0000223    	1	20060106	G	3411		PITOT SYSTEM    			LEAR  	35    	35A         	5170602	CE  										UNKNOWN	INTERMITTENT    	D			H51R	K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			NM	03	122JW					217				ON 1/4/06 PILOT REPORTED ALTIMETER JUMPS DURING DESCENT, 300 FT, AND WARNING HORN SOUNDS.  NO OVERSPEED.  ALTIMETER SYST	EM WAS TESTED, IAW SRM AND FOUND TO BE OPERATIONAL.  NO TROUBLE NOTED.  AIRCRAFT REMAINS RVSM COMPLAINT.  (K)					2	L	7	2 	4F				A10CE   					 
2006050200002	20060502	00002		2006	5	2	2006FA0000224    	1	20060228	G	2422	2001012	CIRCUIT BOARD   	MARATHON    																INVERTER	INOPERATIVE     	B			NE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07					1108					RECEIVED STATIC INVERTER FOR OVERHAUL.  PRELIMINARY INSPECTION REVEALED THAT THE  PRINTED CIRCUIT BOARD (PCB) HAD BEEN M	ODIFIED WITH IC SOCKETS.  THE IC CHIPS WERE INSTALLED IN THE SOCKETS AND SEALED WITH A  SILICONE LIKE SUBSTANCE RATHER T	HAN BEING SOLDERED DIRECTLY INTO THE PCB.  JUMPER WIRE INSTALLED ON NON COMPONENT SIDE OF PCB.  POOR (COLD) SOLDER JOINT	S THROUGHOUT THE PCB NO SEALANT (CONFORMAL COATING) APPLIED TO NON COMPONENT SIDE OF PCCB AFTER REWORK.  (K)																 
2006032000018	20060320	00018	EU  	2006	3	20	2006FA0000225    	1	20060227	G	2121	125021116	BLOWER MOTOR    			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AC SYSTEM	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	865AF					85005	RL2631948A			PILOT REPORTED EXCESSIVE VIBRATION WITH AIR CONDITION ON.  WHILE TECH WAS TROUBLESHOOTING SYSTEM FOUND THAT BLOWER MOTOR	 HAD TOO MUCH END PLAY ON BLOWER FAN SHAFT MAKING IT VIBRATE.  NO RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2006032000011	20060320	00011	SO  	2006	3	20	2006FA0000226    	1	20060128	G	5610	1159SCB31029	WINDSHIELD      			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					PILOT WINDSHIELD	BROKEN          	B			VZGR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	05	99PD	5415 				314				AT FL 380 PILOTS WINDSHIELD SHATTERED.  SHATTERED AT HEATING ELEMENT. (K)						2	L	7	2 	4F	4	F		A12EA   	E2EU				 
2006050200009	20060502	00009		2006	5	2	2006FA0000227    	1	20060222	G	2434	ALU1003	HOUSING         																	ALTERNATOR	WORN            	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					F123155					THIS ALTERNATOR HAS 0 HRS TIME IN SERVICE.  DURING INSPECTION OF THIS UNIT.  IT WAS DISCOVERED THAT THE DRIVE-END BEARIN	G BORE WAS .006, OVERSIZE AND THE BEARING WAS VERY LOOSE IN THE BEARING BORE.  THIS END FRAME SHOULD HAVE BEEN REJECTED 	DURING THE OVERHAUL PROCEDED DUE TO THE EXCESSIVE WEAR OF THE BEARING BORE.  THIS SAME DEFECT WAS NOTED ON 2 OF THE LAST	 3 UNITS RECEIVED.  RECOMMENDATION INCLUDE A CLOSER INSPECTION FOR WEAR OF THE DRIVE END BEARING BORE SINCE THIS IS A FR	EQUENT PROBLEM WITH THIS MODEL. (K)															 
2006050200010	20060502	00010		2006	5	2	2006FA0000228    	1	20060302	G	2434	ALU1003	HOUSING         																	ALTERNATOR	OUT OF TOLERANCE	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					F123149					THIS ALTERNATOR HAS 0 HOURS.  DURING INSPECTIONOF THIS UNIT PRIOR TO INSTALLING ON AIRCRAFT, IT WAS DISCOVERED THAT THE 	ROTOR HAD EXCESSIVE SIDE PLAY AND WAS ALLOWING THE ROTOR TO RUB AGAINST THE STATOR LAMINATIONS.  THE DRIVE END BEARING B	ORE HAS EXCESSIVE WEAR AND THE BEARING IS LOOSE IN THE BORE.  THIS CONDITION WOUD HAE RESULTED IN ALTERNATOR FAILURE AND	 POSSIBLY RESULTED IN ENGINE FAILURE SINCE THIS UNIT IS GEAR DRIVEN BY THE ENGINE.  THIS IS THE 3RD UNIT IN 3 WEEKS FROM	 THIS SUPPLIER THAT HAD THIS SAME PROBLEM.  RETURNED FOR EVALUATION AND WARRANTY REPLACEMENT.  (K)															 
2006032100229	20060321	00229	SO  	2006	3	21	2006FA0000230    	1	20060223	G	3221	6705403	TRUNNION        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					NOSE GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	196SQ	3921 				32R7780259				UPON INSPECTION OF THE NOSE GEAR.  A 4.5 INCH CRACK WAS FOUND IN THE TUBULAR AREA OF THE LANDING GEAR TRUNNION CAUSE IS 	UNKNOWN, BUT SUSPECT HARD LANDING OR NOSE WHEEL TURNED BEYOND LIMITS.  (K)					1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006032100153	20060321	00153	SW  	2006	3	21	2006FA0000231    	1	20060227	G	5302	2050318211P	FITTING         			BELL  	204   	UH1H        	1181407	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAILBOOM	FRACTURED       	D				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			NM	13	623PB				BBBD1521	6413689				AC LANDED FOR SHUTDOWN AFTER OPERATING FOR APPROX 3 FLIGHT HOURS, AC WAS SHAKING DURING SHUTDOWN.  DURING POST FLIGHT IN	SP IT WAS FOUND THAT UPPER LT MOUNT HARD POINT PN 2050318211P ON TAILBOOM (PN 20503280071), WAS FRACTURED, HAD TORN THRU	 FWD TAILBOOM BLKHD (PN 205030807123S) ON AIRFRAME WAS ALSO CRACKED IN 2 PLACES RADIATING FROM BOOM MOUNT HOLE TO EDGE O	F FITTING.  AC RECORDS DO NOT REFLECT ANY INSTANCE OF HARD LANDING, OVER TORQUE, OR OTHER DAMAGE HISTORY.  AC HAS APPROX	 8400 HOURS TT, RECORDS SHOW THAT TAILBOOM WAS INSTALLED APPROX 5000 HOURS AGO.  SUSPECTED, WHEN UPPER FITTING FAILED IN	SIDE TAILBOOM, BOOM ASSY SAGGED, PLACING EXCESSIVE TWIST ON LWR LT AIRFRAME MOUNT CAUSING IT TO CRACK IN 2 PLACES.  (K)	1	G	7	1 	4U	3	U		EXPA1G71	E4CE				 
2006032100129	20060321	00129	CE  	2006	3	21	2006FA0000232    	1	20060223	G	2130	10138402831	SWITCH          			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A6       	52043	EA  					CABIN	OUT OF TOLERANCE	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	100BE					FL403				DURING INITIAL 12 MONTH TEST OF CABIN ALTITUDE WARNING SYS FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM TOLERAN	CE.  REPLACED SWITCH WITH NEW SUPERSEDING (PN 101-38402845) SWITCH ASSY FROM STOCK, NEW SWITCH ALSO TESTED OUT OF SERVIC	E LIMITS.  REPLACED WITH NEW (PN 101384028-45 SWITCH SUPPLIED BY RAPID, TESTS PASSED SUCCESSFULLY.  SUSPECT NEW 101-3840	28-31 AND 101-384028-45 SWITCH ASSY MAY HAVE FAULT WHICH CAUSES THEM TO PASS INITIAL QA TESTS, BUT FAILED AFTER USE OR I	N STORAGE.  (K)		2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2006032100116	20060321	00116	CE  	2006	3	21	2006FA0000233    	1	20060224	G	3520	10138402829	SWITCH          			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A6       	52043	EA  					CABIN	OUT OF TOLERANCE	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	100BE	468  				FL403				DURING INITIAL 12 MONTH TEST OF CABIN OXYGEN SYSTEM FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM TOLERANCE.  RE	PLACED WITH NEW SUPERSEDING PN 10138402843 SWITCH SUPPLIED BY RAPID, TESTS PASSED SUCCESSFULLY.  SUSPECT NEW 101384028-2	9 SEITCH ASSY MAY HAVE FAULT WHICH CAUSES THEM TO PASS INITIAL QA TESTS BUT FAIL AFTER USE OR IN STORAGE.  (K)				2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2006032100233	20060321	00233		2006	3	21	2006FA0000234    	4	20060220	G	2215	6226717104	SERVO           			BEECH 	MU300 	400A        	1155402	CE  										RUDDER SERVO	INTERMITTENT    	B			E81R	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	03	467LX					RK447				INVESTIGATED PILOT REPORT OF INTERMITTENT RUDDER BOOST FAILURE ALONG WITH SIMULATANEOUS AUTOPILOT AND YAW DAMPER DISEGAG	EMENT.  FOUND RUDDER SERVO INTERMITTENTLY FAILING.  REPLACED RUDDER SERVO WITH OVERHAULED UNIT, RUDDER BOOST AND AUTOPIL	OT FUNCTIONAL TESTS SATISFACTORY.  (K)				2	H	7	2 	4F			RT	A16SW   					 
2006032100119	20060321	00119	NE  	2006	3	21	2006FA0000235    	2	20060215	G	7200		ENGINE          			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					FUSELAGE	UNKNOWN         	B			UO2R	E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			GL	19	23FM	3127 	1811 			296	115241			OIL TEMP 112, OIL PSI 50, MASTER CAUTION LIGHT CAME ON OIL SMELL IN CABIN.  SHUT NR 3 ENGINE DOWN LANDED AT AIRPORT.  CA	USE UNKNOWN AT THIS TIME REMOVE ENGINE FOR INSPECTION AND REPAIR, INSTALLED RENTAL.  (K)					2	L	7	3 	4F	4	F		A46EU   	E1NM				 
2006032100234	20060321	00234		2006	3	21	2006FA0000236    	4	20060227	G	3460	70000006000	FLIGHT DIR      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					COCKPIT	INTERMITTENT    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	56FS					0576				JUST GOT 2003 SR22 BACK FROM GETTING REVISION 6 COMPLETED.  PUT ABOUT 10 HOURS ON THE AIRPLANE.  TWICE DURING THIS TRIP,	 THE PFD DISPLAY ROTATED OR ROLLED LIKE THE OLD TELEVISION SETS DID.  ONCE FOR ONLY 2 OR 3 SECONDS AND ANOTHER TIME FOR 	MAYBE 10 TO 20 SECONDS.  BOTH OF THESE OCCURRED IN LIGHT TO ODERATE CHOP AND AFTER MORE THAN AN HOUR OF FLIGHT.  ONE OF 	THESE OCCURRENCES WAS IN SOLID INSTRUMENT CONDITIONS AND THE OTHER WHILE ON IFR FLIGHT, WAS IN THE CLEAR.  HE IS A PILOT	 FOR A MAJOR AIRLINE.  HIS OPINION WAS THAT THERE COULD BE A WIRE OR CONNECTION LOOSE INSIDE THE BOX.  (K)		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006032100228	20060321	00228	SW  	2006	3	21	2006FA0000237    	1	20060217	G	2800	212040122101	DEBRIS MONITOR  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					SCAVENGE CUP	DEBONDED        	E			CUCA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	911KW	1147 				30592				AFTER REMOVAL OF DEBRIS MONITOR FOR 50 HR, CLEAN AND INSP, THE SCAVENGE CUP/SCREEN TUBE ASSY (PN A8858 IS UNSCREWED FROM	 UNIT.  THE O-RING FLANGE RING GLUED ONTO SCREEN TUBE SHEARS OFF OF SCREEN GLUE LINE, AND STAYS IN THE MAIN UNIT.  FIX M	AYBE TO APPLY GLUE TO RUFFED SURFACES (NOT DONE APARENTLY) AN TO INSIDE STEP OF ORING FLANGE RING TO THROUGH TUBE ASSY,O	R OTHER METHOD.  (K)			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006032100231	20060321	00231	EA  	2006	3	21	2006FA0000238    	1	20060225	G	3200		LANDING GEAR    			BLANCA	1413  	14132       	1201004	EA  	FRNKLN	6A4165	6A4165*     	27025	EA  					WINGS	FAULTY          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	07	74212					1325				THIS LANDING GEAR RETRACTED AT TOUCH-DOWN.  AIRCRAFT WAS IN STORAGE FOR A NUMBER OF YEARS.  IT WAS PUT BACK IN SERVICE T	HE SUMMER OF 2005.  THE LANDING GEAR WAS OVERHAULED (MECHANICAL) IN JAN 2006.  THE GEAR WAS MODIFIED FROM HAND CRANK RET	RACT TO ELE/HYD RETRACT, QUITE SOME TIME BACK.  FEEL THE ELECTRICAL PART OF THE DESIGN SHOULD BE LOOKED AT.  (NO SQUAT S	WITCH, ETC) GOOD GROUND SYS IN WOOD AIRCRAFT.  (K)			1	L	7	1 	3O	3	O		A773    	E238				 
2006032200100	20060322	00100	SO  	2006	3	22	2006FA0000239    	2	20060315	G	8550		RELIEF VALVE    			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ENGINE OIL SYS	RESTRICTED      	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	216N	34   				1801	689051			LOSS OF OIL PRESSURE, INSPECTED OIL PRESSURE RELIEF VAVLE AND FOUND TIP OF DRILL BIT LODGED IN RELIEF VALVE.  REMOVED TI	P OF DRILL BIT AND REASSEMBLED RELIEF VALVE.  GROUND RAN, OPS CHECKED GOOD.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006032200102	20060322	00102		2006	3	22	2006FA0000240    	4	20060208	G	2565	D31591478	SLIDE           			BOEING	737   	737300      	1384610	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					FUSELAGE	OUT OF ALIGNMENT	B			I6XR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	389UA					24664				THE ESCAPE SLIDE FOR DOOR R-2 WAS DEPLOYED FOR A SAMPLE INSPECTION.  THE SLIDE DID NOT DEPLOY CORRECTLY, THE SLIDE INFLA	TED TO THE FULL LENGTH, STRAIGHT OUT FROM THE AIRCRAFT, HOWEVER, IT WAS ROTATED 90 DEGREES, AND DID NOT TOUCH THE FLOOR.	  (K)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006032200103	20060322	00103	EA  	2006	3	22	2006FA0000241    	2	20060313	G	7420	M2917	HARNESS         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					SPARK PLUG CAPS	MISMANUFACTURED 	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	5228E					17271783				THE AIRCRAFT HAD MAGNETO LEADS THAT NEEDED TO BE REPLACED.  A NEW HARNESS SET WAS RECEIVED AND WAS INSTALLED ON THE ENGI	NE.  THE ENGINE RAN POORLY.  FOUND (T-4).  ALSO NOTED THAT THE SHIELD ON NR 1 BOTTOM WIRE HAD BEEN CUT DURING MANUFACTUR	ER AND THE SHIELD WAS OPEN.  MFG REPLACED THE HARNESS FREE OF CHARGE AND FREIGHT FREE.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006032200138	20060322	00138	CE  	2006	3	22	2006FA0000242    	1	20060216	G	3240		LINE            			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ44        	66000	GL  					LT MLG BRAKE	FAILED          	C				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			SO	35	701TF					525A0112	126045			AIRCRAFT DEPARTED THE RUNWAY DURING LANDING ROLLOUT.  FAILURE OF BOTH THE HYDRAULIC AND PNEUMATIC LINES TO THE LT MAIN L	ANDING GEAR BRAKE CAUSED THE AIRCRAFT TO SPIN INTO A GRASSY AREA ADJACENT TO THE RUNWAY.  THE NOSE LANDING GEAR SHEARED 	OFF AND THE AIRCRAFT CAME TO REST ON THE MAIN LANDING GEAR AND NOSE OF THE AIRCRAFT.  THERE IS SUBSTANTIAL DAMAGE TO THE	 NOSE OF THE AIRCRAFT AND SOME MINOR DAMAGE TO THE WINGS.  CAUSE OF THE LINE FAILURE IS UNDER INVESTIGATION.  (SO3520060	3622)		1	L	7	1 	4F	4	F	RT	A1WI    	E3GL				 
2006032200150	20060322	00150	SW  	2006	3	22	2006FA0000243    	1	20060207	G	3230		ACTUATOR        			GULSTM	114   	114TC       	0145002	SW  	LYC   	O540  	TIO540*     	41532	EA  					NLG	UNKNOWN         	B			CB5Y	K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	35	115TB					20031	L1061461A			AFTER REFITMENT, NLG FAILED TO EXTEND TO LAND POSITION.  AC HAD BEEN UNDERGOING WORK TO SATISFY AD.  AFTER WORK, GREEN N	OSE WHEEL INDICATOR WOULD NOT ILLUM.  FLYBY OF TWR, NLG WAS PARTIALLY EXTENDED TO ANGLE OF 45 DEGREES.  RECYCLING STILL 	FAILED TO EXTEND NLG BEYOND 45 DEGREES. PWROFF LANDING WAS EXECUTED, NLG COLLAPSED, AC CAME TO REST ON 2 PROP BLADES, NO	SE WHEEL BAY DOORS. LANDING HAD PUSHED NLG BACK TOWARD RETRACTED POSITION BUT WITH PART OF TIRE PROTRUDING THROUGH PARTI	ALLY OPEN NOSE BAY DOORS.  PIN ATTACHING  NOSE GEAR ACTUATOR TO NOSE LEG WAS REMOVED.  GEAR FELL UNHINDERED AND UNAIDED 	TO DOWNLOCKED POSITION.  INSP OF NLG, WHEN NG ACTUATOR IS AVAILABLE, (SHAFT BENT 45 DEGREES IN ACCIDENT) .  (K)	1	L	7	1 	3O	3	O	RT	A12SO   	E14EA				 
2006032200260	20060322	00260	CE  	2006	3	22	2006FA0000244    	1	20060210	G	5753	052390138	FLAP            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	WINGS	CRACKED         	B			NM2R	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	19	3533U	1200 				172S8890	L2982051A	UK23072		AIRCRAFT CAME IN FOR AN ANNUAL INSPECTION, DAMAGE TO THE FLAPS WERE FOUND DURING ROUTINE INSPECTION PROCESS.  RT FLAP HA	D CRACKS RADIATING OUT FROM RIVETS ON LOWER T/E SKIN, PLUS CRACKS RADIATING OUT FROM L/E SKIN, ON BOTTOM OF FLAP, IB OF 	MOUNTING BRACKET.  DAMAGE DESCRIBED WAS ON RT FLAP.  LT FLAP HAD SAME DAMAGE, ONLY LESS SEVERE.  THE PROBABLE CAUSE WAS 	SUSPECTED TO BE CAUSED FROM LOWERING THE FLAPS AT TOO HIGH AN AIRSPEED.  FLIGHT DEPARTMENT CHAIRMAN AGREED TO DISCUSS TH	IS POSSIBLE PROBLEM WITH THE OTHER FLIGHT INSTRUCTORS, SO THEYY CAN DISCUSS THE PROBLEM WITH THEIR STUDENTS.  (K)		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006032300042	20060323	00042	EA  	2006	3	23	2006FA0000245    	2	20060218	G	7200		ENGINE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT WING	MAKING METAL    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	72GC					264	PCE41557			LT ENGINE OIL PRESSURE STARTED FLUCTUATING.  PILOT RETURNED TO AIRPORT.  MAINTENANCE CHECKED OIL FILTER AND FOUND METAL 	IN OIL.  ENGINE REMOVED AND SENT TO REPAIR FACILITY.  (K)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006032300163	20060323	00163	EU  	2006	3	23	2006FA0000246    	1	20060221	G	5740	T700A5760031020	ATTACH BRACKET  			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  					OB LT WING	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	703QD	5659 				129				DURING A ROUTINE PHASE INSPECTION, THE LT WING TIP ASSY WAS REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON CABL	E.  AFTER REMOVAL OF THE TIP, THE INSPECTING TECHNICIAN NOTICED A CRACK IN AT THE OB ATTACH POINT.  THE BRACKET WAS REMO	VED AND INSPECTED WITH A 20X MAGNIFYING GLASS WHICH REVEALED NO LESS THAN 6 CRACKS IN THE BRACKET.  IT IS RECOMMENDED TH	AT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACKS WITH THE WING TIPS REMOVED.  (K)			1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2006032300050	20060323	00050	EU  	2006	3	23	2006FA0000247    	1	20060221	G	5740	T700A5760031000	SUPPORT BRACKET 			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  					AILERON	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	701QD	5954 				126				DURING A 6000 HOUR INSPECTION, THE LT AND RT WING TIP ASSEMBLIES WERE REMOVED TO FACILITATE FURTHER INSPECTION OF THE AI	LERON SYSTEM.  AFTER REMOVAL OF THE TIPS THE INSPECTING TECHNICIAN NOTED CRACKS IN BOTH THE LT AND RT AILERON OB ATTACH 	POINTS.  THE BRACKET WAS REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS WHICH CONFIRMED CRACKS IN BOTH THE BRACKETS. 	 IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACKS WITH THE WING TIPS REMOVED.  LT BRACKET (P	N T700A5760031000) RT BRACKET (PN T700A5760031001)		1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2006032300164	20060323	00164	EU  	2006	3	23	2006FA0000248    	1	20060221	G	5740	T700A5760031001	ATTACH BRACKET  			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  					OB WING ASSY	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	701QD					126				DURING A 6000 HOUR INSPECTION, THE LT AND RT WING TIP ASSEMBLIES WERE REMOVED TO FACILITATE FURTHER INSPECTION OF THE AI	LERON SYSTEM.  AFTER REMOVAL OF THE TIPS THE INSPECTING TECHNICIAN NOTED CRACKS IN BOTH THE LT AND RT AILERON OB ATTACH 	POINTS.  THE BRACKET WAS REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS WHICH CONFIRMED CRACKS IN BOTH THE BRACKETS. 	 IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACK WITH THE WING TIPS REMOVED.  LT BRACKET (PN	 T700A5760031000) ( RT BRACKET (PN T700A5760031001) (K)		1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2006040600211	20060406	00211	CE  	2006	4	6	2006FA0000249    	1	20060215	G	3510	553008	GASKET          			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE7313A    	01518	WP  					O2 MASK	LEAKING         	B			OVVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	32KJ				8953	93				PILOT O2 MASK HAD ORIGINAL O/H DATE OF 6/05.  MASK WAS PLACED IN SERVICE IN AC 55093.  MASK DID NOT TEST PROPERLY AT DEL	IVERY DATE OF 6/23/05.  MASK WAS SENT BACK, FOUND TO HAVE A LEAK.  MASK WAS REPAIRED AND SENT BACK TO AC.  MASK WAS FOUN	D TO BE LEAKING AGAIN AFTER 2 WEEKS IN AIRCRAFT.  AGAIN, IT WAS REPAIRED.  PLACED BACK IN SERVICE, AFTER 2 MONTHS MASK W	AS FOUND LEAKING AGAIN.  IT WAS SENT BACK FOR ANOTHER REPAIR, DATED 12/5/05.  MASK HAS BEEN FOUND TO BE LEAKING FOR FOUR	TH TIME, SENT BACK FOR FOURTH TIME FOR REPAIR.  4 REPAIRS ON THIS MASK SINCE O/H DATE OF 6/05 IS UNACCEPTABLE.  HAVE SER	IOUS DOUBTS AS TO CAPABILITIES TO MAKE OVERHAULS AND REPAIRS THAT LAST.  PILOT O2 MASK IS VERY CRITICAL COMPONENT.	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006032300043	20060323	00043	CE  	2006	3	23	2006FA0000250    	1	20060222	G	5346	051313211	BRACKET         	CESSNA      		CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					ENGINE COMPARTMT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7362M	2268 				55662				INSP 0513132-11, MOUNT BRACKET WAS FOUND TO BE CRACKED. CRACK RAN VERT THROUGH BRACKET AROUND OUTER RADIUS OF AN960-616 	WASHER ON UPPER ENG MOUNT BOLT. INSP WAS DONE DUE TO 2 OTHER KNOWN REPORTS OF CRACKS IN THIS BRACKET ON SAME MODEL OF AC	, ONE RESULTED IN A PARTIAL ENG AND FIREWALL SEPARATION FROM AC ON LANDING.  MUST LOOK INSIDE STRINGER BEHIND  INSTRUMEN	T PANEL. RECOMMEND THAT SPECIAL ATTENTION BE PAID TO UPPER ENG MOUNT BRACKETS DURING INSP.  0513132-3 AND -4 STRINGER AS	SEMBLIES WERE USED ON 175 SN 55001 THRU 17557119, 172 SN 17247747 THRU 17272884P172 SN P17257120 THRU P17257188 F172 SN 	F17201235 THRU F17201909  FR172 SN FR172-0001 THRU FR17200655R172 SN R1722000 THRU R1723199.	1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2006051200044	20060512	00044	CE  	2006	5	12	2006FA0000251    	1	20060222	G	3010	SMR20142112	BOOT            			BEECH 	90    	B90         	1152912	CE  										WINGS	MISLOCATED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	379VM					LW27				UPON INSTALLATION OF NEW LT AND RT WING DE-ICE BOOTS WITH NEW PMA P/N SMR2014-21-1, AND -2, IT WAS DISCOVERED THE AIR IN	LET TUBES ARE INSTALLED IN THE WRONG LOCATION, MAKING IT IMPOSSIBLE TO MATCH THE BOOT CENTERLINE WITH THE LE CENTERLINE.	  MFG AND OEM DRAWINGS SHOW 1 INCH FROM BOOT CENTERLINE TO INLET TUBE CENTERLINE.  SMR BOOTS HAVE 1.5625 INCH.  THE ONLY	 WAY THIS BOOT CAN BE INSTALLED IS TO SHIFT THE ENTIRE BOOT UP ON THE WING AT LEAST .5625 INCH.  THIS CAUSES CONCERN FOR	 CHANGE IN STALLING SPEED AT SLOW FLIGHT WITH THE BOOTS INFLATED.  SMR HAS BEEN VERY HELPFUL AND CONCERNED.  OEM BOOTS W	ERE PURCHASED AND INSTALLED.  SMR BOOTS WERE RETURNED.	1	L	7	2 	3T				3A20    					 
2006051200057	20060512	00057	CE  	2006	5	12	2006FA0000252    	1	20060222	G	3010	SMR20142112	BOOT            			BEECH 	90    	B90         	1152912	CE  										WINGS	MISMANUFACTURED 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	379VM					LW27				ON INSTALLATION OF NEW LT AND RT WING DE-ICE BOOTS, PMA P/N SMR2014-21-1,  -2, WAS DISCOVERED AIR INLET TUBES ARE INSTAL	LED IN WRONG LOCATION, MAKING IT IMPOSSIBLE TO MATCH BOOT CENTERLINE WITH LE CENTERLINE.  OEM DRAWINGS SHOW 1 INCH FROM 	BOOT CENTERLINE TO INLET TUBE CENTERLINE.  SMR BOOTS HAVE 1.5625 INCH.  ONLY WAY THIS BOOT CAN BE INSTALLED IS TO SHIFT 	ENTIRE BOOT UP ON WING AT LEAST .5626 INCH.  CAUSES CONCERN FOR CHANGE IN STALLING SPEED AT SLOW FLIGHT WITH BOOTS INFLA	TED.  SMR HAS SOLD APPROX 20 UNITS WITH NO COMPLAINTS.  SEVERAL MECHANICS  (THAT IS JUST REF LINE ON BOOT, GO AHEAD AND 	GLUE THEM ON).  SMR HAS BEEN VERY HELPFUL AND CONCERNED.  OEM BOOTS WERE PURCHASED, INSTALLED.  SMR BOOTS WERE RETURNED.	1	L	7	2 	3T				3A20    					 
2006032300054	20060323	00054	SO  	2006	3	23	2006FA0000253    	1	20060217	G	8000		WIRE            	PIPER       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	CONTACTOR	LOOSE           	B				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	15	9206H					2841006	L1229139A	A53071		MFG HAS RECENTLY ISSUED REPLACEMENT PWR CONTACTORS, IN THIS CASE FOR ENG STARTER, WITH CONTACTORS THAT HAVE PLASTIC INSU	LATED MOUNTING (FEET). REPLACEMENT CONTACTORS UTILIZE A GROUND WIRE UNDER BOLT HEAD OF ONE OF MOUNT BOLTS FOR CONTACTOR 	ACTIVATION CIRCUIT GROUND. PLASTIC PORTION OF FEET COMPRESS DURING INSTALLATION, TORQUE PROCESS. CONTACTOR ATTACH POINT 	LOOSENS CAUSING CIRCUIT WIRE TO GROUND, TO LOOSEN RESULTING IN HIGH RESISTANCE TO GROUND FOR STARTER CONTACTOR ACTIVATIO	N CIRCUIT. RESULT, PLASTIC (FEET) MELT DUE TO HIGH RESISTANCE HEAT, CAUSING MATERIAL ON CABIN SIDE OF FIREWALL TO CAUSE 	SMOKE IN COCKPIT.  BELIEVE THAT THIS COULD CAUSE A FIRE.	1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006032300201	20060323	00201	CE  	2006	3	23	2006FA0000254    	1	20060223	G	5511		SPAR            			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					STABILIZER	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	355RM					033				INSPECTIONS, HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HINGE BRACKETS OF AT L	EAST 2 AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT	 OF THE STABILIZER.  RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME 	BETWEEN INSPECTION REQUIREMENTS. THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE INTERIORITY OF THE SPAR A	ND ATTACHED ELEVATOR HINGE MOUNTING.		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006032300067	20060323	00067	CE  	2006	3	23	2006FA0000255    	1	20060223	G	5511		SPAR            			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					STABILIZER	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	355RM					033				DURING 12,000/12 YR DEMATE INSPECTIONS WE HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE EL	EVATOR HING BRACKETS OF AT LEAST TWO AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF T	HE SPAR FLANGES OR REPLACEMENT OF THE STABALIZER.I RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSID	ERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. IN MY OPINION, THE CORROSION HAD PROGRESSED TO THE POINT 	OF COMPROMISING THE INTERURITY OF THE SPAR AND ATTACHED ELEVATOR HING. MOUNTING.		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006032300202	20060323	00202	CE  	2006	3	23	2006FA0000256    	1	20060223	G	5511		SPAR            			LEAR  	55    	55LEAR      	5170702	CE  										STABILIZER	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	355RM					033				INSPECTIONS HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HINGE BRACKETS OF AT LE	AST 2 AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT 	OF THE STABILIZER.  RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME B	ETWEEN INSPECTION REQUIREMENTS. IN MY OPINION, THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE SPAR AND AT	TACHED ELEVATOR HINGE MOUNTING.		2	L	7	2 	4F				A10CE   					 
2006032300118	20060323	00118		2006	3	23	2006FA0000257    	4	20060303	G	2211	065001767904	AUTOPILOT SYS   			CESSNA	182   	182T        	2072703	CE  											INTERMITTENT    	B			FSER	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NE	05										INTERMITTENT PITCH TRIM AND ACCELEROMETER FAILURES.  POSSIBLY CAUSED BY INADEQUATE CONNECTOR ENGAGEMENT WITH THE MOUNTIN	G RACK CONNECTORS, CAUSED BY IMPROPER POSITIONING OF THE TOP COVER.					1	H	7	1 	3O			NT	3A13    					 
2006032300132	20060323	00132	CE  	2006	3	23	2006FA0000258    	1	20060301	G	2700		FLT CONTROLS    			CESSNA	172   	172M        	2072418	CE  											SEIZED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	00	1295U					17266989				AIRCRAFT HAD BEEN TREATED WITH ACF-50 OVER THE LIFE OF THE AIRFRAME.  SEVERAL PULLEYS IN THE AILERON, ELEVATOR AND FLAP 	SYSTEMS WERE FOUND SEIZED OR GUMMED UP WITH ACF-50.  LAST APPLICATION OF ACF-50; 18MO.					1	H	7	1 	3O			NT	3A12    					 
2006040500225	20060405	00225	CE  	2006	4	5	2006FA0000259    	1	20060307	G	2710	2424000258	CASTING         			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					LT AILERON	BENT            	B			JGVR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CE	09	647TS					047				INCOMING INSPECTION FOUND AILERON DRIVE YOKE ATTACH CASTING BENT.  UPON FURTHER INSPECTION IT WAS DISCOVERED THE DRIVE Y	OKE UPPER OR LOWER SHIMS WERE NOT INSTALLED.  DRIVE YOKE ATTACH BOLT WAS INSTALLED CAUSING THE CASTING TO BE BENT AND RE	QUIRES REPLACEMENT BY OEM.  THIS COULD HAVE BEEN PREVENTED BY FOLLOWING MAINTENANCE MANUAL INSTALLATION INSTRUCTIONS.  (	K)			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006040400238	20060404	00238	CE  	2006	4	4	2006FA0000260    	1	20060306	G	7921	8406R	OIL COOLER      			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A1A     	41514	EA  						SPLIT           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5496H					17265466	L2971136A			DURING ROUTINE RUN-UP FOLLOWING AN OIL CHANGE, AN IMMEDIATE EXPULSION OF SEVERAL QUARTS OF OIL OCCURRED IN SECONDS.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2006040400237	20060404	00237	CE  	2006	4	4	2006FA0000262    	1	20060301	G	2810	PMA20331	FUEL CELL       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					LT, RT WINGS	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	56JK	2814 	1778 		690	TC1938				FOUND FUEL SYTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE.  AFTER HAVING THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE	 FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN.  AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AG	AIN AND THE SUBSTANCE WAS FOUND AGAIN.  BOTH FORWARD FUEL CELLS WERE REMOVED FROM THE AIRCRAFT.  THE SPONGE-LIKE MATERIA	L INSIDE THE WING ROOT HEADER TANK PORTION OF THE FUEL CELL WAS FOUND IN A DETERIORATED CONDITION AND CONTAMINATING THE 	ENTIRE FUEL SYSTEM. NEW FUEL CELLS WERE ORDERED.  (K)		1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2006040500153	20060405	00153	CE  	2006	4	5	2006FA0000265    	1	20060301	G	2810	PMA20332	BAFFLE          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					WING FUEL CELLS	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	56JK	2814 	1778 		692	TC1938				FOUND FUEL SYSTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE.  AFTER HAVE THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE 	FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN.  AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGA	IN AND THE SUBSTANCE WAS FOUND AGAIN.  BOTH FORWARD FUEL CELLS WERE REMOVED FROM THE AIRCRAFT.  THE SPONGE-LIKE MATERIAL	 INSIDE THE WING ROOT HEADER TANK PORTION OF THE FUEL CELL WAS FOUND IN A DETERIORATED CONDITION AND CONTAMINATING THE E	NTIRE FUEL SYSTEM.  NEW FUEL CELLS WERE ORDER.  (K)		1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2006040500228	20060405	00228	EU  	2006	4	5	2006FA0000266    	1	20060217	G	2120	4783658519	FLEX DUCT       			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN FLOOR DUCT	DETERIORATED    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	290CA	10907				216				DURING C-CHECK, BY ACCESS OF FUSELAGE REPAIR, IT WAS FOUND THAT FLEXIBLE AIR CONDITIONING DUCTS WERE BADLY DETERIORATED.	  FOAM ON INSIDE OF DUCTS WERE COMING LOOSE AND SOME OF DUCTS WERE COLLAPSED.  THESE DUCTS ARE JUST PLAIN OLD.  MFG TIME	 LIMITS DO NOT COVER THESE DUCTS AND DURING  800 HOUR C-CHECK AIRFRAME INSP THERE IS NOT A REQUIREMENT TO INSPECT INSIDE	 OF DUCTS FOR BLOCKAGE OR COLLAPSED DUCTS.  FLEX DUCTS CONNECT BELOW THE BLOW AND RUN UP SIDE OF THE FUSELAGE TO LWR AIR	 CONDITIONING VENTS.  THESE ARE NOT HOT AIR DUCTS, UNDER A UNFORSEEN CIRCUMSTANCE, POSES A POSSIBLE FIRE HAZARD IF DUCT 	TEMPERATURES GET HOT.  CALLED MFG TO GET FLEX DUCTS, PN CROSSED TO A NEW STYLE DUCT (PN BWT103080360A.)  (K)	2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2006040500175	20060405	00175	SO  	2006	4	5	2006FA0000267    	1	20060228	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540*     	41532	EA  					RMLG	FAILED          	B			DZZR	O				OTHER                   				P			NO WARNING INDICATION     			CR	CRUISE         	1			GL	09	59815					317612041				AFTER SELECTING (GEAR DOWN), PILOT WAS UNABLE TO GET A GREEN LIGHT FOR RT MLG, IN EITHER NORMAL OR EMERGENCY EXTENSIONS.	  GROUND OBSERVERS ADVISED RMLG WAS DOWN AND IB GEAR DOORS WERE OPEN.  UNEVENTFUL LANDING FOLLOWED.  INVESTIGATION REVEA	LED RMLG DOWNLOCK SWITCH FAILED ELECTRICALLY.   SWITCH WAS REPLACED, SEVERAL GEAR CYCLES ON JACKS.  AIRCRAFT TEST FLOWN,	 SATISFACTORY.  (K)			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006040500184	20060405	00184	NE  	2006	4	5	2006FA0000268    	2	20060302	G	7250	0292817220	RING            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ENGINE	CRACKED         	B			HXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	405AE					3286	22103			IN COMPLIANCE WITH AD AND SB, OUR MECHANIC WAS INSPECTING THE ABOVE DESCRIBED ENGINE AND FOUND THE COMPONENT LISTED BELO	W TO BE OUT OF SERVICEABLE LIMITS AS INDICATED IN THE 2 DOCUMENTS.  REMOVED THE CONTAINMENT RING FROM SERVICE AND INSTAL	LED A NEW POST MOD TU-22 RING AS ADVISED.  (K)				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006040400240	20060404	00240	NM  	2006	4	4	2006FA0000269    	1	20060215	G	2913	123412	COVER           	SMITHSIND   		BOEING	737   	737*        	       	NM  										SHUTOFF VALVE	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					6313					(REF NR:  204244/PH3) COVERED CRACKED.  PROBABLE CAUSE: FATIGUE.  REDESIGN COVER.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006040500235	20060405	00235	NM  	2006	4	5	2006FA0000270    	1	20060215	G	2913	123412	COVER           	SMITHSIND   		BOEING	737   	737*        	       	NM  										HYD SYS	CRACKED         	D			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					6314					(REF NR: 204200/PH3)  COVER CRACKED, PROBABLE CAUSE, FATIGUE.  REDESIGN COVER.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006040400236	20060404	00236	NM  	2006	4	4	2006FA0000271    	1	20060213	G	2900	271T00714	HOUSING         	BOEING      		BOEING	767   	767*        	       	NM  										HYDRAULIC SYS	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		28833			3087					(203230/FXS) HOUSING CRACK AT THE PRESSURE (INLET) PORT FOR THE CHECK VALVE BORE.  PROBABLE CAUSE: FATIGUE.  REDESIGN HO	USING.  (K)					2	L	7	2 	4F			RT	A1NM    					 
2006040400233	20060404	00233	NM  	2006	4	4	2006FA0000272    	1	20060213	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										LANDING GEAR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										(204174/PH3) HOUSING CRACKED IN THE BORE OF THE MOUNTING LUG.  PROBABLE CAUSE: FATIGUE.  REDESIGN HOUSING.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006032700002	20060327	00002	CE  	2006	3	27	2006FA0000273    	1	20060301	G	7120	051313211	MOUNT           			CESSNA	175   	175A        	2072504	CE  										ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	6997E	1900 				56497				DURING VISUAL INSPECTION FOUND THE 0513132-11 UPPER LEFT HAND ENGINE MOUNT BRACKET IN THE 0513132-3 STRINGER ASSEMBLY CR	ACKED.  INSPECTION WAS PERFORMED DUE TO OTHER REPORTED FAILURES OF THIS BRACKET ON THE SAME MODEL OF AIRCRAFT.  RECOMMEN	D INSPECTION OF BRACKETS IN ALL AIRCRAFT WITH THE 0513132-3 ENGINE MOUNT STRINGER ASSEMBLY.				1	H	7	1 	3O				3A17    					 
2006032700034	20060327	00034	NM  	2006	3	27	2006FA0000274    	1	20060301	G	6320	5100400	HOSE            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					XMSN OIL	CRACKED         	D				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			EA	11	902PD	489  	489  			9000084				HOSE IS INSTALLED ON MD902 HELICOPTERS.  MD P/N IS 900D3409526-105.  HOSE IS USED FOR MAIN TRANSMISSION OIL COOLING.  FO	UND LARGE ACCUMULATION OF OIL ON TRANSMISSION DECK AFTER FLIGHT.  HOSE WAS FOUND TO BE CRACKED IN ONE OF THE BELLOWS. (C	ORE OF HOSE IS STAINLESS STEEL BELLOWS WITH A COVERING OF STAINLESS STEEL BRAID).  REPLACED HOSE WITH NEW.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006032700045	20060327	00045	CE  	2006	3	27	2006FA0000275    	1	20060307	G	2420	991059112	ALTERNATOR      			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					ENGINE	BURNED          	C				H	O			DEACTIVATE SYST/CIRCUITS	OTHER                   			H	J	S	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        	AFFECT SYSTEMS            	CR	CRUISE         	1			CE	07		76   	76   			08255	L3083148E			BATTERY TERMINAL LUG BURNT OFF DUE TO SHORT CAUSED BY TERMINAL ON WIRE HARNESS BREAKING OFF.  THIS CAUSED THE ALTERNATOR	 CONTROL UNIT TO FAIL (SMOKE) AND HEAVY ARCING AT TERMINAL LUG.  THERE WAS AN INDICATION OF NOT CHARGING ON G-1000 MFD A	ND PFD SCREENS.  THIS ALSO CAUSED FLUCUATION ON THE FUEL FLOW INDICATION.  SUSPECT SHORTED CABLE THRU ALTERNATOR ATTACHE	D TO ENGINE THRU ENGINE AND THEN THRU SENSOR.  NOTE: NO CIRCUIT BREAKER POPPED AND NO FUSEABLE LINK BETWEEN BATTERY HARN	ESS CONNECTED TO THE ALTERNATOR AND ALTERNATOR CONTROL UNIT.  SUSPECT WEAK TERMINAL AT ALTERNATOR ALONG WITH POOR INSTAL	LATION SUPPORT BY CLAMPS OR TIE-WRAPS.  CORRECTED AS REQUIRED WITH A MORE HEAVIER DUTY TERMINAL.	1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2006032700046	20060327	00046	SO  	2006	3	27	2006FA0000276    	1	20060306	G	3230		SEQUENCE VALVE  			PIPER 	PA46  	PA46350P    	7104602	SO  										NLG	DEFECTIVE       	B				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CE	03	55WH	1912 				4636204				LOUD NOISE REPORTED BY PILOT, AND FOUND NOSE GEAR DOOR ACUATOR ROD END BROKEN.  LANDING GEAR UNSAFE LIGHT STAYS ON WITH 	GEAR UP.  FOUND NOSE GEAR DOOR SEQUENCE VALVE INOPERTIVE.					1	L	7	1 	3O			RT	A25SO   					 
2006032700047	20060327	00047	SW  	2006	3	27	2006FA0000285    	1	20060302	G	2730	740101000	TORQUE TUBE     			MOONEY	M20   	M20J        	5870219	SW  										TRIM SYS	WORN            	B			CTYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	913JN	7274 				241184				EMPENNAGE TRIM CONTROL TORQUE FOUND TO HAVE A DEEP GROOVE FROM WEARING ON CAT TRACK/GROMMET WHERE IT PASSES THROUGH STIF	FENERS.  THIS TUBE WAS ALSO WELD REPAIRED AT SOME TIME PREVIOUS THEN SWAPPED END FOR END SO TUBE WOULD WEAR ON A NEW SUR	FACE.  IT APPEARS THIS WAS DONE DURING AN AIRCRAFT REPAIR AFTER AN ACCIDENT.  NO DOCUMENTATION IN AIRCRAFT RECORDS OF TH	IS REPAIR.  NEW TUBE INSTALLED BY REPAIR STATION.  THIS AIRCRAFT HAD BEEN THROUGH NUMEROUS ANNUAL INSPECTIONS AND NOT RE	PLACED OR DOCUMENTED.  		1	L	7	1 	3O				2A3     					 
2006051800252	20060518	00252	GL  	2006	5	18	2006FA0000286    	1	20060227	G	7603		THROTTLE CABLE  			AMTR  	SONEX 	SONEX       	056085Q	GL  										COCKPIT	BINDING         	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	03	415KP	20   				514				AIRCRAFT EXPERIENCED A LOSS OF POWER, AND A SUBSEQUENT FORCED LANDING RESULTING IN EXTENSIVE DAMAGE TO THE AIRCRAFT, DUE	 TO THE THROTTLE BEING STUCK IN THE IDLE POSITION. WHILE REDUCING POWER TO THE ENGINE PILOT EXPERIENCED BINDING IN THE T	HROTTLE CABLE , FURTHER ATTEMPTS TO FREE THE THROTTLE RESULTED IN THE THROTTLE BEING STUCK IN THE IDLE POSITION.  FOLLOW	 ON INSPECTIONS OF THE CARBURETOR AND ASSOCIATED LINKAGE FOUND EXCESSIVE PLAY IN THE CABLE BETWEEN THE THROTTLE CONTROL 	AND THE FIREWALL. THE EXCESS SLACK IN CABLE WAS NOT SECURED OR CLAMPED CAUSING THE CABLE ASSEMBLY TO BEND WHILE MOVING T	HE THROTTLE AND CAUSING BINDING.	1	L	7	1 	3O			NC	EXPA1L71					 
2006033000003	20060330	00003	NE  	2006	3	30	2006FA0000299    	1	20060316	G	3020		HINGE           			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1A    	41514	EA  					CARB HEAT BOX	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	2994P	2470 	59   			956	L1997351A			DURING ANNUAL INSPECTION FOUND ALTERNATE AIR VALVE HINGE WORN THRU.  REMOVED HEAT BOX ASSY AND FOUND BOX CRACKED 50 PERC	ENT AROUND MOUNTING FLANGE.  CRACK COULD NOT BE SEEN WITH BOX ON AIRCRAFT.					1	H	7	1 	3O	3	O		1A13    	1E10				 
2006033000083	20060330	00083	NM  	2006	3	30	2006FA0000300    	1	20060315	G	2761	BACS12HL4H10P	BOLT            			BOEING	737   	7372H6      	1384604	NM  										SPOILER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	902WG					22620				DURING A CHECK FOUND LOWER AFT BOLT HEAD BROKEN AT ACTUATOR TO MANIFOLD MOUNT FLANGE.  NO OTHER DAMAGE FOUND AND NO LEAK	 SEEN.					2	L	7	2 	4F			RT	A16WE   					 
2006033100070	20060331	00070	CE  	2006	3	31	2006FA0000301    	1	20060304	G	5551	0431148	ATTACH FITTING  			CESSNA	150   	152         	2071835	CE  										HORIZONTAL STAB	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	48968	13660				15281080				PART ATTACHES VERTICAL STABILIZER SPAR TO HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9.  PROBABLE CAUSE IS HI	GH ACTT.					1	H	7	1 	3O			NT	3A19    					 
2006041100052	20060411	00052	SO  	2006	4	11	2006FA0000302    	2	20060310	G	7414	6310	MAGNETO         			CESSNA	185   	185F        	2072820	CE  	CONT  	O550  	IO550D      	17042	SO  					ENGINE	CHAFED          	C				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	23		126  					680081			ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GE	AR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.					1	H	7	1 	3O	3	O		3A24    	E3SO				 
2006041100055	20060411	00055	SO  	2006	4	11	2006FA0000303    	2	20060310	G	7414	6310	MAGNETO         			CESSNA	185   	185F        	2072820	CE  	CONT  	O550  	IO550D      	17042	SO  					ENGINE	CHAFED          	C				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	23	PKMCD	126  					680081			ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GE	AR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.					1	H	7	1 	3O	3	O		3A24    	E3SO				 
2006041100053	20060411	00053	SO  	2006	4	11	2006FA0000304    	2	20060310	G	7414	6310	MAGNETO         			CESSNA	185   	185F        	2072820	CE  	CONT  	O550  	IO550D      	17042	SO  					ENGINE	CHAFED          	C				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	23	PKMCD	126  					680081			ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GE	AR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.					1	H	7	1 	3O	3	O		3A24    	E3SO				 
2006041100054	20060411	00054	SO  	2006	4	11	2006FA0000305    	2	20060310	G	7414	6310	MAGNETO         			CESSNA	185   	185F        	2072820	CE  	CONT  	O550  	IO550D      	17042	SO  					ENGINE	CHAFED          	C				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	23	PKMCD	126  					680081			ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GE	AR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.					1	H	7	1 	3O	3	O		3A24    	E3SO				 
2006041100106	20060411	00106	SO  	2006	4	11	2006FA0000307    	2	20060208	G	8500		ENGINE          	CONT        		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	RT WING	UNKNOWN         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	106GA				824277R	TH437	824277R	ED3372		RT ENGINE WAS STARTED AND PILOT NOTICED LOW OIL PRESSURE.  INSTALLED ANOTHER GAUGE IN LINE TO VERIFY PROBLEM RAN ENGINE,	 OIL PRESSURE CERTIFIED LOW.  CHANGED OIL AND INSPECTED FILTER.  FOUND NO OBVIOUS PROBLEMS, STARTED ENGINE, HAD NO OIL P	RESSURE, PULLED RELIEF VALVE.  DETERMINED THAT SOMETHING INSIDE THE ENGINE WAS COMING APART.  REMOVED ENGINE TO SEND BAC	K TO ENGINE OVERHAULER.  (K)			1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P36EA	 
2006041100034	20060411	00034	EA  	2006	4	11	2006FA0000309    	2	20060224	G	7320	63B23440	FLOW DIVIDER    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE	CORRODED        	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CE	07	696MS	91   	50   			172S10079	L3242151E	JHA7660		AIRCRAFT FAILED TO START & RUN. NO FUEL FLOW INDICATED ON G-1000. TROUBLSHOOT FUEL SYS & FOUND FUEL NOT PASSING THROUGH 	FLOW DIVIDER. SENT UNIT FOR REPAIR. AT THAT TIME AIRCRAFT HAD 41.0 HRS SINCE NEW. SECOND TIME AT 91.0 HRS.SINCE NEW, HAD	 THE SAME PROBLEM AS INDICATED AS ABOVE.  BOTH TIMES FOUND THE VALVE STEM STUCK INSIDE THE BORE. APPEARS TO BE A RUST/BR	OWN COLORED CONTAMINATION AND SLIGHT SCORING. FLOWED FUEL INTO TEST JAR AND NO PARTICLES WAS NOTED ON AIRCRAFT FUEL SYST	EM. APPEARS TO BE CORROSION INSIDE BORE. B&S AIRCRAFT POLISHED VALVE STEM AND BORE, OPS. CK. OK.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006041100036	20060411	00036	CE  	2006	4	11	2006FA0000311    	1	20060224	G	2842		FLOAT           			CESSNA	172   	172H        	2072424	CE  										FUEL INDICATION	FAILED          	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	01	3786R					17255586				LEFT WING FUEL GAGE REGISTERED EMPTY. UPON INSPECTION OF THE FLOAT ASSEMBLY, FOUND FLOAT TO BE ONE THIRD FULL OF FUEL. M	ETAL FLOAT HAS MULTIPLE PIN HOLES. RIGHT SIDE WAS FINE - NO LEAKS.					1	H	7	1 	3O			NT	3A12    					 
2006041100037	20060411	00037	EA  	2006	4	11	2006FA0000312    	2	20060224	G	7261	156F00512D0260	HOSE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE OIL	DAMAGED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	11	220FS					31T7620052	PCE51064	BU13482		DURING CLIMB, PILOT NOTED RT OIL PRESS FLUTUATING SLIGHTLY & SLOWLY FALLING.  ENGINE SHUTDOWN & RETURNED TO BASE.  INVES	TIGATION REVEALED A LEAKING OIL COOLER HOSE. LEAK POINT COVERED BY FIRESLEEVING.  HOSE REMOVED & SLEEVING CUT OPEN REVEA	LING WIRE BRAID.  EXTERNAL EXAMINATION DID NOT INDICATE ANY OBVIOUS VISIBLE DEFECT.  FURTHER INVESTIGATION USING A FLEXI	BLE LIGHT SOURCE REVEALED A FAILED INNER WALL MID-WAY IN THE HOSE AND ON THE INSIDE RADIUS OF THE HOSE BEND. THE HOSE MA	NF. DATE 01/04.  PROBABLE CAUSE WAS INCORRECT HANDLING OR INSTALLATION OF HOSE AT SOME POINT WHICH RESULTED IN KINKING O	F THE HOSE AND EVENTUAL FAILURE OF THE INNER WALL.	1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2006041100038	20060411	00038	CE  	2006	4	11	2006FA0000313    	1	20060226	G	5346	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENGINE MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7536M	2641 				55836				DURING VISUAL INSPECTION OF UPPER ENGINE MOUNT BRACKETS IN THE UPPER ENGINE MOUNT STRINGER ASSEMBLIES, FOUND THE L/H 051	3132-11 BRACKET CRACKED. INSPECTION WAS PERFORMED DUE TO RECENT REPORTS OF FINDING BRACKETS CRACKED ON LIKE MODELS OF AI	RCRAFT.				1	H	7	1 	3O			NT	3A17    					 
2006041100040	20060411	00040	CE  	2006	4	11	2006FA0000318    	1	20060227	G	5346	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENGINE MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	141JA	4791 				55224				FOUND THE LEFT UPPER ENGINE MOUNT BRACKET P/N 0513132-11 CRACKED THROUGH AROUND THE WASHER. BRACKET IS LOCATED AT THE FR	ONT OF THE 0513132-3 ENGINE MOUNT STRINGER AND IS DIFFICULT TO SEE DURING ROUTINE INSPECTIONS. INSPECTION WAS PERFORMED 	DUE TO SEVERAL OTHER CASES OF THE BRACKET BEING FOUND CRACKED ON LIKE AIRCRAFT.				1	H	7	1 	3O			NT	3A17    					 
2006041100042	20060411	00042	CE  	2006	4	11	2006FA0000320    	1	20060301	G	5346	051313211	BRACKET         			CESSNA	175   	175A        	2072504	CE  										ENG MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	6997E	1900 				56497				DURING VISUAL INSPECTION FOUND THE 0513132-11 UPPER RIGHT HAND ENGINE MOUNT BRACKET IN THE 0513132-4 STRINGER ASSEMBLY C	RACKED. INSPECTION WAS PERFORMED DUE TO OTHER REPORTED FAILURES OF THIS BRACKET ON THE SAME MODEL OF AIRCRAFT. RECOMMEND	 INSPECTION OF BRACKETS IN ALL AIRCRAFT WITH THE 0513132-4 ENGINE MOUNT STINGER ASSEMBLY.				1	H	7	1 	3O				3A17    					 
2006041100043	20060411	00043	CE  	2006	4	11	2006FA0000321    	1	20060301	G	5541	05310051	RIB             			CESSNA	172   	172         	2072402	CE  										RUDDER	MISSING         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	6775A	2262 				28875				RUDDER WAS REMOVED TO REPLACE CRACKED CORRUGATED SKIN BETWEEN LOWER TWO RIBS. ON SKIN REMOVAL, IT WAS DISCOVERED THAT SL	ANT RIB 0531005-1, (EXTENSION OF REAR SPAR) WAS MISSING. THERE WERE NO HOLES DRILLED IN BOTTOM RIB P/N 0531001-25 OR RIB	 P/N 0531001-22 TO WHICH THE SLANT RIB ATTACHES. LOGBOOK INDICATES THAT RUDDER WAS NEVER REPLACED OR REPAIRED, SO THE AS	SUMPTION IS THAT THE PART WAS LEFT OUT DURING AIRCRAFT CONSTRUCTION. NEW RIB WAS INSTALLED.			1	H	7	1 	3O			NT	3A12    					 
2006041300259	20060413	00259		2006	4	13	2006FA0000325    	1	20060314	G	2510	71513	SEAT FRAME      																		BROKEN          	B				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	15	116SG	544  	50   							THE LOWER SEAT FRAME CONSISTS OF A PERIMETER RECTANGULAR TUBE FRAME THAT HAS THE ENDS OF STEEL STRAPS WELDED TO IT TO FO	RM A LOOSE WEBBING ASSEMBLY WHICH SUPPORTS THE SEAT CUSHION. DURING A PREFLIGHT THE PILOT NOTICED THE SEAT SAGGING AND F	OUND THE ENDS OF TWO STRAPS HAD BROKEN WELDS.																	 
2006041300271	20060413	00271		2006	4	13	2006FA0000326    	4	20060407	G	3421		ART HORIZION    			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										COCKPIT	MISWIRED        	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	01	875LP					258308				PILOT REPORTED STANDBY ARTIFICIAL HORIZON ILS NEEDLES MOVE IN OPPISITE DIRECTION OF #1 AND #2 ILS NEEDLES ON ILS APPROAC	H.  CONFIRMED REPORT.  FOUND THAT ARKANSAS AEROSPACE COMPLETION DRAWINGS( WERE NOT CORRECT WHEN COMPARED TO HONEYWELL RN	Z-850 INSTALLATION MANUAL.  RNZ-850 PIN B78 VOR LFT DEVIATION WAS WIRED TO STANDBY HORIZON (JET ADI-322B) PIN G NAV DEVI	ATION +RT.  RNZ-850 PIN B75 DEV RTN WAS WIRED TO ADI-322B PIN H NAV DEVIATION + LT.  SWAPPED WIRES AT ADI-322B AND TESTE	D.  ILS DEVIATION LEFT AND RIGHT NOW MATCHES PRIMARY ILS DISPLAYS.		2	L	7	2 	4F			RT	A3EU    					 
2006041200040	20060412	00040	SO  	2006	4	12	2006FA0000327    	2	20060313	G	7414		IMPULSE COUPLING			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					MAGNETO	RUSTED          	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	2278S	448  				TC2110				DURING A ROUTINE INSP, ALL MAGNETOS WERE REMOVED FOR POINTS AND CONDENSER REPLACEMENT.  RUST WAS FOUND ON THE FLYWEIGHT/	AXLE AREA OF THE IMPULSE COUPLING.  A WEAR CHECK WAS MADE AND IT WAS DETERMINED THAT ALL COUPLINGS FAILED IAW MSB.  NOTE	:  THE FLYWEIGHT/ AXLE PIN WEAR IS IN EXCESS OF .014 AND MAY BE DUE TO RUST.  THIS AREA OF INSPECTION MAY BE OVERLOOKED 	DUE TO THE OMISSION OF MANY IMPULSE COUPLINGS INSTALLED ON ENGINE NOT INCLUDED IN AD.  (K)			1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2006041200078	20060412	00078	EA  	2006	4	12	2006FA0000328    	2	20060309	G	7414	M3548	SHAFT           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	MAGNETO	SHEARED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5321U				98070601	2844042	L2958751A	002421		ENGINE RUNUP INDICATED A DEAD MAGNETO.  REMOVED AND DISASSEMBLED MAGNETO HOUSING.  FOUND ROTOR SHAFT SHEARED OFF AT BOTT	OM OF CAM SLOT.  A FEW CRACKED SHAFTS HAVE BEEN FOUND AT 500 HR INSPECTIONS.  RECOMMEND CLOSE INSPECTION OF THIS AREA AT	 REPAIR AND OVERHAUL.  (K)				1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA	 
2006041300168	20060413	00168	GL  	2006	4	13	2006FA0000330    	2	20060410	G	7230	59084	STATOR          								WILINT	FJ44  	FJ44        	66000	GL  					COMPRESSOR	DETERIORATED    	B			WI5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23							126173			3RD STAGE IP STATOR ABRADABLE WAS EXFOLIATING CAUSING THE 3RD STAGE IP BLADES TO CONTACT THE STATOR ABRADABLE.  THIS RES	ULT IN N1 LOCK-UP.  BASED UPON HARDWARE EVALUATION, ROOT CAUSE OF THE ABRADABLE EXFOLIATING WAS DUE TO THE WATER WASH PR	OCEDURES (COASTAL A/C) NOT BEING FOLLOWED PG THE ENGINE MM.  (K)									4	F			E3GL				 
2006041200038	20060412	00038	SO  	2006	4	12	2006FA0000331    	1	20060306	G	2140	A23D0475	REGULATOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					CABIN HEATER	LEAKING         	B			GFVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6549A					277954006				AIRCRAFT RECEIVED FROM NEW OWNER WANTING HEATER MADE OPERATIONAL: TOTALLY DEACTIVATED.  REPLACED HEATER ASSY DUE TO EXTR	EME DETORATION.  FUEL REGULATOR REPLACED DUE TO LEAKAGE AND FAILURE TO REGULATE FOUND INLET PORT PARTIALLY PLUGGED BY CO	RROSION BY-PRODUCTS AND REMNANTS OF DAMAGED THREADS.  N/E REPAIRABLE.  (K)				1	L	7	2 	3O	3	O		1A10    	E14EA				 
2006041300272	20060413	00272	CE  	2006	4	13	2006FA0000332    	1	20060327	G	5412	569500511	BULKHEAD        			CESSNA	340   	340A        	2076405	CE  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	340JY	3462 				340A0979				DURING 500 HR. VISUAL INSPECTION PER AD2000-01-16 PARA (D) FOUND LEFT ENGINE AFT CANTED BULKHEAD #5695005-11 AND SUPPORT	 DOUBLER #5695005-6 CORRODED AND HEAT DAMAGED COMPLETELY THROUGH STRUCTURE.  DAMAGE LOCATED NEAR OUTBOARD SECTION ABOVE 	EXHAUST ELBOW CUT OUT AREA. 				1	L	7	2 	3O				3A25    					 
2006051000249	20060510	00249	CE  	2006	5	10	2006FA0000333    	1	20060327	G	5412	569500511	BULKHEAD        			CESSNA	340   	340A        	2076405	CE  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	340JY	3462 				340A0979				DURING 500 HR. VISUAL INSPECTION PER AD2000-01-16 PARA (D) FOUND LEFT ENGINE AFT CANTED BULKHEAD NR 5695005-11 AND SUPPO	RT DOUBLER NR 5695005-6 CORRODED AND HEAT DAMAGED COMPLETELY THROUGH STRUCTURE.  DAMAGE LOCATED NEAR OB SECTION ABOVE EX	HAUST ELBOW CUT OUT AREA. 				1	L	7	2 	3O				3A25    					 
2006051100250	20060511	00250	EA  	2006	5	11	2006FA0000335    	2	20060322	G	7210	3013132	SLEEVE          	PWA         	PT6A27      						PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	SHIFTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03			805  		42083100		PCE42083			OPERATOR ATTEMPTED TO ROTATE THE PROPELLER DURING A PREFLIGHT CHECK AND NOTED PROP SHAFT LOOSENESS AND DRAG. THE ENGINE 	WAS REMOVED FOR REPAIR. EXAMINATION OF THE 2ND STAGE CARRIER IN THE RGB REVEALED THAT THE SLEEVE USED TO REPAIR THE NR 5	 BEARING JOURNAL HAD SHIFTED OFF OF THE JOURNAL. THERE WAS NO COLLATERAL DAMAGE DUE TO SLEEVE SHIFT.									4	T			E4EA				 
2006041400094	20060414	00094	SO  	2006	4	14	2006FA0000337    	1	20060406	G	2434	ALU8539LS	ALTERNATOR      			PIPER 	PA46  	PA46350P    	7104602	SO  										ENGINE	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	110ST	142  				4636373				OUTPUT POST WAS LOOSE AND BURNED.  TERMINAL ON OUTPUT WIRE GOING TO BOSS BAR WAS BURNED, MELTED, AND SEPARATED FROM ALTE	RNATOR.  (K)					1	L	7	1 	3O			RT	A25SO   					 
2006041700045	20060417	00045	SO  	2006	4	17	2006FA0000338    	1	20060317	G	5711	PA28140	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	6399W					2820467				DURING 100 HR INSPECTION ON REAR SPAR CHANNEL, RIVET HEADS WERE POPPED ON BOTH SIDES.  A COMPLETE INSPECTION REVEALED SE	VERE CORROSION BETWEEN CHANNEL AND STEEL PLATES.  ALSO, SEVERE CORROSION EXISTED BETWEEN REAR IB ATTACH FITTINGS TO SPAR	.  THE ATTACH FITTINGS HID VIEW FROM THE OUTSIDE.  WITH NO INSPECTION PANELS IN THAT AREA THE INSPECTION HAS TO BE MADE 	THROUGH THE IB RIB LOOKING AFT.  THE STRUCTURAL INTEGRITY OF THE LT SPAR ATTACH AREA WAS SEVERELY COMPROMISED.  (K)			1	L	7	1 	3O	3	O		2A13    	E274				 
2006041400092	20060414	00092	SO  	2006	4	14	2006FA0000339    	1	20060317	G	5711	62054000	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  										LT WING	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	6399W	3744 				2820467				DURING 100 HR INSPECTION ON REAR SPAR CHANNEL, RIVET HEADS WERE POPPED ON BOTH SIDES.  A COMPLETE INSPECTION REVEALED SE	VERE CORROSION BETWEEN CHANNEL AND STEEL PLATES.  ALSO, SEVERE CORROSION EXISTED BETWEEN REAR IB ATTACH FITTINGS TO SPAR	.  THE ATTACH FITTINGS HID VIEW FROM THE OUTSIDE.  WITH NO INSPECTION PANELS IN THAT AREA THE INSPECTION HAS TO BE MADE 	THROUGH THE IB RIB LOOKING AFT.  THE STRUCTURAL INTEGRITY OF THE LT SPAR ATTACH AREA WAS SEVERELY COMPROMISED.  (K)			1	L	7	1 	3O				2A13    					 
2006041900207	20060419	00207	CE  	2006	4	19	2006FA0000340    	1	20060210	G	3397	L143J20	WIRE            			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  	MCAULY	3A32C	D3A32C*     	GL  	RT WING NAV LITE	CHAFED          	B				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	23	806NH					E2702	686012	912713		PILOT REPORTED NAVIGATION LIGHT BREAKER SWITCH (POPPED) IN FLIGHT AND WAS NOT ABLE TO RESET.  MAINTENANCE PERSONAL TROUB	LESHOT NAVIGATION LIGHT SYSTEM AND FOUND A SHORT IN THE WIRING IN THE RT WING AT APPROXIMATE WING STATION 162.5.  A NEW 	WIRE WAS PULLED THROUGH TO REPLACE THE OLD WIRE.  TIME IN SERVICE IS A FACTOR IN THIS OCCURRENCE.  ALSO IN SERVICE IS A 	FACTOR IN THIS OCCURRENCE.  ALSO THE WIRE LAYS IN A STRINGER CHANNEL AND HAS NO OTHER MEANS OF SUPPORT OTHER THAN GLUED 	IN STRIPS AT VARIOUS INTERVALS TO KEEP THE WIRE IN THE CHANNEL.  THERE IS NO ACCESS TO THIS WIRE FROM WING STA 122.75 TO	 191.00.  THERE SHOULD BE A PLASTIC CONDUIT TUBING FOR THIS WIRE TO RUN THROUGH.  (K)	1	L	7	1 	3O	3	O		3A15    	E3SO	5	C	P21EA	 
2006041900219	20060419	00219	NM  	2006	4	19	2006FA0000342    	1	20060315	G	3520	417N31002933E	CABLE           			BOEING	737   	7373G7      	1384595	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					PX OXY SYS	MISROUTED       	B			LH6Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	370WL					24011				(REF: ATC0662) THE ACTUATING CABLE TO THE CHEMICAL OXYGEN GENERATORS ON PASSENGER SERVICE UNITS WERE FOUND INCORRECTLY R	OUTED.  IE: IT WAS UNDER THE PIN AND RESTING ON THE PLASTIC MOULDING.  DEFECT RAISED AS AN (IORS) INTERNAL OCCURRENCIES 	REPORT AND UPGRADED TO MALFUNCTION AND DEFECT REPORT DUE TO SYSTEM BEING (EMERGENCY).  (K)				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006041900206	20060419	00206	SO  	2006	4	19	2006FA0000343    	2	20060401	G	7414	M3081	POINTS          			AMTR  	LANCAR	LC41550FG   	5150001	GL  	CONT  	O550  	TSIO550C    		SO  					RT MAGNETO	BROKEN          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			NM	09	79HR					41017	802655			ON ENGINE GROUND RUN PRIOR TO FLIGHT MAGNETO CHECK FOUND RT MAGNETO HAD FAILED INSPECTION FOUND POINTS BROKEN PICTURE IN	CLOSED.  (K)					1	L	7	1 	3O	3	O	RT	EXPA1L71	E5SO				 
2006041900321	20060419	00321	SO  	2006	4	19	2006FA0000344    	1	20060317	G	2731	8646002	CABLE           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					FUSELAGE	JAMMED          	B			RJUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	259AT	3151 				4496080				PILOT REPORTED THAT STABILATOR TRIM WAS JAMMING IN THE NOSE-UP POSITION.  IT WAS DISCOVERED THAT TRIM CABLE TURNBUCKLE W	AS CATCHING ON BULKHEAD JAMMING CABLE.  CABLE TENSIONS WERE ADJUSTED TO SPECIFICATIONS AND PROBLEM REPEATED.  RECOMMEND 	SLIGHT RADIUS OF MATERIAL AND REINFORCEMENT OF AFFECTED AREA TO PREVENT RECURRENCE OF PROBLEM.  (K)				1	L	7	2 	3O	3	O		A19S0   	E286				 
2006041900312	20060419	00312	CE  	2006	4	19	2006FA0000345    	1	20060215	G	3230	NAS4645A15	BOLT            			CESSNA	177   	177RG       	2073709	CE  										NLG	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	52643					177RG1225				NOSE LANDING GEAR FAILED TO LOCKDOWN.  THE NAS404-5A15 BOLT THAT BOTH SECURES AND PROVIDES A PIVOT POINT FOR THE LOCK AS	SY TO THE DRAG LINK HAD BACKED OUT OF THE DRAG LINK TOTALLY DISCONNECTING THE LOCK ASSY FROM THE DRAG LINK.  THERE WAS E	VIDENCE OF RED LOCKTITE IN THE DRAG LINK AS IS REQUIRED BY THE SRM BUT IT BACKED OUT ANY WAY.  THIS BOLT IS NOT A DRILLE	D HEAD BOLT, BUT I RECOMMEND THAT IT BE REPLACED WITH ONE TO AVOID REOCCURRENCE.  (K)			1	H	7	1 	3O				A20CE   					 
2006041900327	20060419	00327	CE  	2006	4	19	2006FA0000346    	1	20060320	G	3710	1U478003	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5521A	304  				CE1338	830070R			PILOT REPORTED THAT AT 1700 RPM INSTRUMENT AIR PRESSURE (3.5 HG) UPON TROUBLESHOOTING OF THE INSTRUMENT AIR PRESSURE SYS	TEM TECHNICIAN FOUND AIR PUMP WAS NOT PRODUCING ENOUGH PRESSURE.  PROBABLE CAUSE IS UNKNOWN AT THIS TIME.  NO RECOMMENDA	TION AT THIS TIME EITHER.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006041900320	20060419	00320	EA  	2006	4	19	2006FA0000347    	2	20060324	G	7322	105267	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CONTAMINATED    	H			CE8S	K				NONE                    				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			SO	15	25566					15280734	RL2324815			CONTAMINANT FOUND INSIDE OF THE MAIN JET OF THE CARBURETOR.  ENGINE QUIT ON TAKE OFF ROLL.  (K)						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006050200004	20060502	00004		2006	5	2	2006FA0000348    	1	20060227	G	8011	MHB4016R	STARTER         																	ENGINE	NOISY           	B			WS9R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	07										STARTER WHINING, AND WILL NOT START ENGINE.  WILL START WITH HAND PROP, BUT WHINES.  (K)																			 
2006041900324	20060419	00324	NM  	2006	4	19	2006FA0000349    	1	20060328	G	5711		SPAR CAP        			UNIVAR	415   	415C        	0420302	NM  	CONT  	C90   	C90*        	17009	SO  					RT WING	CRACKED         	B			N5DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	3158H					3783				DURING ACCOMPLISHMENT OF SB NR 32, A 0.625 INCH LONG, SPANWISE CRACK WAS NOTED ON THE RT UPPER SPAR CAP IN THE MAIN SPAR	 CENTER SECTION APPROX 0.250 INCH IB OF THE CENTER SECTION OB END.  PROBABLE CAUSE IS UNKNOWN.  (K)					1	L	7	1 	3O	3	O		A718    	E252				 
2006041900322	20060419	00322	NM  	2006	4	19	2006FA0000350    	1	20060321	G	2740	07322P11070	BALL END        			BOEING	737   	737*        	       	NM  										HORIZ STABILIZER	FOD             	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					0728					THE MAJOR COMPONENTS ARE BEYOND ECONOMICAL REPAIR (SCRAP).  THE DAMAGE WAS CAUSED BY A FOREIGH OBJECT, PROBABLY LOOSE BA	LL.  THIS CAN HAPPEN ANYTIME THE BALLNUT ASSY IS REMOVED FROM THE SCREWSHAFT.  (K)					2	L	7	2 	4F			RT	A16WE   					 
2006050200006	20060502	00006		2006	5	2	2006FA0000351    	1	20060320	G	8011	ES6462751	STARTER         																	ENGINE	TIGHT           	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										STARTER IS TOO TIGHT AND WOULD NOT TURN.  (K)																			 
2006041900328	20060419	00328	CE  	2006	4	19	2006FA0000352    	1	20060322	G	5312	071220510	BULKHEAD        			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					AFT FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2233G					51533	668916L			BULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE.  BULKHEAD, PN 0712206 CRACKED AT BOLT HOLES ATTACHMENT TO ELEVATOR BEL	LCRANK SUPPORT MOUNT.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2006041900323	20060419	00323	CE  	2006	4	19	2006FA0000353    	1	20060322	G	5312	071220510	BULKHEAD        			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					FUSELAGE TAIL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2233G					51533	668916L			BULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE.  BULKHEAD, PN 0712206, CRACKED AT BOLTHOLES ATTACHMENT TO ELEVATOR BEL	LCRANK SUPPORT MOUNT.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2006050200005	20060502	00005		2006	5	2	2006FA0000354    	1	20060228	G	8100	4066109005	TURBOCHARGER    																	ENGINE	WEAK            	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07		2    								TURBO CHARGER WOULD NOT MAKE ENOUGH BOOST.  (K)																			 
2006041900325	20060419	00325	NE  	2006	4	19	2006FA0000355    	2	20060318	G	7320	0292858570	HMU             			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ENGINE	UNKNOWN         	C				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			WP	13	11QF					3482				PRECAUTIONARY LANDING DUE TO BANG HEARD IN FLIGHT BY PILOT.  NORMAL LANDING ACCOMPLISHED W/O ACCIDENT, OR INJURIES.  AC 	LANDED ON PRIVATE PROPERTY.  UPON LANDING, GOVERNOR WARNING LIGHT ILLUMINATED.  SUBSEQUENT INVESTIGATIVE TROUBLESHOOTING	 REVEALED VEMD TO DISPLAY A CODE (192) HMU FAULT, INDICATING A FAILURE OF EBCAU STEPPER MOTOR.  VISUALLY INSPECTED ENG A	SSY AND SURGE BLEED VALVE ASSY.  NO DEFECTS NOTED, HMU AND EBCAU UNITS WERE REPLACED WITH SERVICABLE UNITS.  GROUND AND 	FLIGHT TESTS PROVED GOOD WITH NO INDICATED ERROR CODES.  AC TEST FLOWN BACK TO MAINTENANCE BASE WITH NO FURTHER PROBLEMS	 NOTED.  DETERMINED THE INITIAL BANG HEAR IN FLIGHT WAS MOST LIKELY A COMPRESSOR STALL DUE TO THE MALFUNCTION HMU.  (K)	1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2006041900326	20060419	00326	CE  	2006	4	19	2006FA0000356    	1	20060313	G	7100	10191000495	DUCT            			BEECH 	200   	B200        	1152922	CE  										LT ENGINE	CRACKED         	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	326PG					BB1709				LT ENGINE LOWER AFT COWLING, LWR DUCT FOUND CRACKED ABOUT 80 PERCENT ITS ENTIRE WIDTH ALONG FIRST RIVET ROW.  REMOVED CR	ACKED DUCT AND FOUND NOT TO BE ROLLED ENOUGH.  THIS PUT STRESS ON RIVET ROW.  NEW SPARE PART ORDER FROM MFG WAS ROLLED C	ORRECTLY AND FIT WITHOUT STRESS.  (K)				1	L	7	2 	4T				A24CE   					 
2006041800218	20060418	00218	EA  	2006	4	18	2006FA0000357    	2	20060313	G	7320	2576543	SERVO           			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					ENGINE FUEL SYS	INOPERATIVE     	B			EHHR	K				NONE                    				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			EA	17	236KS					20608236				AIRCRAFT LANDED AND ENGINE QUIT.  TO RESTART ENGINE MIXTURE HAD TO PULL MIXTURE BACK TO .5 INCH OF IDLE CUT TO KEEP ENGI	NE RUNNING.  TRIED TO ADJUST IDLE MIXTURE WITHOUT SUCCESS.  AT THE ADJUSTMENT LEANEST SETTING THERE WAS STILL A 600 RPM 	RAISE WHEN MIXTURE PULLED TO IDLE CUT OFF.  REMOVED SERVO AND SENT.  REINSTALLED ON RETURN WITH SMALL ADJUSTMENTS ENGINE	 RAN SATISFACTORY.  THIS SAME SYMPTOMS SHOW ON ANOTHER AC WITH SAME PN SERVO.  THE AIRCRAFT HAD 129 HOURS, THIS SERVO EX	CHANGED FOR AN OVERHAULED UNIT.  TECH SUPPORT STATED THAT THE DIAPHRAGMS HAVE SHIFTED AND THE METERING SEATS NEEDED POLI	SHING.  (K)	1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2006041900203	20060419	00203	NM  	2006	4	19	2006FA0000358    	1	20060321	G	2740	07322P11070	BALL SCREW      			BOEING	737   	737*        	       	NM  										STABILIZER	FOD             	B			N9GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					0728					FOREIGH OBJECT DAMAGE DISCOVERED DURING INSPECTION OF BALLSCREW ASSY BY SUBCONTRACTOR.   THE MAJOR COMPONENTS ARE BEYOND	 ECONOMIC REPAIR (SCRAP).  THE DAMAGE WAS CAUSED BY A FOREIGN OBJECT, PROBABLY LOOSE BALL.  THIS CAN HAPPEN ANYTIME THE 	BALLNUT ASSY IS REMOVED FROM THE SCREWSHAFT.  (K)				2	L	7	2 	4F			RT	A16WE   					 
2006050200003	20060502	00003		2006	5	2	2006FA0000359    	1	20060322	G	8011	ES6462751	STARTER         																	ENGINE	TIGHT           	B			WS9R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										STARTER TOO TIGHT.  (K)																			 
2006041900168	20060419	00168		2006	4	19	2006FA0000360    	4	20060314	G	6113	D78115P	SPINNER         			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01						TH2135				SPINNER HAS CRACKS IN 3 PLACES NEAR SCREW HOLES ADJACENT TO PROPELLER BLADES.  (K)						1	L	7	2 	3O				3A16    		5	C	P22EA	 
2006041800219	20060418	00219	CE  	2006	4	18	2006FA0000361    	1	20060310	G	2910	605700311	FLEX LINE       			LEAR  	60    	60LEAR      	5170707	CE  										HYD SYS	RUPTURED        	D				A				UNSCHED LANDING         				K	F		FLUID LOSS                	FLT CONT AFFECTED         		CR	CRUISE         	1			SW	11	898PA					111				DURING FLIGHT, LOST NR 1 HYDRAULIC PRESSURE, DIVERTED INTO AIRPORT AND LANDED WITHOUT INCIDENT.  TROUBLESHOOT AND FOUND 	RUPTURED HYDRAULIC FLEX LINE, PN 605700311 WHICH IS MOUNTED ON THE PRESSURE SIDE OF THE HYDRAULIC EDP.  INSTALLED NEW HY	DRAULIC FLEX LINE WITH PN 605700311.  (K)				2	L	7	2 	4F			RT	A10CE   					 
2006041900194	20060419	00194	EU  	2006	4	19	2006FA0000362    	1	20060314	G	6220	C622A1002104	PLATE           			UROCOP	EC120 	EC120B      	8680987	EU  										MAIN ROTOR HEAD	UNBONDED        	B			KW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	453F	3429 			M309	1205				LOWER DROOP RING WEAR PLATE BECAME UNBONDED AND CAME OFF THE MAIN ROTOR HUB.  THE ENTIRE PLATE WAS FOUND APPROXIMATELY 2	0 FT FROM THE AIRCRAFT.  IT IS NOT CLEAR WHETHER THE PART FELL OFF DURING ENGINE START UP OR SHUTDOWN.  WE BELIEVE THE U	NBONDING TO BE THE RESULT OF THE DROOP RING STOPS COMING INTO CONTACT WITH THE WEARPLATE, DURING PERIODS OF TIME WHEN TH	E AIRCRAFT IS STATIC ON THE RAMP AND SUBJECT TO HIGH WINDS.  RECOMMEND SECURING THE MAIN ROTOR BLADES WHEN THE PREVAILIN	G WINDS REACH 15 KNOTS.  (K)		1	G	7	2 	3U			NC	R0001RD 					 
2006041800221	20060418	00221	SO  	2006	4	18	2006FA0000363    	1	20060301	G	2700	62701100	CABLE           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	962WW	4810 				2844022				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR, BO	TH FORWARD RUDDER CABLES WERE FOUND TO BE BADLY WORN AND FRAYED.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PR	EVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB 	WAS APPLICABLE TO THIS AIRCRAFT.  (K)			1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900204	20060419	00204	SO  	2006	4	19	2006FA0000364    	1	20060301	G	2720	62701124	CABLE           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	962WW	4810 				2844022				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 RT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY A FEW STRANDS LT INTACT.  RESEARCH OF THE MAIN	TENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF AL	L FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)			1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900205	20060419	00205	SO  	2006	4	19	2006FA0000365    	1	20060301	G	2740	62701103	CABLE           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	962WW	4810 				2844022				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 LT STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY A FEW STRANDS LT INTACT.  RESEARCH OF THE MAINTENAN	CE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLI	GHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)			1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900264	20060419	00264	SO  	2006	4	19	2006FA0000366    	1	20060301	G	2740	62701102	CABLE           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	962WW	4810 				2844022				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 RT FWD STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PRE	VIOUS OWNERS HAD FAILED TO COMPLY WITH SB  WHICH  REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB	 WAS APPLICABLE TO THIS AIRCRAFT.  (K)			1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900235	20060419	00235	SO  	2006	4	19	2006FA0000367    	1	20060301	G	2740	62701100	CABLE           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	963PA	5350 				2844023				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 LT FORWARD STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  THE AREA OF FRAYING WAS LOCATED UNDER THE REAR SEAT	S IN THE INSPECTION AREA AT THE REAR PULLEYS.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  R	ESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIV	E INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)		1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900288	20060419	00288	SO  	2006	4	19	2006FA0000368    	1	20060301	G	2720	62701100	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	963PA	5350 				2844023				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 RT FWD RUDDER CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  THE LOCATION OF THE FRAYING WAS JUST UNDER THE CENTER CONSO	LE FOR THE STABALATOR TRIM AND JUST AS IT EXITED IN TO THE INSPECTION AREA UNDER THE REAR SEATS AT THE FORWARD PULLEY.  	THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT 	THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  TH	IS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)	1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900279	20060419	00279	SO  	2006	4	19	2006FA0000369    	1	20060301	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					WING	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	963PA	5350 				2844023				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 LT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  THE LOCATION OF THE FRAYING WAS AT THE 1ST IB PULLEY I	N THE WING ROOT.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RE	CORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT C	ONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)		1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900291	20060419	00291	SO  	2006	4	19	2006FA0000370    	1	20060301	G	2710	62701124	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					WING	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	963PA	5350 				2844023				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE	 RT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY 1 STRAND LEFT HOLDING IT TOGETHER.  THE LOCATI	ON OF THE FRAYING WAS AT THE 1ST IB PULLEY IN THE WING ROOT.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MOD	EL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB 1048 WHIC	H REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)		1	L	7	1 	3O	3	O		2A13    	1E10				 
2006041900299	20060419	00299	SO  	2006	4	19	2006FA0000371    	1	20060301	G	2710	62701099	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  										LT WING	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	962WW	4810 				2844022				WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ON LINE AFTER PURCHASING IT FROM A LOCAL OPERATOR TH	E LT FORWARD AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED TH	AT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB 1048 WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CAB	LES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)			1	L	7	1 	3O				2A13    					 
2006041900257	20060419	00257	SO  	2006	4	19	2006FA0000372    	1	20060309	G	3213	3948903	AXLE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O300  	O300*       	17022	SO  					MLG	CRACKED         	D			NTBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	9219X					3448038				CRACKS IN BOTH UPPER BOLT HOLES THAT SECURE AXLE TO STRUT ASSEMBLY ON BOTH LT AND RT MLG.  PROBABLE CAUSE MAYBE HARD LAN	DING OR FATIGUE CRACKS DO TO NORMAL USE.  (K)					1	L	7	2 	3O	3	O		A7SO    	E253				 
2006042000120	20060420	00120	CE  	2006	4	20	2006FA0000373    	1	20060322	G	5510	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	49053	*    				15281124				3 CRACKS WHERE FOUND ON THE TOP RT OB BOLT HOLE AND ONE CRACK IN WELD JUST AFT OF SAME BOLT HOLE, (NUT PLATES HAD BEEN P	REVIOUSLY REMOVED).  UNKNOWN CAUSE, AD SHOULD BE REVISED TO REFER FURTHER INSPECTION OF COMPLETE BRACKET ASSY.  (K)					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006042000117	20060420	00117	SO  	2006	4	20	2006FA0000374    	1	20060403	G	2730	1159CS52093409	STOP            			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					LT ELEVATOR	BROKEN          	B			CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	780F	3750 				530				DURING SCHEDULED TAIL INSPECTION LT ELEVATOR UP AND DOWN STOP WAS FOUND BROKEN OFF AND LAYING IN ELEVATOR ATTACH/HINGE A	REA.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2006042000171	20060420	00171	CE  	2006	4	20	2006FA0000375    	1	20060403	G	3397		CONNECTOR       			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					WIRE HARNESS	WRONG PART      	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	493CW					RK93				DURING SCHEDULED INSPECTION FOUND SEVERAL INCORRECT TYPE SPLICE CONNECTORS AND REPAIRS IN CABIN COLD CATHODE LIGHTING WI	RING.  HAVE FOUND THIS TO BE THE APPARENT CAUSE OF MINOR FIRES AND OVERHEATING ABOVE THE HEADLINER IN SEVERAL AIRCRAFT P	REVIOUSLY..  SEVERAL COMMUNIQUS HAVE NOTED THIS SUBJECT PREVIOUSLY.  SUGGEST A MANDATORY SB OR SAFETY COMMUNIQU BE ISS	UED FOR A ONE TIME INSPECTION OF COLD CATHODE WIRING FOR NON-APPROVED CONNECTORS AND WIRING REPAIRS.  WARNINGS AND SPECI	FIC REPAIR INSTRUCTIONS SHOULD BE ADDED TO THE MM.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006042000172	20060420	00172	CE  	2006	4	20	2006FA0000376    	1	20060330	G	5610	10138402518	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	03	37TD	1236 				FL25				FLIGHT CREW REPORTED CO-PILOTS WINDSHIELD RAPIDLY FAILED IN CRUISE FLIGHT, INNER LAYER (SPIDER WEBBED) OVER ENTIRE INTER	IOR SURFACE.  DELAMINATIONS NOTED SPREADING FROM BOTH IB CORNERS UPON REMOVAL.  TECH INSTALLING REPLACEMENT WINDSHIELD N	OTED PREVIOUS INSTALLATION MAY HAVE HAD SEALS INSTALLED INCORRECTLY, CAUSING INCREASED STRESS ON WINDSHIELD ASSY.  RECOM	MEND TECH INSTALLING REPLACEMENT WINDSHIELDS REVIEW CURRENT STRESS FREE INSTALL KIT INSTRUCTIONS AND MM INSTALL PROCEDUR	ES CAREFULLY PRIOR TO INSTALLATION.  (K)		2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2006042000174	20060420	00174	GL  	2006	4	20	2006FA0000377    	1	20060327	G	5552		ATTACH FITTING  			AMTR  	ZENITH	ZENITHCH701 	05611WI	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ELEVATOR HINGE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	701BX					71514				DURING CONDITION INSPECTION IT WAS DISCOVERED THAT THE RT ELEVATOR HINGE ATTACH SUPPORT HAD A CRACK IN THE T/E RADIUS TH	AT WAS STOP DRILLED.  A DOUBLER REPAIR WAS INSTALLED.  THE ELEVATOR HORN ATTACH ALSO HAD A LOOSE RIVET.  THIS WAS REPAIR	ED BY INSTALLING AN HARDWARE.  CLOSE ATTENTION SHOULD BE PAID TO THESE AREA EVEN ON PREFLIGHT AS THIS IS THE THIRD KNOWN	 INCIDENCE OF THIS KIND IN THE AREA.  (K)			1	H	7	1 	3I	3	I	NT	EXPA1H71	EXPE3I				 
2006050200008	20060502	00008		2006	5	2	2006FA0000378    	1	20060329	G	8011	MHB4016	STARTER         																		MALFUNCTIONED   	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										BENDIX DRIVE WOULD NOT DISENGAGE.  (K)																			 
2006042000160	20060420	00160	CE  	2006	4	20	2006FA0000379    	1	20060403	G	2400	10300B	ALTERNATOR      			CESSNA	207   	207         	2073602	CE  											OVERTORQUED     	B			UT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										PART RECEIVED O/H FROM STOCK.  NO CURRENT OUTPUT WHEN INSTALLED ON AIRCRAFT.  BENCH CHECKING RESULTED IN MALFUNCTION OF 	BRUSH BLOCK HARDWARE DUE TO POSSIBLE OVER TORQUING OF HARDWARE DURING ASSY.  COMPONENT WAS OVERHAULED BY CRS NR UT2R226L	 UNDER W/O NR M940120 DATED AUG 17, 2005, FORM TRACKING NR F082283.  (K)				1	H	7	1 	3O				A16CE   					 
2006042000180	20060420	00180	WP  	2006	4	20	2006FA0000380    	2	20060330	G	7510	3751160	FITTING         			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					TAIL	MISINSTALLED    	B			BIOR	O				OTHER                   				F	I		FLT CONT AFFECTED         	FLT. ATTITUDE INST.       		AP	APPROACH       	1			EA	23	288JP					288				AIRCRAFT EXPERIENCED HORIZONTAL STABILIZER STALL DURING APPROACH, DURING SEVERE ICING.  AIRCRAFT RECOVERED FROM STALL AN	D LANDING NORMAL.  INSPECTION OF TAIL DE-ICE SYSTEM FOUND BLEED AIR LEAKING IN AFT PART OF TAIL AT 90 DEGREE ELBOW.  DUR	ING REMOVAL OF 90 DEGREE ELBOW IT WAS FOUND THAT THE WIGGINS SEALS WERE INSTALLED INCORRECTLY, UNABLE TO DETERMINE WHEN 	THIS FITTING WAS INSTALLED.  COULD HAVE COME FROM MFG DURING PRODUCTION.  HAS NOT BEEN CHANGED BY OWNER IN 11 YEARS.  TA	IL AND WING HEAT FUNCTIONAL CHECKED NORMAL AT LAST INSPECTION.  NO INFO IN MM FOR INSTALLING THIS TYPE.  (K)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006042000226	20060420	00226	CE  	2006	4	20	2006FA0000381    	1	20060324	G	3213	054119810	STRUT           			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360*       	41514	EA  					MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	739YA					17270902	RL514576T			LANDING GEAR BROKE JUST OUTSIDE OF THE GEAR BOLT.  THE FACE OF THE CRACKED AREA APPEARS TO HAVE RUST ON IT THAT COULD IN	DICATE A PREVIOUS CRACK.  (NE01200603823) (K)					1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2006051200126	20060512	00126	SO  	2006	5	12	2006FA0000382    	1	20060323	G	3320	AL1235T422C27	LAMP            			GULSTM	GV    	GV          	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					GALLEY	INOPERATIVE     	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1KE	400  				574				DURING ROUTINE LAMP REPLACEMENT, IT WAS DISCOVERED THAT ONE END OF THE REMOVED UNIT WAS DISCOLORED.  THE DISCOLORATION W	AS THOUGHT TO BE DUE TO OVERHEATING.  THE LOCATION OF THE FAILED LAMP WAS IN THE GALLEY OVERHEAD.  INSTALLED NEW UNIT OF	 SAME MFG AND PN.  OPERATIONAL CHECK, OK.  REPORTING THIS DUE TO CONCERN THAT THE OPERATION OF THIS LIGHT COULD RESULT I	N A POSSIBLE FIRE CAUSED BY OVERHEATING OF THESE UNITS.  (K)			2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2006042400184	20060424	00184	SO  	2006	4	24	2006FA0000383    	1	20060306	G	2140	A23D04	REGULATOR       	JANITROL    		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					CABIN HEATER	LEAKING         	B			GFVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6549A				8213015F	277954006				AIRCRAFT RECEIVED FROM NEW OWNER WANTING HEATER MADE OPERATIONAL:  TOTALLY DEACTIVATED.  REPLACED HEATER ASSY DUE TO EXT	REME DETERORATION.  FUEL REGULATOR REPLACED DUE TO LEAKAGE AND FAILURE TO REGULATE.  FOUND INLET PORT PARTIALLY PLUGGED 	BY CORROSSION BY-PRODUCTS AND REMNANTS OF DAMAGED THREADS.  N/E REPAIRABLE.  (K)				1	L	7	2 	3O	3	O		1A10    	E14EA				 
2006042400135	20060424	00135	CE  	2006	4	24	2006FA0000384    	1	20060327	G	3230	101810151	BOLT            			BEECH 	300   	300BEECH    	1152930	CE  										RT GEAR DRAG LEG	MISDRILLED      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	810N					FL419				THIS IS AN ALEMITE TYPE BOLT.  IT WAS FOUND THAT GREASE WAS NOT GETTING TO THE BUSHINGS ON THE FAR END OF THE BOLT.  UPO	N EXAMINATION, IT WAS FOUND THAT THE CENTER GREASE PORT IN THE BOLT WAS NOT DRILLED FAR ENOUGH TO ALLOW GREASE TO GET TO	 THE FINAL SIDE-DRILLED PORT.  THUS THE BUSHING FOR THAT PORT WAS NOT GETTING LUBRICATION.  DRAG LINKS WITH THIS PN BOLT	 SHOULD BE CHECKED FOR PROPER LUBRICATION.  (K)			2	L	7	2 	4T				A24CE   					 
2006042400174	20060424	00174	SO  	2006	4	24	2006FA0000385    	2	20060331	G	8530		CYLINDER HEAD   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520BB   	17040	SO  					RT ENG	SEPARATED       	D				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	414AM					414A0850	287566R			DURING FLIGHT, VIBRATION WAS NOTED ON RT ENGINE.  INSPECTED ENGINE AND FOUND NR 6 CYLINDER SEPARATED WHERE BARREL MEETS 	HEAD.  PROBABLE CAUSE: UNKNOWN.  RECOMMENDATIONS:  THIS IS AN ECI CYLINDER.  REFERENCE NEEDS TO BE MADE TO THEM TO RESOL	VE THE PROBLEM.  (K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2006042400145	20060424	00145	SO  	2006	4	24	2006FA0000386    	1	20060405	G	2121	553002	COOLING FAN     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					INST PANEL	BURNED          	B				E				ENGINE SHUTDOWN         				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			EA	23	52WW	6112 				278154014				AFTER STARTING ENGINES, THE PILOT SMELLED SMOKE AND OBSERVED FLAMES BEHIND CO-PILOTS INSTRUMENT PANEL.  ENGINES WERE SHU	TDOWN.  WHEN MASTER SWITCH WAS TURNED OFF, THE FLAME WENT OUT.  INVESTIGATION REVEALED THAT THE AVIONICS COOLING FAN HAD	 CAUGHT FIRE.  (K)				1	L	7	2 	3O	3	O		1A10    	1E4				 
2006042400182	20060424	00182	CE  	2006	4	24	2006FA0000387    	1	20060328	G	3040	260148830	DEICE SYSTEM    			CESSNA	208   	208B        	2073701	CE  										WINDSHIELD	LEAKING         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	208JH					208B1144				WATER LEAKS AROUND/THROUGH EDGE SEAL OF WINDSHIELD DE-ICE HOT PLATE AND OBSTRUCTS FORWARD VIEW OF PILOT.  THIS WATER FRE	EZES BETWEEN THE HOT PLATE AND THE WINDSHIELD.  IN RAIN CONDITIONS WITH TEMPERATURE ABOVE FREEZING WATER ACCUMULATES AND	 FILLS 4 TO 5 INCHES OF THE LOWER PORTION OF THE HOT PLATE.  THIS WATER FLOATS AROUND THE IN THE LAYER BETWEEN THE HOT P	LATE AND THE WINDSHIELD MAKING LANDING THE AC VERY DANGEROUS FROM THE PILOTS SEAT.  IN TEMPERATURES BELOW FREEZING THIS 	WATER FREEZES AND COMPLETELY BLOCKS THE PILOTS FORWARD VIEW.  THIS IS THE SECOND HOT PLATE TRIED ON THIS NEW AIRCRAFT WI	TH TWO DIFFERENT EDGE SEAL CONFIGURATIONS.  THE WINDSHIELD DEICE HOT PLATE HAS BEEN REMOVED FROM THIS AC FOR SAFETY.	1	H	7	1 	3T				A37CE   					 
2006042400153	20060424	00153	SO  	2006	4	24	2006FA0000388    	1	20060307	G	5511	89T20543	RIB             	GRUMAN      		GRUMAV	S2    	S2F         	3951006	SO  	GARRTT	TPE331	TPE331*     	01514	WP  					RT HORIZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	448DF				N11140	152347				DURING MAINTENANCE ON THE RT SIDE HORIZONTAL STABILIZER, CRACKS WERE ON 2 RIB SECTIONS.  CRACKS WERE DETECTED ON RIBS PN	 89T920543, STA 138.858 AND PN 89T1029-1, STA 80.608.  THESE CRACKS WERE FOUND ON THE UPPER FWD LEADING EDGE TABS WHERE 	THE RIB ATTACHES TO THE HORIZONTAL STAB SKIN.  RIBS WERE REPAIRED IAW THE STRUCTURAL REPAIR MANUAL.  (K)				2	H	7	2 	4O	3	T	RT	EXPA2H72	E2WE				 
2006042400155	20060424	00155	CE  	2006	4	24	2006FA0000389    	1	20060128	G	3232	12810281	ACTUATOR        	CESSNA      		CESSNA	210   	210L        	2073448	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	D3A34	D3A34C402   	GL  	RT MLG DOOR	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			EA	11	4FL	5258 	15   		4486	21061382	289006R	921108		MECHANICAL FAILURE OF THE RT MLG DOOR ACTUATOR, PREVENTED THE EXTENSION OF THIS AC LANDING GEAR EITHER BY NORMAL OF EMER	GENCY PROCEDURES.  THE FAILURE WAS THE ACTUATOR GLAND AND CIRCLIP COMING APART FROM THE ACTUATOR.  THE RT MLG ACTUATOR W	AS REMOVED AND RESEALED BY A LOCAL MAINTENANCE FACILITY ON 9/24/2004 AT 343.8 HOURS TACH 14.7 HOURS SINCE RESEAL.  INVES	TIGATION OF THIS INCIDENT WAS INCONCLUSIVE OF WHAT CAUSED THIS FAILURE.  (K)			1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P47GL	 
2006042400227	20060424	00227	SO  	2006	4	24	2006FA0000390    	1	20060320	G	2560	45402	HARNESS         			PIPER 	PA28  	PA28161     	7102803	SO  										SHOULDER HARNESS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2203T	50   				287916300				HAVE HAD NUMEROUS PROBLEMS WITH PACIFIC SCIENTIFIC INERTIA REELS, PN 1107447-29,  MFG PN 564-863 (PS50039-4-49).  THESE 	HARNESSES DO NOT RETURN AND/OR DO NOT FUNCTION UNDER A SUDDEN LOAD.  ON OCCASION, HAVE FOUND THEM BAD STRAIGHT OUT OF TH	E BOX.  THEY ARE ALSO VERY SUSCEPTABLE TO WARPAGE/ MALFUNCTION UPON INSTALLATION.  (K)				1	L	7	1 	3O				2A13    					 
2006042400228	20060424	00228	SO  	2006	4	24	2006FA0000391    	1	20060329	G	3246	16403506	BRAKE DISC      	CLEVELAND   		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	WHEEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9007Y					3111	R47161	981497		FOUND CRACK IN BRAKE DISC ON OUTER EDGE. CRACK STARTED ON THE (P) IN PARKER FROM THE STAMPED NAME, MODEL, DATE, AND SN. 	 WHEN STAMPED COULD HAVE CAUSED A STRESS CRACK.  THE USE OF AN INK STAMP WOULD NOT CAUSE ANY STRESS ON THE DISC. (K)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	 	 
2006042400229	20060424	00229	SO  	2006	4	24	2006FA0000392    	2	20060410	G	7414	6310	MAGNETO         			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	8411Q	348  				U20603271				CHECKING ENGINE FOR PERSISTENT OIL LEAK, FOUND IT TO BE COMING FROM AREA OF LT MAG.  MAG REMOVED AND WAS FOUND TO HAVE 1	.5 INCH SECTION OF MOUNTING FLANGE CRACKED OFF.  THIS IS THE SECOND MAG ON THIS ENGINE TO HAVE THIS PROBLEM.  PREVIOUS M	AG WAS TORQUED TO SPECS AS WAS THIS ONE.  (K)				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006050200007	20060502	00007		2006	5	2	2006FA0000393    	1	20060411	G	2434	ALU1003	HOUSING         																	ENGINE	WORN            	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										THIS ALTERNATOR HAS -0- HOURS TIME-IN-SERVICE.  DURING INSPECTION, PRIOR TO SALE, IT WAS DISCOVERED THAT THE ROTOR HAD E	XCESSIVE LATERAL MOVEMENT AS A RESULT OF EXCESSIVE WEAR OF THE DRIVE END HOUSING BEARING BORE.  THIS CONDITION WOULD HAV	E LEAD TO PREMATURE FAILURE OF THE DRIVE GEAR/ALTERNATOR AND COULD HAVE LEAD TO A COMPLETE ENGINE FAILURE.  HAVE SEEN TH	IS SAME PROBLEM IN A VERY LARGE PERCENTAGE OF THESE ALTERNATORS RETURNED TO SERVICE BY OVERHAULER.  (K)																 
2006042500129	20060425	00129	SO  	2006	4	25	2006FA0000394    	1	20060401	G	5751	42972	SPAR            			PIPER 	J3    	J3C*        	       	SO  										AILERON	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02										AILERON SPARS FOUND EXCESSIVE CORROSION UNDER ALL 3 HINGES.  NEEDED TO REPLACE SPAR ON BOTH LT AND RT AILERONS BEFORE RE	COVERING AILERONS.  (K)					1	H	7	1 	3O				ATC660  					 
2006042400235	20060424	00235	CE  	2006	4	24	2006FA0000397    	1	20060209	G	5753	052390134	FLAP            			CESSNA	182   	T182        	2072736	CE  	LYC   	O540  	O540L3C5    	41532	EA  					RT WING	DAMAGED         	D			AVXR	K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NE	01	5464N					18267735	L2248140A			ON DEC 4, 2005, THE RT FLAP JAMMED AT THE IB ATTACH ARMS IN ABOUT THE 20 DEGREE POSITION.  FLAP MOTOR CONTINUED TO RUN F	OR A SHORT PERIOD OF TIME, CAUSING SEVERE DAMAGE AND DISTORTION TO THE JAMMED FLAP,  THE PILOT WAS ABLE TO LAND THE AIRP	LANE WITHOUT FURTHER INCIDENT.  INSPECTION REVELED THAT THE TIP OF THE RT IB FLAP SUPPORT ARM CAME IN CONTACT WITH A BRA	CKET ON THE FLAP TRACK RIB ASSY CAUSING THE FLAP TO BIND.  REPAIRED BY REPLACING THE RT FLAP INCLUDING ALL THE ROLLERS A	ND BY REPLACING BOTH BRACKETS ON THE IB FLAP TRACK RIB ASSY.  (K)		1	L	7	1 	3O	3	O		3A13    	E295				 
2006042700207	20060427	00207	CE  	2006	4	27	2006FA0000398    	1	20060327	G	5346	051313211	BRACKET         	CESSNA      		CESSNA	175   	175         	2072502	CE  										ENGING MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7259M	3822 				55559				FOUND THE UPPER LEFT ENGINE MOUNT BRACKET, P/N 0513132-11 IN THE 0513132-3 UPPER ENGINE MOUNT STRINGER CRACKED THROUGH T	HE BRACKET AROUND THE RADIUS OF THE WASHER.  INSPECTION WAS ACCOMPLISHED DUE TO NUMEROUS REPORTS OF THE SAME CONDITION F	OUND ON LIKE MODELS OF AIRCRAFT.				1	H	7	1 	3O			NT	3A17    					 
2006042700228	20060427	00228	CE  	2006	4	27	2006FA0000399    	1	20060327	G	7120	051313211	BRACKET         	CESSNA      		CESSNA	175   	175         	2072502	CE  										ENGINE MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7259M	3822 				55559				FOUND THE UPPER RIGHT ENGINE MOUNT BRACKET, P/N 0513132-11 IN THE 0513132-4 UPPER ENGINE MOUNT STRINGER, CRACKED.  INSPE	CTION WAS ACCOMPLISHED DUE TO NUMEROUS REPORTS OF THE SAME CONDITION FOUND ON LIKE MODELS OF AIRCRAFT.					1	H	7	1 	3O			NT	3A17    					 
2006051200047	20060512	00047	SO  	2006	5	12	2006FA0000400    	1	20060106	G	2824	236405492189	VALVE           			PIPER 	PA34  	PA34200T    	7103406	SO  										FUEL SYS	LEAKING         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	05										FUEL COULD NOT BE SHUT OFF AND FUEL WAS CROSS-FEEDING. SEVERAL CROSSFEED VALVES HAVE BEEN EXAMINED AND FOUND TO HAVE DEF	ECTIVE SEALS. O-RINGS WERE DISSOLVED AND RESEMBLED A TAR LIKE SUBSTANCE. IF THERE IS AN ENGINE FIRE OR LEAK, FUEL CANNOT	 BE SHUT OFF WHICH CREATES A SAFETY OF FLIGHT CONDITION THAT MUST BE CORRECTED.				1	L	7	2 	3O				A7SO    					 
2006051000247	20060510	00247	CE  	2006	5	10	2006FA0000401    	1	20060425	G	5553	04311481	FITTING         	CESSNA      		CESSNA	150   	152         	2071835	CE  										VERTICLE STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	48968					15281080				PART ATTACHES VERTICLE STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS B	EEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (R	EF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT.				1	H	7	1 	3O			NT	3A19    					 
2006051000248	20060510	00248	CE  	2006	5	10	2006FA0000402    	1	20060425	G	5553	04311481	FITTING         	CESSNA      		CESSNA	150   	152         	2071835	CE  										VERTICLE STAB	CRACKED         	B			N2YR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	48968					15281080				PART ATTACHES VERTICAL STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS B	EEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (R	EF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. AIRCRAFT TOTAL TIME IS 12,762.1				1	H	7	1 	3O			NT	3A19    					 
2006042600116	20060426	00116	NM  	2006	4	26	2006FA0000403    	1	20060419	G	5740	2000610102501	BRACKET         			PIPER 	PA60  	PA60600     	7106001	NM  										RIGHT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	78LS	2177 				600546176				FWD WING ATTACHMENTS, LEFT & RIGHT WINGS, FWD & AFT BRACKETS WERE NEVER RIVETED TO TOP & BOTTOM WING SKINS & INBOARD RIB	 FLANGES ALLOWING ALL LOADING TO BE TAKEN BY BRACKET FLANGES & INBD WING RIBS. ALL 4 BRACKETS ARE CRACKED. PICTURES AVAI	LABLE.  IT SEEMED MORE THAN COINCIDENTAL TO ME THAT THE FOUR RIVETS NEEDED TO ATTACH THE WING SKIN TO THE RIB AND THE AT	TACHMENT BRACKET WERE MISSING ON BOTH WINGS, TOP AND BOTTOM. PERHAPS THERE WAS A MISTAKE ON THE ASSEMBLY DRAWING AT THE 	TIME OF MANUFACTURE. THE HOLES WERE NEVER EVEN DRILLED FOR THE RIVETS. THE AIRCRAFT WAS MANUF. IN 1978, 4 NEWER MODELS W	ERE INSPECTED AND FOUND TO BE CORRECTLY ASSEMBLED. PICTURES PROVIDED.	1	M	7	2 	3O			RT	A17WE   					 
2006051100297	20060511	00297	CE  	2006	5	11	2006FA0000404    	1	20060331	G	3250	59420011	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  										NLG STEERING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	340JY	4544 				340A0979				DURING ANNUAL INSPECTION FOUND NOSE GEAR STEERING BELLCRANK ASSY #5942001-1 CRACKED LEFT AND RIGHT SIDES AT PIVOT RADIOU	S. NEW REPLACEMENT PART WITH SAME PART NUMBER OBTAINED FROM CESSNA AIRCRAFT IS MADE MUCH HEAVIER WITH ADDITIONAL MATERIA	L IN CRACK PRONE AREA.  PART FAILURE COULD LEAD TO LOSS OF NOSE GEAR STEERING CONTROL.				1	L	7	2 	3O				3A25    					 
2006051100299	20060511	00299	CE  	2006	5	11	2006FA0000405    	1	20060331	G	3250	59420011	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  										NLG STEERING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	340JY	4544 				340A0979				DURING ANNUAL INSPECTION FOUND NOSE GEAR STEERING BELLCRANK ASSY #5942001-1 CRACKED LEFT AND RIGHT SIDES AT PIVOT RADIOU	S. NEW REPLACEMENT PART WITH SAME PART NUMBER OBTAINED FROM CESSNA AIRCRAFT IS MADE MUCH HEAVIER WITH ADDITIONAL MATERIA	L IN CRACK PRONE AREA.  PART FAILURE COULD LEAD TO LOSS OF NOSE GEAR STEERING CONTROL.				1	L	7	2 	3O				3A25    					 
2006051200049	20060512	00049		2006	5	12	2006FA0000406    	4	20060314	G	3452		TRANSPONDER     			CESSNA	680   	680CE       	2076811	CE  	PWA   	306   	PW306B      	 	NE  					COCKPIT	MALFUNCTIONED   	C				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	35	2428					6800046				DEPARTED AND WAS TOLD BY DEPARTURE CONTROL THEY DID NOT HAVE A TARGET ON US.  SWITCHED TO SECOND TRANSPONDER WITH SAME R	ESULT.  BOTH TRANSPONDERS APPERARED TO BE IN NORMAL OPS.  LANDED AT AND WENT TO A BLACK AIRCRAFT(COMPLETE SHUTDOWN).  RE	STARTED AND ALL WAS NORMAL DURING NEXT LEG.  DOWNLOADED COMPUTERS ON POST FLIGHT AT HOME BASE AND FOUND NO FAULTS.  HAVE	 FLOWN 49 LEGS SINCE THE OCCURANCE AND HAVE HAD NO FAILURES.			2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
2006051800175	20060518	00175	SO  	2006	5	18	2006FA0000407    	1	20060414	G	1410	LW18724	HOSE            	LYC         	TIO540AH1A  	PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	DETERIORATED    	B			UXCR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	05	126LM					3257336	L1146461A			PARTIAL POWER LOSS, TWO CYLINDERS DROPPED OUT, CAUSED BY SMALL PARTICLES OF RUBBER HOSE FROM UPPER DECK AIR REFERENCE LI	NES FLAKING OFF AND OCCLUDING THE FUEL INJECTORS					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2006051800243	20060518	00243	SO  	2006	5	18	2006FA0000408    	1	20060329	G	3230	67146004	DRAG LINK       			PIPER 	PA44  	PA44180     	7104402	SO  										NLG	FRACTURED       	B				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	15	938ER	620  	27   			4496200				DURING LANDING, THE NOSE GEAR RETRACT DRAG BRACE FAILED AT THE PIVOT POINT. THE NOSE GEAR COLLAPSED AND THE AIRCRAFT VEE	RED OFF OF THE RUNWAY STRIKING A LARGE RUNWAY SIGN WITH THE RT OB WING SECTION. THE CAUSE OF THE FAILURE IS STILL UNDER 	INVESTIGATION.				1	L	7	2 	3O				A19S0   					 
2006051800244	20060518	00244	SO  	2006	5	18	2006FA0000409    	1	20060329	G	3230	67146004	DRAG LINK       			PIPER 	PA44  	PA44180     	7104402	SO  										ZONE 700	FRACTURED       	B				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	15	938ER	620  	27   			4496200				DURING LANDING, THE NOSE GEAR RETRACT DRAG BRACE (PN-67146-004) FAILED AT THE PIVOT POINT. THE NOSE GEAR COLLAPSED AND T	HE AIRCRAFT VEERED OFF OF THE RUNWAY STRIKING A LARGE RUNWAY SIGN WITH THE RT OB WING SECTION.  THE CAUSE OF THE FAILURE	 IS STILL UNDER INVESTIGATION.				1	L	7	2 	3O				A19S0   					 
2006051800255	20060518	00255	CE  	2006	5	18	2006FA0000410    	1	20060406	G	7120	07516001	MOUNT           			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	7551S	2290 				18265200	286916R			DURING ANNUAL INSPECTION THE LT AFT ENGINE MOUNT P/N 0751600-1 WAS FOUND CRACKED THRU THE ENGINE MOUNT BOLT AREA.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2006051800257	20060518	00257	CE  	2006	5	18	2006FA0000411    	1	20060406	G	2760	632550033	LUG             			CESSNA	525   	525A        	2076615	CE  										SPEED BRAKE	MISDRILLED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	20GP	445  				525A0131				AC WAS IN FOR A PHASE 1 AND 2 INSPECTION.  A BROKEN BONDING STRAP AT THE UPPER LT SPEEDBRAKE DOOR NECESSITATED REMOVAL O	F THE BOLT CONNECTING THE PUSH ROD TO THE UPPER DOOR LUG.  DURING BOLT REMOVAL THE HELICOIL INSERT CAME OUT WITH THE BOL	T AND WAS DEFORMED.  PROPER INSERTION OF A NEW HELICOIL WAS UNSUCCESSFUL AS THE BOLT WOULD NOT THREAD INTO IT.  A COUPLE	 OF ATTEMPTS INSUED AND DETERMINATION WAS MADE THAT THE HOLE WAS NOT PROPERLY DRILLED AND TAPPED TO ACCEPT THE HELICOIL.	  MAINTENANCE SUPPORT HOTLINE REPRESENTATIVE AGREED WITH THE ASSESSMENT AND PROVIDED TECHNICAL DATA TO REMOVE THE UPPER 	DOOR LUG, BACK DRILL AND TAP TO THE PROPER SIZE.  INSTALLATION OF THE HELICOIL WAS THEN SUCCESSFUL.	1	L	7	1 	4F			RT	A1WI    					 
2006052200234	20060522	00234	SO  	2006	5	22	2006FA0000412    	2	20060424	G	8520	6416311052	THRU BOLT       			CESSNA	188   	A188B       	2073005	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ENGINE	BROKEN          	D				K				NONE                    				D			INFLIGHT SEPARATION       			AG	AGRICULTURE    	1			NM	09	4918R	200  				18802435T	284455R	EC1151A		THE ENGINE CRANKCASE THRU-BOLT BROKE. THIS THRU-BOLT IS LOCATED UNDER THE TOP OF THE OIL COOLER ADAPTER PLATE THRU TO TH	E NR 6 CYL TOP FRONT. IT BROKE OFF FLUSH AT THE CYL BASE WHILE IN FLIGHT. THE BOLT END WHICH BROKE OFF WITH THE CYL BASE	 NUT FLEW OUT THE FRONT OF THE COWL, PUT A GOUGE IN THE FACE OF THE PROP BLADE AND THEN HIT THE TOP OF THE COWL LEAVING 	A LARGE DENT. WHEN IT BROKE, THE OPPOSITE END OF THE BOLT WAS FORCED BACK AGAINST THE OIL COOLER ADAPTER PLATE AND DEFOR	MED THE PLATE. THIS THRU-BOLT IS A REPLACEMENT INSTALLED LAST AUGUST 2005 DUE TO THE ORIGINAL THRU-BOLT, 650 HRS SINCE R	EMAN, ALSO BREAKING AT THE SAME LOCATION. A NEW CYL BASE NUT HAD BEEN USED AND TORQUED TO 800 INCH LBS IAW SB96-7C.	1	L	7	1 	3O	3	O		A9CE    	E3SO	5	C	P25EA	 
2006051200153	20060512	00153	SO  	2006	5	12	2006FA0000413    	1	20060427	G	8011	MZ6222	DRIVE ASSY      			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320B1A     	41508	EA  					STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	3326P	152  				231277				STARTER DRIVE FAILED.						1	L	7	2 	3O	3	O		1A10    	E274				 
2006051200154	20060512	00154	SO  	2006	5	12	2006FA0000414    	1	20060427	G	8011	MZ6222	DRIVE ASSY      			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320B1A     	41508	EA  					STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	3326P	152  				231277				STARTER DRIVE FAILED						1	L	7	2 	3O	3	O		1A10    	E274				 
2006053000169	20060530	00169	SO  	2006	5	30	2006FA0000415    	1	20060425	G	2721	31731	CABLE           			MAULE 	MX7   	MX7180      	5460185	SO  										RUDDER	FRAYED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	45829									FOUND RIGHT AND LEFT RUDDER TRIM CABLE BADLY FRAYED AS THE CABLE EXISTED THE RUDDER SKIN.						1	H	7	1 	3O			NC	3A23    					 
2006053000170	20060530	00170	CE  	2006	5	30	2006FA0000416    	1	20060425	G	5553	04311481	FITTING         	CESSNA      		CESSNA	150   	152         	2071835	CE  										RUDDER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	48968					15281080				PART ATTACHES VERTICLE STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS B	EEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (R	EF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. AIRCRAFT TOTAL TIME IS 12,762.1				1	H	7	1 	3O			NT	3A19    					 
2006061300211	20060613	00211	SO  	2006	6	13	2006FA0000417    	2	20060329	G	8530		PACKING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					ENGINE	OUT OF POSITION 	E				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			SW	99										#1 CYLINDER EXHAUST PUSHROD HOUSING PACKING BLEW OUT.  SUSPECT POSSIBLE CRANKCASE PRESSURIZATION.  PACKING HAD SMALL CUT	 MOST LIKELY FROM INSTALLATION HOWEVER THAT SOULD NOT HAVE ALLOWED IT TO BLOW OUT.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2006051800241	20060518	00241	SO  	2006	5	18	2006FA0000418    	1	20060422	G	3213	6703704	STRUT           			PIPER 	PA44  	PA44180T    	7104404	SO  										LT MLG	BROKEN          	C				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	838PC					448107056				LT GEAR STRUT BROKE AT HOUSING.						1	L	7	2 	3O				A19SO   					 
2006051800242	20060518	00242	SO  	2006	5	18	2006FA0000419    	1	20060422	G	3213	6703704	STRUT           			PIPER 	PA44  	PA44180T    	7104404	SO  										LT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	838PC					448107056				LH MLG STRUT BROKE ON TAXI						1	L	7	2 	3O				A19SO   					 
2006051000139	20060510	00139	CE  	2006	5	10	2006FA0000420    	1	20060414	G	2460	50369101163	BUSS BAR        	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					RT WING	CORRODED        	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	968T					BB570				DURING SCHEDULED INSPECTION FOUND EXCESSIVE CORROSION ON RT WS 54.80 WEB HOT BATTERY BUS PANEL BUS BAR AND FUSE HOLDERS,	 REQUIRING COMPONENT REPLACEMENT.  AIRCRAFT PREVIOUSLY MODIFIED WITH SEALED LEAD-ACID BATTERY.  HAVE NOTED SIMILAR CORRO	SION ISSUES ON OTHER OLDER AC MODIFIED WITH LEAD-ACID BATTERY INSTALLATIONS.  RECOMMEND THAT AREAS ADJACENT TO THE BATTE	RY BOX SHOULD BE INSPECTED CAREFULLY FOR CORROSION EACH SCHEDULED PHASE INSPECTION, ESPECIALLY THE ELECTRICAL SYSTEM COM	PONENTS, FOR AIRCRAFT RETROFITTED WITH LEAD-ACID BATTERIES.  (K)		1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2006051100098	20060511	00098	CE  	2006	5	11	2006FA0000421    	1	20060410	G	1430	MS27039109	SCREW           	BEECH       		BEECH 	MU300 	400A        	1155402	CE  										FLOOR PANEL	WRONG PART      	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	907JE					RK107				DURING INSPECTION IAW MFG SB, FOUND BRAKE HYDRAULIC LINE DAMAGED BY FLOOR PANEL ATTACHING SCREW.  REPAIRED TUBING AND MO	DIFIED FLOOR PANELS IAW SB.  HAVE FOUND THIS SAME CONDITION ON OTHER AIRCRAFT.  (K)					2	H	7	2 	4F			RT	A16SW   					 
2006051100200	20060511	00200	CE  	2006	5	11	2006FA0000422    	1	20060410	G	3610	45A6351771	TUBE            			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR SYS	BROKEN          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	907JE	5113 				RK107				DURING RECURRING 400 HR INSPECTION REQUIRED BY AD, FOUND AFT FUSELAGE RT BLEED AIR DUCT ASSY.  BELLOWS BRAIDED WIRE MESH	 BLOWN OUT OF END FITTINGS.  SUSPECTED TO BE CAUSED BY BLEED AIR LEAK FROM EITHER CRACKED BELLOWS OR FATIGUE/TUBING MIS-	ALIGNMENT STRESS.  REPLACED TUBE ASSY WITH SUPERSEDING (PN 45A63517-075) TUBE ASSY.  RECOMMEND POSSIBLE AFT FUSELAGE BLE	ED AIR TUBING OF OLDER PN`S HAVE A 5000 HR LIFE LIMIT.  (K)			2	H	7	2 	4F			RT	A16SW   					 
2006051200142	20060512	00142	CE  	2006	5	12	2006FA0000423    	1	20060419	G	3230	1698200111	DRAG BRACE      			BEECH 	23    	A24R        	1151252	CE  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	BROKEN          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	13	8015R	2111 				MC54				THE AIRCRAFT TOUCHED DOWN  UNEVENTFUL.  DURING ROLLOUT, THE NOSE GEAR COLLAPSED ABOUT 1500 FT AFTER TOUCHDOWN.  THE DRAG	 BRACE FAILED AT THE YOKE WHERE IT ATTACHES TO THE NOSE GEAR.  (K)					1	L	7	1 	3O	3	O		A1CE    	1E10				 
2006051000226	20060510	00226	CE  	2006	5	10	2006FA0000425    	1	20060417	G	8011	S539800M30	SPRING          			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  					STARTER	BROKEN          	G				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	01	8503S				S1475691	18256603	1317375R4			STARTER DRIVE WAS OVERHAULED BY A CERTIFIED REPAIR STATION.  (PN S539800M30) STARTER ADAPTER SPRINGS WERE INSTALLED IAW 	STC DURING THE OVERHAUL.  THE STARTER WAS INSTALLED ON THIS ENGINE AND WAS OPERATED FOR 4.06 HOURS (5 STARTS) BEFORE IT 	FAILED.  AN INSPECTION OF THE STARTER DRIVE ADAPTER FOUND THE STARTER ADAPTER SPRING WAS BROKEN AND DEFORMED.  THE INTER	NAL PARTS WERE DISCOLORED, AND THERE WERE METAL SHAVINGS FOUND IN THE OIL.  (K)			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2006051200062	20060512	00062	CE  	2006	5	12	2006FA0000426    	1	20060412	G	2434	E3FF10300AA	ALTERNATOR      			CESSNA	210   	T210M       	2073451	CE  										ENGINE	FAILED          	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										ALTERNATOR FAILED, PLATE SCREWS FELL OUT.  (K)						1	H	7	1 	3O				3A21    					 
2006051200144	20060512	00144	WP  	2006	5	12	2006FA0000427    	1	20060412	G	6220	5143711	HUB             			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					MAIN ROTOR HUB	CRACKED         	B			ECGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	46MV	2391 	264  			5046	L248043			M/R HUB DYE CHECK INSPECTION.  HUB WAS FOUND TO BE CRACKED.  RETIREMENT LIFE, 2500 HOURS.  (K)						1	G	7	1 	3O	3	O		4H11    	E304				 
2006051000134	20060510	00134	EU  	2006	5	10	2006FA0000428    	1	20060421	G	3233	273T411B1	ACTUATOR        			ROLSCH	LS    	LS3A        	3801214	EU  	GE    	CF6   	CF680       	30025	NE  					NLG	CRACKED         	B			DM4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	325OP					3350				NLG RETRACT ACTUATOR WAS RECEIVED WITH THE PISTON ROD CRACKED.  3 CRACKS RUN AROUND THE CIRCUMFERENCE OF THE ROD AT THE 	THREADED END.  CRACKS RUN ABOUT 95 PERCENT AROUND ROD BUT DO NOT CONNECT (RUN IN A SPIRAL) CORROSION FOUND ON INTERIOR T	HREADS.  CORROSION APPEARS TO BE IN CRACK.  (K)				1	K	0	0 	  	4	F		G37EU   	E13NE				 
2006051100289	20060511	00289	CE  	2006	5	11	2006FA0000429    	1	20060407	G	2750	S19062	SWITCH          			CESSNA	172   	172N        	2072434	CE  										FLAPS	STUCK           	B			BNZR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	4668G					17273294				FLAP UP LIMIT SWITCH STUCK IN THE OPEN POSITION.  (K)						1	H	7	1 	3O			NT	3A12    					 
2006051200152	20060512	00152	CE  	2006	5	12	2006FA0000430    	1	20060331	G	7120	34415377	MOUNT           			BEECH 	35    	D35         	1151510	CE  	CONT  	E225  	E2258       	17015	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	2950B	4649 				D3591	35004D286			MOUNT WAS CROOKED IN WELD.  THINK IT HAPPENED DUE TO TIME ON PORT AND AGE OF AIRCRAFT.  CLOSE INSPECTION OF THIS AREA DU	RING ROUTINE MAINTENANCE (UPPER LT, MOUNT CLUSTER/ WEB .1250 INCH CRACK).  (K)					1	L	7	1 	3O	3	O		A777    	E267				 
2006050800093	20060508	00093	SO  	2006	5	8	2006FA0000431    	1	20060418	G	3260	211C24312	PRESSURE SWITCH 			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					LANDING GEAR	CORRODED        	G				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SW	11	4967T					28R7235164	RL1770951A			LANDING GEAR FAILED TO RETRACT IN FLIGHT.  PLACING THE AC ON JACKS, THE LANDING GEAR FAILED TO COMPLETELY RETRACT.  BY P	LACING A JUMPER WIRE BYPASSING THE HYDRAULIC PRESSURE SWITCH THE LANDING GEAR WORKED NORMALLY.  AFTER REMOVING THE PRESS	URE SWITCH, CORROSION AND PITTING WAS OBSERVED ON THE CONTACTOR ALLOWING IT TO HEAT, WHICH INCREASED RESISTANCE, IN TURN	 CAUSING A LOW VOLTAGE CONDITION THAT DID NOT ALLOW THE GEAR MOTOR TO OPERATE AND CAUSED PARTIAL RETRACTION.  IT WAS NOT	ED THAT AS THE PRESSURE SWITCH COOLED, IT AGAIN ACTIVATED THE GEAR MOTOR AND CONTINUED THIS CYCLE UNTIL THE LANDING GEAR	 WAS IN THE UP POSITION.  (K)	1	L	7	1 	3O	3	O		2A13    	1E10				 
2006051200139	20060512	00139	SO  	2006	5	12	2006FA0000432    	1	20060418	G	5712	62021005	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										WING STA 49.25	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	518MW	1301 				2844105				RIB CRACKED IN FLANGE WHERE LANDING GEAR SIDE BRACE FITTING BOLTS.  THE CRACK HAS BEEN NOTED ON LIKE MODELS (6 WINGS).  	ALL PREVIOUS NOTATIONS FOUND ON AC IN EXCESS OF 6000 HRS TO BE CAUSED BY AN IMPRESSION LEFT BY THE AN960-4 WASHER USED U	NDER THE LOCKNUT.  THE WASHER APPEARS TO CUT INTO THE RADIUS AND THE CRACKS ORIGINATE AND FOLLOW THE WASHER OUTLINE UNTI	L IT PROGRESSES TO A POINT OF CONTINUING IN BOTH DIRECTIONS VERTICALLY.  (K)			1	L	7	1 	3O				2A13    					 
2006051000201	20060510	00201	SO  	2006	5	10	2006FA0000433    	1	20060414	G	5712	78475005	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										RT WING STA49.25	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	518MW	1301 				2844105				INSPECTED RIB IAW SB 1161 AND FOUND RIB CRACKED.  THE SAME RIB HAS BEEN FOUND CRACKED IN THE SAME LOCATION ON SIX OTHER 	WINGS.  ALL OTHER WINGS HAD EXCESS OF 6000 HRS REPAIRED AND APPEARED TO HAVE BEEN INSTALLED CROOKED. THE ASSEMBLY PROCES	S HAD THIS PART INSTALLED UNDER AN INITIAL LOAD LEADING TO PART CRACKING PREMATURELY.  (K)				1	L	7	1 	3O				2A13    					 
2006051000202	20060510	00202	EA  	2006	5	10	2006FA0000434    	2	20060414	G	8520		CAM             			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	336PA	1100 				4496140				NOTED EXCESS MATERIAL IN REMOVED OIL FILTER, SAMPLE ANALYZED AND DETERMINED CAM/LIFTER WEAR.  ENGINE REMOVED FOR REPAIRS	.  WHILE CASE SPLIT SB 569 COMPLIED WITH REPLACING CRANKSHAFT.  (K)					1	L	7	2 	3O	3	O		A19S0   	E286				 
2006051000232	20060510	00232	EU  	2006	5	10	2006FA0000435    	1	20060411	G	6220	109011211101	ROD END         			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					MAIN ROTOR	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	820NA				0109	14011	PU0025			DURING DAILY INSPECTION FOUND RED BLADE MAIN ROTOR DAMPER OB ROD END HAD COME APART.  BEARING HAD SEPARATED COMPLETELY F	ROM ROD END. (K)					1	G	7	2 	3U	3	T		H7EU    	E2NE				 
2006051000233	20060510	00233	EU  	2006	5	10	2006FA0000436    	1	20060405	G	2913	4005303	PUMP            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	FAILED          	B			BONR	O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			GL	19	700FH		1447 			158				NR 1 HYDRAULIC PUMP FAILED ON TAKEOFF ROLL.  REMOVED PUMP AND INSPECTED BUT FOUND NO OBVIOUS PHYSICAL DEFECTS.  REMOVED 	HYDRAULIC SYSTEM FILTER AND INSPECTED FOR DEBRIS, NONE NOTED.  INSTALLED SERVICEABLE HYDRAULIC PUMP IN NR 1 POSITION, AL	L SYSTEMS FUNCTION NORMALLY.  (K)				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2006051000218	20060510	00218	SO  	2006	5	10	2006FA0000437    	1	20060413	G	5712	6701603	RIB             			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360A1A    	41514	EA  					WING	CRACKED         	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	7536J	2294 				28R30910				DURING MODIFICATION OF AFT RIB IAW SB, 2 CRACKS WERE FOUND PROPAGATING FROM THE OB BOLT HOLE FOR THE ATTACHMENT OF (PN 9	564307) BRACKET.  (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
2006051600136	20060516	00136		2006	5	16	2006FA0000438    	1	20060417	G	2560	BK05SL	PIN             																	SEAT BELT BUCKLE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										DURING DYNAMIC CERTIFICATION TESTING,  2-PLACE SIDE FACING DIVAN, THE BUCKLE ON THE AFT ANTHROPOMORPHIC TEST DUMMY (ATD)	 POSITION RESTRAINT SYSTEM DISENGAGED ALLOWING THE ATD TO MOVE UNRESTRAINED.  PROBABLE CAUSE APPEARS TO BE FAILURE OF TH	E BUCKLE`S LOCKING PIN TO FULLY ENGAGE THE STRIKING PLATE (CONNECTOR) ON THE OPPOSITE HALF OF THE LAP BELT.  PART MAY HA	VE BEEN DEFECTIVE.  MFG SHOULD IMPROVE INSPECTION PROCESS TO ENSURE THAT NO DEFECTIVE PARTS LEAVE THEIR FACILITY.  (K)																 
2006051200140	20060512	00140	EA  	2006	5	12	2006FA0000439    	2	20060128	G	8530	73938	INTAKE VALVE    			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					CYLINDER NR 3	DISINTEGRATED   	B			XXOR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			WP	01	56709	127  				327440020				INTAKE VALVE DISINTEGRATED, FALLING INTO CYLINDER HEAD NR 3.  VALVE BOUNCED AROUND, BEATING THE TOP OF PISTON AND CYL HE	AD CAUSING EXTENSIVE DAMAGE, FINALLY THE VALVE WAS SUCKED INTO THE INTAKE CAUSING A GAPPING HOLE ON THE INTAKE PORT.  IN	TAKE VALVE FAILURE IS BELIEVED TO BE THE ONLY CAUSE OF CATASTROPIC FAILURE.  (K)				1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006050800052	20060508	00052		2006	5	8	2006FA0000440    	4	20060223	G	3417	8220839429	ADC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					LT AFT AVIONICS	DEFECTIVE       	B			BSYR	O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			GL	07	160AN					126				ALL ADC OUTPUTS ON THE COPILOTS PFD (ALTIMETER, VSI AND AIRSPEED, ECT) FLAGGED IN FLIGHT INTERMITTENTLY AND WOULD RESET 	ITSELF.  CREW REQUESTED TO LEAVE RVSM AIRSPACE.  THE ADC WAS FOUND TO BE DEFECTIVE AND WAS REPLACED.  THE SYSTEM WAS TES	TED AND INSPECTED IAW MM AND FOUND TO COMPLY WITH FAR 91.411 PART 43 AND MFG RVSM ADC INSPECTIONS.  THE AIRCRAFT REMAINS	 RVSM COMPLIANT.  (K)			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006051100273	20060511	00273	SO  	2006	5	11	2006FA0000441    	2	20060417	G	8550	CH48110	OIL FILTER      			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	58946					18262417				MOUNTING STUD TOO LONG, APPROX .200 LONGER.  INSTALLED OIL FILTER AFTER OIL CHANGE, RAN ENGINE TO LEAK CHECK AND LOST AL	MOST 2 QTS OF OIL.  INVESTIGATION FOUND THAT THE OIL FILTER STUD WAS TOO LONG CAUSING THE FILTER TO TORQUE BEFORE SEAL T	OUCHED FLANGE, LEAVING .050 GAP.  REPLACED FILTER WITH SAME PN BUT WITH SHORTER STUD AND LEAK CHECKED, OK.  (K)				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2006051200158	20060512	00158	SO  	2006	5	12	2006FA0000442    	1	20060323	G	2910		HYDRAULIC LINE  			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					RT CABIN SIDE	CHAFED          	D				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			EA	07	63868	8803 				277854020				COMPLETE INTERIOR REFURBISHING WAS DONE.  100 HRS AFTER AC WAS RETURNED TO SERV, NOSE AND LT MAIN GEAR WOULD NOT LOCK DO	WN, PILOT LANDED WITH ONLY RT GEAR EXTENDED.  HYD FLUID WAS DRIPPING FROM BELLY,  UPON INVESTIGATION, ALUMINUM HYD LINE 	WAS CHAFED THROUGH BY AILERON CABLE IN FRONT OF MAIN SPAR, UNDER CABIN ENTRANCE DOOR SILL.  SUSPECTED THAT AFTER AC WAS 	INSP, WHEN DISCREP WERE BEING CLEARED, INTERIOR WORK BEING DONE, PERSONNEL SOMEHOW BENT LINE DOWN TO WHERE IT CONTACTED 	CABLE.  WHEN PANEL IS REMOVED UNDER DOOR, HYD LINES ARE EXPOSED, LITTLE SUPPT IN THIS AREA, LITTLE CLEARANCE BTWN LINES,	 CABLES.  LINES, CABLES ON LT SIDE OF CABIN ARE LESS LIKELY TO BE DISTURBED AS AUTOPILOT ROLL SERVO PROTECTS THEM.  (K)	1	L	7	2 	3O	3	O		1A10    	1E4				 
2006051200143	20060512	00143	NM  	2006	5	12	2006FA0000443    	1	20060419	G	5400	F2MA581200817	COWLING         			AMD   	FALC50	FALCON2000  	2730170	NM  										LT ENGINE	SEPARATED       	B			UO2R	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	19	722JB					13				AIRCRAFT WAS RETURNING TO HOME FIELD AFTER MAINTENANCE WHEN CREW HEARD A LOUD NOISE AND ELECTED TO RETURN TO DEPARTURE. 	 AFTER ENGINE SHUTDOWN, IT WAS DETERMINED THAT THE LT ENGINE UPPER AND LOWER COWLING HAD SEPARATED FROM THE AC IN FLIGHT	.  SB CONCERNING COWLING SEPARATION, HAD BEEN PREVIOUSLY APPLIED.  COWL SEPARATION HAS BEEN THE SUBJECT OF PREVIOUS SERV	ICE ADVISORIES AND SERVICE NEWS FLASHES.  (K)			2	K	7	2 	4F			RT	A50NM   					 
2006051100285	20060511	00285	NM  	2006	5	11	2006FA0000444    	1	20060419	G	5400	F2MA581260813	COWLING         			AMD   	FALC50	FALCON2000  	2730170	NM  										LT ENGINE	SEPARATED       	B			UO2R	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	19	722JB					13				AC WAS RETURNING TO HOME FIELD AFTER MAINTENANCE WHEN CREW HEARD A LOUD NOISE AND ELECTED TO RETURN TO DEPARTURE.  AFTER	 ENGINE SHUT-DOWN, IT WAS DETERMINED THAT THE LT ENGINE UPPER AND LOWER COWLING HAD SEPARATED FROM THE AC IN FLIGHT.  SB	 CONCERNING COWLING SEPARATION, HAD BEEN PREVIOUSLY APPLIED.  COWL SEPARATION HAS BEEN THE SUBJECT OF PREVIOUS SERVICE A	D AND SERVICE NEWS FLASHES.  (K)			2	K	7	2 	4F			RT	A50NM   					 
2006050800165	20060508	00165	CE  	2006	5	8	2006FA0000445    	1	20060330	G	5610	NH2401691	WINDSHIELD      			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	CRACKED         	D				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			EA	07	333PC	4619 				258277				LEVEL FLIGHT AT 360, PILOTS (B) PANEL OUTER HEATED LAYER CRACKED ALONG LOWER FRONT CORNER THEN CONTINUED UP AND ACROSS T	OP OF WINDOW.  CREW DECLARED AN EMERGENCY AND DESCENDED TO 8000 FT.  OUTER PANEL STAYED WITH AIRCRAFT, NO AD OR SB APPLY	 TO PANEL AT THIS TIME.  WINDOW REPLACED WITH NEW UNIT.  PRESSURIZATION AND OPS CHECK GOOD.  THIS WINDOW HAD NO VISIBLE 	OR OPERATIONAL PROBLEMS PRIOR TO FAILURE.  (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007051100153	20070511	00153	SW  	2007	5	11	2006FA0000446    	1	20060410	G	6210	3G6220A00251	BOLT            			AGUSTA	AB139 	AB139       	0260110	SW  	PWA   	PT6   	PT6*        	52043	EA  					MAIN ROTOR	GOUGED          	B			LWXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	139HS	50   				31016				DURING ACCOMPLISHMENT OF THE MAIN ROTOR BLADE REMOVAL, IT WAS DISCOVERED THAT EACH OF THE BLADE BOLTS HAS RADIAL GOUGE M	ARKS AT THE BLADE TO HUB BUSHING LOCATIONS.  THE DAMAGE IS OUTSIDE THE AMM PERMITTED REPAIR LIMITS.  (REFERENCE: 39A6222	1300A286AB) MFG HAS BEEN CONTACTED AND PROVIDED THIS INFORMATION.  (NOTE:  THERE ARE ALSO TYPOGRAPHICAL ERRORS IN THE AM	M MILLIMETER TO INCHES CONVERSIONS IN FIGURE 2 INCH (MAXIMUM DAMAGE AND REPAIR DEPTHS).  FIG CALLS OUT (MM/IN) 0.02 / 0.	0080, SHOULD BE  0.0008.  (K)		2	G	7	2 	6U	3	T		R00002RD	E2NE				 
2006050900199	20060509	00199	SO  	2006	5	9	2006FA0000447    	1	20060226	G	3213	1180500	STRUT           			PIPER 	PA17  	PA17        	7101702	SO  	CONT  	A65   	A65*        	17003	SO  					LANDING GEAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	4879H	725  				17178				CHANGING SHOCK CORDS, DISCOLORATION OF INNER STRUT TUBE (LONGER ONE), REMOVED IT FROM OUTER TUBE (SHORTER ONE) OF INNER 	STRUT TUBES WAS CORRODED APPROX 50 PERCENT OF CIRCUM.  OTHER INNER STRUT HAD MULTIPLE CORROSION HOLES THROUGH METAL.  BO	TH SHORT TUBES (OUTER) SHOWED  ELONGATION AT ENDS INDICATING FLEXING/ BENDING OF ASSY DURING LANDING/TAKEOFF.  ONLY NEW 	BUNGEES KEPT GEAR FROM FINAL FAILURE,  RESULTANT GROUND LOOP.  BUNGEE CORDS, WHEN INSTALLED, COVER THIS AREA, USUALLY HA	VE A CLOTH OR ALUMINUM FAIRING OVER THEM.  DETECTION REQUIRES REMOVAL OF FAIRINGS AT A MINIMUM, AND REMOVAL OF BUNGEES T	O CLEARLY SEE OUTER TUBES CIRCUM.  NECESSARY TO DISASSEMBLE UNIT, VIEW INNER PIECE, OUTER PIECE SEPARATELY.   (K)	1	H	7	1 	3O	3	O		A805    	E205				 
2006050900237	20060509	00237	SO  	2006	5	9	2006FA0000448    	2	20060414	G	7322	6297032	FCU             			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03		2240 					1740067F			FOUND SHAFT AND LINKAGE EXCESSIVELY WORN.  HAD COMPLETE ASSEMBLY OVERHAULED.  (K)						1	H	7	1 	3O	3	O		3A21    	E5CE				 
2006051000130	20060510	00130	CE  	2006	5	10	2006FA0000449    	1	20060501	G	3320	6900042000	LIGHT           	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN	BURNED OUT      	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	11	800HA					BB220				FLUORESCENT LIGHT ASSY FAILED AND DISPERSED SMOKE IN CABIN. POWER SUPPLY GOT HOT AND DAMAGED ADJACENT INSULATION. LIGHT 	ASSY WAS REPLACED WITH FACTORY NEW.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006051000133	20060510	00133	CE  	2006	5	10	2006FA0000450    	1	20060501	G	3320	6900042000	LIGHT           	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN	BURNED OUT      	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	11	800HA					BB220				FLUORESCENT LIGHT ASSY FAILED AND DISPERSED SMOKE IN CABIN. POWER SUPPLY GOT HOT AND DAMAGED ADJACENT INSULATION. LIGHT 	ASSY WAS REPLACED WITH FACTORY NEW.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006050900241	20060509	00241	EA  	2006	5	9	2006FA0000451    	2	20060505	G	8530		VALVE           	LYC         	0360J2A     						LYC   	O360  	O360J2A     	41514	EA  						MALFUNCTIONED   	P			JWEG	R				AUTOROTATION            				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	09					L3963136A		L3963136A			NEW ENGINE IN NEW HELICOPTER. AFTER FLYING 1.5 HOURS, ENGINE WILL START POPPING AND BACKFIRING, CAUSING AN AUTOROTATION.	  MFG SAID IT'S A NORMAL MAINTENANCE ITEM TO REMOVE VALES AND REAM VALVE GUIDES.										3	O			E286				 
2006051200050	20060512	00050	EA  	2006	5	12	2006FA0000452    	2	20060425	G	7322	MA4SPA105135	CARBURETOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	UNSERVICEABLE   	D				O				OTHER                   				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		TX	TAXI/GRND HDL  	1			EA	17	2203T		800  			287916300				REF:  NM-02-47 DATED 9/30/02 AND CE-06-33R1, DATED 4/12/06.  ENGINE QUITS AT IDLE; IDLE SET AT 600, WILL DROP OFF AND QU	IT.  FUEL SOMETIMES DRAINS FROM CARB AFTER SHUTDOWN.  BOTH SYMPTONS MATCH THOSE IN NM-02-47.  (K)					1	L	7	1 	3O	3	O		2A13    	E274				 
2006051000238	20060510	00238	SO  	2006	5	10	2006FA0000453    	2	20060418	G	8530	AEC65385	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					RT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3149P	1301 	1301 			TH1470	810387R			NR 1 CYLINDER CRACKED AT SPARK PLUG HOLE.  (RT ENGINE) (K)						1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006051000239	20060510	00239	SO  	2006	5	10	2006FA0000454    	2	20060418	G	8530	AEC65385	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3149P	1301 	1301 			TH1470	810386R			NR 5 CYLINDER CRACKED AFT OF VALVES.  (STILL HAD GOOD COMPRESSION BUT COULD HEAR AIR) (LT ENGINE) (K)						1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006051200051	20060512	00051	SO  	2006	5	12	2006FA0000455    	2	20060418	G	8530	AEC65385	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3149P	1301 	1301 			TH1470	810386R			NR 2 CYLINDER COMPLETELY CRACKED ALL THE WAY AROUND AFT OF VALVES.  (LT ENGINE) (K)						1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006051000241	20060510	00241	SO  	2006	5	10	2006FA0000456    	2	20060418	G	8530	AEC65385	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3149P	1301 	1301 			TH1470	810386R			NR 6 CYLINDER CRACKED AFT OF VALVES.  (STILL HAD GOOD COMPRESSION COULD HEAR AIR.) (LT ENGINE) (K)						1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006051200058	20060512	00058	SO  	2006	5	12	2006FA0000457    	2	20060418	G	8530	AEC65385	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3149P	1301 	1301 			TH1470	810386R			NR 4 CYLINDER CRACKED AFT OF VALVES.  (STILL HAD GOOD COMPRESSION BUT COULD HEAR AIR) (LT ENGINE) (K)						1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006051200059	20060512	00059	CE  	2006	5	12	2006FA0000458    	1	20060419	G	2750	0400107146	CABLE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					FLAP CONT SYS	BROKEN          	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			NM	09	5494P	12872				15284959				ON FINAL, STUDENT SELECTED 30 DEGREE FLAPS, A LOUD POP WAS HEARD, RT FLAP CAME DOWN TO 30 DEGREES, NO MOVEMENT AT LT FLA	P. AIRCRAFT LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED SWAGGED BALL END OF CABLE, PN 0400107-146 BROKE FROM REMAIN	ING CABLE.  SUSPECT HIGH TIME AND CYCLES AS CONTRIBUTING FACTORS.  (K)				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006051200045	20060512	00045	SO  	2006	5	12	2006FA0000459    	1	20060419	G	5341		ATTACH FITTING  			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540*       	41532	EA  					FUSELAGE	OUT OF LIMITS   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	6719Z	3732 				252328				ATTACHMENT CONNECTIONS AT RT AND LT SIDES ARE BELOW MINIMUM SPECIFIED IN AD.  INSPECTION METHOD- ULTRASONIC.  (K)						1	L	7	1 	3O	3	O		2A10    	E295				 
2006051700236	20060517	00236	CE  	2006	5	17	2006FA0000460    	1	20060413	G	2840	S38521	GAUGE           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT FUEL TANK	FLUCTUATES      	B			BNZR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	19	5335G	50   				17281158				PART HAS A DEAD SPOT IN ITS TRAVEL CAUSING FUEL GAUGE TO FLUCTUATE RAPIDLY BETWEEN FULL AND EMPTY ALSO CAUSES LOW FUEL W	ARNING LIGHT TO FLASH CONTINUOUSLY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006051100182	20060511	00182	CE  	2006	5	11	2006FA0000461    	1	20060314	G	2842	S38522	SENSOR          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RT FUEL TANK	FLUCTUATES      	B			BNZR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	19	5335G	86   				17281158				PART HAS A DEAD SPOT IN ITS TRAVEL (NEAR FULL POSITION AT TOP OF TRAVEL) CAUSING FUEL GAUGE TO FLUCTUATE RAPIDLY BETWEEN	 FULL AND EMPTY, ALSO CAUSES LOW FUEL WARNING LIGHT TO FLASH CONTINUOUSLY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006051100184	20060511	00184		2006	5	11	2006FA0000462    	4	20060316	G	6113	05503214	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2G     	41508	EA  					SPINNER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	734QQ	292  				17269034	L3871627A			DURING ROUTINE PHASE INSPECTION FWD PROP BULKHEAD FOUND TO BE CRACKED NEAR SEVERAL MOUNTING BOLT HOLES.  HAVE SEEN THIS 	SEVERAL TIMES BEFORE.  SUSPECT DEFECT IN CURRENT MFG PROCESS.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006051200075	20060512	00075	CE  	2006	5	12	2006FA0000463    	1	20060427	G	3246	300257	WHEEL           			BEECH 	90    	C90A        	1152911	CE  										MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	164WS	199  			A5643	LJ1736				CRACKED IB WHEEL HALF CAUSING LOSS OF TIRE AIR PRESSURE.  NOTE:  THIS WAS A BRAND NEW PART ON A NEW AIRPLANE.  NOT AN OV	ERHAULED PART (SEE 5(I) AND 6(I)					1	L	7	2 	3T			RT	3A20    					 
2006051200133	20060512	00133	CE  	2006	5	12	2006FA0000464    	1	20060509	G	5741	130909B103	BOLT            			BEECH 	36    	B36TC       	1151609	CE  										WING ATTACH	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	7258E	142  				EA455				MAG PART INSP FOUND FWD WING ATTACH POINTS BOLT P/N 130909B103 AND 131790-3 WITH CRACKS.  THE BOLTS WERE INSTALLED NEW I	N FWD WING BOLT FITTINGS ON BEECH MODEL 36 SERIES AIRCRAFT S/N EA-455 ON 1/25/2002. THE LH UPPER BOLT (P/N 130909B103) W	AS REMOVED FOR IT'S FIRST 5 YEAR NDT INSPECTION AND WAS CRACKED AT THE HEAD RADIUS USING MAG PART NDT PROCESS. PART TOTA	L TIME 142 HRS SINCE INSTALLED. NO DAMAGE NOTED ON THE ASSOCIATED WING FITTING THAT WOULD INDICATE A CONTRIBUTING STRESS	 CONDITION. THE RT LOWER WING BOLT ON THE OPPOSITE SIDE OF THE A/C WAS ALSO CRACKED IN THE SAME LOCATION. THIS BOLT IS A	 DIFFERENT P/N (131790-3). BEECH TECH SUPPORT WAS GIVEN THE BOLTS & INFO FOR EVALUATION.	1	L	7	1 	3O				3A15    					 
2006051200134	20060512	00134	CE  	2006	5	12	2006FA0000465    	1	20060509	G	5741	1317903	BOLT            			BEECH 	36    	B36TC       	1151609	CE  										WING ATTACH	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	7258E	142  				EA455				MAG PART INSP FOUND FWD WING ATTACH POINTS BOLT P/N 130909B103 AND 131790-3 CRACKED.  BOLTS INSTALLED NEW IN FWD WING BO	LT FITTINGS ON BEECH MODEL 36 SER A/C S/N EA-455 ON 1/25/2002. THE LT UPPER BOLT (P/N 130909B103) REMOVED FOR FIRST 5 YE	AR NDT INSPECTION AND WAS CRACKED AT THE HEAD RADIUS. USED MAG PART INSP. TTSN 142 HRS. NO DAMAGE WAS NOTED ON THE ASSOC	IATED WING FITTING THAT WOULD INDICATE A CONTRIBUTING STRESS CONDITION. RT LOWER WING BOLT ON THE OPPOSITE SIDE OF THE A	/C ALSO CRACKED IN SAME LOCATION. THIS BOLT IS A DIFFERENT P/N (131790-3). BEECH TECH SUPPORT GIVEN BOLTS AND ALL THE IN	FO PERTINENT TO THESE PARTICULAR BOLTS FOR EVALUATION. OPERATING CONDITIONS OF THE AIRCRAFT ARE UNKNOWN.	1	L	7	1 	3O				3A15    					 
2006051100187	20060511	00187	EA  	2006	5	11	2006FA0000466    	2	20060410	G	8520		CONNECTING ROD  			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					RT ENGINE	BROKEN          	B			BOER	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	19	90JP					3078	L805848			CUSTOMER WAS ENROUTE TO MAINTENANCE SHOP TO GET ANNUAL INSPECTION, BOTH ENGINES OVERHAULED.  RT ENGINE CYLINDER NR 2 CON	NECTING ROD BROKE AT THE CRANKSHAFT ATTACHMENT CAUSING MAJOR DAMAGE TO THE CAMSHAFT, AND CRANKCASE BREAKING OPEN IN SEVE	RAL PLACES AROUND THE FRONT PART OF THE ENGINES.  (K)				1	H	7	2 	3O	3	O		6A1     	1E4				 
2006051700237	20060517	00237	SO  	2006	5	17	2006FA0000467    	2	20060410	G	8530	631397	CYLINDER        			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CRACKED         	C			BOER	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	984MW					340A0070	521294			AT 400 HR TSO FOUND CYLINDER NR 4 CRACKED AT THE HEAD 5 FINS BACK TOWARD THE BARREL FROM THE TOP SPARK PLUG.  CRACK GOES	 FROM THE EXHAUST VALVE SEAT TO THE TOP SPARK PLUG HOLE ON THE INSIDE OF THE CYLINDER.  AD 04-08-10 DID NOT APPLY BY CLY	.  SN 13516-4 AND CODE A STAMPED ON THE BOSS FLANGE.  (K)				1	L	7	2 	3O	3	O		3A25    	E8CE				 
2006051700217	20060517	00217		2006	5	17	2006FA0000468    	4	20060419	G	3425	NSD360	HSI             			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	DEACTIVATED     	B			F3OR	O				OTHER                   				G			MULTIPLE FAILURE          			NR	NOT REPORTED   	1			SO	03	594HS					340A0440				PILOT REPORTED HSI WAS INOPERATIVE AND SUSPECTED A PLUG WAS OFF.  VISUAL INSPECTION REVEALED THAT THE PUG TO THE HSI, AN	D THE VACUUM HOSE HAD BOTH BEEN PULLED OFF BY THE AC CONTROL WHEEL.  THE HOSES AND WIRING HARNESS HAD BEEN INCORRECTLY R	OUTED AROUND THE CONTROL WHEEL.  THE AC HAD VERY LITTLE ROOM BEHIND THE INSTRUMENT PANEL, AND THE CORRECT ROUTING OF HOS	ES AND HARNESSES IS CRITICAL TO FLIGHT SAFETY.  THE CONTROLS WERE FREE AFTER THE HOSE AND HARNESS CAME OFF THE PILOTS HS	I. WITH MORE AC BEING UPGRADED WITH NEWER AVIONICS AND INSTRUMENTS, INSPECTIONS OF HARNESSES AND HOSES BEHIND THE INSTRU	MENT PANEL IS AN AREA THAT REQUIRES INCREASED VIGILANCE.  (K)	1	L	7	2 	3O	3	O		3A25    	E8CE				 
2006051200138	20060512	00138	CE  	2006	5	12	2006FA0000469    	1	20060426	G	8100	4656809004	TURBOCHARGER    			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					ENGINE	LEAKING         	B			WS9R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	4773P					P21000102				OIL LEAKING OUT FROM JOINT IN CENTER OF TURBO. FIRST RUN ON OVERHAULED UNIT JUST INSTALLED ON AIRCRAFT.  (K)						1	H	7	1 	3O	3	O		3A21    	E8CE				 
2006080700096	20060807	00096		2006	8	7	2006FA0000470    	1	20060404	G	8011	X13041	BEARING         								CONT  	O520  	TSIO520C    	17040	SO  					STARTER	FAILED          	B			R04R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04		1    								WHILE REMOVING THE STARTER FOR MAINTENANCE, THE STARTER ADAPTER WORM SHAFT ROLLER BEARING RETAINER CAGE HALF WAS FOUND S	TUCK TO THE STARTER FLANGE.  ALL THE ROLLER BEARING BALLS WERE STILL IN THEIR RACES BUT BLUISH IN COLOR.  AFTER DISASSEM	BLING THE ADAPTER, THE INNER HALF AND SMALLER PIECES OF THE CAGE WERE FOUND IN THE LOWER RECESSES OF THE  ADAPTER HOUSIN	G. FORTUNATELY, NONE WAS SUSPECTED TO HAVE ENTERED THE ENGINE SUMP. IT WAS SUSPECTED THAT THE STARTER RELAY REMAINED ENG	AGED AND THE STARTER WAS ENERGIZED DURING ONE OR MORE GROUND RUNS.							3	O			E8CE				 
2006061300210	20060613	00210	CE  	2006	6	13	2006FA0000471    	1	20060412	G	3246	300257	WHEEL HALF      	BFGOODRICH  		BEECH 	90    	C90A        	1152911	CE  										LT MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	164WS	177  			A5665	LJ1736				LEFT MAIN WHEEL (INBOARD HALF) FOUND CRACKED.  PROBLEM SHOWED ITSELF DUE TO WHEEL/TIRE ASSY SUFFERING A SLOW LEAK OF AIR	 PRESSURE.  THIS IS NOT THE SAME PROBLEM REPORTED FOR THIS AIRCRAFT ON 4/27/2006.  THIS IS A PREVIOUS OCCURRENCE ON THE 	OTHER SIDE.  BOTH MAIN WHEELS HAVE NOW BEEN CHANGED.				1	L	7	2 	3T			RT	3A20    					 
2006061300234	20060613	00234	CE  	2006	6	13	2006FA0000472    	1	20060502	G	2842	99144272	FLOAT SWITCH    			CESSNA	560   	560XL       	2076702	CE  										FUEL SYS	INOPERATIVE     	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	09	635QS	2291 				5605358				THE RIGHT LOW FUEL LEVEL SYSTEM WAS INOPERATIVE.  REMOVED SWITCH AND FOUND SIGNS OF ARCING ON THE TOP SIDE OF THE SWITCH	.  TROUBLESHOT FURTHER AND FOUND THE PC BOARD WAS DEFECTIVE.  IT IS NOT KNOWN IF THE SWITCH DAMAGED THE PC BOARD.  THIS 	IS NOT THE FIRST TIME WE HAVE SEEN A DEFECTIVE FLOAT SWITCH WITH SIGNS OF ARCING, HOWEVER, IT IS THE FIRST TIME THAT A D	AMAGED PC BOARD WAS ASSOCIATED WITH IT.  IT WAS NOTED THAT WHEN THE FLOAT SWITCH IS IN THE 'HIGH FUEL LEVEL' POSITION TH	E CONTACT SURFACES ARE ALIGNED.  WHEN THE SWITCH IS IN THE 'LOW FUEL LEVEL' THE CONTACTS ARE NEARLY COMPLETELY MISALIGNE	D.	2	L	7	2 	4F			RT	A22CE   					 
2006051100301	20060511	00301	CE  	2006	5	11	2006FA0000473    	1	20060510	G	2910	2607003453	HYDRAULIC LINE  			LEAR  	35    	35A         	5170602	CE  										REAR EQUIP BAY	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	13	222BG					35A448				PRE-FLIGHT FOR SECOND LEG OF FLIGHT CREW REPORTED HYDRAULIC FLUID DRIPPING OUT OF REAR EQUIPMENT BAY. INSPECTION REVEALE	D THAT THE HYDRAULIC PRESSURE LINE HAD CHAFED THROUGH AND WAS LEAKING FLUID. INSTALLED NEW LINE. COMPLIED WITH PRESSURE 	CHECK OF SYSTEM WITH NO ADDITIONAL LEAKS NOTED. CHECKED ROUTING OF LINE AND INSTALLED CHAFE MATERIAL WHERE NEEDED. PART 	HOURS OR CYCLES UNKNOWN.			2	L	7	2 	4F				A10CE   					 
2006051800261	20060518	00261	EU  	2006	5	18	2006FA0000474    	1	20060510	G	3246	AHA1814	WHEEL HALF      			BRAERO	DH125 	BAE125800A  	1500285	EU  										LANDING GEAR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	2QG					NA0467				DURING ROUTINE TIRE CHANGE AND EDDY CURRENT INSPECTION OF DUNLOP MAIN WHEEL HALF AND FLANGE. EDDY CURRENT INSPECTION REV	EALED TWO CRACKS WHICH RADIATED OUT FROM WHEEL TIE BOLT HOLE. BOTH CRACKS WERE APPROMIXATELY .050 INCHES IN LENGTH. PART	 WAS REJECTED AND REPLACED WITH NEW PART. WHEEL PART NO. AHA1814 FLANGE PART NO.AH43949. PART HOURS OR CYCLES UNKNOWN.				2	L	7	2 	4F			RT	A3EU    					 
2006051800262	20060518	00262	CE  	2006	5	18	2006FA0000475    	1	20060510	G	2730	083200054	HINGE BRACKET   	CESSNA      		CESSNA	421   	421B        	2076014	CE  										RT ELEVATOR	ELONGATED       	B				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			WP	23	1944G	8307 				421B0844				CUSTOMER REPORTED VIBRATION AT HIGH SPEEDS. INSPECTED AIRCRAFT AND FOUND CENTER ELEVATOR HINGE IB AND OB BRACKETS ELONGA	TED ON THE RT ELEVATOR.   INSTALLED MFG SERVICE KIT SK421-130B REPLACING ALUMINUM ELEVATOR HINGE BRACKETS WITH STAINLESS	 STEEL BRACKETS.				1	L	7	2 	3O				A7CE    					 
2006051900242	20060519	00242	WP  	2006	5	19	2006FA0000476    	2	20060426	G	7210	8687813	GEAR            			MTSBSI	MU2   	MU2B36A     	5780413	CE  	GARRTT	TPE331	TPE33110T   	 	WP  					LT ENGINE GRBOX	CRACKED         	B			IZ2R	O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			SW	15	777LP					719SA				PILOT REPORTED DURING CRUISE LEVEL FLIGHT FEELING A SUDDEN VIBRATION AND HEARING A SCREAMING NOISE FROM THE LT ENGINE.  	PILOT THEN NOTICED TORQUE INDICATION ON LT ENGINE INDICATING 120 PERCENT WITH NO YAW INDICATED OR NOTICED BY PILOT. WHIL	E RETARDING LT POWER LEVER TO REDUCE TORQUE THE LT ENGINE SHUTDOWN UNCOMMANDED.  ENGINE NTS SYSTEM FUNCTIONED NORMALLY A	ND AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE.  UPON ENGINE ASSEMBLY A 2 INCH PIECE OF THE BULL GEAR OUTER RIM WAS LAY	ING IN THE BOTTOM OF THE ACCESSORY HOUSING.  INSPECTION OF THE BULL GEAR REVEALED THE MISSING SECTION AND AN APPROX 4 IN	CH CRACK IN THE HUB AREA WHICH CAUSED LOSS OF DRIVE TO THE PROPELLER SHAFT.	1	H	7	2 	3T	4	T		A10SW   	E4WE				 
2006051700208	20060517	00208	EA  	2006	5	17	2006FA0000478    	2	20060501	G	7414	S6LSC21BL5005162	MAGNETO         			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  					ENGINE	DISINTEGRATED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	7339Z		740  			253289	L1154840			MAGNETO WAS REMOVED FROM ENGINE FOR ROUTINE MAINTENANCE INSPECTION.  THREADS ON MAGNETO SHAFT AND NUT WERE COMPLETELY ST	RIPPED.  SLOT IN SHAFT FOR WOODRUFF KEY WAS WALLOWED OUT.  COTTER KEY WHICH RETAINED NUT TO SHAFT WAS STILL IN PLACE. AT	 TIME OF REMOVAL ENGINE WAS OPERATING NORMALLY.  ONLY THE MAG BUSHINGS AND RETAINER WERE HOLDING THE IMPULSE COUPLING IN	 PLACE.  THE DRIVE SHAFT AND OR THE WOODRUFF WERE DEFECTIVE AT THE TIME OF MANUFACTURE.  THIS CONDITION IF UNDETECTED WI	LL LEAD TO COMPLETE ENGINE FAILURE.  (K)		1	L	7	1 	3O	3	O		2A10    	E295				 
2006051800132	20060518	00132	CE  	2006	5	18	2006FA0000479    	1	20060508	G	2400	70008840	CIRCUIT BREAKER 			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	TRIPPED         	C				B				EMER. DESCENT           				H	G		ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          		CR	CRUISE         	1			SW	11	242MT	10053				621				(ELECTRICAL ANOMALY), LT AND RT ESSENTIAL (A) CIRCUIT BREAKERS DEPLOYED.  ALL EFIS WENT DARK.  YAW DAMP AND AUTO PILOT D	ISENGAGED.  LOST ALL NAV AND COMM. RADIOS, LOST ANNUNCIATOR PANEL LIGHTS.  MAY HAVE LOST AIRSPEED INDICATORS AND FUEL CO	MPUTERS.  LOST BOTH N 1S .  BOTH ITTS, DC AND AC ELECTRICAL INDICATORS FUNCTIONED NORMALLY AND INDICATED NORMAL ELECTR	ICAL SYSTEM CONDITION.  GEAR, FLAPS, SPOILERS, TRIMS, TRS ALL FUNCTIONED NORMALLY.  TR ARM AND DEPLOY LIGHTS DID NOT WO	RK.  		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006051600183	20060516	00183		2006	5	16	2006FA0000480    	4	20060503	G	2215		ROLL SERVO      			GULSTM	112   	112A        	7630302	SW  	LYC   	O360  	IO360A1A    	41514	EA  					AUTO PILOT SYS	MISINSTALLED    	B			TP4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	1346J					346				THE ROLL SERVO WAS INSTALLED AND RIGGED INCORRECTLY, THE SET WAS NOT TIGHT ON THE BRIDLE CABLE PIN AND THE BRIDLE CABLE 	WAS WRAPPED ON THE CAPSTAN INCORRECTLY.  THE INCORRECT INSTALLATION IN CONJUNCTION WITH THE LOOSE SET SCREW ALLOWED THE 	BRIDLE CABLE LOCATING PIN TO PULL OUT OF THE SERVO CAPSTAN.  THE LOCATING PIN LOCKED THE AILERONS AT FULL DEFLECTION AGA	INST THE CAPSTAN GUARD.  THIS CONDITION OCCURRED ON THE GROUND, IN FLIGHT THIS CONDITION WOULD VERY LIKELY RESULT IN AN 	ACCIDENT.  RECOMMEND ROLL SERVO INSTALLATIONS BE INSPECTED FOR PROPER INSTALLATION AND RIGGING.  THE CONDITION HAS BEEN 	CORRECTED IAW FLIGHT DOCUMENT AK 1056.  (K)	1	L	7	1 	3O	3	O		A12SO   	1E10				 
2006051700209	20060517	00209	SO  	2006	5	17	2006FA0000481    	2	20060425	G	8530	646743	PISTON          			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360SB   	 	SO  					ENGINE	ERODED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	43PG	700  				252019				THE OIL CONTROL RING LANDS ON PISTON SEVERLY ERRODED AT PISTON PIN HOLE, BOTH SIDES OF PISTON.  THIS IS THE 13 TH PISTON	 THAT WE HAVE SEEN THIS ON, IN OUR ENGINE SHOP.  SC MODIFICATIONS, HAS 12 OF THEM, HAVE SAME PROBLEM.  HAVE ONE TO SHOW.	 (K)				1	L	7	1 	3O	3	O		2A3     	E9CE				 
2006051600210	20060516	00210		2006	5	16	2006FA0000482    	4	20060501	G	2562	EBC502	ELT             			DIAMON	DA20  	DA20A1      	2990000	GL  										BAGGAGE COMPT	MISINSTALLED    	B			UKJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	71LV					10070				WHEN REMOVING ELT FROM AIRCRAFT TO REPLACE ELT BATTERY, FOUND THAT SOMEONE HAD PUT THE ELT IN BACKWARDS.  THE DIRECTION 	OF FLIGHT ARROW WAS POINTING AFT.  THIS INSTALLATION IS LOCATED IN THE BAGGAGE COMPT AND THE PILOT CAN SLIDE IT OUT OF I	TS MOUNT AND REINSTALLED IT BACKWARDS.  (K)				1	L	7	1 	3O			NT	TA4CH   					 
2007051100155	20070511	00155	SW  	2007	5	11	2006FA0000483    	1	20060428	G	6210	3G62200A251	BOLT            			AGUSTA	AB139 	AB139       	0260110	SW  										MAIN ROTOR	GOUGED          	B			LWXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	140HS	8    				31036				UPON RECEIPT OF THE AIRCRAFT, THE MAIN ROTOR BLADE BOLTS WERE REMOVED FOR INSPECTION.  IT WAS DISCOVERED THAT ONE BLADE 	BOLTS HAS A RADIAL GOUGE MARK AT THE LOWER BLADE TO HUB BUSHING LOCATION.  THE DAMAGE IS OUTSIDE THE AMM PERMITTED REPAI	R LIMITS.  THE AC TT IS APPROXIMATELY 58.4 HOURS.  ALL OF THE BLADE BOLTS WERE PREVIOUSLY CHANGED APPROX 8.5 HOURS PRIOR	 TO COMING TO REPAIR STATION.  REF: 39A62221300A286AB, MFG HAS BEEN CONTACTED AND PROVIDED THIS INFORMATION.  (K)			2	G	7	2 	6U				R00002RD					 
2006051800181	20060518	00181	CE  	2006	5	18	2006FA0000484    	1	20060223	G	5743	5041000201	TRUNNION        			CESSNA	402   	402B        	207590P	CE  										LT WING	BROKEN          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	19	400AR	2300 				402B0338				ON FEBRUARY 23RD, 2006, PILOT WAS OPERATING AC, VISUAL FLIGHT RULES PREVAILED.  UPON LANDING, THERE WAS A FAILURE OF THE	 TRUNNION (P/N 5041000-201) ON THE LT MAIN LANDING GEAR STRUT CAUSING THE COLLAPSE OF THE LT MAIN LANDING GEAR.  THE AIR	CRAFT TURNED 180 DEGREES TO THE LT AND SLID OFF THE LT SIDE OF RUNWAY 27L, CAUSING DAMAGE TO THE LT WING, HORIZONTAL STA	BILIZER AND LT PROPELLER.			1	L	7	2 	3O				A7CE    					 
2006051600211	20060516	00211	CE  	2006	5	16	2006FA0000485    	1	20060511	G	2742	071250013	JACKSCREW       			CESSNA	185   	A185F       	2072821	CE  										TRIM SYS	STRIPPED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	27532	8672 				18503688				MAINTENANCE PERSONNEL WERE ADVISED BY THE PILOT THE HORIZONTAL STABILIZER TRIM QUIT WORKING.  INSPECTION FOUND THE BARRE	L SIDE OF THE TRIM SCREW JACK HAD STRIPPED OUT.  THE SYSTEM INCLUDES 2 TRIM SCREW JACKS THE OTHER TRIM SCREW JACK TOOK A	LL OF THE LOAD AND JAMMED UP.  INSPECTION OF SECOND TRIM SCREW JACK BARREL FOUND THE UPPER THIRD OF THE THREADS WERE STR	IPPED IN THE SECOND TRIM SCREW BARREL.  MFG DOES NOT SPECIFY ANY INSPECTION CRITERIA FOR WEAR OF THE JACK SCREW THREADS 	OR THE BARREL THREADS.  RECOMMEND EITHER MANDATORY INSPECTION CRITERIA FOR THE BARRELS AND THREADS OR AN AIRWORTHINESS D	IRECTIVE TO PRECLUDE LOSS OF CONTROL OF THE TAIL OF THE AIRCRAFT.  (K)	1	H	7	1 	3O				3A24    					 
2006051800263	20060518	00263	CE  	2006	5	18	2006FA0000486    	1	20060511	G	2821	331996	GASKET          			BEECH 	58    	58          	1152740	CE  										WHEEL WELL	SWOLLEN         	D				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			WP	15	2335R					TH1835				THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OB WHILE IN FLIGHT. THE PILOT WA	S UNAWARE OF THE LOSS OF FUEL UNTIL AFTER LANDING.  APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. 	WAS TOLD BY MFG TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF	 THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME.			1	L	7	2 	3O				3A16    					 
2006051800265	20060518	00265	CE  	2006	5	18	2006FA0000487    	1	20060511	G	2821	331996	GASKET          			BEECH 	58    	58          	1152740	CE  										WHEEL WELL	SWOLLEN         	D				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			WP	15	2335R					TH1835				THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OVERBOARD WHILE IN FLIGHT. THE P	ILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER HE LANDED.  APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS O	F 100LL. WAS TOLD BY MFG TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SW	ELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME.			1	L	7	2 	3O				3A16    					 
2006051800267	20060518	00267	CE  	2006	5	18	2006FA0000488    	1	20060511	G	2821	331996	GASKET          			BEECH 	58    	58          	1152740	CE  										WHEEL WELL	SWOLLEN         	D				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			WP	15	2335R					TH1835				THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OVERBOARD WHILE IN FLIGHT. THE P	ILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER HE LANDED. APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF	 100LL. WAS TOLD BY RAYTHEON TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING TH	E SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME.			1	L	7	2 	3O				3A16    					 
2006051800272	20060518	00272	SO  	2006	5	18	2006FA0000489    	2	20060503	G	8530	AEC631397	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  	MCAULY	3A32C	D3A32C*     	GL  	ENGINE	SEPARATED       	B			MW8R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	8277D					E2798	G675825	930397		NR 2 CYLINDER HEAD (SN 2253724) SEPARATION WITH 170.2 TOTAL SINCE NEW.  NR 6 CYLINDER HEAD (SN 223899) SEPARATION WITH 1	71.7 TOTAL SINCE NEW.  AD 2004-08-10 N/A TO SN.  RECOMMEND ALL SN`S APPLICABLE AND REOCCURING CHECKS FOR ECI CYLINDERS U	SING M 91-6.  (K)				1	L	7	1 	3O	3	O		3A15    	E3SO	5	C	P21EA	 
2006051700213	20060517	00213	SW  	2006	5	17	2006FA0000490    	1	20060302	G	2913	5001908	COUPLING        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HYD PUMP	SEPARATED       	B			YJ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	37AJ				00010491	1877				HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO SEPARATE FROM DRIVE GEAR SHAFT.  MFG SHOULD	 CHECK THE STRENGTH OF BRAZE AFTER WELDING.  WHEN THIS COUPLING FAILS, LOSS OF ROTOR TACH OCCURS.  (K)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006051800279	20060518	00279	SW  	2006	5	18	2006FA0000491    	1	20060302	G	2913	5001908	COUPLING        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYD PUMP	FAILED          	B			XJ2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	59479	196  			99100424	1194				HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO BECOME LOOSE.  MFG SHOULD CHECK THE STRENGT	H OF BRAZE AFTER WELDING.  WHEN THIS COUPLING FAILS, LOST OF ROTOR TACH OCCURS.  (K)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006051700214	20060517	00214	SW  	2006	5	17	2006FA0000492    	1	20060302	G	2913	5001908	COUPLING        			BELL  	206   	206B        	1181511	SW  										HYD PUMP	FAILED          	B			XJ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	158H				00010463	2974				HYDRAULIC PUMP TACH DRIVE COUPLING BRAZE WELDING FAILED, CAUSING COUPLING TO SEPARATE FROM DRIVE GEAR SHAFT.  MFG SHOULD	 CHECK THE STRENGTH OF BRAZE AFTER WELDING.  WHEN THIS COUPLING FAILS, LOSS OF ROTOR TACH OCCURS.  (K)					1	G	7	1 	3U				H2SW    					 
2006051900250	20060519	00250	CE  	2006	5	19	2006FA0000493    	1	20060504	G	5740	50110231	FITTING         			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT WING	CRACKED         	B			AIHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	352TS	3751 				4140352				DURING ANNUAL INSP FOUND LT STUB WING AFT SPAR, UPPER FITTING CRACKED AT OB BOLT HOLE.  FOUND NO CORROSION OR STRESS IN 	SURROUNDING AREAS.  SUSPECT BOLT WAS OVERTORQUED.  (K)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2006051700230	20060517	00230	CE  	2006	5	17	2006FA0000494    	1	20060426	G	7160		AIR BOX         			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	MAINT ERROR     	B			BIIR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	21	65764	1443 	231  			17275868	RL3482936A			AC HAD 180 HP ENGINE INSTALLED ON 7/10/96.  AC HAS 1443.5 HOURS SINCE INSTALLATION.  OPERATOR NOTED 2300 RPM AT CRUISE, 	FULL THROTTLE.  INSPECTED AND FOUND AIRBOX STILL HAD THE HOLE SIZE FOR 160 HP ENGINE.  AIRBOX HAD NOT BEEN MODIFIED IAW 	STC. IT HAD BEEN REPAIRED ON SEVERAL OCCASIONS SINCE ENGINE INSTALLED AND HAD NOT BEEN FOUND.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2006051700231	20060517	00231	EA  	2006	5	17	2006FA0000495    	2	20060509	G	8550	CH481101	OIL FILTER      			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C    	41514	EA  					ENGINE	LEAKING         	B			JULR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	01	1663H					28R7737007	RL723851A			PILOT REPORTED OIL SPOTS ON HANGAR FLOOR.  ENGINE WAS WASHED AND GROUND RUN FOR LEAK CHECK.  INSPECTED ENGINE AFTER ENGI	NE RUN AND FOUND OIL ON BOTTOM SIDE OF OIL FILTER.  FURTHER INSPECTION OF THE OIL LEAK REVEALED THAT THE OIL WAS LEAKING	 FROM THE HEX NUT ON THE BACK OF THE FILTER.  (K)				1	L	7	1 	3O	3	O		2A13    	1E10				 
2006051900251	20060519	00251	EU  	2006	5	19	2006FA0000496    	1	20060505	G	6210	355A11002011	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	5806H					1935				CRACK FOUND ON LOWER SURFACE OF MAIN ROTOR BLADE NEAR STATION 1000.  EXACT CAUSE OF CRACK WOULD ONLY BE SPECULATIVE.  (K	)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006051800069	20060518	00069	CE  	2006	5	18	2006FA0000497    	1	20060509	G	5310	551124914S	THRESHOLD       			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					CABIN DOOR FRAME	CRACKED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	318QS	8377 				5600418				CABIN ENTRY THRESHOLD CRACKED AT AFT STEP ATTACH BOLT HOLE.  COMBINATION OF BOLT HOLE LOCATED IN RADIUS OF FRAME AND MAT	ERIAL THICKNESS NOT SUFFICIENT TO SUPPORT WEIGHT OF PERSON ENTERING OR EXITING AIRCRAFT.  RECOMEND STRENGTHING STRUCTURE	, USING THICKER METAL.  NOTE: HAVE FOUND THESE CRACKS ON MFG INSPECTION PHASE 5.  APPROX 75 PERCENT OF AIRCRAFT INSPECTE	D ARE FOUND CRACKED.  (K)			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006051800038	20060518	00038	SO  	2006	5	18	2006FA0000498    	2	20060511	G	8530	AEC631397	CYLINDER        			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			GL	13	710US	330  				4140083	519719			DURING DECENT TO AIRPORT, PILOT REPORTED RT ENGINE STARTED HAVING EXCESSIVE VIBRATION.  NO OTHER MAJOR ENGINE INDICATION	S WERE NOTED.  AFTER LANDING, A MAGNETO CHECK WAS CONDUCTED AND NO DESCREPANCIES WERE FOUND.  UPON REMOVAL OF COWLING, R	T ENGINE NR 6 CYLINDER WAS FOUND TO HAVE CRACKED AROUND THE CIRCUMFERENCE OF CYLINDER HEAD AT THE NR 9 AND 10 COOLING FI	N, COMPLETELY SEPARATING THE CYLINDER HEAD FROM THE BARREL AT THE VERY TOP OF STEEL CYLINDER BARREL.  AFTER RESEARCHING 	AD, AMENDMENT, THE CYLINDER ASSY WAS FOUND NOT TO APPLY DUE TO S/N OF CYLINDER AND THE PRESENCE OF THE (A) STAMPED ON TH	E ROCKER BOX FLANGE.  (K)	1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2006051700206	20060517	00206	SO  	2006	5	17	2006FA0000499    	2	20060411	G	8530	641916A1	CYLINDER        			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	2566Y		1432 			17249866	27538			NR 1 CYLINDER WAS REMOVED DUE TO A CRACK .75 AROUND STEEL BARREL.  IT APPEARS THAT AN OIL CONTROL RING BROKE AND EVENTUA	LLY DESTROYED THE PISTON AND JAMMED BETWEEN THE PISTON AND CYLINDER.  TT ON THE ENGINE IS 4156.9 HRS.  SMOH IS 1432.9 HR	S, THE CYLINDER WAS LAST REMOVED AT 598.4 HOURS FOR HONE AND NEW RINGS.  TT ON CYLINDERS, UNKNOWN.  AIRCRAFT WAS ANNUALE	D 1.1 HRS PRIOR.  THE OIL ANALYSIS PERFORMED AT ANNUAL WAS NORMAL AND ALL READINGS/RESULT WERE LOWER THAN THAT OF PREVIO	US AVIATION LABORATORY SAMPLES WHICH WERE ALSO NORMAL.  ENGINE WILL BE TORN DOWN FOR INTERNAL INSPECTION.  (K)		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2006051900243	20060519	00243	SW  	2006	5	19	2006FA0000500    	1	20060428	G	5711	271L	SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	88237					74474				DURING WING RECOVER, FOUND LT WING FRONT SPAR WITH A CRACK ORIGINATING AT THE BUTT END, FOLLOWING THE WOOD GRAIN OB THRO	UGH UPPER ATTACH BRACKET HOLES AND EXTENDING APPROXIMATELY 1 INCH PAST IB MOST FUEL TANK SUPPORT BRACKET, UPPER HOLE.  N	O EVIDENCE OF CRACKS IN BUTT ENG SPAR DOUBLERS.  TOTAL LENGTH OF CRACK APPROX 8.3750 INCHES.  NO RECOMMENDATION FOR CAUS	E OR RECURRENCE.  (K)			1	H	7	1 	3O	3	O	NC	A759    	E274				 
2006051800138	20060518	00138	NM  	2006	5	18	2006FA0000501    	1	20060516	G	7921	900D3658501103	OIL COOLER      			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					ENG OIL SYS	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	11	902PD	589  				9000084				FOUND WETTING OIL MAIN TRANSMISSION/ENGINE OIL COOLER CORE. REMOVED AND SENT OUT FOR EVALUATION. COOLER FOUND TO HAVE IN	TERNAL CORROSION THAT CAUSED MATERIAL LOSS AND SUBSEQUENT LEAKING. REPLACED COOLER WITH NEW. LEAK CHECK WAS SATISFACTORY	.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006051800266	20060518	00266	SO  	2006	5	18	2006FA0000502    	1	20060503	G	2910	1159SCH5019	SHUTOFF VALVE   			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					LT & RT WING	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	130GV	2943 				630				DURING A SCHEDULED INSPECTION, OPERATIONAL CHECK OF THE AILERON HARD OVER PROTECTION TEST.  BOTH LT AND RT AILERON HYD S	HUT OFF CIRCUIT BREAKERS POPPED.  REPLACED RT AILERON , LT HYD SYSTEM SHUTOFF VALVE AND LT AILERON, LT HYD SYS SHUTOFF V	ALVE.  (K)				2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2006051800230	20060518	00230	NM  	2006	5	18	2006FA0000503    	1	20060516	G	6320	51003400	HOSE            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAINTRANSMISSION	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	11	902PD	489  				9000084				DISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAI	DING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY, P/N 900D3409526-105.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006051800256	20060518	00256	GL  	2006	5	18	2006FA0000504    	1	20060508	G	5524	10146008	RIVET           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ELEVATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	5226R					1767				BOTH LT AND RT ELEVATOR OB HINGE BRACKETS ARE RIVETED TO THE ELEVATORS WITH FLUSH HEAD BLIND RIVETS AND FLUSH HEAD SOLID	 DRIVE RIVETS.  AT 121 HOURS TT.  DURING A 100 HOUR INSPECTION, THE RIVETS ON THE OB HINGE BRACKETS, LT AND RT ELEVATORS	, WERE FOUND TO BE SMOKING- STREAKS OF BLACK POWDER TRAILING BEHIND THEM, AND THE PAINT AROUND THE RIVET HEADS BROKEN.  	RECOMMEND MFG DESIGN FIND A SECURE WAY TO HOLD THE ELEVATOR HINGE BRACKETS TO THE ELEVATORS SUCH AS THROUGH USE OF SOLID	-DRIVEN RIVETS INSTEAD OF BLIND RIVETS.  (K)		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006051800196	20060518	00196	NM  	2006	5	18	2006FA0000506    	1	20060516	G	6320	51003400	HOSE            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MAIN TRANSMSN	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	11	902PD	489  				9000084				DISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAI	DING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY.  P/N 900D3409526-105	.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006051800057	20060518	00057	NM  	2006	5	18	2006FA0000507    	1	20060516	G	6220	900R1103001113	BEAM            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MR HUB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	902PD	1898 	100  			9000084				DURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MAIN	TENANCE MANUAL. REPLACED WITH NEW FLEXBEAM.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006051800246	20060518	00246	NM  	2006	5	18	2006FA0000508    	1	20060516	G	6220	900R1103001113	BEAM            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					MR HUB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	902PD	1898 	100  			9000084				DURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MM. 	REPLACED WITH NEW FLEXBEAM.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006053000175	20060530	00175	SW  	2006	5	30	2006FA0000509    	1	20060513	G	6720	500N72205	CABLE           			HUGHES	500N  	500N        	3027374	SW  										TAILBOOM	SEVERED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	520HB					LN029				DURING PRACTICE AUTOROTATIONS, PILOT FELT A CHANGE IN THE ANTI-TORQUE PEDALS. AFTER TOUCHDOWN HE ATTEMPTED TO RAISE THE 	COLLECTIVE AND THE HELICOPTER BEGIN TO SPIN, HE LOWERED THE COLLECTIVE AND SHUTDOWN. NO DAMAGE WAS NOTED. THE ROTATING C	ONE CONTROL CABLE WAS FOUND TO HAVE A CLEAN BREAK. THE OTHER CABLES WERE INSPECTED AND FOUND TO BE OK. P/N 500N7220-05 W	AS INSPECTED AT THE LAST 300HR INSPECTION 232.8 HOURS AGO, AND WAS FOUND TO BE AIRWORTHY. THIS PART DOES NOT HAVE A SERV	ICE LIFE LIMIT FROM THE MFGR. RECOMMEND A SERVICE LIFE OF 1000 HOURS.		1	G	7	1 	3U			NC	H3WE    					 
2006052200172	20060522	00172	SO  	2006	5	22	2006FA0000510    	1	20060421	G	3220	402940	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  										NOSE GEAR	BROKEN          	B			NI1R	K				NONE                    				O			OTHER                     			LD	LANDING        	1			CE	03	554PC					4496073				NOSE GEAR COLLAPSED ON TOUCHDOWN.  MAINS TOUCHED FIRST THEN NOSE.   2 COMPONENTS THAT ARE DAMAGED IN NOSE GEAR RETRACT/E	XTEND SYS.  W/O DISASSEMBLING LINKAGE, VISUAL EVIDENCE, BOLT CONNECTING UPPER DRAG LINK TO LWR DRAG LINK FAILED DUE TO P	OSSIBLE OVERLOAD CONDITION.  (FRACTURED END OF BOLT IS BRIGHT AND SHINNY, INDICATING AN INSTANTANEOUS FAILURE).  ONE HAL	F OF THAT BOLT, WASHER, NUT AND COTTER PIN IS STILL INSERTED IN JOINT.  OTHER DAMAGED COMPONENT IS BOLT THAT DOWNLOCK HO	OK ENGAGES, BOLT IS BENT IN SUCH A WAY AS TO INDICATE IT WAS DAMAGED AS A RESULT OF NOSE GEAR COLLAPSE.  AFTER UPPER AND	 LWR DRAG LINK ASSEMBLIES HAVE BEEN REMOVED SENT TO MFG FOR FURTHER INSP AND ANALYSIS.	1	L	7	2 	3O				A19S0   					 
2006052200142	20060522	00142	CE  	2006	5	22	2006FA0000511    	1	20060504	G	7920	9696001123	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					ENGINE	CHAFED          	D				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			EA	13	251P					TH2139	686637			2 LINES CHAFFING TOGETHER.  NEED TO SEPARATE THE LINES.  LOW OIL PSI IN FLIGHT.  PILOT SHUTOFF ENGINE IN FLIGHT AND LAND	ED THE AIRCRAFT.  REMOVED AND REPLACED THE LINE.  (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006052200144	20060522	00144		2006	5	22	2006FA0000512    	4	20060421	G	3425	70000006000	FLIGHT DIR      			CIRRUS	SR    	SR22        	2130001	GL  										COCKPIT	FAILED          	D			OBKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	629LF					0843				PFD WAS JUST UPDATED TO REV 6.  2 DAYS AFTERWARDS, SCREEN WOULD FAIL IN FLIGHT.  DISPLAY WOULD FLICKER AND NOT BE USABLE	.  UNIT WOULD ALSO FAIL TO BOOT UP IN HANGAR.  CUSTOMER WAS GIVEN EXCHANGE.  (K)					1	L	7	1 	3O			NT	A00009CH					 
2006052200170	20060522	00170		2006	5	22	2006FA0000513    	4	20060404	G	3425	70000006000	FLIGHT DIR      			CIRRUS	SR    	SR22        	2130001	GL  										COCKPIT	FAILED          	D			OBKR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	13	623KT					0486				THIS PARTICULAR PFD HAD 3 BACK TO BACK FAILURES THAT COULD ONLY BE DETECTED AFTER 1 HOUR + OF FLIGHT.  DISPLAY WOULD LIG	HTEN UP, TURN GREEN AND FLICKER.  WOULD NOT BE USABLE.  THIS UNIT WAS UPGRADED TO REV 6 SOFTWARE FOR FLIGHT DIRECTOR.  F	AILURES HAPPENED AFTER THIS MOD.  FAILURES HAPPENED AFTER THIS MOD UNIT WAS SENT TO MFG AFTER FIRST 2 FAILURES, THIRD FA	ILURE RESULTED IN AN EXCHANGE.  (1ST-3-6-06-W/O AVO6-6617) (2ND - 3-29-06, W/O AVO6-6658) (3RD-4-4-06 W/O AVO6-6687)			1	L	7	1 	3O			NT	A00009CH					 
2006052200150	20060522	00150	SO  	2006	5	22	2006FA0000514    	2	20060420	G	8530		CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	ERODED          	D				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CE	01	5337Y				517945	21064171	517945			FOUND NR 6 PISTON ERODED FROM POSSIBLE DETONATION BY UNKNOWN CAUSES.  FOUND NR5 CYLINDER CONNECTING ROD CAP MISSING AND 	INTERNAL DAMAGE TO THE CRANKCASE.  NO OIL WAS NOTED ON THE DIPSTICK PRESUMED TO BE FORCED OUT OF THE ENGINE DUE TO EXCES	SIVE BLOW BY FROM THE ERODED NR 5 CYL.  THE ENGINE WAS SHUT DOWN AND LANDED IN A GRASS FIELD WITH NO DAMAGE TO THE AIRCR	AFT.  (K)			1	H	7	1 	3O	3	O		3A21    	E5CE				 
2006052200173	20060522	00173		2006	5	22	2006FA0000515    	4	20060505	G	2562		ELT             			CESSNA	210   	2105        	2073404	CE  										FUSELAGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	8197Z					2050197				ELT FAILED UPON INSPECTION AFTER 12 MONTHS OF SERVICE, DID NOT TRANSMIT THROUGH ANTENNA, LIGHT WENT ON INDICATING FUNCTI	ON.  THIS IS THE 3RD FAILURE ON UNITS NEWER THAN ONE YEAR OLD, IN 1.5 YEARS IN OUR SHOP.  (K)					1	H	7	1 	3O				3A21    					 
2006052200154	20060522	00154		2006	5	22	2006FA0000516    	4	20060306	G	2562	AK450	ELT             			HUGHES	269   	269A        	4470402	WP  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	62273					291096				ELT FAILED UPON INSPECTION AFTER EIGHT MONTHS OF SERVICE, DID NOT TRANSMIT THOUGH ANTENNA, LIGHT WENT ON INDICATING FUNC	TION.  THIS IS THE SECOND TIME THIS HAS FAILED THIS YEAR.  (K)					1	G	7	1 	3O	3	O		4H12    	1E10				 
2006052200166	20060522	00166		2006	5	22	2006FA0000517    	4	20060306	G	2562	AK450	ELT             			HUGHES	269   	269A        	4470402	WP  										FUSELAGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	62273					291096				ELT FAILED UPON INSPECTION AFTER NINE MONTHS OF SERVICE.  DID NOT SWEEP.  (K)						1	G	7	1 	3O				4H12    					 
2006052200171	20060522	00171	GL  	2006	5	22	2006FA0000518    	1	20060505	G	8011		SOLENOID        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					STARTER	INTERMITTENT    	B			LC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	343CD	399  				1343	917602			THE STARTER ON THIS AIRCRAFT FAILED.  THIS IS THE THIRD FAILURE OF THIS TYPE STARTER HAS A SOLENOID ATTACHED AND THE PRO	BLEM NOTED IS THAT THIS SOLENOID BECOMES INTERMITTENT. (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006052200147	20060522	00147	CE  	2006	5	22	2006FA0000519    	1	20060331	G	3233	508202085	ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  										NOSE GEAR	UNSERVICEABLE   	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			GL	11	641TS					BB641				AIRCRAFT NOSE WHEEL FAILED TO EXTEND WHEN GEAR SELECTOR WAS PLACED IN DOWN POSITION.  NOSE GEAR WAS OBSERVED BY TOWER PE	RSONNEL TO BE PARTIALLY EXTENDED BUT NOT LOCKED DOWN.  PILOT ATTEMPTED EMERGENCY EXTENSION WITHOUT SUCCESS.  AIRCRAFT LA	NDED ON MAIN GEAR AND SLOWED AS MUCH AS POSSIBLE BEFORE LOWERING NOSE TO GROUND.  AIRCRAFT SUSTAINED VERY LITTLE DAMAGE 	UPON LANDING.  ENGINES WERE SHUT DOWN AND PROPELLERS FEATHERED PRIOR TO LOWERING NOSE.  DAMAGE WAS CONTAINED TO RAYDOME,	 PITOT TUBES, NOSE GEAR DOORS AND PROPELLERS.  AIRCRAFT WAS FURTHER DAMAGED DURING RECOVERY PHASE WHEN HOISTING STRAP BR	OKE AND AIRCRAFT FELL BACK TO GROUND APPROX 4 FEET CAUSING STRUCTURE DAMAGE TO AFT FUSELAGE BEHIND PRESSURE BULKHEAD.	1	L	7	2 	4T				A24CE   					 
2006052300231	20060523	00231	EA  	2006	5	23	2006FA0000521    	2	20060518	G	8520	LW13820	CRANKCASE       	LYC         	O360A4M     	CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	1962F	4956 	1460 		L1726436A	17273052	L1726436A			DURING A 100 HR INSPECTION, AN OIL LEAK WAS NOTED AROUND THE L/H FORWARD CRANKCASE AROUND THE UPPER CRANKCASE BOLT (PN 6	-34A WITH PN LW-11866 NUT).  THE ENGINE WAS CLEANED AND A DYE PENETRANT INSPECTION PERFORMED.  A CRACK ROUGHLY 4 INCHES 	LONG WAS FOUND RUNNING VERTICALLY ON THE CRANKCASE FROM ABOUT 1 INCH BELOW THE CRANKCASE SEAM DOWN TO THE EDGE OF THE BE	ARING SURFACE OF THE BOLT HOLE, THEN DOWN ANOTHER 3 INCHES.  THE ENGINE IS BEING REMOVED FOR REPAIR OF CRANKCASE (IF POS	SIBLE) OR REPLACEMENT.		1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2006052200200	20060522	00200	CE  	2006	5	22	2006FA0000522    	1	20060522	G	2424	UAM100	CURRENT LIMITER 	RAYTHN      		RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					ELECT PANEL	MISDRILLED      	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	875QS					258375				MOUNTING HOLES IN CURRENT LIMITER DOES NOT MATCH LUGS IN ELECTRICAL PANEL.						2	L	7	2 	4F	3	T	RT	A3EU    	E2WE				 
2006052300232	20060523	00232	CE  	2006	5	23	2006FA0000523    	1	20060520	G	5500	550	SKIN            	CESSNA      		CESSNA	500   	550         	2076604	CE  										EMPENNAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	1255K				0505	5500505				AFTER A PHASE 1,2,3,4,49&59 CORROSION AND DELAMINATION WAS FOUND ON TOP AND BOTTOM SKINS LT AND RT SIDES OF THE HORIZONT	AL STABILIZER, LT SKIN OF THE VERTICAL STABILIZER. TAIL SKINS 5512010-9 AND 6512010-20 (SKINS UNDER VERT. STAB.) AS WELL	 AS THE AFT BULKHEAD 6412016-1SP WERE REPLACED.				1	L	7	2 	4F				A22CE   					 
2006052300233	20060523	00233	CE  	2006	5	23	2006FA0000524    	1	20060521	G	3710	1U478003	PUMP            	CONT        		BEECH 	33    	F33A        	1151425	CE  										ENGINE	BROKEN          	D				O				OTHER                   				I	G		FLT. ATTITUDE INST.       	MULTIPLE FAILURE          		CR	CRUISE         	1			GL	19	11BX	219  				CE388				VACUUM PUMP FAILURE INFLIGHT - FIRST NOTICED ATTITUDE CHANGE (STARTED DECENDING RAPIDLY) (AUTOPILOT ENGAGED)						1	L	7	1 	3O				3A15    					 
2006052300235	20060523	00235	CE  	2006	5	23	2006FA0000525    	1	20060520	G	5520	5534000204	ELEVATOR        	CESSNA      		CESSNA	500   	550         	2076604	CE  										RT ELEVATOR	MAINT ERROR     	B				L				ABORTED APPROACH        				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	1255K	9471 				0505				AFTER A REPAIR AT ANOTHER FACILITY THIS ELEVATOR WAS IN A BIND AND NOT ABLE TO STREAMILINE WITH THE STABILIZER (COULD NO	T RIG). IT APPEARS THAT THIS CONTROL WAS NOT INSTALLED CORRECTLY IN A JIG FIXTURE. WHILE REPLACING THE UPPER AND LOWER S	KINS IT WAS ALSO FOUND THAT THE FWD. SPAR WAS DAMAGED BY ALLOWING DRILL BITS TO GO THROUGH AND IMPACT ON THE SPAR. THIS 	CAUSED THE FWD. SPAR TO ALSO BE REPLACED.			1	L	7	2 	4F				A22CE   					 
2006052300236	20060523	00236	CE  	2006	5	23	2006FA0000526    	1	20060520	G	5751		AILERON         	CESSNA      		CESSNA	500   	550         	2076604	CE  										RT AILERON	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	43SA	9863 				0086				DURING A PHASE 1,2,3,4 INSPECTION THE RT AILERON WAS FOUND TO BE CRACKED AT THE LEADING EDGE IN THE AREA OF ATTACHMENT P	OINTS FOR THE WEIGHTS. THE SKIN WAS REMOVED AND REPLACED. HAD SEVERAL CRACKED AILERONS IN OUR OTHER AIRCRAFT BOTH LT AND	 RT CRACK IN THIS AREA. WE OPERATE A FLEET OF THESE AIRCRAFT AND LOOK AT THIS ON A 300HR. INSPECTION SCH.  THE CRACKS GO	 AROUND THE SCREW HOLES OR RADIATE OUT FROM THEM.			1	L	7	2 	4F				A22CE   					 
2006052300237	20060523	00237	CE  	2006	5	23	2006FA0000527    	1	20060521	G	3710	1U478003	PUMP            	CONT        		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					ENGINE	FAILED          	D				O				OTHER                   				I	G		FLT. ATTITUDE INST.       	MULTIPLE FAILURE          		CR	CRUISE         	1			GL	19	11BX	219  				CE388				VACUUM PUMP FAILURE INFLIGHT, FIRST NOTICED ATTITUDE CHANGE (STARTED DECENDING RAPIDLY) (AUTOPILOT ENGAGED).						1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006053000158	20060530	00158	SW  	2006	5	30	2006FA0000528    	1	20060518	G	5302		FITTING         	BELL        		BELL  	204   	UH1H        	1181407	SW  										TAIL BOOM	CRACKED         	H				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	15		4000 								TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE]						1	G	7	1 	4U				EXPA1G71					 
2006053000159	20060530	00159	SW  	2006	5	30	2006FA0000529    	1	20060518	G	5302		FITTING         	BELL        		BELL  	204   	UH1H        	1181407	SW  										TAIL BOOM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		4000 								TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE]						1	G	7	1 	4U				EXPA1G71					 
2006053000160	20060530	00160	SW  	2006	5	30	2006FA0000530    	1	20060518	G	5302		FITTING         	BELL        		BELL  	204   	UH1H        	1181407	SW  										TAIL BOOM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		4000 								TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE]						1	G	7	1 	4U				EXPA1G71					 
2006053000161	20060530	00161	CE  	2006	5	30	2006FA0000531    	1	20060521	G	2424	UAM100	CURRENT LIMITER 			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										ELECT REG SYS	FAILED          	B				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			SW	11	203TM					258653				CURRENT LIMITER BLOWN, CAUSING LOSS OF ELECTRICAL POWER						2	L	7	2 	4F			RT	A3EU    					 
2006053000162	20060530	00162	SO  	2006	5	30	2006FA0000532    	1	20060521	G	2436	UAM100	CURRENT LIMITER 			PIPER 	PA18  	PA18        	7101802	SO  										ELECT REG SYS	FAILED          	B				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			SW	11	203T					182317				CURRENT LIMITER BLOWN, CAUSING LOSS OF ELECTRICAL POWER.						1	H	7	1 	3O				1A2     					 
2006053000164	20060530	00164	GL  	2006	5	30	2006FA0000533    	1	20060518	G	7810	DC00015B	EXHAUST RISER   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	107TX	52   				C0310				ON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006052200241	20060522	00241	GL  	2006	5	22	2006FA0000534    	1	20060518	G	7810	DC00015B	EXHAUST RISER   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	107TX	52   				C0310				ON A 100HR INSP #2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006053000165	20060530	00165	GL  	2006	5	30	2006FA0000535    	1	20060518	G	7810	DC00015B	EXHAUST RISER   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	107TX	52   				C0310				ON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006053000166	20060530	00166	GL  	2006	5	30	2006FA0000536    	1	20060518	G	7810	DC00015B	EXHAUST RISER   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	107TX	52   				C0310				ON A 100HR INSP NR 2 EXHAUST RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006053000173	20060530	00173	CE  	2006	5	30	2006FA0000537    	1	20060520	G	5220		CHANNEL         			CESSNA	500   	550         	2076604	CE  										ESC DOOR FRAME	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	43SA					0086				THE STRIKER PLATE HAD COME LOSE AT THE TOP LATCH POINT FOR THE ESCAPE HATCH ALLOWING THE LOCK PIN TO ELONGATE OUT THE HO	LE. THIS REQUIRED THE REPLACEMENT OF 5511162-12 CHANNEL AND 5511162-48 ZEE CHANNEL.					1	L	7	2 	4F				A22CE   					 
2006052400216	20060524	00216	SO  	2006	5	24	2006FA0000538    	2	20060510	G	8520		CAMSHAFT        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  	HARTZL	HCJ2Y	BHCJ2YF2C   	GL  	ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	866SH					TH1083	298751R	DZ699		COMPRESSION CHECKED ENGINE, NR 2 CYLINDER 40/80.  REMOVED NR 2 CYL FOR REPAIR.  INSP INSIDE OF ENG, FOUND NR 1 CYL EXHAU	ST LIFTER/CAM LOBE BADLY WORN.  UNKNOWN HOW LONG IT HAS BEEN LIKE THIS, KNOW IT WOULD NOT HAVE LASTED TOO MUCH LONGER.  	REBUILT/ZERO TIMED.  AIRPLANE SHOWN TO HAVE FLOWN AS LITTLE AS 5 HRS IN 9 MONTHS.  SUSPECT TOO LONG PERIOD BETWEEN ENGIN	E RUNS, LOSING OIL FILM ON LIFTER/LOBE CONTACT, MAYBE LITTLE CORROSION, CAUSING METAL /METAL WEAR AND (GALLING) BEARING 	SURFACES.  HAVE BEEN PULLING WAY TOO MANY CYLINDERS LATELY DUE TO LONG PERIODS OF STORAGE OF AIRCRAFT THAT WERE NOT PRES	ERVED FOR STORAGE.  (K)	1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P37EA	 
2006052400217	20060524	00217		2006	5	24	2006FA0000539    	4	20060507	G	8300	7650004503074	BREATHER TUBE   			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					ACCY GEARBOX	DETERIORATED    	D				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			GL	09	176BA					760317				ENROUTE TO A PICK UP A PATIENT.  WITHIN 4 MINUTES OF TAKEOFF, MEDICAL CREW REPORTED, SMELLED SMOKE IN CABIN, BECOMING VI	SIBLE ALSO.  PILOT NOTICED IT ABOUT SAME TIME.  PILOT RETURNED WITHOUT DELAY, APPROX 30 SECONDS BEFORE TOUCHDOWN, BAGGAG	E COMPARTMENT SMOKE DETECTOR WENT OFF.  AC LANDED WITHOUT INCIDENT.  INVESTIGATION SHOWED NR 2 ENG ACCY GEARBOX VENT TUB	E HAD BROKEN FREE OF ENG DECK FITTING.  THIS OVERBOARD BREATHER TUBE MADE OF A  VINYL MATERIAL, HAD DETERIORATED TO POIN	T OF BREAKING OFF OF FITTING ON BOTTOM OF ENG DECK.  TUBE RUNS THROUGH AFT CORNER OF BAGGAGE COMPT, WHEN TUBE BROKE, FIL	LED COMPT WITH OIL MIST/VAPOR THAT ILLUMINATED SMOKE DETECTOR.  VINYL TUBE WAS REPLACED, AC RETURNED TO SERVICE.  (K)	1	G	7	2 	4U	4	U		H1NE    	E4EA				 
2006061200267	20060612	00267	NE  	2006	6	12	2006FA0000540    	1	20060508	G	2612	7630607902103	FIRE DETECTOR   			SKRSKY	S76   	S76B        	8143007	NE  										NR 1 ENGINE	FALSE ACTIVATION	D				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			GL	09	176BA					760317				ENROUTE, WHEN NR 1 ENG FIRE WARNING SYS WAS ACTIVATED.  PILOT REPORTED WARNING LIGHTS, HORN AND T-HANDLES ILLUMINATED WI	TH FIRE WARNING INDICATION.  WARNING STAYED ON FOR 30 SECONDS, WENT OUT.  AFTER SHORT PERIORD OF TIME, WARNING CAME BACK	.  PILOT DECLARED EMERGENCY WITH GRR CONTROLLERS.  WARNING WENT OUT AND CAME BACK ON 2 ADDITIONAL TIMES.  ENG PWR WAS RE	DUCED TO IDLE,THEN WAS SECURED USING FIRE T-HANDLE.  WHEN AC WAS IN SIGHT, IT WAS REPORTED, NO VISIBLE SMOKE TRAILING AC	.  PILOT CONTINUED, MADE EMERGENCY LANDING W/O INCIDENT.  ENG WAS OPENED AND INSPECTED FOR ANY VISIBLE SIGNS OF DAMAGE. 	 NO FIRE INDICATIONS.  TROUBLESHOOTING RESULTED FROM DEFECTIVE FIRE WARNING SENSOR, REPLACED.  AC RETURNED TO SERVICE.	1	G	7	2 	4U				H1NE    					 
2006053000174	20060530	00174	SO  	2006	5	30	2006FA0000541    	1	20060523	G	3221	6705403	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  										NLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	8184U					448095023				NOSE LANDING GEAR TRUNNION CRACKED AT UPPER ATTACH POINTS AND LOWER DRAG LINK ATTACH POINT.						1	L	7	2 	3O				A19S0   					 
2006053000115	20060530	00115		2006	5	30	2006FA0000542    	4	20060515	G	2562	AK450	ELT             			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					FUSELAGE	DEFECTIVE       	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	14	9894G					17259794				BRAND NEW ELT UNIT AMERIKING AK-450 WAS INSTALLED ON THE AIRCRAFT 8/04. UNIT WORKED AFTER INSTALLATION WITH REMOTE PANEL	, G-SWITCH AND TOGGLE SWITCH LOCATED ON THE UNIT AND AT SUBSEQUENT ANNUAL INSPECTION. AIRCRAFT HAS FLOWN APPROXIMATELY 2	5 HOURS SINCE INSTALLATION. ELT UNIT WAS FOUND DEFECTIVE DURING A ROUTINE INSPECTION ON 5/15/06. THE SIX D BATTERIES WER	E FOUND TO BE AT FULL CHARGE, NO SIGNS OF CORROSION. UNIT SENT BACK TO AMERIKING IN CA. FOR WARRANTY REPAIR.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006061400208	20060614	00208		2006	6	14	2006FA0000543    	4	20060515	G	2562	AK450	ELT             			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					FUSELAGE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	9894G					17259794				BRAND NEW ELT UNIT WAS INSTALLED ON THE AIRCRAFT 8/04. UNIT WORKED AFTER INSTALLATION WITH REMOTE PANEL, G-SWITCH AND TO	GGLE SWITCH LOCATED ON THE UNIT AND AT SUBSEQUENT ANNUAL INSPECTION. AIRCRAFT HAS FLOWN APPROXIMATELY 25 HOURS SINCE INS	TALLATION. ELT UNIT WAS FOUND DEFECTIVE DURING A ROUTINE INSPECTION ON 5/15/06. THE 6 (D) BATTERIES WERE FOUND TO BE AT 	FULL CHARGE, NO SIGNS OF CORROSION. UNIT SENT BACK TO MFG FOR WARRANTY REPAIR.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006061400210	20060614	00210	GL  	2006	6	14	2006FA0000544    	2	20060526	G	8510		DRIVE GEAR      			AMTR  	AVDFLY	AVIDFLYER   	       	GL  	AMTR  	430   	CUYUNA430   	19050	GL  					ENGINE	DAMAGED         	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NM	05	157VM	75   				0157				ACCIDENT INVESTIGATION.  ON CLIMB-OUT ENGINE RPM INCREASED AND PROPELLER RPM DECREASED. THE GRD-2000 GEAR REDUCTION UNIT	 WAS DISASSEMBLED AND THE DRIVE GEAR WAS FOUND TO DAMAGED.  (TEETH GONE)					1	H	7	1 	3O	3	I		EXPA1H71	EXPE3I				 
2006061300198	20060613	00198	EU  	2006	6	13	2006FA0000545    	1	20060511	G	2720		RUDDER PEDAL    			GROB  	103TWN	G103ATWINII 	1660206	EU  										COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4446T					3824				SIGNIFICANT CORROSION NOTED AT HORIZONTAL BASE OF LEFT RUDDER PEDAL.  RUDDER PEDAL CRACKED AND STARTED TO DEFORM SLIGHTL	Y IN THE VICINITY OF THE CRACK.  THE RUDDER PEDAL IS PLATED AND THE CORROSION APPEARED TO HAVE STARTED FROM THE INSIDE B	UT THE EXACT CAUSE HAS YET TO BE DETERMINED.  THESE PEDALS SHOULD BE EXAMINED AT LEAST EVERY YEAR DURING THE ANNUAL INSP	ECTION WITH A MIRROR AND LIGHT.			1	K	0	0 	3O			0	G39EU   					 
2006061300229	20060613	00229	GL  	2006	6	13	2006FA0000546    	1	20060526	G	2434	657046	BRACKET         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360CONT   	17025	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SO	06	145CD	446  				1020				ALTERNATOR BRACKET FOUND CRACKED.  NEW PART IS OF A HEAVIER DESIGN BUT RETAINS THE SAME PART NUMBER.						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2006060900267	20060609	00267	SW  	2006	6	9	2006FA0000547    	1	20060602	G	7810	40B19822	EXHAUST RISER   			MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  					ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	223KT	631  				270067				CUSTOMER SENT IN THE EXHAUST SYSTEM BECAUSE OF CRACKS FOUND IN THE WELDS OF THE RISER LEGS TO THE STACK TUBES OF THE NR 	1 AND NR 2 SECTIONS.  ADVISED CUSTOMER TO REPLACE COMPONENTS. CUSTOMER BOUGHT NEW PARTS AND BROUGHT THEM IN TO HAVE ATTA	CHING PIECES INSTALLED TO CHECK ALIGNMENT.  THE CUSTOMERS REQUIREMENTS THAT THEY FIT UNIFORMLY.  GENERAL COMMENTS REGARD	ING THESE PARTS: THE WORKMANSHIP OF THE NEW PIECES WAS GENERALLY POOR IN MY OPINION, NOT REPRESENTATIVE OF THE TYPE OR Q	UALITY THAT SHOULD BE EXPECTED FROM A MAJOR AIRCRAFT ENGINE MANUFACTURER.   IF IMPROVEMENTS ARE NOT MADE TO THE COMPONEN	TS ON THIS ENGINE/AIRCRAFT MODEL, SIGNIFICANT SAFETY PROBLEMS SHOULD BE EXPECTED.	1	L	7	1 	3O	3	O	RT	2A3     	E14EA				 
2006061200233	20060612	00233		2006	6	12	2006FA0000548    	4	20060517	G	6113	05522311	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	123GJ	1100 				17270706				DURING AN ANNUAL INSPECTION FO THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND 3 OF THE BOLT HOLWS OD THE FOR	WARD SPINNER BULKHEAD.  THE PROBABLE CAUSE IS THAT THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS BEING TIGHTENED AGAI	NST THE PROPELLER HUB.  IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF A THICKER MATERIAL.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006061200265	20060612	00265	CE  	2006	6	12	2006FA0000549    	1	20060516	G	2710	0510105365	CABLE           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RT AILERONS	FRAYED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	141CW	2657 				172S9389				DURING A 100 HOURS INSPECTION THE RT AILERON CROSSOVER CABLE WAS FOUND TO BE FRAYED AT THE PHANALIC BLOCK.  PROBABLE CAU	SE IS FRICTION BETWEEN THE CABLE AND THE WARE BLOCK.  TO PREVENT RECURRENCE REMOVE PHANALIC BLOCK AND INCREASE TENSION O	N CABLES.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006060900249	20060609	00249		2006	6	9	2006FA0000550    	4	20060511	G	6113	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	533BM					172S8340				DURING 100 HRS INSPECTION, FOUND FORWARD SPINNER BULKHEAD CRACKED IN 2 PLACES AROUND PROPELLER BOLT HOLES.  RECOMMENDATI	ON: DIMPLING OF BOLT HOLES.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006061200157	20060612	00157		2006	6	12	2006FA0000551    	4	20060517	G	6113	05522311	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	123GJ					17270706				DURING AN ANNUAL INSPECTION OF THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND 3 OF THE BOLT HOLES OF THE FOR	WARD SPINNER BULKHEAD.  THE PROBLEM CAUSE IS THAT THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS BEING TIGHTENED AGAIN	ST THE PROPELLER HUB.  IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF A THICKER MATERIAL.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006060600242	20060606	00242	SW  	2006	6	6	2006FA0000552    	1	20060513	G	6720	500N72205	CABLE           			HUGHES	500N  	500N        	3027374	SW  										ROTAT CONE CNTRL	BROKEN          	B			H2BR	R				AUTOROTATION            				F			FLT CONT AFFECTED         			DE	DESCENT        	1			WP	05	520HB					LN029				PILOT WAS PRACTICING AUTOROTATION AND FELT A CHANGE IN THE PEDALS.  AFTER TOUCHDOWN, HE ATTEMPTED TO HOVER BY RAISING TH	E COLLECTIVE, AND THE HELICOPTER BEGAN TO SPIN, HE LOWERED THE COLLECTIVE, AND SHUTDOWN.  NO DAMAGE TO THE HELICOPTER WA	S NOTED.  THE ROTATING CONE CONTROL CABLE WAS FOUND TO HAVE A CLEAN BREAK.  THE OTHER CABLES WERE INSPECTED AND FOUND OK	.  PAN 500N72205 CABLE WAS INSPECTED AT THE LAST 300 HR INSPECTION AND WAS FOUND TO BE AIRWORTHY.  THIS PART IS NOT A LI	FE LIMITED PART SO NO RECORD OF HRS IN SERVICE IS AVAILABLE.  RECOMMEND A SERVICE LIFE FOR THE CABLE: 1000 HRS.  (K)		1	G	7	1 	3U			NC	H3WE    					 
2006061200118	20060612	00118		2006	6	12	2006FA0000554    	1	20060523	G	8011	ES6462382	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										STARTER IS DIFFICULT TO TURN.  (K)																			 
2006061200160	20060612	00160	EA  	2006	6	12	2006FA0000555    	2	20060519	G	7320		CLIP            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	MISSING         	B			DYTR	E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	15139					347350025				THE RETAINING CLIP FROM THE ROD END EITHER BROKE OR FELL OFF CAUSING THE THROTTLE CABLE TO DETACH FROM THE FUEL INJECTIO	N SERVO.  THE ENGINE THEN WENT TO FULL POWER.  ENGINE HAD TO BE SHUT DOWN AND FEATHERED IN ORDER TO LAND THE AIRCRAFT.  	RECOMMEND USING PN 452-606 BEARING INSTEAD WITH APPROPRIATE HARDWARE AND COTTER PIN.  (K)				1	L	7	2 	3O	3	O		A7SO    	1E10				 
2006060600239	20060606	00239	NE  	2006	6	6	2006FA0000556    	1	20060512	G	2100	S76A12	A/C PACK        			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	BURNED          	G			MV1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	17	38	2749 				760087				AFTER THE DAYS FLIGHT, THE PILOT REPORTED THAT THE AIR CONDITIONING SYSTEM WAS INOPERATIVE.  MAINTENANCE WENT TO CHECK T	HE FREON CHANGE, WHEN THEY OPENED THE BAGGAGE AREA A FAINT SMELL OF BURNT WIRING WAS DETECTED.  UPON INSPECTION IT WAS F	OUND THAT WIRE A1K925A1130AMP WAS BURNT THRU.  THE CURRENT LIMITER AND ITS MOUNT WERE HEAT DAMAGED.  THE RELAY K9 FOR TH	E AIR CONDITIONING SYSTEM ALSO LOOKS LIKE IT WAS EXPOSED TO HEAT.  THE DAMAGED PARTS WERE REMOVED, THE SYSTEM DEACTIVATE	D AND STOWED.  REP WAS CALLED AND IS COMING TO SEE WHAT WAS FOUND.  NO OTHER SYSTEMS ON BOARD THE AIRCRAFT ARE EFFECTED 	AND ALL DAMAGE CONFINED TO THE AIR-CONDITIONING SYSTEM.  (K)	1	G	7	2 	3U				H1NE    					 
2006061200126	20060612	00126		2006	6	12	2006FA0000557    	1	20060517	G	8011	MZ6222	STARTER         																	ENGINE	INOPERATIVE     	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										WHINNING STARTER, WOULD NOT ENGAGE.  (K)																			 
2006061200158	20060612	00158		2006	6	12	2006FA0000558    	2	20060509	G	7314		DIAPHRAGM       																	FUEL PUMP	WORN            	B			YV4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	05										DURING DISASSEMBLY FOR OVERHAUL, OVER THE PAST FEW MONTHS, HAVE NOTED THAT THE STEEL WASHER ON TOP OF THE DIAPHRAGM STEM	 IS LOOSE ON THE STEM AND IN SOME CASES IS PARTIALLY EATEN THROUGH OR WORN AWAY BY HAMMERING AGAINST UPSET END OF DIAPHR	AGM STEM.  IF WASHER COMES COMPLETELY OFF, FUEL PUMP WILL BE INOPERABLE.  SOME WASHERS HAVE BEEN OBSERVED TO BE WORN 60-	80 PERCENT THROUGH THEIR THICKNESS.  SB NR 548A IS APPLICABLE TO THIS ISSUE.  HOWEVER, MANY OF THE PUMPS WITH WORN/LOOSE	 WASHERS ARE OUTSIDE DATE CODES COVERED BY SB.  THIS HAS BEEN OBSERVED IN MODELS 15472 AND 15473.  AT THE SAME TIME, A M	ODEL 16775 WAS DISCOVERED TO HAVE A WORN/LOOSE WASHER.  THIS MODEL NR WAS NOT IN THE SB.  (K)														 
2006060900251	20060609	00251	CE  	2006	6	9	2006FA0000559    	1	20060430	G	5346	051313211	ATTACH BRACKET  			CESSNA	175   	175         	2072502	CE  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENG MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	9366B					55166				ENGINE MOUNT ATTACHMENT BRACKET BROKEN AND WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION.  CRACKS ON IB AND OB SIDES OF T	HE AN960-616 WASHER.  NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED.  POSSIBLE CAUSE AN960-616 WASHER TOO SMALL.  LAR	GER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER LOAD.  (K)				1	H	7	1 	3O	3	O	NT	3A17    	1E10	5	C	P920	 
2006061200115	20060612	00115	CE  	2006	6	12	2006FA0000560    	1	20060430	G	5346	051313211	ATTACH BRACKET  			CESSNA	175   	175         	2072502	CE  	FRNKLN	6AV350	6A350C1     	27043	EA  					ENG MOUNT	BROKEN          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	175FW					55020				ENGINE MOUNT ATTACHMENT BRACKET BROKEN AND WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION.  CRACKS ON IB AND OB SIDES OF T	HE AN960-616 WASHER.  NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED.  POSSIBLE CAUSE AN960-616 WASHER TOO SMALL.  LAR	GER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER ENGINE MOUNT LOAD.  (K)				1	H	7	1 	3O	3	O	NT	3A17    	E9EA				 
2006061200059	20060612	00059	CE  	2006	6	12	2006FA0000561    	1	20060531	G	5346	051313211	ATTACH BRACKET  			CESSNA	175   	175         	2072502	CE  	CONT  	IO360 	IO360*      	17025	CE  					ENG MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	6622E					56122				ENGINE MOUNT ATTACHMENT BRACKET WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION.  CRACKS ON IB AND OB SIDES OF THE AN960-61	6 WASHER.  NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED.  POSSIBLE CAUSE AN960-616 WASHER TOO SMALL.  LARGER AREA AN	D THICKER WASHER NEEDED TO SUPPORT THE UPPER ENGINE MOUNT LOAD. (K)				1	H	7	1 	3O	3	O	NT	3A17    	E1CE				 
2006060900252	20060609	00252	CE  	2006	6	9	2006FA0000562    	1	20060518	G	3010	40653481	BLANKET         			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					STABILIZER	DAMAGED         	B			FJKR	K				NONE                    				P			NO WARNING INDICATION     			CR	CRUISE         	1			SO	17	417AM					123				THIS INCIDENT HAPPENED IN FLIGHT.  CREW REPORTED THAT THERE WAS NO INDICATION IN COCKPIT, THAT THERE WAS A PROBLEM.  CRE	W DISCOVERED DAMAGE TO RT HORIZONTAL STAB ICE GUARD BLANKET DURING THERE POST FLIGHT INSPECTION.  IB SECTION OF THE RT I	CE GUARD BLANKET WAS DAMAGED.  UPON FURTHER INVESTIGATION BY MECHANICS, WAS NOTED THAT A HOLE HAD BEEN MADE IN THE HORIZ	ONTAL LEADING EDGE BY THE ARCING OF THE HORIZONTAL LEADING EDGE ICE GUARD BLANKET WIRING.  THE RT HORIZONTAL STAB LEADIN	G EDGE AND ICE GUARD BLANKET WERE REPLACED.  (K)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006061200164	20060612	00164	EA  	2006	6	12	2006FA0000563    	1	20060424	G	2420	728318	ADG             			CNDAIR	CL600 	CL6001A11   	1900302	EA  	LYC   	ALF502	ALF502*     	41580	EA  					NOSE BAY	DEPLOYED        	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	05	777GD					1023				AIR DRIVEN GENERATOR (ADG) UNEXPECTED DEPLOYED ON POST TAKEOFF CLIMB OUT.  PRECAUTIONARY LANDING ACCOMPLISHED.  ADG MECH	ANICALLY RETRACTED/ SAFED; AIRCRAFT FERRIED TO MAINTENANCE DEPOT.  ALL WORK ACCOMPLISHED IAW MM.  (K)					2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2006060700135	20060607	00135	CE  	2006	6	7	2006FA0000564    	1	20060418	G	2820	530010854	LINE            			CESSNA	340   	340A        	2076405	CE  										CABIN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	320RM	5275 				340A0939				DURING AC MAINT, A STRONG FUEL ODOR WAS OBSERVED IN CABIN OF THE AC.  THIS AC HAD SAT IDLE ON RAMP FOR AT LEAST 10 MONTH	S.  EXTERIOR OF AC WAS INSPECTED FOR OBVIOUS FUEL LEAKS WITH NONE BEING DETECTED.  BY THIS TIME FUEL SMELL IN CABIN HAD 	CLEARED UP, AC ENGINES WERE OPERATED.  DURING PART OF THIS OPERATION, MECH WAS RUNNING ENGINES WITH FUEL SYS IN CROSSFEE	D POSITION, AGAIN NOTICED A STRONG FUEL ODOR.  AC WAS BROUGHT BACK TO HANGER, FLOOR PANELS WERE TAKEN UP IN AREA OF CROS	SFEED LINES WHERE THEY RUN THROUGH CABIN AREA.  IT WAS OBSERVED THAT A HEATER DUCT THAT WAS RUNNING PERPENDICULAR TO CRO	SSFEED LINES AND WAS IN CONTACT WITH LINES HAD CAUSED CORROSION TO FORM AND RESULTED IN PINHOLES IN BOTH LINES.  (K)	1	L	7	2 	3O				3A25    					 
2006060700137	20060607	00137	CE  	2006	6	7	2006FA0000566    	1	20060524	G	5610	991438011	WINDSHIELD      			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	240B	3548 				5605057				PILOTS WINDSHIELD OUTER PANE CRACKED AT 39,000 FT.  IT IS BELIEVED THAT A HEATING ELEMENT SHORTED CAUSING THE OUTER PANE	 TO CRACK.  WINDSHIELD REMAINS STRUCTURALLY INTERGRAL WITH THE OUTER PANE CRACKED.  MFG ENGINEERING IS EVALUATING THE FA	ILURE.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006060700140	20060607	00140	EA  	2006	6	7	2006FA0000567    	2	20060601	G	7321		BEARING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					FCU	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	530CH	2896 				LJ1322				THE BEARING IN FUEL CONTROL UNIT FAILED CAUSING THE LT ENGINE TO SURGE AND EXCEED THE N1, ITT AND TORQUE LIMITS.  THE IT	T EXCEEDED 1000 C AND THE TORQUE EXCEEDED 1500 FT POUNDS FOR 5-10 SECONDS.  SHORTLY AFTER TAKEOFF, PILOTS REPORTED PLANE	 HAD YAWED TO THE RT AND FIRST CORRECTED FOR THE YAW BEFORE NOTICING ITT AND TORQUE ABOVE RED LINE.  PILOTS THEN REDUCED	 POWER AND RETURNED TO AIRPORT.  ENGINE WAS REMOVED FOR REPAIR AND ALL ROTATING PARTS WERE FOUND TO BE IN NEED OF REPLAC	EMENT.  IN-SITU TEST HAD BEEN DONE REGULARLY AND NO INDICATION OF BEARING INSPECTION BUT IT IS AT THE END OF THE NOTES U	NDER THE FUEL SYSTEM INSPECTION.  BEARINGS ARE CALLED OUT FOR INSP/ REPLACEMT AT MID TBO OR 6 YEARS.	1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2006061200199	20060612	00199	GL  	2006	6	12	2006FA0000568    	1	20060601	G	2720		SPRING          			DIAMON	DA40  	DA40        	2990002	GL  										RUDDER	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	422DL					42L002				THIS HAS TO DO WITH RUDDER CENTERING BUNGEES OR SPRINGS THERE IS ONE ON BOTH SIDES OF THE RUDDER.  AFTER FLT, MECHANIC N	OTICED SOME PARTS SETTING ON RUDDER HORN AS IF THEY HAD BEEN REMOVED AND PUT THERE, AN INSP OF  RUDDER, IT WAS DETERMINE	D THAT THEY FELL OFF JUST AS AC WAS PARKED AS ALL OF PARTS FOR BUNGEE WAS THERE.  AFTER CONSULTING MAINT, PARTS ALONG WI	TH AC PARTS WERE REASSEMBLED USING LOCK TIGHT AS THERE IS NO LOCKING DEVICE.  PNS FOUND ON RUDDER ARE: (ROD, D60-2723-00	-31) (SPACER, D60-2723-00-32) (SPRING, VD-283A-10) (SPACER, D60-2723-00-33) IF THESE PARTS WOULD HAVE FALLEN OUT IN FLIG	HT THIS COULD HAVE LOCKED UP THE RUDDER. SUGGEST THERE SHOULD BE SOME SORT OF LOCKING DEVICE INSTALLED.  (K)	1	L	7	1 	3O			NT	A47CE   					 
2006061300197	20060613	00197	NE  	2006	6	13	2006FA0000569    	2	20060606	G	7414	6351	SCREW           			MAULE 	MT7235	MT7235      	5470209	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					MAGNETO	LOOSE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	116CP	394  	394  			18063C				CHECKED TIMING BOTH WERE OUT OF TIME.  REMOVED BOTH MAGS, THE PIVOT SCREW WAS LOOSE.  REPLACED POINTS & CAP, WITH 500 HR	 INSP.  BOTH MAGS WERE INSTALLED NEW IN 04/2002 AT 46.1 TT.					1	H	7	1 	3O	3	O	NC	3A23    	1E4				 
2006061200116	20060612	00116	SO  	2006	6	12	2006FA0000571    	1	20060531	G	7400	10382585	POINTS          			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	8456H	9    				348233011	268216R			THE POINTS WHICH ONLY HAD A TOTAL OF 9.3 HR, HAD THE PLASTIC PORTION WHICH RIDES THE CAM, MELT ON THE METAL OF THE POINT	S WHICH REDUCED THE GAP TO CAUSE MISFIREING.  CAPACITOR CHECKED GOOD AND WAS NOT REPLACED ON THE 500 HR INSP.  AFTER A N	EW POINT SET WERE INSTALLED CHANGED THE CAPACITOR.  NOTE:  WIRE BROKE ON OLD CAPACITOR.  (K)				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2006061200114	20060612	00114	SW  	2006	6	12	2006FA0000572    	1	20060519	G	3210	AN3H11A	BOLT            			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE33110    	01514	WP  					NLG STEERING ACT	SHEARED         	B			O9IR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	09	333UP	3934 				96015				DURING LANDING GEAR EXTENSION ON APPROACH, (GEAR IN TRANSIT) LIGHT REMAINED ON, NLG DID NOT INDICATE DOWN AND LOCKED.  I	NITIAL FLY BYS INDICATED NLG TO BE ONLY PARTIALLY EXTENDED.  AFTER RECYCLING GEAR SEVERAL TIMES, CLUNK WAS HEARD, NLG EX	TENDED.  INSP REVEALED 4 (AN3) BOLTS USED TO SECURE HYD STEERING ACTUATOR TO NLG OLEO STRUT, SHEARED RESULTING IN STEERI	NG ACTUATOR HANGING ONLY BY ITS HYD LINES.  UNSECURED STEERING ACTUATOR HAD POSSIBLY JAMMED PREVENTING FULL EXTENSION OF	 NLG.  RADOME DAMAGE WAS EVIDENT, NO OTHER DAMAGE HAS BEEN FOUND.  4 BROKEN BOLTS CAN BE DAMAGED BY EXCEEDING NLG TURN L	IMITS DURING TOWING.  BOLTS WERE WEAKENED BY EXCESSIVE TURNING WHILE TOWING. SOMETIME IN PAST, FAILED DURING FLIGHT. (K)	1	H	7	2 	4T	4	T		2A4     	E4WE				 
2006061200122	20060612	00122	CE  	2006	6	12	2006FA0000573    	1	20060525	G	5541	053100121	RIB             	CESSNA      		CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					RUDDER	CRACKED         	H			ET9T	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	5039A	5752 				28039	10851D5B			RIB, CRACKED AT VERTICAL HINGE LINE JUNCTURE.  STRESS FROM COUNTER WEIGHT AND NORMAL WEAR.  AGE OF THE PART AND THE WIND	.  SUBMITTER RECOMMENDS CLOSE INSPECTION AND REPLACEMENT OF PART IF DAMAGED.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2006061200130	20060612	00130	GL  	2006	6	12	2006FA0000574    	1	20060531	G	7810		FLANGE          	DIAMON      		DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	EXHAUST RISER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	431JP	82   			1PA520014	40431	L31683351A	CH338383B		FOUND NR 2 CYLINDER EXHAUST RISER FLANGE BROKEN.  DISCOVERED WHEN DISASSEMBLY EXHAUST FOR MODIFICATION IAW MSB-4000411. 	 PROBABLE CAUSE OF BREAKING FROM EXCESS VIBRATION.  RECOMMEND INSTALLING MSB-40-004/1 MUFFLER BRACE.  (K)					1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920	 
2006061200174	20060612	00174	EU  	2006	6	12	2006FA0000575    	1	20060309	G	7600	L810BQ54	SOLENOID        			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					AUTOTHROTTLE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	01	187AE	673  				3846	22469			PROLONGED OPERATION IN MANUAL MODE CAN CAUSE SOLENOID OVERHEATING AND PISTON SEIZURE.  FAILURE OF THE PISTON MOVEMENT MA	Y RESULT IN THE PILOT BEING UNABLE TO APPLY ADDITIONAL MANUAL THROTTLE BEYOND THE VOL (GATE).  THIS CAN RESULT IN ROTOR 	RPM DECAY IN CERTAIN CRITICAL SITUATIONS.  WHILE PERFORMING MAINTENANCE OF COLLECTIVE TWIST GRIP THROTTLE AUTO/MAN SOLEN	OID PISTON, SYSTEM WAS ACTIVATED FOR 10 MIN.  FOLLOWING A 30 SECOND TIME IN WHICH SOLENOID WAS RELAXED PWR WAS AGAIN APP	LIED.  PISTON FAIL TO FULLY SEAT IN THE SOLENOID.  PART WILL BE REPLACED. CMD AS350-06-15 RESCINDED AND REPLACED BY CMD 	AS350-06-16.  NEW CMD CHANGES RELAXED TIME FROM 30 SEC TO 15 MIN TO ALLOW THE SOLENOID TO COOL BEFORE REACTIVATION.  (K)	1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006061400229	20060614	00229	SO  	2006	6	14	2006FA0000576    	2	20060606	G	8520		NUT             			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					NR 4 CYLINDER	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	746C	699  				0413	686383			THRU STUD NUT SPLIT ON NR 4 CYLINDER TOP THRU STUD.  (K)						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006061400219	20060614	00219	SW  	2006	6	14	2006FA0000577    	1	20060521	G	2841	2731	GAUGE           			BBAVIA	7     	7CCM        	21101MW	SW  	CONT  	C90   	C90*        	17009	SO  					COCKPIT	STUCK           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	4629E					7CCM196				AIRCRAFT LOST POWER AND LANDED IN A HAYFIELD UP ON ITS NOSE.  PILOT STATED HE CHECKED THE FUEL GAUGE PRIOR TO THE FLIGHT	 AND IT READ (HALF FULL).  HE DID NOT VISUALLY CHECK THE QUANTITY.  INVESTIGATION REVEALED FUEL TANK TO BE EMPTY AND GAU	GE STUCK IN THE (HALF FULL) POSITION.  (K)				1	H	7	1 	3O	3	O		A759    	E252				 
2006061400227	20060614	00227	EA  	2006	6	14	2006FA0000579    	1	20060420	G	5310		DOOR FRAME      			DHAV  	DHC3  	DHC3        	2800202	EA  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	435B	12295				183				FORWARD FUSELAGE STRUTS (DOOR POSTS) CORRODED THROUGH FROM INSIDE OUT.  THIS IS THE SAME DESIGN AS THE DOOR POST THAT AR	E REQUIRED BY AD TO BE REPLACED EVERY 15 YEARS OR INSPECTED ANNUALLY BY ULTRASOUND.  (K)					1	H	7	1 	3R				A815    					 
2006061400223	20060614	00223	SO  	2006	6	14	2006FA0000580    	2	20060508	G	8520		CONNECTING ROD  			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	LT ENGINE	UNKNOWN         	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	11	106GA					TH437	8244276R	ED3372		50 MILES OUT OF HOME BASE, PILOT HEARD A (POP) CAME FROM LEFT ENGINE,  THEN NOTICED OIL PRESSURE START THE FALL.  FEATHE	RED PROP AND SECURED ENGINE.  MADE A UNEVENTFUL LANDING.  INSP FOUND NR 4 CYLINDER ON L/E DDEPARTED FROM ENGINE AND NR 4	 ROD BROKEN.  SUSPECT EITHER ROD BOLTS FAILED OR IMPROPERLY TORQUED, OR CYLINDER  IMPROPERLY TORQUED.  ENGINE COMPLETE L	OSS.  (K)			1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P36EA	 
2006061400213	20060614	00213		2006	6	14	2006FA0000581    	4	20060504	G	6113	05503214	BULKHEAD        			CESSNA	172   	172M        	2072418	CE  										PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9379H	445  				17266128				DURING ROUTINE SCHEDULED PHASE INSPECTION.  FOUND FORWARD PROP SPINNER BULKHEAD CRACKED RADIALLY OUTWARD FROM MOUNTING B	OLT HOLES NEXT TO BEND RADIUS.  PROPELLER MOUNTING BOLT BOLT TORQUE AND INDEXING FOUND CORRECT.  SUSPECT EITHER IMPROPER	 HEAT TREAT DURING MFG, OR POSSIBLY TOO TIGHT OF BEND RADIUS.  (K)				1	H	7	1 	3O			NT	3A12    					 
2006061400216	20060614	00216	SO  	2006	6	14	2006FA0000582    	1	20060522	G	3211	401421	BOLT            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					NLG	LOOSE           	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	13	7609C					347670097				NOSE GEAR RETRACTED ON LANDING.  FOUND BOLT PN 401-421 (AN6-41A) LOOSE WHERE NOSE GEAR MOUNT BOLTS TO BULKHEAD AT STA 49	.5.  THIS RELEAVED DOWNLOCK LINK OVER CENTER POSITION.  BOLTS SHOULD BE CHECKED EACH 500 HRS. (K)					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2006062100234	20060621	00234	CE  	2006	6	21	2006FA0000584    	1	20060602	G	5543	96630000335	TRIM TAB        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A11      	52043	NE  					RUDDER TRIM	MISMANUFACTURED 	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	690GT	164  			LJ1728	LJ1727				WHEN INSPECTED IAW SB, THIS AC WAS IDENTIFIED AS MISSING THE DRAIN PROVISIONS.  C/A WAS TAKEN IAW SB.  DURING OUR RESEAR	CH INTO THIS MATTER IT WAS IDENTIFIED THAT THE CCORRELATING AD TO THIS ISSUE.  THIS IS A NEARLY NEW AC.  (K)					1	L	7	2 	3T	3	T		3A20    	E4EA				 
2006062100236	20060621	00236	CE  	2006	6	21	2006FA0000585    	1	20060518	G	2434	991059111RX	ALTERNATOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	SHORTED         	B			NF2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	140JA					172S8653				ALTERNATOR WENT SEVERE OVER VOLT DUE TO INTERNAL SHORT IN THE FIELD WINDINGS.  SHORT FRYED THE ACU AND BOSS 1 DIODE (AVI	ONICS BUSS) DUE TO BADLY DAMAGED ACU, ACU COULD NOT GET ALTERNATOR OFF LINE.  DUE TO BOSS 2 DIODE FAILURE AVIONICS BUSS 	WAS HOT WITH AVIONICS MASTER OFF OVER VOLT BURNED UP ALL RADIOS.  ALL ENGINE GAUGES, FUEL GAUGES ANNUNICATOR PANEL AND F	LASHING BEACON.  THIS IS THE 5TH ALTERNATOR WITH MAJOR PROBLEMS IN THE PAST 11 MONTHS.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006062100262	20060621	00262	CE  	2006	6	21	2006FA0000586    	1	20060518	G	2435	230790001	STARTER GEN     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  						SEIZED          	B			R4OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	33	301TS					BE76	P271610			RT ENGINE WOULD NOT START.  TROUBLESHOT AND FOUND RT STARTER GENERATOR SEIZED DUE TO BRUSHES WORN BEYOND LIMITS AND PIGT	AILS ARCHING TO ARMATURE.  (K)					1	L	7	2 	4T	4	T		A14CE   	E4WE				 
2006062100232	20060621	00232	EU  	2006	6	21	2006FA0000587    	1	20060202	G	3213	TB2047007	CYLINDER        			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540*      	41532	EA  					LT MLG	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2808W	800  				1083				MLG HYD CYL, PN TB2047007/SN WO300497 WAS REMOVED AND SENT FOR INTERNAL LEAK AND A VERY STIFF SPOT ABOUT CENTER OF TRAVE	L.  CYL WAS RETURNED, REPAIRED, WARRANTY AS IS.  INSTALL CYL ON LT MLG.  INTERNAL LEAK NO LONGER EXISTED.  UPON TESTING 	EMERGENCY EXTENSION CYL WOULD NOT ALLOW LT MAIN TO EXTEND, STIFF SPOT CENTER OF TRAVEL,  CAUSE: REPAIR STATION STAMPED T	AG, DISTORTING CYLINDER? CYLINDER HAS TO BE REPLACED WITH SERVICEABLE UNIT.  (K)			1	L	7	1 	3O	3	O	RT	A51EU   	1E4				 
2006062100238	20060621	00238	NM  	2006	6	21	2006FA0000588    	1	20060607	G	2910		CAP             			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					CHECK VALVE	INOPERATIVE     	C			NACR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP				0448	23465				AFTER COMPLETING 2 FLIGHTS, (A) HYDRAULIC SYSTEM BECAME INOPERATIVE.  A LARGE AMOUNT OF FLUID WAS NOTED ON THE GROUND UN	DER THE LT WHEEL.  UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE RT (A) SYSTEM MODULE CHECK VALVE INSTALLATION CAP HA	D SHEARED IN THE MODULE CHECK VALVE INSTALLATION CAP HAD SHEARED IN THE MODULE PACKAGE, ALLOWING A LARGE QUANTITY OF HYD	RAULIC FLUID TO BE LOST.  DO NOT HAVE A PROBABLE CAUSE OR ANY RECOMMENDATIONS.  (K)			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006062100250	20060621	00250		2006	6	21	2006FA0000589    	4	20060412	G	2562		BATTERY         			CNDAIR	CL600 	CL6001A11   	1900302	EA  										ELT	LEAKING         	C			PAIR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01	673TS				WO62231	1073				A STRONG ACIDIC ODOR WAS PRESENT AFTER REMOVING ELT BATTERY FROM ELT INSPECTION FOUND A THICK WHITE LIQUID ON THE NEGATI	VE SIDE OF ONE BATTERY CELL.  THE EXPIRATION DATE OF THE ELT BATTERY IS APRIL 2010 (4 MORE YEARS).  THE ELT BATTERY OUTP	UT IS 13.2 VOLTS.  (K)				2	L	7	2 	4F			RT	A21EA   					 
2006062700311	20060627	00311	CE  	2006	6	27	2006FA0000590    	1	20060608	G	2810	714145	VENT LINE       			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					FUEL CELL	CRACKED         	B				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			GL	21	316CA	152  	152  			10132006	L3247851A			CREW REPORTED STRONG SMELL OF FUEL IN CABIN.  MX INSPECTED FOUND FUEL LEAKING ONTO CARPET ON THE FWD LT SIDE OF CABIN. T	RACED LEAK TO THE VENT LINE HEADER TANK ATTACH FITTING.  FITTING FOUND TO BE TIGHT BUT LINE CRACKED AT COMPRESSION SLEEV	E CONNECTOR. LINE AND CONNECTOR REPLACED NO LEAKS NOTED.				1	H	7	1 	3O	3	O		A21CE   	1E10				 
2006061900189	20060619	00189	CE  	2006	6	19	2006FA0000591    	1	20060608	G	2810	714145	SLEEVE          			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					FUEL LINE	BROKEN          	B				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			GL	21	316CA	152  	152  			10132006	L3247851A			CREW REPORTED STRONG ODOR OF FUEL IN CABIN.MX INSPECTED FOUND FUEL LEAKING ONTO CARPET ON THE FWD LEFT SIDE OF CABIN. TR	ACED LEAK TO THE VENT LINE HEADER TANK ATTACH FITTING. FITTING FOUND TO BE TIGHT BUT LINE CRACKED AT COMPRESSION SLEEVE 	CONNECTOR. LINE AND CONNECTOR REPLACED NO LEAKS NOTED.				1	H	7	1 	3O	3	O		A21CE   	1E10				 
2006062100261	20060621	00261		2006	6	21	2006FA0000592    	4	20060605	G	6113	0522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					SPINNER	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	787WW	100  				172S8589				DURING A 100 HOUR INSPECTION FO THE PROPELLER IT WAS NOTICED THAT THE FORWARD SPINNER BULKHEAD HAD CRACKS AROUND ALL 6 B	OLT HOLES.  THE PROBABLE CAUSE IS DURING THE TORQUING PROCESS THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS PULLED TI	GHT TO THE PROP HUB.  IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF THICKER MATERIAL.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006062100209	20060621	00209	CE  	2006	6	21	2006FA0000593    	1	20060606	G	3240	12806160	LINE            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					RT MLG BRAKE	LEAKING         	B			WIWR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	2147Q	117  				T20608420				DURING NORMAL OPERATION RT BRAKE STARTED LEAKING.  REMOVED WHEEL FAIRING AND FOUND A SCREW FROM THE FAIRING CHAFING INTO	 THE LOWER BRAKE LINE CAUSING THE LINE TO LEAK AND ALMOST FAIL, THEREFORE IT IS RECOMMENDED THAT PROPER ROUTING IS ASSUR	ED DURING INSPECTIONS AND THIS AREA IS ROUTINELY INSPECTED FOR LEAKS AT EVERY PREFLIGHT.  (K)				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2006062100031	20060621	00031	NE  	2006	6	21	2006FA0000594    	2	20060427	G	7250	0292208230	MANIFOLD        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					GAS GEN	COKED           	B			GO4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	711JH	2551 				3397	7022			DURING A 500 HR (T-INSPECTION), COULD NOT SPIN COMPRESSOR DISK, DUE TO GAS GENERATOR INJECTION MANIFOLD COKING.  MFG TEC	H REMOVED AND REPLACED INJECTION MANIFOLD ON MODULE NR 3.  (K)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062100254	20060621	00254	SW  	2006	6	21	2006FA0000595    	1	20060602	G	5711	5271L	SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235C1      	41505	EA  					LT WING	CRACKED         	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	9562S	2573 				84	RL338815			REQUIRED INSPECTION OF WOODEN WING SPARS IN ACCORDANCE WITH AD.  REVEALED A COMPRESSION CRACK IN THE LT WING FWD SPAR AT	 THE TOP OB OF WING STRUT ATTACH DOUBLER PLATE.  (K)					1	H	7	1 	3O	3	O		A759    	E223				 
2006062100245	20060621	00245	CE  	2006	6	21	2006FA0000596    	1	20060607	G	3233	6632201000005	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  										NLG	LEAKING         	B			B08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	CFBLJ					45270				DURING MAINTENANCE, TECH DISCOVERED LEAKING NLG ACTUATOR.  FACILITY GAINED ACCESS, REMOVED AND REINSTALLED THE ACTUATOR 	WITH A REPAIRED UNIT AND RETURNED THE AC TO SERVIC.  DURING ATTEMPT TO BEGAN NORMAL TOWING OPERATIONS TO POSITION THE AI	RCRAFT FOR DEPARTURE, NLG BEGAN TO RETRACT.  IMMEDIATELY CEASED THE TOWING OPERATION AND WERE ABLE TO PLACE A JACK UNDER	NEATH THE AIRCRAFT TO SUPPORT IT AND PREVENT ANY DAMAGE.  WITH LANDING GEAR FULLY EXTENDED AN INTEGRAL MECHANISM HOLDS T	HE ACTUATOR DOWN AND LOCKED UNTIL HYDRAULIC PRESSURE IS APPLIED.  SUSPECT FAILURE OF INTEGRAL LOCKING MECHANISM.  (K)		2	L	7	2 	4F			RT	T00008WI					 
2006062100257	20060621	00257	CE  	2006	6	21	2006FA0000597    	1	20060613	G	7120	051313211	GUSSET          			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					ENGINE MOUNT	CRACKED         	B			QI2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	6540E	2043 				56040				FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED, BRACELETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL.  	POSSIBLE CAUSE OF CRACKING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS.  (K)					1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2006062100243	20060621	00243	CE  	2006	6	21	2006FA0000598    	1	20060613	G	7120	051313210	GUSSET          			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					ENGINE MOUNT	CRACKED         	B			QI2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	6540E	2043 				56040				FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED, BRACKETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL.  P	OSSIBLE CAUSE OF CRACKING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS.  (K)					1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2006062100225	20060621	00225	CE  	2006	6	21	2006FA0000599    	1	20060613	G	7120	05131329	GUSSET          			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					ENGINE MOUNT	CRACKED         	B			QI2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	6540E	2043 				56040				FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED.  BRACKETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL.  	POSSIBLE CAUSE OF CRACKEING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS.  (K)					1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2006062100248	20060621	00248	SO  	2006	6	21	2006FA0000600    	1	20060609	G	5511	63460000	SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	8402W	2360 				282616				WHILE OPENING SOME SKIN LAPS TO TREAT SURFACE CORROSION THE LT SIDE OF THE MAIN SPAR ABOUT 2.5 FEET FROM TIP WAS FOUND T	O HAVE SEVERE INTERGRANULAR CORROSION TO THE POINT WHERE A 4-5 INCH LONGITUDNAL CRACK ABOUT .2500 INCH WIDE WAS FOUND.  	PART WAS SCRAPPED AND REPLACED WITH NEW ASSY, TREATED AC WITH ACF50.  (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
2006062100259	20060621	00259	CE  	2006	6	21	2006FA0000601    	1	20060601	G	2450	251005	FUSE            			BEECH 	MU300 	400A        	1155402	CE  										EMER BUSS	FAILED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	787TA					RK260				FLIGHT CREW REPORTED NO BATTERY VOLTAGE INDICATION ON VOLTMETER WITH ALL DC BUSSES POWERED.  TROUBLESHOOTING FOUND AIRCR	AFT WOULD NOT GO INTO EMERGENCY POWER OR PERFORMED FEEDER FAULT TEST.  FOUND 5A MICROFUSE F105 CONNECTED TO K005 EMERGEN	CY BUSS POWER RELAY OPEN.  REPLACED F105 FUSE, ALL DC POWER FUNCTIONS NORMAL, NO FAULTS NOTED.  (K)				2	H	7	2 	4F			RT	A16SW   					 
2006062100252	20060621	00252		2006	6	21	2006FA0000602    	4	20060530	G	2213	6227410302	CIRCUIT CARD    			BEECH 	MU300 	400A        	1155402	CE  										FCC	INTERMITTENT    	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	408CW					RK108				FLIGHT CREW REPORTED AUTOPILOT PITCH TRIM FAILURE ANNUNCIATION CAME ON DURING CLIMB WITH AUTO PILOT DISCONNECTED.  AIRCR	AFT REPPORTED TO HAVE PITCH-UP MOVEMENT.  FOUND NR 1 FCC-850 CARD INTERMITTENTLY NOT CROSS-TALKING TO NR 2 FCC-850 CARD.	  REPLACED NR 1 FCC 850 CARD WITH OVERHAULED UNIT.  GROUND/FLIGHT CHECKS SATISFACTORY.  (K)				2	H	7	2 	4F			RT	A16SW   					 
2006062100231	20060621	00231		2006	6	21	2006FA0000603    	4	20060530	G	2213	6226717004	SERVO           			BEECH 	MU300 	400A        	1155402	CE  										YAW DAMPER	INTERMITTENT    	B			E81R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	03	408CW					RK108				FLIGHT CREW REPORTED PILOTS CONTROL WHEEL TRIM INTERRUPT/AUTOPILOT DISENGAGE SWITCH NOT DISCONNECTING YAW DAMPER ON FINA	L APPROACH.  FOUND CONTROL WHEEL SWITCH OPERATIONS NORMAL.  REPLACED SVO-85C YAW DAMPER SERVO WITH OVERHAULED UNIT.  ALS	O, REPLACED NR 1 FCC-850 CARD WITH OVERHAULED UNIT TO CORRECT ADDITIONAL AUTOPILOT INTERMITTENT PITCH TRIM FAILURE FAULT	.  GROUND AND FLIGHT TESTS SATISFACTORY.  (K)			2	H	7	2 	4F			RT	A16SW   					 
2006062100256	20060621	00256	SO  	2006	6	21	2006FA0000604    	1	20060614	G	2730	62701159	CONTROL CABLE   			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  	HARTZL	HCC3Y	HCC3Y*      	GL  	ELEVATORS	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	31709	2741 				32R7885121	L1571048A	DY4524A		CABLE TURNBUCKLE MALE END SEPARATED AT FITTING DURING ROLLOUT AFTER LANDING.  FITTING SEEMS TO HAVE CORRODED FROM THE SH	ANK CORE AND PROGRESSED OUTWARD TO THE SURFACE OVER TIME.  (K)					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P25EA	 
2006071100106	20060711	00106		2006	7	11	2006FA0000605    	4	20060621	G	3460		DISPLAY         																	COCKPIT	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07										TO DATE, HAVE EXPERIENCED 12 SEPARATE FAILURES OF THE MULTIFUNCTION DISPLAYS (MFD) WITH 6 OF THE 7 AIRCRAFT. THESE FAILU	RES HAVE OCCURRED EITHER IN FLIGHT OR ON THE GROUND. THERE IS NO APPARENT PATTERN OR FOREWARNING RELATED TO THESE FAILUR	ES.  THESE FAILURES CAUSE AN UNAIRWORTHY CONDITION OF THE AIRCRAFT DUE TO THE LACK OF OIL TEMPERATURE INDICATION. ALSO, 	ACCORDING TO THE PA 28-161 MFG POH, SECTION 9, SUPPLEMENT 10, SECTION 2, PARAGRAPH B TITLED "MFD LIMITATIONS", ITEM 4, (	AIRCRAFT DISPATCH IS PROHIBITED WHEN THE MFD IS INOPERATIVE.)  CURRENTLY, MANUFACTURERS ARE INVESTIGATING THIS PROBLEM, 	BUT NO RESOLUTION HAS BEEN FOUND.														 
2006062700312	20060627	00312	CE  	2006	6	27	2006FA0000606    	1	20060622	G	5730		SKIN            			CESSNA	402   	402B        	207590P	CE  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	6375X	5321 				402B1338				DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE LT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAI	N FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SP	AR WERE FOUND SHEARED, CAUSING THE MAIN FUEL TANK TO HAVE MOVEMENT.  IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRE	SS AT THE FORWARD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF TANK. THIS IS THE SECOND AIRCRAFT THAT THIS	 PROBLEM WAS FOUND ON.		1	L	7	2 	3O				A7CE    					 
2006062700313	20060627	00313	CE  	2006	6	27	2006FA0000607    	1	20060622	G	5730		SKIN            			CESSNA	402   	402B        	207590P	CE  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	6375X	5321 				402B1338				DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE LT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAI	N FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SP	AR WERE FOUND SHEARED, CAUSING THE MAIN FUEL TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRES	S AT THE FORWARD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF TANK. THIS IS THE SECOND AIRCRAFT THAT THIS 	PROBLEM WAS FOUND ON.		1	L	7	2 	3O				A7CE    					 
2006062700314	20060627	00314	SO  	2006	6	27	2006FA0000608    	1	20060612	G	2730	62701159	CONTROL CABLE   			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ELEVATOR	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			SO	16	31709	2741 				32R7885121	L1809048A			UP ELEVATOR CABLE SEPARATED IN LANDING FLARE.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006062700315	20060627	00315	SO  	2006	6	27	2006FA0000609    	1	20060612	G	2730	62701159	CONTROL CABLE   			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ZONE 300	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			SO	16	31709	2741 				32R7885121	L1809048A			UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006062700316	20060627	00316	SO  	2006	6	27	2006FA0000610    	1	20060612	G	2730	62701159	CONTROL CABLE   			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ZONE 300	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			SO	16	31709	2741 				32R7885121	L1809048A			UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006062700317	20060627	00317	SO  	2006	6	27	2006FA0000611    	1	20060612	G	2730	62701159	CONTROL CABLE   			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ZONE 300	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			SO	16	31709	2741 				32R7885121	L1809048A			UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006062700318	20060627	00318	CE  	2006	6	27	2006FA0000612    	1	20060621	G	5311	1054200116	FRAME           			BEECH 	76    	76          	1153005	CE  										RT WINGFEATHERIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	141P	2269 				ME237				CRACK IN RT FORWARD WING BOLT ATTACH FRAME, P/N: 105-420011-6.						1	L	7	2 	3O				A29CE   					 
2006062700319	20060627	00319	CE  	2006	6	27	2006FA0000613    	1	20060621	G	5311	1054200116	FRAME           			BEECH 	76    	76          	1153005	CE  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	141P	2269 				ME237				CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.						1	L	7	2 	3O				A29CE   					 
2006062700321	20060627	00321	CE  	2006	6	27	2006FA0000614    	1	20060621	G	5311	1054200116	FRAME           			BEECH 	76    	76          	1153005	CE  										ZONE 100	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	141P	2269 				ME237				CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.						1	L	7	2 	3O				A29CE   					 
2006062700322	20060627	00322	CE  	2006	6	27	2006FA0000615    	1	20060621	G	5311	1054200116	FRAME           			BEECH 	76    	76          	1153005	CE  										ZONE 100	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	141P	2269 				ME237				CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.						1	L	7	2 	3O				A29CE   					 
2006062700323	20060627	00323	CE  	2006	6	27	2006FA0000616    	1	20060621	G	5311	1054200116	FRAME           			BEECH 	76    	76          	1153005	CE  										ZONE 100	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	141P	2269 				ME237				CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.						1	L	7	2 	3O				A29CE   					 
2006062700324	20060627	00324	CE  	2006	6	27	2006FA0000617    	1	20060621	G	5311	1054200116	FRAME           			BEECH 	76    	76          	1153005	CE  										ZONE 100	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	141P	2269 				ME237				CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.						1	L	7	2 	3O				A29CE   					 
2006062700325	20060627	00325	    	2006	6	27	2006FA0000618    	1	20060623	G	2612	7503611	CONTROL PANEL   			AMD   	STC   	STCFALC50   	       	    										FIRE DETECTION	FAILED          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	11	223HD	2811 				283				FIRE CONTROL PANEL FAILED.						2	L	7	2 	4F				A46EU   					 
2006062700326	20060627	00326	EU  	2006	6	27	2006FA0000619    	1	20060623	G	2612	7503611	CONTROL PANEL   			AMD   	FALC50	FALCON50MYST	2730106	EU  										FIRE DETECTION	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	223HD	2811 				283				FIRE CONTROL PANEL FAILED.						2	L	7	3 	4F				A46EU   					 
2006062700327	20060627	00327	NM  	2006	6	27	2006FA0000620    	1	20060608	G	6230	5100400	HOSE            			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      		NE  					XMSN OIL	CRACKED         	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	11	902PD	450  				9000084				PILOT NOTICED TRANSMISSION OIL PRESSURE INDICATION DROPPED FROM GREEN TO YELLOW TO RED.  MADE UNSCHEDULED LANDING. FOUND	 FWD LT TRANSMISSION OIL COOLER HOSE LEAKING. HOSE IS A FLEXIBLE STAINLESS STEEL HOSE WITH A STAINLESS STEEL OUTER BRAID	. HOSE WAS INSPECTED AFTER REMOVAL AND FOUND TO BE CRACKED. REPLACED HOSE P/N 900D3409526-105.				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2006062700328	20060627	00328	CE  	2006	6	27	2006FA0000621    	1	20060622	G	5730		SKIN            			CESSNA	414   	414         	2075908	CE  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	414JS	6794 				4140811				DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAI	N FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SP	AR WERE FOUND SHEARED, CAUSING THE MAIN TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT 	THE FWD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF THE TANK.			1	L	7	2 	3O			RT	A7CE    					 
2006062700329	20060627	00329	CE  	2006	6	27	2006FA0000622    	1	20060622	G	5730		SKIN            			CESSNA	414   	414         	2075908	CE  										ZONE 600	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	414JS	6794 				4140811				DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAI	N FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SP	AR WERE FOUND SHEARED, CAUSING THE MAIN TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT 	THE FWD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF THE TANK.			1	L	7	2 	3O			RT	A7CE    					 
2006070500025	20060705	00025	CE  	2006	7	5	2006FA0000624    	1	20060607	G	3200	174302120	SHIMMY DAMPENER 	CESSNA      		CESSNA	177   	177B        	2073708	CE  										MLG	LEAKING         	D				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			WP	17	34597	4025 				17701892				PART BECAME SUSPECT WHEN DAMPENER FLUID WAS NOTICED DRIPPING OFF END OF SHAFT. DURING THE CLEANING/INSP. COMPRESSED AIR 	WAS INTRODUCED TO SHAFT'S OPEN END.  AIR BUBBLES WERE OBSERVED AT BASE OF PISTON. FOUND CRACK ON DAMPENER SHAFT AT BASE 	OF PISTON.  CRACK IS NOTICEABLE 360 DEGREES AROUND SHAFT EVEN THOUGH SHAFT IS STILL INTACT.  LOSS OF FLUID MAY HAVE EXAG	GERATED VIBRATIONS CAUSING SHAFT TO FATIGUE OR MFG HEAT TREATING PROCESSES SINCE SHAFT IS NOT BROKEN COMPLETELY THROUGH.	  INSPECT IMMEDIATELY IF FLUID IS SEEN DRIPPING FROM THE END OF THE SHAFT.  OR, REMOVE AND DYE PENETRANT INSPECT SHIMMY 	DAMPENER SHAFT AT NEXT 25/50 HOUR MAINTENANCE INTERVAL.	1	H	7	1 	3O				A13CE   					 
2006070500304	20060705	00304	EA  	2006	7	5	2006FA0000625    	1	20060620	G	2910	604752383	TUBE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					HYD SYSTEM	CHAFED          	B			JAVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	881TW	4180 				5348				PRESSURE LINE FROM NR 1 ENGINE DRIVEN PUMP CHAFED AT AFTMOST CLAMP LOCATION (NEAR NR 1 SYSTEM RESERVOIR) UNTIL THE LINE 	FAILED UNDER PRESSURE CAUSING A COMPLETE LOSS OF NR 1 HYDRAULIC SYSTEM IN FLIGHT.  CLAMP CUSHION FAILED CAUSING METAL TO	 METAL CONTACT.  SUSPECT THAT DEFECT WAS NOT READILY VISIBLE BEFORE FAILURE.  (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006070500010	20060705	00010	CE  	2006	7	5	2006FA0000626    	1	20060612	G	2497	K3A2	CABLE           			CESSNA	421   	421A        	2076012	CE  										LT STARTER	SHORTED         	B			AGER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	99VK					421A0091				DURING STARTING OF LT ENGINE, SMOKE WAS OBSERVED COMING FROM THE LOUVERS ON TOP OF THE LT ENGINE.  THE ENGINE WAS SHUTDO	WN AND THE SMOKE SUBSIDED.  INSP REVEALED THAT THE 2-GAUGE STARTER AND ALTERNATOR POWER CABLES WERE BURNED IN HALF NEAR 	THE TURBOCHARGER.  FOURTEEN OTHER WIRES IN THE SAME BUNDLE WERE ALSO BURNED IN HALF OR SEVERELY HEAT DAMAGED.  THE ELECT	RICAL FIRE WAS A RESULT OF THE STARTER CABLE SHORTING TO GROUND ON THE TURBO SUPPORT BRACKET (PN 5155101-20).  THE ELECT	RICAL WIRE BUNDLE HAD BEEN RESTING ON THIS BRACKET FOR SOME TIME UNTIL THE WIRE INSULATION WAS CHAFFED THROUGH.  INSP OF	 THE OTHER ENGINE REVEALED SIMILAR CHAFFING AND POSSIBLILITY OF A SHORT.  (K)	1	L	7	2 	3O				A7CE    					 
2006071100105	20060711	00105	EA  	2006	7	11	2006FA0000627    	2	20060605	G	8500	71907	WASHER          			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540*       	41532	EA  					COUNTER WEIGHT	CRACKED         	G				O				OTHER                   				Y			ENGINE STOPPAGE           			AG	AGRICULTURE    	1			GL	27	7785Z	835  	835  			253989	L677440			COUNTER WEIGHT RETAINING WASHER P/N 71907 CRACKED AND BROKE. THIS ALLOWED THE COUNTER WEIGHT RETAINING PIN TO FALL OUT. 	ENGINE SEIZED.					1	L	7	1 	3O	3	O		2A10    	E295				 
2006070500294	20060705	00294		2006	7	5	2006FA0000628    	1	20060613	G	8120	4066109026	TURBOCHARGER    																		INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										TURBO WILL NOT PRODUCE BOOST.  (K)																			 
2006070500303	20060705	00303		2006	7	5	2006FA0000629    	1	20060615	G	2420	ALY6521	ALTERNATOR      																		INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										ALTERNATOR WOULD NOT ENGAGE.  (K)																			 
2006070500008	20060705	00008	EA  	2006	7	5	2006FA0000630    	2	20060612	G	7414	ES10357174	CONTACT         	BENDIX      		PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2B5    	41532	EA  					MAG POINTS	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	09	4811Y	44   			6010962	254592	L713540			MAG FAILED IN FLIGHT, UPON INSPECTION POINTS WERE FOUND TO BE BROKEN WITH 44 HOURS TT ON THE POINTS.  THE SPRING PORTION	 WAS BROKEN DUE TO A DEFECT IN THE STAMPING WHICH SET UP A STRESS POINT AT THE ATTACH SCREW.  RECOMMEND MFG CONTACT ASSY	 BE INSPECTED FOR PROPER BENDING OF THE PARTS AND REMOVE FROM SERVICE THAT DO NOT HAVE PROPER FORMING OF THE SPRING.  (K	)			1	L	7	1 	3O	3	O		2A10    	E295				 
2006070500013	20060705	00013	CE  	2006	7	5	2006FA0000631    	1	20060602	G	2910	1240016CR0164	LINE            			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6*        	52043	EA  					HYDRAULIC SYS	RUPTURED        	B			TIMR	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			NM	07	326CA					U135				DURING CLIMBOUT THE (GEAR IN TRANSIT) AND (DO NOT REVERSE) ANNUNCICATOR ILLUMINATED AND THEN THE LANDING GEAR CIRCUIT BR	EAKER POPPED.  PILOT CONTINUED, HAND PUMPED THE GEAR TO GET 3 GREEN.  LANDED OK.  INVESTIGATION DETERMINED THAT HYDRAULI	C HOSE ON THE LT UP LINE HAD RUPTURED.  (K)				1	L	7	2 	3T	3	T		A14CE   	E2NE				 
2006070500003	20060705	00003	CE  	2006	7	5	2006FA0000632    	1	20060620	G	2720	00252400023	CONTROL CABLE   			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					RUDDER	FRAYED          	B			Y5VR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	8259C					CE1763				AT ANNUAL INSP RT AFT RUDDER CABLE WAS FOUND FRAYED ALMOST IN TWO.  CABLE WAS FOUND ROUTED OVER THE TOP OF ONE CABLE PUL	LEY GUARD PIN, AND UNDER ANOTHER AT SAME LOCATION IN AFT TAIL SECTION.  CABLE REMOVED APPEARED TO BE THE ORIGINAL CABLE 	INSTALLED IN AIRCRAFT AT FACTORY.  LOGBOOKS DID NOT REVEAL ANY EVIDENCE THAT THE CABLE HAD EVER BEEN REMOVED OR DISCONNE	CTED THAT MAY HAVE CAUSE THIS.  BY THE AMOUNT OF CABLE THAT WAS FRAYED, IT APPEARS TO HAVE BEEN RUBBING ON THE PULLEY GU	ARD PIN FOR SOME TIME.  IT IS SUSPECTED THAT THIS CABLE WAS ROUTED INCORRECTLY AT THE FACTORY.  POSSIBLE QUICK FASHION A	NNUAL PREVIOUS.  RECOMMEND THOROUGH ANNUAL IN ITS ENTIRETY.	1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006070500306	20060705	00306	CE  	2006	7	5	2006FA0000634    	1	20060519	G	7600	45A431755	LINK            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT ENGINE	WORN            	D			EKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	435CW					RK35	PCE100250			DURING OPERATIONAL CHECK FLIGHT OF AIRCRAFT, PILOT ADVANCED POWER LEVERS FORWARD AND NOTED LT ENG (N) REACHED MAX OF 117	 PERCENT N2, REACHED MAXIMUM OF 100 PERCENT.  IT IS DETERMINED THAT PROBABLE CAUSE OF OVERSPEED WAS ACHIEVED BY WORN THR	OTTLE LEVER LINK NOT PROVIDING ACCURATE RANGE OF MOTION TO CORRECTLY ACTUATE THROTTLE STOP.  ENGINE LEVERS WERE ENABLE T	O ADVANCE FURTHER THAN NORMAL, CAUSING OVERSPEED CONDITION.  IT IS RECOMMENDED THAT LINK AND ASSOCIATED HARDWARE BE REPL	ACED.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006070500299	20060705	00299	EU  	2006	7	5	2006FA0000635    	2	20060608	G	7250	9514M71PO4	SHAFT           			BOEING	737   	737300      	1384610	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					ENGINE	FRACTURED       	B			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	B2943	30987					857655			REF: MRD/001/06 - AC CUFFERED AN ABORTED TAKEOFF.  INVESTIGATION REVEALED FAILURE AND LIBERATION OF THE HPT REAR SHAFT W	HERE A SECTION OF MATERIAL MEASURING 3.5 INCH CIRCUMFERENCE HAD LIBERATED AROUND THE 3 SEAL TOOTH RACK.  SIMILAR FAILURE	S HAVE BEEN EXPERIENCED ON ENGINE.  PARTS ARE RETURNED TO MFG FOR INVESTIGATION.  EDDY CURRENT INSPECTION INTO 3Q95.  (K	)			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500308	20060705	00308		2006	7	5	2006FA0000636    	2	20060501	G	7497		WIRE            			DHAV  	DHC8  	DHC8*       	       	NM  										EXCITER	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05			415  		895					EXCITER ROTOR LEAD WIRES BREAK AT SOLDER CONNECTION TO DIODE.  (K)						2	H	7	2 	4T			RT	A13NM   					 
2006070500309	20060705	00309		2006	7	5	2006FA0000637    	2	20060501	G	7497		WIRE            			DHAV  	DHC8  	DHC8*       	       	NM  										EXCITER	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05					392					EXCITER ROTOR LEAD WIRES BROKEN AT SOLDER CONNECTION TO DIODES.  (K)						2	H	7	2 	4T			RT	A13NM   					 
2006070500291	20060705	00291	EU  	2006	7	5	2006FA0000638    	1	20060621	G	2720	NB45D1803	CONTROL ROD     			BNORM 	BN2   	BN2A        	1520204	EU  										RUDDER	DAMAGED         	I				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	17	131JL	25031				225				AFTER TAKEOFF THE PILOT NOTICED THAT THE RUDDER HAD TO MUCH PLAY IN FLIGHT.  HE LANDED AND TAXIED BACK IN.  UPON INSPECT	ION THE RUDDER CONTROL ROD WAS FOUND TO BE DAMAGED, FROM A WIND STORM THE NIGHT BEFORE.  TO PREVENT REOCCURANCE, THE AIR	CRAFT RUDDER SHOULD BE LOCKED IN PLACE AFTER EACH FLIGHT.				1	H	7	2 	3O				A17EU   					 
2006070500340	20060705	00340	EU  	2006	7	5	2006FA0000639    	1	20060525	G	7603	L810BQ54	SOLENOID        			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					THROTTLE SYS	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	186AE					3872	22484			WHILE PERFORMING CHECK OF TWIST GRIP SOLENOID, ENGAGED SOLENOID BY PLACING THE AUTO/MAN SWITCH TO MAN MODE FOR A TOTAL O	F 10 MINUTES.  AFTER 10 MINUTE PERIOD HAD ELAPSED.  RETURNED AUTO/MAN SWITCH TO AUTO.  AFTER 15 SECONDS, MOVED AUTO/MAN 	SWITCH BACK TO MAN, PISTON FROM SOLENOID FAILED TO MOVE.  PISTON SHOULD HAVE RETRACTED IMMEDIATELY.  SOLENOID OVERHEATED	 AND MALFUNCTIONED.  RECOMMENDATION TO PREVENT RECURRENCE: REPLACING CURRENT PN OF SOLENOID WITH ONE THAT CAN EITHER RUN	 COOLER OR WITHSTAND THE HEAT.  (K)		1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006071800161	20060718	00161	NM  	2006	7	18	2006FA0000640    	1	20060705	G	5100	35006931	CARRIER ASSY    			DOUG  	MD80  	MD83        	3023681	NM  										UNKNOWN	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										CARRIER PN 3500693-1 FOUND CRACKED DURING PENERANT INSPECTION OF PART. PART WAS BEING INSPECTED FOR OVERHAUL REPAIR, CRA	CK IS BEYOND REPAIR LIMITS.					2	L	7	2 	4F			RT	        					 
2006071800168	20060718	00168	SO  	2006	7	18	2006FA0000641    	1	20060623	G	8011	MZ4204R	STARTER         			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	MISOVERHAULED   	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	3341P					231294				UPON RECEIPT OF STARTER, INITIAL INSPECTION REVEALED LOOSE HARDWARE ATTACHING FRONT HOUSING TO STATOR HOUSING. DISASSEMB	LED UNIT AND FOUND TWO PIECES OF SOLDER IN ARMATURE AREA; ONE APPROX .2500 X .7500 X .0625 INCH, THE SECOND APPROX .2500	 INCH X 2 INCHES X .0625 INCH. ALSO FOUND 1 OF 4 BRUSHES NOT SEATED IN BRUSH HOLDER AND NOT IN CONTACT WITH COMMUTATOR. 	FASTENER HOLES IN STATOR HOUSING WERE STRIPPED AS THOUGH FASTENERS WERE OVER-TORQUED TO SEAT FRONT HOUSING IN STATOR HOU	SING. RECOMMEND RE-EVALUATE OVERHAUL PROCEDURES, QUALITY CONTROL, AND POST-OVERHAUL TEST PROCEDURES. RECOMMEND ALL OPERA	TORS CAREFULLY INSPECT COMPONENTS RECEIVED BEFORE INSTALLING ON AIRCRAFT.	1	L	7	2 	3O	3	O		1A10    	E274				 
2006071900002	20060719	00002	EU  	2006	7	19	2006FA0000643    	1	20060609	G	2750	50B275103B	ROD             			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					TE FLAPS	CHAFED          	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	85TN	6712 				237				WHEN COMPLYING WITH SB, FOUND FLAP ROD LOCATED IN RT MAIN LANDING GEAR COMPARTMENT CHAFFED AT IB END.  FLAP ROD STIRRUP 	INSTALLED INCORRECT CAUSING ROD TO CHAFFE WHEN FLAPS ARE OPERATED.  REMOVED STIRRUP REPOSITIONED 180 DEGREES.  REINSTALL	ED AND REPLACED FLAP ROD WITH NEW.  (K)				2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2006071900016	20060719	00016	CE  	2006	7	19	2006FA0000644    	1	20060628	G	5311	10581002367	FRAME           			BEECH 	76    	76          	1153005	CE  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6720T	9119 				ME335				A-FRAME TUBE ASSY FAILED AT CORROSION PREVENTION PORT CAUSING LT MAIN GEAR COLLAPSE.  (K)						1	L	7	2 	3O				A29CE   					 
2006071800171	20060718	00171	CE  	2006	7	18	2006FA0000646    	1	20060628	G	5343	20410201	SUPPORT         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					MLG	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	177R	4400 				177RG0955				MLG ACTUATOR SUPPORT WEB BROKEN AND CRACKED.  (K)						1	H	7	1 	3O	3	O		A20CE   	1E10				 
2006071900003	20060719	00003	CE  	2006	7	19	2006FA0000647    	1	20060628	G	3233	20410202	PIN             			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					MLG ACTUATOR	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	177R	4400 				177RG0955				ACTUATOR RETAINING PIN, FRACTURED.  (K)						1	H	7	1 	3O	3	O		A20CE   	1E10				 
2006071900008	20060719	00008	CE  	2006	7	19	2006FA0000648    	1	20060614	G	2797	35823071	CONNECTOR       			BEECH 	MU300 	400A        	1155402	CE  										WIRE HARNESS	DAMAGED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	907JE					RK107				INVESTIGATED REPORT OF FLAP ASYMMETRY ANNUNCIATOR LIGHT FLICKERING IN-FLIGHT.  FOUND WIRE C458A22 ROUTED SO THAT EXCESSI	VE WIRE TENSION AT P156 PLUG WAS CAUSING INTERMITTENT CONTACT WITH A156 PC BOARD J1 CONNECTOR.  REROUTED WIRING AS REQUI	RED FOR REVEALING WIRE TENSION AT P156 PLUG.  FLAP ASSYMETRY FUNCTIONAL TEST SATISFACTORY.  (K)				2	H	7	2 	4F			RT	A16SW   					 
2006071900017	20060719	00017	CE  	2006	7	19	2006FA0000649    	1	20060622	G	2130	1013840283	SWITCH          			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					CABIN PRESSURE	OUT OF LIMITS   	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	261GB	4490 				LJ1119				DURING SCHEDULED 12 MONTH TEST OF CABIN ALTITUDE WARNING SYSTEM FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM.  	REPLACED PN 1013384028-3 SWITCH ASSY.  CABIN ALTITUDE WARNING TESTS WITHIN SPECIFIED SERVICE LIMITS ON RETEST.  SUGGEST 	A SB BE ISSUED TO REPLACE OLDER PN BAROMETRIC SWITCHES THAT TEND TO FAIL BETWEEN TEST PERIODS WITH MORE RELIABLE SWITCHE	S.  (K)			1	L	7	2 	3T	4	T		3A20    	E4EA				 
2006071800159	20060718	00159		2006	7	18	2006FA0000650    	4	20060620	G	2312	CI108	ANTENNA         			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FUSELAGE	DEBONDED        	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	731TA					RK273				INVESTIGATED PILOT REPORT OF LOSS OF NR 1 AND NR 2 VHF COMMUNICATION RADIOS WHEN FLYING IN PRECIPITATION.  IAW P-STATIC 	TESTING FOUND POOR NR 1 AND NR 2 VHF ANTENNAS BONDS TO FUSELAGE.  CLEANED, REBONDED AND REINSTALLED ANTENNAS.  ALSO INST	ALLED LT FUEL VENT LINE BONDING JUMPER.  P-STATIC TESTS AND OPERATIONAL TESTS SATISFACTORY AFTER REPAIRS.  SUGGEST VHF A	NTENNAS BE REMOVED AND CLOSELY INSPECTED AT SCHEDULED INTERVALS, SUCH AS AN INITIAL 5000 HR OR 10 YEAR INSPECTION, FOLLO	WED BY RECURRING 1200 HR OR 2 YEAR INTERVALS (IN CONUNCTION WITH C-CHECK INSPECTIONS).		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006072100298	20060721	00298	NE  	2006	7	21	2006FA0000651    	2	20060628	G	7250	3028601	BLADE           								PWA   	JD15  	JT15D1A     	 	NE  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		2818 					PCE76791			DURING POST LEASE INSPECTION, FOUND 1 HIGH TURBINE BLADE SEPARATED AT MID SPAN.  APPARENTLY NO OPERATIONAL PROBLEMS.  MF	G HAS PRODUCED REPLACEMENT BLADES UNDER SPARE PARTS BULLETIN 75.  (K)										4	F			E25EA				 
2006071100112	20060711	00112	CE  	2006	7	11	2006FA0000652    	1	20060601	G	2620		GAUGE           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					FIRE BOTTLE	BROKEN          	B			KW3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	456Q					282				THIS THE THIRD FIRE BOTTLE FOUND, ON 2 DIFFERENT AIRCRAFT WITH THE PRESSURE GAUGE SCALE BROKEN FREE FROM ITS MOUNTED POS	ITION.  THE RESULT WAS A FALSE INDICATION OF AGENT (HALON CBRF3) PRESENT INSIDE THE BOTTLE.  THE LOCAL QA MANAGER IS LAU	NCHING A FORMAL INVESTIGATION WITH THE MFG QA.  FORTUNATELY THIS AC WAS NOT INVOLVED IN AN ACCIDENT OR INCIDENT.  GOOD R	OOT CAUSE ANALYSIS AND CRITICAL THOUGHT FOUND THIS DEFECT.  (K)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006072100132	20060721	00132		2006	7	21	2006FA0000653    	2	20060626	G	7414			SLICK       																		B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					05111170					HIGH MAGNETO DROP.  (K)																			 
2006071900006	20060719	00006		2006	7	19	2006FA0000654    	1	20060621	G	8120	4066109005	TURBOCHARGER    																	ENGINE	LEAKING         	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										LEAKING BETWEEN HOT AND COLD SECTION.  (K)																			 
2006071800165	20060718	00165	GL  	2006	7	18	2006FA0000655    	1	20060608	G	3210	750B	POWERPACK       			BLANCA	1419  	1419        	1220402	GL  	LYC   	O435  	O435A       	41516	EA  					LANDING GEAR	STUCK           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	6561N					2014				RELIEF VALVE IN LANDING GEAR POWER PACK WAS STUCK.  WOULD NOT ALLOW LANDING GEAR HYDARULIC SYSTEM PRESSURE TO BE RELIEVE	D TO ALLOW GEAR TO EXTEND.  RESULT GEAR UP LANDING.  POST INCICENT TESTING VALVE WORKED NORMALLY. (K)					1	L	7	1 	3O	3	O		1A3     	E228				 
2006071800166	20060718	00166	NE  	2006	7	18	2006FA0000656    	2	20060620	G	7200	TFE73160	ENGINE          			AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE73160    	 	NE  					NR 1	DAMAGED         	G				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			SO	19	977LP	1317 				77	P112347			AT FL350, AIRCRAFT EXPERIENCED A LOUD BANG AND FAILURE OF NR 1 ENGINE (ITT WENT TO RED AND N1 APPROXIMATELY 20 PERCENT).	  ENGINE WAS SHUTDOWN.  DURING DESCENT EXPERIENCED VIBRATION IN AIR FRAME AND CONTROL COLUMN.  POST FLIGHT INSPECTION RE	VEALED EXTENSIVE DAMAGE TO THE NR 1 ENGINE REAR TURBINE BLADES AND COOKIE CUTTER.  NO EXTERNAL DAMAGE WAS NOTED.  ENGINE	 WAS REPALCED.  (K)			2	L	7	3 	4F	4	F	RT	A46EU   	E1NM				 
2006072100156	20060721	00156	NM  	2006	7	21	2006FA0000657    	1	20060720	G	5751	65192613	SUPPORT         			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D5       	52046	NE  					LT AILERON	CRACKED         	B			NP1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	932UP	53694				19856				DURING C-CHECK ROUTINE INSPECTION A 1 INCH CRACK (APPROX) WAS FOUND IN LT OB AILERON LOCKOUT MECHANISM SUPPORT ASSY CAST	ING IN THE RADIUS AREA OF THE AILERON CRANK PIVOT POINT.  SUPPORT ASSY IS BEING REPLACED BY ASSY PN 65-2177613. (K)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006071900004	20060719	00004	SO  	2006	7	19	2006FA0000658    	2	20060710	G	7313	652312112E	NOZZLE          			TCRAFT	BC    	BC12D       	8850316	GL  	CONT  	O550  	IO550N      	17042	SO  					FUEL SYSTEM	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	716B					7919				DURING MAINTENANCE THE MECHANIC WAS REPLACING THE FUEL INJECTION NOZZLES DUE TO THE REQUEST OF THE OWNER.  THE OWNER WAN	TED TO INSTALL A NEW KIT THE POSITION-TUNED FUEL INJECTION NOZZLES IAW THE ID SID05-7.  DURING THE INSTALLATION OF THESE	 NOZZLES 1 CRACKED PRIOR TO REACHING THE TORQUE VALUE AS LISTED IN SID05-7.				1	H	7	1 	3O	3	O		A696    	E3SO				 
2006071900020	20060719	00020	EA  	2006	7	19	2006FA0000660    	2	20060710	G	7414		BUSHING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					MAGNETO	FAILED          	D				B				EMER. DESCENT           				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	07	70746	469  	469  		H279705FR	3240521				MAGNETO'S DISTRIBUTOR GEAR BUSHING FAILED RESULTING IN AN ACCIDENT. MAGNETO LAST OVERHAULED EIGHT YEARS BEFORE. DFW06LA1	72					1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006072500183	20060725	00183		2006	7	25	2006FA0000662    	1	20060629	G	6510	538715	SHAFT           																	TAIL ROTOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										MAGNETIC PARTICLE INSPECTION 7 PCS WITH TRANSVERSE CRACKS INDICATIONS ON O.D. OF THE PART																			 
2006071800170	20060718	00170	CE  	2006	7	18	2006FA0000665    	1	20060711	G	3220		LANDING GEAR    			BEECH 	35    	35BEECH     	1151502	CE  										NOSE	COLLAPSED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99						D2053				NOSE LANDING GEAR COLLAPSED.						1	L	7	1 	3O				A777    					 
2006072500239	20060725	00239	SO  	2006	7	25	2006FA0000666    	2	20060623	G	8550	629218	IMPELLER        			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C401   	GL  	OIL SYSTEM	MISMANUFACTURED 	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	50901	38   				U20601951	532305	972059		INSTALLED NEW ENGINE  FOLLOWED RECOMMENDED PROCEDURES FOR BREAK IN.  REMOVED & CUT OPEN OIL FILTER AT 1.4 HRS TTSN, AT 7	.9HRS, & AT 24.7HRS. NORMAL PRACTICE WITH A NEW OR OVERHAULED ENGINE. EACH TIME FILTERS WERE NORMAL FOR A NEW ENGINE.  A	CFT DUE A 100 HR INSPECTION AT 38.9HRS TTSN. DURING INSPECTION, EXCESSIVE METAL APPEARED TO BE BRASS NOTED IN OIL FILTER	. TOOK OFF STARTER DRIVE & FOUND NO PROBLEMS. TOOK OFF ROCKER COVERS TO SEE IF A ROCKER ARM BUSHING BAD. DISCOVERED THAT	 BUSHINGS IN OIL PUMP DRIVEN IMPELLER EXCESSIVELY WORN.  IMPELLER WOULD CONTACT AN EDGE WITHIN PUMP. RECEIVED NEW PUMP A	SSY. BEFORE INSTALLING PUMP PREFORMED DIMENSIONAL INSPECT OF IMPELLER & SHAFT, WITHIN NEW PARTS LIMITS. FLEW THE ACFT FO	1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2006071800173	20060718	00173	EA  	2006	7	18	2006FA0000667    	2	20060707	G	7314	15473	PUMP            			AMTR  	VANRV4	VANSRV4     	       	GL  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	FUEL SYS	FAULTY          	G				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			GL	11	342MG	19   				1863	L136451A			T/O ROLL OK, ENG STARTED LOSING PWR JUST AFTER T/O AT APROX 150 FT, DETECTED A SLIGHT MISS OR LOSS OF PWR, MADE A SHARP 	LT TURN , ENG CONTINUED TO LOSE PWR, SWITCHED ON BOST PUMP AT THIS TIME, ENG SEEMED TO RESPOND FOR A SECOND, BUT CONTINU	ED TO LOSE PWR, MADE ANOTHER LT, LANDED, PULLED AC BACK TO HANGER.  AC HAS VISION VM1000 INSTRUMENT.  CKD LAST FLT READI	NGS, FUEL PRES LOW 18 PSI, HIGH OF 29 PSI. RESTARTED ENG, IDLE WAS OK, FUEL PRESS WAS JUMPING FROM 20 TO 31 PSI.  PWR WA	S INCREASED TO FULL PWR, HELD APROX 30 SECONDS, ENG STARTED LOSING PWR, BOOST PUMP ON NO CHANGE. TURNED BOOST PUMP OFF, 	WATCHED FUEL PRESS, IT WAS JUMPING FROM 19 TO 31 PSI THEN DOWN TO 23.   BYPASSED ENG DRIVEN PUMP AND ENG RAN, HELD PWR.	1	L	7	1 	3O	3	O		EXPA1L71	1E10	5	C	P43GL	 
2006071800181	20060718	00181		2006	7	18	2006FA0000668    	4	20060630	G	6113		SPINNER         			BEECH 	300   	300BEECH    	1152930	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	RT PROPELLER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	603WM					FA198		FWA2935		RT PROPELLER WAS OVERHAULED AND INSTALLED IN THE RT POSITION.  ENGINE RAN TO LEAK CHECK AND FUNCTIONAL CHECK PROPELLER S	YSTEM ON THE RT SIDE AND TO FULL POWER FOR APPROXIMATELY 60 SECONDS. A SLIGHT CHANGE IN THE HARMONICS WAS NOTED BUT NOT 	A SIGNIFICANT CHANGE.  AIRCRAFT RETURNED TO HANGER AFTER THE MAINTENANCE RUN UP AND A LEAK CHECK WAS PERFORMED.  IT WAS 	NOTED THAT ONE BLADE HAD A LARGE AMOUNT OF GREASE ON THE BLADE FACE.  THE SPINNER WAS REMOVED AND IT WAS FOUND BY VISUAL	 INSPECTION THAT A BLADE CLAMP BOLT HAD BROKEN AT THE HEAD.  THE HEAD OF THE BOLT WAS RECOVERED LODGED IN THE HUB AND BU	LKHEAD AREA.  THE BOLT P/N ACA-1372.	2	L	7	2 	4T				A24CE   		6	C	P56GL	 
2006071900011	20060719	00011	CE  	2006	7	19	2006FA0000669    	1	20060712	G	3211	NAS15288	CONE BOLT       			CESSNA	188   	188B        	2073007	CE  										LT MLG	FAILED          	G				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17	4996R					18802483T				LT LANDING GEAR STRUT IB ATTACHMENT BOLT HEAD POPPED OFF DURING TAXI CAUSING PARTIAL GEAR COLLAPSED						1	L	7	1 	3O				A9CE    					 
2006071900018	20060719	00018		2006	7	19	2006FA0000670    	4	20060622	G	3460		COMPUTER        			AMD   	FALC50	FALCON2000  	2730170	NM  										FLT MANAGEMENT	INTERMITTENT    	B				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CR	CRUISE         	1			SW	11	620MS					31				ALL 3 FMS INTERMITTENTLY RESETS IN FLIGHT WITH INFORMATION RETURNING AT RANDOM.						2	K	7	2 	4F			RT	A50NM   					 
2006071900019	20060719	00019		2006	7	19	2006FA0000671    	2	20060627	G	7414	6364	MAGNETO         																	ENGINE	FAILED          	B			S4CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25										DEFECTIVE COIL WINDINGS FOUND. SECONDARY READINGS INDICATE DISCONTINUOUS INTERNAL CONDUCTORS. READINGS VARIED FROM NO RE	SISTANCE (INDICATING AN OPEN CIRCUIT) TO VERY HIGH, OUT OF TOLERANCE OHMS OF RESISTANCE (20 TIMES NORMAL). OHMMETER WAS 	CALIBRATED RECENTLY, CROSS REFERENCED AGAINST OTHER COILS TO VERIFY TEST EQUIPMENT USED, WAS STILL FUNCTIONING DURING TH	IS INSP.  OPERATOR OF THIS COMPONENT REPORTED NO DETECTABLE OPERATIONAL MALADIES. SECONDARY WINDING FAILURES MAY AFFECT 	ENG STARTING, PRODUCE MISFIRING, OR NON-OPERATIONAL IGNITION FROM THE AFFECTED MAGNETO. O.E.M. TYPE (TORQUE SEAL) PRODUC	T INTACT AT TIME OF INSP, INDICATING NO INTERNAL MAINT OR INSP SINCE MAGNETO WAS MANUFACTURED.														 
2006071900086	20060719	00086	CE  	2006	7	19	2006FA0000672    	1	20060104	G	3260	IN4001	DIODE           			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	WARNING UNIT	INOPERATIVE     	G				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			SO	19	LVWHD					21061943	270473R	900308		DURING LANDING, FORGOT TO EXTEND THE LANDING GEAR AND GEAR UP LANDING WAS CARRIED OUT.  ACCIDENT INVESTIGATION INCLUDED 	A SATISFACTORY OPS CHECK OF LANDING GEAR RETRACTION/EXTENSION SYSTEM, BUT WARNING HORN FAILED TO OPERATE.  AFTER DISASSE	MBLING THE WARNING UNIT ASSEMBLY, A BURNED DIODE WAS FOUND OUT.  THEN CONSULTED SM AND REALIZED THAT THERE IS NOT A SPEC	IFIC ITEM TO CHECK THE OPERATION OF THE GEAR WARNING HORN.  THIS SITUATION ALSO TAKES PLACE WITH MFG SRM.  GEAR INDICATO	R LIGHT AND WARNING HORN-CHECK FOR OPERATION (GEAR EXTENDED AND RETRACTED).		1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
2006072100130	20060721	00130	WP  	2006	7	21	2006FA0000673    	2	20060316	G	7260	31080412	BEARING         	GARRTT      		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE	CORRODED        	B			X2ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	438MA				P44090C	AC721B	P44090C			DUE TO CHIP LIGHT ILLUMINATION. TEST RUN COMPLETED. TORQUE SYS CALIBRATION AND ALL REQUIRED FUNCTIONAL/LEAK CHECKS CARRI	ED OUT.  NEW TORQUE DATA ISSUED.  NTS TRIF CK REQUIRED PRIOR TO RETURN TO SERVICE.  PERFORMED SOAP SAMPLE WITHIN 10-25 O	PERATING HRS.  FAILURE OF ACCY GEAR ASSY BRG WAS ATTRIBUTED TO RUST PITTING ON ROLLING ELEMENT SURFACES.  SIMILAR PITTIN	G WAS FOUND ON FWD PROP SHAFT BRG WITH SPALLING.  LOOSENING OF ONE PLANETARY PIN CAUSED CHAFFING OF PIN AND SCORING OF C	ARRIER.  ALL REMAINING BRGS IN ENGINE WERE DISASSEMBLED FOR INSP.  ALL BRGS WITH RIVETED CAGES WHICH DID NOT ALLOW FOR I	NSP WERE REPLACED AS A PRECAUTIONARY MEASURE DUE TO SUSPECTED RUST PITTING.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2006072100371	20060721	00371	CE  	2006	7	21	2006FA0000674    	1	20060612	G	2720	031019613	SPRING          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					RUDDER PEDALS	BROKEN          	B			C85R	O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NE	01	94467	677  				15285682				FLIGHT INSTRUCTOR WAS DEMO-ING A STALL TO STUDENT.  MANUVER STARTED AT 2700 FT.  CONTROLS LOCKED UP- AC WENT NOSE DOWN. 	 FLT INST RECOVERED AT 700 FT.  (K)					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006072100131	20060721	00131	EA  	2006	7	21	2006FA0000675    	2	20060703	G	8540		BUSHING         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	SPUN            	B			X18R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	3860H	932  				241044	L2178051A			FOUND DURING ANNUAL INSP, AN ALUMINUM BUSHING THAT IS LOCATED IN  ACCESSORY CASE, WHERE MAGNETO DRIVE GEAR IS LOCATED HA	D BECOME LOOSE IN CASE AND SPUN.  FOUND THIS PROBLEM, WERE NOT ABLE TO INSTALL MAGNETO  CORRECTLY, WHEN MAGNETO WAS INST	ALLED, IMPULSE COUPLING WOULD SOMETIMES NOT ENGAGE.  FOUND AT LAST OVERHAUL, ACCESSORY CASE WAS SENT OUT FOR OVERHAUL TO	 ECI.  TALKING TO TEAR DOWN PERSONNEL, SAID THAT THIS IS AN APPROVED REPAIR TO INSTALL AN ALUMINUM BUSHING IF IT IS DONE	 CORRECTLY, THERE SHOULD HAVE BEEN A DRILLED HOLE IN THE BUSHING FOR LUBRICATION, BUT NO HOLE. THUS NOT ALLOWING LUBRICA	TION TO BUSHING AREA, ALLOWING EXCESSIVE WEAR AND PART FAILURE.  SUGGEST WELDING AREA AND DRILLING  NEW BOSS.  (K)	1	L	7	1 	3O	3	O		2A3     	1E10				 
2006072100163	20060721	00163	EU  	2006	7	21	2006FA0000676    	1	20060706	G	6123	A3496	SPRING          			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	FEATHER SYSTEM	BROKEN          	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		15619	3801 					EV755		FEATHERING SPRING WAS FOUND TO BE BROKEN WHILE STILL INSTALLED IN SPRING KIT.  THE SPRING BROKE IN 3 DIFFERENT PIECES.  	KIT WAS DISASSEMBLED AND INSPECTED FOR FURTHER DAMAGE.  NOTE:  PROPELLER WAS REMOVED FROM SERVICE 08-DEC-00.  (K)					2	H	7	2 	4T				A41EU   		6	C	P44GL	 
2006072100137	20060721	00137	GL  	2006	7	21	2006FA0000677    	1	20060701	G	7820	14836001	MUFFLER         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					EXHAUST	DETERIORATED    	C			QRQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	752C					0421	686750			REPLACED LT MUFFLER ON AIRCRAFT DO TO THE DETERIORATED CONDITION OF THE SPARK ARRESTER INSIDE OF THE MUFFLER.  LT SIDE S	PARK ARRESTER MELTED AND FOLDED OVER.  LT MUFFLER, PN 14836001.  THE FIRST DETECT REPORT WAS FILED WHEN AC HAD A TT 682 	HRS.  BOTH LT AND RT SPARK ARRESTERS HAD FOLDED OVER AGAIN.  THATS 413 HRS SINCE LAST TIME.  RECOMMEND MANDITORY REPLACE	MENT AT A SPECIFIED TIME OR REDESIGN OF ARRESTERS.  (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006072500243	20060725	00243	SO  	2006	7	25	2006FA0000678    	1	20060713	G	3210	7521604	FORK            			PIPER 	PA42  	PA421000    	7104225	SO  	GARRTT	TPE331	TPE331*     	01514	WP  					LT MAIN GEAR	CRACKED         	D			FO7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4WE	1934 				425527041				PILOT REPORTED A LEAKING LT MAIN GEAR STRUT, BUT WAS LEAKING FROM JOINT BETWEEN ALUMINUM FORK ASSY AND CHROMED STEEL STR	UT TUBE.  STRUT DISASSEMBLED AND A RADIAL CRACK WAS FOUND, 2 INCH LOGN AND .5 INCH.  BELOW TOP OF ALUMINUM FORK ASSY.  A	 SERIOUS ACCIDENT COULD RESULT IF THE FORK ASSY DETACHED UPON LANDING.  NO DAMAGE OR HARD LANDINGS REPORTED.  (K)				1	L	7	2 	4T	3	T	RT	A23SO   	E2WE				 
2006072100330	20060721	00330	EA  	2006	7	21	2006FA0000679    	2	20060626	G	7260		CHIP DETECTOR   			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6   	PT6*        	52043	EA  					NR 1 ENGINE	CONTAMINATED    	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	15	413EV					36381	CPPSTH0691			AC EXPERIENCED NR 1 ENG CHIP LIGHT.  MASTER CAUTION WAS EXTINGUISHED, LIGHT WENT OUT.  ABOUT 2 SECONDS LATER LIGHT CAME 	BACK ON WITH MASTER CAUTION, WAS AGAIN EXTINGUISHED, WENT OUT THEN CAME BACK ON.  PILOT ELECTED RETURN TO BASE.  AFTER L	IGHT CAME ON AGAIN FOR 4TH OR 5TH TIME IN 2 MINUTES, PILOT DECIDED TO SECURE ENG, FUEL VALVES AND BOOST PUMPS WERE LEFT 	ON, IN EVENT THAT THEY NEED TO RESTART ENG.  ENG HAD JUST COME OUT OF 300 HR INSP, FLIGHT TO BASE, LANDING WAS UNEVENTFU	L.  MAINT WAS DISPATCHED, INSPECTED CHIP PLUGS, FOUND A SMALL SILVER ON PLUG.  SILVER WAS REMOVED, CHIP PLUG WAS REINSTA	LLED, SAFETY WIRED.  AC WAS 20 MINUTE RUN CHECK FOR ANY ADDITIONAL CHIP LIGHTS AND WAS RELEASED BACK INTO SERVICE.  (K)	1	G	7	2 	4U	3	T		H4SW    	E2NE				 
2006072100297	20060721	00297	CE  	2006	7	21	2006FA0000680    	1	20060622	G	2510	551900922	SEAT FRAME      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CHAIR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	982NA					5500345				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  CHAIR WAS REPAIRED IAW STRUCTURAL SEAT REPAIR.  (K)						1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006072100324	20060721	00324	CE  	2006	7	21	2006FA0000681    	1	20060601	G	5210	05170392	HANDLE          			CESSNA	206   	U206F       	2073333	CE  										REAR DOOR	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	736					U20601781				DOOR HANDLE WAS SPINNING INDEPENDENTLY OF THE MECHANISM FOR THE DOOR LATCH.  THE PORTION OF THE HANDLE WITH THE SPLINE I	S PRESSED INTO THE HANDLE.  THE PRESS FIT WAS DEFECTIVE ALLOWING THE HANDLE TO SPIN FREELY.  (K)					1	H	7	1 	3O				A4CE    					 
2006072400039	20060724	00039	SO  	2006	7	24	2006FA0000682    	2	20060717	G	8520		CRANKCASE       	CONT        		CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	7916Q	798  	798  		182575	401B0016	182575			FOUND A CRACK IN BOTH CASE HALF AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WERE FOUND	 ON AN INSPECTION OF ENGINE.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2006072400057	20060724	00057	SO  	2006	7	24	2006FA0000683    	2	20060717	G	8520		CRANKCASE       	CONT        		CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	7916Q	798  	798  		182575	401B0016	182575			FOUND A CRACK IN BOTH CASE HALVES AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WAS FOUN	D ON AN INSPECTION OF ENGINE.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2006072500185	20060725	00185	CE  	2006	7	25	2006FA0000684    	1	20060717	G	5551	04320052	FITTING         			CESSNA	150   	150M        	2071830	CE  	LYC   	O320  	O320E2D     	41508	EA  					RT STAB	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	7765U	5510 				15077837				ON PREFLIGHT INSP, APPLIED A +/- 5 LB UP AND DOWN FORCE ON RT STABILIZER TIP, HEARD A GRUNTING SOUND.   FURTHER INVESTIG	ATION REVEALED A SMALL RELATIVE MOTION BETWEEN STABILIZER  AFT FITTING, 0432005-2, AND FUSELAGE.   REMOVING NUT OPENED A	 0.020 INCH AIR GAP BETWEEN FITTING AND FUSELAGE. CLEANING GAP WITH A CLOTH DIDNT SHOW ANY METAL PARTICLES. THE FIX WAS	 TO FABRICATE A 0.020 INCH SHIM. THIS FITTING IS A VERY  RIGID CHANNEL SUCH THAT IF THERE WAS AN AIR GAP IT MAY NOT CLAM	P ON TO THE FUSELAGE FITTING HARD ENOUGH WITH BOLT TORQUE. THIS MAY NOT BE A DEFECTIVE PART, JUST TOLERANCE STACK UP.  L	EFT SIDE FITTING WAS CHECKED.  IT REQUIRED A 0.010 INCH SHIM.  THESE 2 AFT MNT POINTS ARE LOAD CYCLED MORE FREQUENTLY.	1	H	7	1 	3O	3	O		3A19    	E274				 
2006072500186	20060725	00186	CE  	2006	7	25	2006FA0000685    	1	20060717	G	5551	04320052	FITTING         			CESSNA	150   	150M        	2071830	CE  	LYC   	O320  	O320E2D     	41508	EA  					RT STAB	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	7765U	5510 				15077837				ON PREFLIGHT INSP, APPLIED A +/- 5 LB UP AND DOWN FORCE ON RT STABILIZER TIP AND HEARD A GRUNTING SOUND.   FURTHER INVES	TIGATION REVEALED A SMALL RELATIVE MOTION BETWEEN STABILIZER AFT FITTING, 0432005-2, AND FUSELAGE.  REMOVING NUT, OPENED	 A 0.020 INCH AIR GAP BETWEEN THE FITTING AND FUSELAGE.  CLEANING GAP WITH A CLOTH DIDNT SHOW ANY METAL PARTICLES. FIX 	WAS TO FABRICATE A 0.020 INCH SHIM.  FITTING IS A VERY  RIGID CHANNEL THAT IF THERE WAS AN AIR GAP IT MAY NOT CLAMP ON T	O FUSELAGE FITTING HARD ENOUGH WITH BOLT TORQUE.  THIS MAY NOT BE A DEFECTIVE PART, JUST TOLERANCE STACK UP.  LT SIDE FI	TTING WAS CHECKED.  IT REQUIRED A 0.010 INCH SHIM.THESE 2 AFT MOUNTING POINTS ARE LOAD CYCLED MORE FREQUENTLY.	1	H	7	1 	3O	3	O		3A19    	E274				 
2006072400086	20060724	00086	GL  	2006	7	24	2006FA0000686    	3	20060714	G	6110	ACA1373	NUT             													HARTZL	HCB4M	HCB4M       	GL  	PROPELLER	FAILED          	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09								FWA2178		WHEN TORQUING OUTER CLAMP NUT P/N ACA1373, 1 EACH NEW OUTER CLAMP NUT THREADS FAILED BEFORE REACHING SPECIFIED TORQUE. P	ROPELLER WAS BEING REASSEMBLED DURING OVERHAUL. ASSEMBLED USING CALIBRATED TOOLS AND NEW HARDWARE.															6	C	P56GL	 
2006072500249	20060725	00249	CE  	2006	7	25	2006FA0000687    	1	20060714	G	5347		SEAT TRACK      			CESSNA	180   	180A        	2072604	CE  											DAMAGED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	180LG					32693				A BOLT WAS INSTALLED ON THE FORWARD MOST HOLE ON THE SEAT TRACK FOR USE AS A FORWARD STOP.  THE SEAT COULD BE POSITIONED	 OVER THE HOLE AND THE SEAT LOCKING PIN WOULD ENGAGE, BUT NOT FULLY DUE TO THE BOLT PASSING THROUGH THE HOLE.  THE MFG D	ESIGN DOES NOT ALLOW THE PIN TO ENTER THROUGH THE SEAT STOP HOLE.				1	H	7	1 	3O				5A6     					 
2006072500252	20060725	00252	CE  	2006	7	25	2006FA0000688    	1	20060714	G	5347		SEAT            			CESSNA	180   	180A        	2072604	CE  											MISINSTALLED    	H				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			WP	23	180LG					32693				A BOLT WAS INSTALLED ON THE FORWARD MOST HOLE ON THE SEAT TRACK FOR USE AS A FORWARD STOP.  THE SEAT COULD BE POSITIONED	 OVER THE HOLE AND THE SEAT LOCKING PIN WOULD ENGAGE, BUT NOT FULLY DUE TO THE BOLT PASSING THROUGH THE HOLE.  THE MFG D	ESIGN DOES NOT ALLOW THE PIN TO ENTER THROUGH THE SEAT STOP HOLE.				1	H	7	1 	3O				5A6     					 
2006072400043	20060724	00043	SO  	2006	7	24	2006FA0000693    	1	20060718	G	2910		CIRCUIT BREAKER 			PIPER 	PA46  	PA46500TP   	7104622	SO  										COCKPIT	OPEN            	B				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			EA	07	53667					4697158				DURING ROUTINE FLIGHT, GEAR WOULD NOT EXTEND UPON SELECTING GEAR LEVER DOWN. FOUND 25 AMP HYDRAULIC PUMP CIRCUIT BREAKER	 OPEN. RESET BREAKER AND GEAR OPERATED NORMALLY. GEAR OPERATED NORMAL FOR SEVERAL CYCLES AFTERWARD. HYDRAULIC SYSTEM WAS	 INSPECTED, INCLUDING CHECK FOR EXCESSIVE CURRENT DRAW WITH NO DISCREPANCY NOTED. INITIAL CURRENT DRAW ON PUMP SPIKES AB	OVE THE 25 AMP LIMIT OF CB BUT IS WITHIN THE OPERATING LIMITS OF THE CB.THIS IS SECOND TIME THIS PROBLEM HAS BEEN NOTED 	ON THIS AIRCRAFT.  THIS SAME SCENARIO HAS BEEN NOTED ON T2 OTHER AIRCRAFT. RECOMMEND REPLACEMENT OF CB TO HIGHER CURRENT	 ( 30 AMPS MINIMUM). THIS MAY REQUIRE PARTIAL REWIRING OF SYSTEM DUE TO INCREASED CURRENT.	1	L	7	1 	3O			RT	A25SO   					 
2006072400046	20060724	00046	SO  	2006	7	24	2006FA0000694    	1	20060718	G	2910		CIRCUIT BREAKER 			PIPER 	PA46  	PA46500TP   	7104622	SO  										COCKPIT	OPEN            	B				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			EA	07	53667					4697158				DURING ROUTINE FLIGHT, GEAR WOULD NOT EXTEND UPON SELECTING GEAR LEVER DOWN. FOUND 25 AMP HYDRAULIC PUMP CIRCUIT BREAKER	 OPEN. RESET BREAKER AND GEAR OPERATED NORMALLY. GEAR OPERATED NORMAL FOR SEVERAL CYCLES AFTERWARD. HYDRAULIC SYSTEM WAS	 INSPECTED, INCLUDING CHECK FOR EXCESSIVE CURRENT DRAW WITH NO DISCREPANCY NOTED. INITIAL CURRENT DRAW ON PUMP SPIKES AB	OVE THE 25 AMP LIMIT OF CB BUT IS WITHIN THE OPERATING LIMITS OF THE CB.THIS IS SECOND TIME THIS PROBLEM HAS BEEN NOTED 	ON THIS AIRCRAFT.  THIS SAME SCENARIO HAS BEEN NOTED ON TWO OTHER AIRCRAFT. RECOMMEND REPLACEMENT OF CB TO HIGHER CURREN	T ( 30 AMPS MINIMUM). THIS MAY REQUIRE PARTIAL REWIRING OF SYSTEM DUE TO INCREASED CURRENT.	1	L	7	1 	3O			RT	A25SO   					 
2006072500196	20060725	00196	CE  	2006	7	25	2006FA0000695    	1	20060202	G	3040		CONNECTOR       			BEECH 	200   	200BEECH    	1152920	CE  										WINDSHIELD HEAT	FAILED          	B			HBKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	440WA					BB700				WHILE INVESTIGATING PILOTS AND CO-PILOTS WINDSHIELD HEAT BEING INOPERATIVE, CONNECTION AT DC PWR DISTRIBUTION PNL WAS AT	 FAULT.  USING MFG WIRING DIAGRAM, CONNECTIONS AT JUNCT 195 AND PLUG 195 HAD BEEN SUBJECTED TO EXCESS HEATING TO POINT T	HAT WIRE AND WIRING INSULATION BEING BURNED AS A RESULT CONNECTIONS BEING LOOSE.  STRAIN RELIEF FOR PLUG DOES NOT ENSURE	 A SECURE CONNECTION FOR 8 AWG WIRE TO MAINTAIN A POS CONTACT.  END RESULT IS CONNECTIONS WORK LOOSE, BEGIN TO ARC. ARCI	NG GENERATES HEAT. BURNING WIRE, CAUSING SOCKET CONNECTION, PIN TO BECOME BRITTLE AND WEAK.  THIS FAILURE OF CONNECTION 	RENDER WINDSHIELD HEAT SYS INOPERATIVE.  HEAT GENERATED FROM CONNECTION FAILURE CREATES A POTENTIAL FIRE HAZARD FOR AC.	1	L	7	2 	4T				A24CE   					 
2006072500244	20060725	00244	CE  	2006	7	25	2006FA0000696    	1	20060210	G	2497		WIRE            			MTSBSI	MU300 	MU300       	5780602	CE  	PWA   	JT15  	JT15D4      	52112	NE  						BURNED          	B			BG5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	109PW					AO46SA	PCE70800			SHORT CIRCUIT, WIRES BURNED ON LT CNTRL JUNCT BOX AREA.  DURING SCHEDULED B INSP IAW MM, FOUND WIRES BURNED, DAMAGED ON 	CABLE LOOM CONNECTOR P AND J 230.  DUE TO SHORT CIRCUIT ON TRIPLE WIRES, INSULATION OF SHIELD TERM SUSPECT ON CABLES LOO	M CONNECTORS.  SB MUST BE APPLIED WHICH MODIFIES SHIELDS GROUND TERM RELOCATION.  ALL WIRES AT EFFECTED CONNECTORS TO BE	 IDENTIFIED, CIRCUITS CHECKED IAW AC WIRING DIAGRAM, CHECKED FOR CONTINUITY, INSULATION RESIST CHECKS ON ALL WIRES NOT O	NLY TO DETERMINE IF ANY OF SCREENED CABLES ARE BREAKING DOWN BUT ALSO NOT BREAKING DOWN TO ADJACENT CABLES FURTHER DOWN 	WIRING LOOM IN AREAS THAT CAN NOT BE VISUALLY INSP  DAMAGED WIRES REPAIRED, CONNECTORS REPLACED IAW MM.	2	H	7	2 	4F	4	F	RT	A14SW   	E1NE				 
2006072500205	20060725	00205	CE  	2006	7	25	2006FA0000705    	1	20060720	G	6100	9696001123	LINE            			BEECH 	58    	58          	1152740	CE  										LT PROPELLER	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	870JA	1717 				TH2036				LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED BY THE SHROUD FOR THE FUEL PUMP HOSE.						1	L	7	2 	3O				3A16    					 
2006072500216	20060725	00216	CE  	2006	7	25	2006FA0000706    	1	20060720	G	6100	9696001123	LINE            			BEECH 	58    	58          	1152740	CE  										LT PROPELLER	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	874JE	1519 				TH2045				LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED BY THE SHROUD FOR THE FUEL PUMP HOSE.						1	L	7	2 	3O				3A16    					 
2006072500218	20060725	00218	CE  	2006	7	25	2006FA0000707    	1	20060720	G	6100	9696001123	LINE            			BEECH 	58    	58          	1152740	CE  										LT PROPELLER	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	876JK	1449 				TH2053				LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED THROUGH BY THE SHROUD FOR THE FUEL PUMP HOSE. OIL LEAK WAS OBSERVED. THE CA	USE WAS DETERMINED AND REMEDIED BEFORE LOSS OF SIGNIFICANT AMOUNT OIL.					1	L	7	2 	3O				3A16    					 
2006072400085	20060724	00085	SO  	2006	7	24	2006FA0000710    	2	20060720	G	8520		CRANKCASE       	CONT        	IO550B      	BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	25	8296R	1320 			8288849R	E2763	828849R			ENGINE CASE CRACKED NEAR (7TH) STUD BETWEEN CYLINDERS 2 AND 4.  PROBLEM FOUND WHEN INVESTIGATING OIL LEAK.						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2006080300004	20060803	00004	EU  	2006	8	3	2006FA0000714    	1	20060713	G	5543	80483205801	ATTACH FITTING  			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A6       	52043	EA  					RUDDER TRIM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	29JS	923  				1046				ON POST MAINTENANCE WALKAROUND INSPECTION, FOUND RUDDER TRIM TAB LOWER CONTROL ROD ATTACH LUG RADIALLY CRACKED.  UNKNOWN	 CAUSE, NO OTHER DAMAGE OR DEFECTS NOTED.  (K)					1	H	7	2 	3O	3	T	RT	A59EU   	E4EA				 
2006080200185	20060802	00185	CE  	2006	8	2	2006FA0000715    	1	20060619	G	3297	TVA209	CAPACITOR       			BEECH 	23    	B24R        	1151253	CE  										GLARE SHLD FWD	EXPLODED        	B			BFYS	A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			NE	05	6978R					MC324				OPERATOR HAD DRAWN THE BATTERY CHARGE DOWN CONSIDERABLY TRYING TO START THE AIRCRAFT.  PILOT REPORTED HEARING A POP AND 	REPORTED SMOKE ING CABIN.  TAKEOFF WAS ABORTED AND AN EMERGENCY (GEAR UP) LANDING WAS MADE RESULTING IN SUBSTANTIAL DAMA	GE TO AC.  ON INSPECTION A CAPACITOR WAS FOUND SECURED TO THE REAR OF THE AUDIO CONTROL PANEL, THIS CAPACITOR WAS INSTAL	LED IN THE KN 4 CB WIRE.  CAPACITOR HAD END BLOWN OUT AND ALL ITS CONTENTS SPLATTERED ON WINSHIELD AIR DUCT.  LOW BATTER	Y CHARGE COUPLED WITH THE HIGH IN RUSH CURRENT DEMAND OF THE GEAR MOTOR OVER AND ABOVE THE NORMAL DEMANDS OF THE AVIONIC	S MOST LIKELY RESULTED IN AN OVER VOLTAGE CONDITION THAT CAUSED THE CAPACITOR TO EXPLODE.  (K)	1	L	7	1 	3O				A1CE    					 
2006080300049	20060803	00049	SW  	2006	8	3	2006FA0000716    	1	20060307	G	2622	344	EXTINGUISHER    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C30      	03013	GL  					COCKPIT	EXPLODED        	D			I22F	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	23	615LH					2263				A NEW 1.25 LB EXTINGUISHER MODEL 344, SN W-968052 CLASSIFICATION 2-B; C WAS INSTALLED IN THE AIRCRAFT ON MARCH 6, 2006. 	 IT WAS REMOVED OVERNIGHT AND REINSTALLED AT 8:50 AM ON MARCH 7, 2006.  AS THE HELICOPTER WAS STARTING, THE END EXPLODED	 OUT OF THE EXTINGUISHER, FIRING IT INTO THE CONSOLE.  THE TEMPERATURE IN THE COCKPIT WAS APPROXIMATELY 36 DEGREES C AND	 THE EXTINGUISHER WAS IN THE SHADE.  THE PRESSURE GAUGE WAS IN THE GREEN WHEN INSTALLED.  (K)			1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006080300008	20060803	00008	SO  	2006	8	3	2006FA0000717    	1	20060311	G	5712		RIB             			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					LEFT & RIGHT	CRACKED         	B			Q2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	8164D	5963 				348233086				DURING COMPLIANCE WITH SB, LT AND RT RIBS FOUND CRACKED AS SUSPECTED.  INSTALLED REPAIR KITS.  LT DRAG BRACE PIVOT, PN 3	9479002, ALSO FOUND CORRODED AND CRACKED.  THIS IS NOT PART OF SB INSPECTION.  (K)					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2006080300103	20060803	00103		2006	8	3	2006FA0000718    	4	20060713	G	2562	DMELT6	ELT             			CESSNA	210   	T210N       	2073456	CE  										CABIN	INOPERATIVE     	B			GFVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	178JD					21063351				FOUND ELT TOTALLY INOPERATIVE DURING ANNUAL INSPECTION, BATTERY VOLTAGE OK.  UNABLE TO DETERMINE IF IMPACT SWITCH WAS AL	SO INOPERATIVE.  (K)					1	H	7	1 	3O				3A21    					 
2006080300010	20060803	00010	SO  	2006	8	3	2006FA0000719    	2	20060601	G	8530		EXHAUST VALVE   			CESSNA	337   	337B        	2075706	CE  	CONT  	O360  	IO360CONT   	17025	SO  					NR 6 CYLINDER	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2362S					3370662				ENGINE RUNNING ROUGH.  COLD COMPRESSION CHECK SHOWED -0- COMPRESSION ON NR 6 CYLINDER.  AIR LEAKING PAST EXHAUST VALVE. 	 DISASSEMBLY REVEALED EXHAUST VALVE STUCK IN OPEN POSITION.  EVIDENCE OF PISTON STICKING EXHAUST VALVE.  THIS IS THE SEC	OND OCCURANCE OF THIS CONDITION ON THIS ENGINE.  (K)				1	H	7	2 	3O	3	O		A6CE    	E1CE				 
2006080300045	20060803	00045	SO  	2006	8	3	2006FA0000720    	2	20060515	G	8530		EXHAUST VALVE   			CESSNA	337   	337B        	2075706	CE  	CONT  	O360  	IO360CONT   	17025	SO  					NR 4	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2362S	275  			AC05AC028	3370662				ENGINE RUNNING ROUGH.  PERFORMED COLD COMPRESSION CHECK.  COMPRESSION WAS ZERO.  AIR LOOKING PAST EXHAUST VALVE.  REMOVE	D ROCKER ARM COVER, NOTED EXHAUST VALVE STICKING IN OPEN POSITION.  REMOVED CYLINDER.  PISTON HAD STRUCK EXHAUST VALVE. 	 REPLACED CYLINDER AND PISTON.  PISTON WAS DIFFERENT THAN ORIGINAL PN WAS  THE SAME, TOP OF PISTON WAS CONCAVE WHERE AS 	ORIGINAL PISTON WAS FLAT.  (K)			1	H	7	2 	3O	3	O		A6CE    	E1CE				 
2006080200276	20060802	00276	CE  	2006	8	2	2006FA0000721    	1	20060619	G	2520	5514551169	SEAT            			CESSNA	501   	501         	2076603	CE  										CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	501CF					5010128				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  ALSO, PREVIOUS INAPPROPRIATE REPAIR.  CHAIR WAS REPAIRED	 IAW STC, STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F				A27CE   					 
2006080300050	20060803	00050		2006	8	3	2006FA0000722    	2	20060725	G	7414	3975	MAGNETO         																	ENGINE	OUT OF TOLERANCE	B			S4CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25										OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH	 AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHM	S, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS IS	SUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SN DATE CODE SUGGE	STS THAT THIS MAGNETO WAS MANUFACTURED IN 1992.															 
2006080300099	20060803	00099		2006	8	3	2006FA0000723    	2	20060725	G	7414	3975	COIL            	SLICK       																MAGNETO	OUT OF TOLERANCE	B			S4CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25					92120190					OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH	 AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHM	S, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS IS	SUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SERIAL NUMBER DATE	 CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992.															 
2006080300101	20060803	00101		2006	8	3	2006FA0000724    	2	20060725	G	7414	3975	COIL            	SLICK       																MAGNETO	OUT OF TOLERANCE	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25					92120190					OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH	 AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHM	S, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS IS	SUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SERIAL NUMBER DATE	 CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992. THANK YOU.															 
2006080200053	20060802	00053	CE  	2006	8	2	2006FA0000725    	1	20060711	G	2710	0510105365	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERON	FRAYED          	B			7TFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2134M	2164 				172S9552				DURING AN ANNUAL INSPECTION OF THE RT WING, THE AILERON CROSSOVER CABLE WAS FOUND TO BE FRAYED AT THE WEAR BLOCK.  PROBA	BLE CAUSE IS THAT THE WEAR BLOCK IS CAUSING FRICTION AND WEAR ON THE CABLE.  A RECOMMENDED SOLUTION IS TO REMOVE THE WEA	R BLOCK.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006080200181	20060802	00181	SO  	2006	8	2	2006FA0000726    	1	20060720	G	3230		DRAG LINK       			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					RT MLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4233P					231730				DURING THE INVESTIGATION, IT WAS DISCOVERED THAT THE RT MLG UPPER DRAG LINK ASSY HAD FAILED AT THE ATTACHMENT POINT FOR 	THE MLG DOWNLOCK LATCH ASSY.  A VISUAL INSPECTION OF THE BROKEN DRAG LINK SHOWED THAT THE ASSY HAD A METAL FATIGUE CRACK	 ALONG THE CIRCUMFERENCE OF THE COMPONENT.  THE CRACKED AREAS SHOWED EVIDENCE OF CORROSION THAT APPEARS TO HAVE BEEN THE	RE FOR A LONG PERIORD OF TIME.  (K)			1	L	7	2 	3O	3	O		1A10    	E274				 
2006080300003	20060803	00003	CE  	2006	8	3	2006FA0000727    	1	20060714	G	2800	07600261	GUARD           			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	OUT OF RIG      	C			GFVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	1568W					T18208394				PROTECTIVE GUARDS ARE CALLED OUT BY IPL ORIGINALLY, IPL REV 7 DOES, REV 8 DOES NOT.  CURRENT REVISION 12, CALLS FOR THE 	GUARDS TO BE INSTALLED REV 13 IS IN TRANSIT BUT SHOULD INCLUDE THE CALL OUT.  THIS AIRCRAFT HAS INDICATIONS THAT ELEVATO	R CONTROL LINES HAVE MADE LIGHT CONTACT WITH FUEL LINES.  BUT THERE IS NO DAMAGE.  PARTS ORDERED.  AIRCRAFT TT 159 HOURS	 (FIRST ANNUAL INSPECTION).  (K)			1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2006080300005	20060803	00005	NM  	2006	8	3	2006FA0000728    	1	20060703	G	2910	AE70577756	HOSE            			BOEING	757   	7572Q8      	1384972	NM  										HYDRAULIC SYSTEM	MISINSTALLED    	B			LH6Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	719BC					25131				NR 1 ENGINE HYDRAULIC PUMP SUCTION/SUPPLY DISCONNECT.  DURING THE REPLACEMENT OF NR 1, ENGINE EDP DUE TO NO OFFLOAD, IT 	NOTED THAT THE SUPPLY DISCONNECT WAS FITTED WITH THE PUMP UNION AT THE WRONG END OF THE DISCONNECT, AND ON REMOVAL IT WA	S NOTED THAT THE INTERVAL S/OFF MECHANISM HAD BEEN REMOVED.  THE VALVE, UNION AND SEALS WERE SUBSEQUENTLY REPLACED.  (K)				2	L	7	2 	4F			RT	A2NM    					 
2006080300007	20060803	00007	EA  	2006	8	3	2006FA0000729    	2	20060714	G	8550		ADAPTER         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	185MH					0976				WHILE CHANGING OIL FILTER DURING ROUTINE 100 HR INSPECTION, OIL FILTER ADAPTER CENTER THREADED SHAFT BROKE OFF LEAVING H	ALF SHAFT INSIDE ADAPTER AND OTHER HALF THREADED INTO OIL FILTER.  THIS OCCURRED WITH MINIMAL ROTATIONAL TORQUE BEING AP	PLIED.  INSPECTION OF SHAFT REVEALED THAT MACHINED CENTER SECTION OF SHAFT AT SHEAR POINT WAS MACHINED TO DEEP LEAVING O	NLY A MAXIMUM WALL THICKNESS OF .020, AND PROBABLY MUCH LESS AT SHEAR LINE JUDGING BY KNIFE EDGE CONDITION OF BREAK POIN	T.  RECOMMENDATION: FURTHER INVESTIGATION AT MFG LEVEL POSSIBLE AD GENERATION TO DETERMINE IF OTHER UNITS CURRENTLY IN S	ERVICE HAVE SAME DEFECT CONDITION.	1	G	7	1 	3O	3	O		H10WE   	E274				 
2006080200297	20060802	00297	CE  	2006	8	2	2006FA0000730    	1	20060702	G	4940	3046342	IGNITER         			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					APU	SEPARATED       	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	826CA					222				PART OF IGNITER PLUG THAT SURROUNDS ELECTRODE SEPARATES AND SHORTS AGAINST THE ELECTRODE CAUSING THE APU NOT TO START.  	PART COULD POSSIBLY ENTER THE COMBUSTION AREA OF THE APU.  (NOTE: APU HAS ONE IGNITER,  HAD 2 RECENT FAILURES).					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006080300093	20060803	00093	CE  	2006	8	3	2006FA0000731    	1	20060702	G	4940	3046342	IGNITER         			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE73160    	 	NE  					APU	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	882CA	792  				155				PART OF IGNITER PLUG THAT SURROUNDS ELECTRODE SEPARATES AND SHORTS AGAINST THE ELECTRODE CAUSING THE APU NOT TO START.  	PART COULD POSSIBLY ENTER THE COMBUSTION AREA OF THE APU.  (NOTE: APU HAS ONE IGNITER, WE HAVE HAD 2 RECENT FAILURES).  	(K)				2	L	7	2 	4F	4	F	RT	T00008WI	E1NM				 
2006080800080	20060808	00080	GL  	2006	8	8	2006FA0000732    	3	20060714	G	6110	ACA1373	NUT             													HARTZL	HCB4M	HCB4M       	GL  	CLAMP	FAILED          	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09								FWA2178		WHEN TORQUING OUTER CLAMP NUT PN ACA1373, NEW OUTER CLAMP NUT THREADS FAILED BEFORE REACHING SPECIFIED TORQUE.  PROPELLE	R WAS BEING REASSEMBLED DURING OVERHAUL.  ASSEMBLED USING CALIBRATED TOOLS AND NEW HARDWARE.  (K)															6	C	P56GL	 
2006080300094	20060803	00094	EU  	2006	8	3	2006FA0000733    	2	20060607	G	7240	9387M34G01	TUBE            			BOEING	737   	737300      	1384610	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUEL DRAIN	DAMAGED         	C			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	GLGTG				41X24410					(REF: MDR NR MDR002/06)  STRIP OF CORE ASSEMBLY NOTED FRETTAGE DAMAGE TO 3 LOCATIONS ON THE NR 3 POSITION FUEL NOZZLE DR	AIN TUBE.  THE DEEPEST WAS TO A DEPTH OF .016 INCH.  THE ROUTE CAUSE OF THE FRETTAGE HAD BEEN DETERMINED AS CONTACT WITH	 RIVETS ON THE DEFLECTOR ASSY.  THE MODULE (41X24410) WAS REFURBISHED IAW BA REFURBISH SPECIFICATION AND IAW 72-41-XX AT	 LAST SHOP VISIT.  (K)			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006082900084	20060829	00084	CE  	2006	8	29	2006FA0000734    	1	20060727	G	3230		LANDING GEAR    			BEECH 	35    	A35         	1151504	CE  	CONT  	E185  	E185*       	17014	SO  					NLG	COLLAPSED       	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	417TZ					D2053				NOSE GEAR COLLAPSED.						1	L	7	1 	3O	3	O		A777    	E246				 
2006080300051	20060803	00051	SO  	2006	8	3	2006FA0000735    	1	20060726	G	2432		CAPACITOR       	ELDEC       		GULSTM	GV    	GULFSTREAMGV	3980116	SO  										BATTERY CHARGER	BURNED          	C				H				DEACTIVATE SYST/CIRCUITS				A			FLAME/FIRE                			LD	LANDING        	1			EA	07	410LM	2996 			B317	578				AFTER LANDING AIRCRAFT TAXIED TO HANGAR. WHEN AIRCRAFT STOPPED GROUND CREW NOTICED SMOKE COMING FROM TAIL COMPARTMENT. I	NVESTIGATION FOUND SMOKE AND FLAMES COMING FROM RT BATTERY CHARGER. ELECTRICAL POWER REMOVED FROM AIRCRAFT. FLAMES SELF 	EXTINGUISHED AND CHARGER WAS THEN REMOVED FROM AIRCRAFT. NO DAMAGE TO SURROUNDING AIRCRAFT STRUCTURE. REPLACEMENT CHARGE	R INSTALLED OPS CHECK OK.			2	L	7	2 	4F			RT	A12EA   					 
2006081600307	20060816	00307	GL  	2006	8	16	2006FA0000736    	2	20060525	G	8530		CYLINDER HEAD   			MTSBSI	MU2   	MU2B20      	5780407	SW  	HIRTH 	2706  	2706*       	 	GL  					ENGINE	STRIPPED        	G				B				EMER. DESCENT           				O			OTHER                     			TO	TAKEOFF        	1			WP	09	555C					129	A882299			NOTE: THIS AIRCRAFT WAS BUILT UNDER FAA EXPERIMENTAL AMATURE BUILT GUIDANCE. THIS AIRCRAFT IS NOT A LIGHT SPORT AIRCRAFT	. IT WAS BUILT FROM A KIT AND CERTIFIED AS AN EXPERIMENTAL AMATURE BUILT AIRCRAFT.  LOST ENGINE POWER AFTER TAKE-OFF AND	 MADE EMERGENCY LANDING WITH EXPERIMENTAL AMATURE BUILT AIRCRAFT: (HORNET)DETAILS: 2 CYLINDER,2 CYCLE ENGINE. 2 SPARK PL	UGS IN EACH CYLINDER.  AFT SPARK PLUG SEPARATED FROM AFT CYLINDER. THREADS THAT WERE MILLED INTO CYLINDER HEAD FAILED TO	 HOLD SPARK PLUG CAUSING DEPARTURE OF PLUG, LOSS OF COMPRESSION AND POWER LOSS CAUSING AN EMERGENCY LANDING. REPAIR WAS 	MADE BY INSTALLING A HELI-COIL INTO CYLINDER HEAD & REINSTALLING A SPARK PLUG.	1	H	7	2 	3T	3	I		A2PC    	EXPE3I				 
2006081400121	20060814	00121	SO  	2006	8	14	2006FA0000740    	1	20060804	G	7810	3022406	EXHAUST DUCT    			GRUMAV	G21   	G21A        	3951204	SO  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	22932	16012	660  			B139	PCE81118			EXHAUST DUCT ASSY CRACKED AND MISSING PARTS.						1	H	7	2 	3R	4	T		TC654   	E4EA				 
2006080800073	20060808	00073	NM  	2006	8	8	2006FA0000741    	1	20060626	G	2497		WIRE            	TRW         		DHAV  	DHC8  	DHC8*       	       	NM  										AC GENERATOR	BROKEN          	B			VNNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65					799					EXCITER ROTOR LEADWIRE BROKEN AT SOLDER CONNECTION TO DIODE.  (K)						2	H	7	2 	4T			RT	A13NM   					 
2006080800076	20060808	00076	NM  	2006	8	8	2006FA0000742    	1	20060706	G	2497		WIRE            	TRW         		DHAV  	DHC8  	DHC8*       	       	NM  										AC GENERATOR	BROKEN          	B			VNNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65			2415 		1163					EXCITER ROTOR LEAD WIRES BROKEN AT DIODE CONNECTION WIRES WERE INCORRECTLY SOLDERED.  (K)						2	H	7	2 	4T			RT	A13NM   					 
2006080800074	20060808	00074	NM  	2006	8	8	2006FA0000743    	1	20060706	G	2497	31708301	WIRE            			DHAV  	DHC8  	DHC8*       	       	NM  										AC GENERATOR	BROKEN          	B			VNNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65			2476 							EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION TO DIODE. (K)						2	H	7	2 	4T			RT	A13NM   					 
2006080800084	20060808	00084	NM  	2006	8	8	2006FA0000744    	1	20060706	G	2497		WIRE            	TRW         		DHAV  	DHC8  	DHC8*       	       	NM  										AC GENERATOR	BROKEN          	B			VNNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65					654					EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION TO DIODES, INCORRECTLY SOLDERED TO DIODE. (K)						2	H	7	2 	4T			RT	A13NM   					 
2006080800077	20060808	00077	NM  	2006	8	8	2006FA0000745    	1	20060706	G	2497		WIRE            	TRW         		DHAV  	DHC8  	DHC8*       	       	NM  										AC GENERATOR	BROKEN          	B			VNNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65			9658 		1188					EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION BETWEEN DIODE AND RESISTOR.  (K)						2	H	7	2 	4T			RT	A13NM   					 
2006081000118	20060810	00118	EA  	2006	8	10	2006FA0000747    	2	20060717	G	7310	050011842	FUEL LINE       			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	79130					17257901				DURING AN ANNUAL INSPECTION, BOTH ENGINE FUEL SUPPLY LINES WERE FOUND TO BE CHAFFING THE FWD BULKHEAD OF THE LANDING GEA	R BOX STRUCTURE AT BS 56.70.  MDG HAS INSTALLED A THIN PLASTIC SLEEVE OVER THE LINES IN THE AREA OF THE CHAFE BUT, AFTER	 2564 HOURS, THE SLEEVE IS CHAFFED TOT HE EXTENT THAT THE TUBES WILL NO LONGER BE PROTECTED.  FEEL THAT THE TUBE INTEGRI	TY WOULD BE COMPROMISED IN THE FUTURE.  ADDITIONAL CHAFE PROTECTION AND LINE SECURING IS REQUIRED.  ILLUSTRATION SHOWS A	 HEAVIER CHAFE BARRIER INSTALLED ON THE TUBES IN THE AREA NOTED ABOVE.  SUGGEST BONDING A LENGTH OF MIL .3750 INCH ID TU	BING  OVER THE MFG LINE IN THE CHAFE ARREARS.  ADDITIONAL ADJUSTMENT OF THE EXISTING LINE CLAMPS MAY ALSO BE REQUIRED.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006081000116	20060810	00116	SO  	2006	8	10	2006FA0000748    	1	20060407	G	2720	6282905	SHAFT           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					RUDDER	MISREPAIRED     	C			NT2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	195PJ					327840092				RUDDER TRIM BUNGEE SHAFT ASSY PN 6282905, HAD BEEN IMPROPERLY REPAIRED BY PERSONS UNKNOWN CAUSING BUNGEE TO BOTTOM OUT W	HEN RUDDER PEDAL DEFLECTED TO LIMIT WHICH IN TURN CAUSED UNDO PRESSURE ON RUDDER CONTROL  ARM, PN 6345703, EVENTUALLY CA	USING ARM TO BREAK.  (K)				1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006081000117	20060810	00117	EA  	2006	8	10	2006FA0000749    	2	20060720	G	8530	LW14995	SPRING          	LYC         		SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2802W	232  				1137	L921061A			THE PUSH ROD HOUSING TUBE RETAINING SPRINGS WERE BROKEN AT THE BEND JUST OB OF THE MOUNT HOLE.  THE UNBROKEN SPRINGS HAD	 A TOOL LINE AT THE POINT OF THE BEND.  THERE WERE 2 BROKEN SPRINGS, LOCATED ON NR 3 AND NR 4 CYLINDERS.  ONE SPRING HAD	 ONE SIDE BROKEN OFF THE OTHER BOTH SIDES WERE BROKEN.  BELIEVE THE TOOL MARKS ARE CAUSING THE PROBLEM.  ALL 6 SPRINGS W	ERE REPLACED WITH NEW MFG PARTS AND SOME ALSO CONTAINED THE TOOL MARKS AT THE BEND.  (K)			1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
2006081000130	20060810	00130	CE  	2006	8	10	2006FA0000750    	1	20060604	G	3233	98820152	HOUSING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ACTUATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	9394D					172RG1150	L3758836A	796893		RT MAINT GEAR ACTUATOR HOUSING CRACKED THROUGH THE BOLT HOLES OF CASTING , CAUSING  RACK TO DISENGAGE FROM PIVOT GEAR.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2006081000121	20060810	00121	EU  	2006	8	10	2006FA0000751    	1	20060713	G	6220	350A310033KIT7	SPRING          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					VIBRATION ABSORB	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	461SA	2130 			M2026	3605				PILOT REPORTED EXCESSIVE CABIN VIBRATION AT FULL POWER WHILE ON THE GROUND.  VIBRATION SUBSIDED IN A HOUR AND THROUGHOUT	 THE FLIGHT ENVELOPE.  DISASSEMBLY AND INSPECTION REVEALED 1 OF 3 SPRINGS IN VIBRATION ABSORBER OF MAIN ROTOR CRACKED AL	L THE WAY THROUGH.  COMPLIED WITH 2500 HR INSPECTION OF VIBRATION ABSORBER JAW MFG MAINT WORK CARDS AND SERVICING RECORD	S.  REPLACED ALL 3 SPRINGS AND PN EN2023R12L.  BEARINGS WHICH HAD EXCESSIVE PLAY.  REINSTALLED AN AIRCRAFT AND VIBRATION	 WAS ELIMINATED.  (K)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006081000112	20060810	00112	GL  	2006	8	10	2006FA0000752    	1	20060720	G	7120		SAFETY WIRE     			AMTR  	LANCAR	LC41550FG   	5150001	GL  										NR 4 ENG MOUNT	MISINSTALLED    	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	07	2542T	391  				41508				ALL 4 ENGINE VIBRATION ISOLATOR MOUNT BOLTS WERE SAFETY WIRED BACKWARDS.  NO EVIDENCE OF DAMAGE.  (K)						1	L	7	1 	3O			RT	EXPA1L71					 
2006081000123	20060810	00123	CE  	2006	8	10	2006FA0000753    	1	20060718	G	5540	081301316	TORQUE TUBE     			CESSNA	310   	310Q        	2074242	CE  										RUDDER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	119RS					310Q0906				RT RUDDER TORQUE TUBE RIPPED AT RUDDER CABLE BRACKET.  INSPECT THIS AREA NEXT TO WELD.  (K)						1	L	7	2 	3O				3A10    					 
2006081000138	20060810	00138	SO  	2006	8	10	2006FA0000755    	1	20060731	G	8011		RING GEAR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540N2BD  	41532	EA  					STARTER	FAILED          	B			EVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	3542D	291  			E052921	317952232	L1000961A			TRIED TO START ENGINE WOULD NOT START VISUAL BENDIX TO RING GEAR TEETH IN BOTTOM OF STARTER HOUSING.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006081000127	20060810	00127	SW  	2006	8	10	2006FA0000756    	1	20060721	G	2497	112	WIRE            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					FIREWALL	SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NE	01	8750V	1568 				110475				WHILE IN FLIGHT, THE PILOT REPORTED HE COULD SMELL SOMETHING BURNING, LANDED AS SOON AS PRACTICAL.  INVESTIGATION REVEAL	ED THAT THE WIRE FROM THE ALTERNATOR TO THE AMMETER, PN 112 HAD SHORTED AGAINST THE FIREWALL, WHERE IR GOES THROUGH THE 	FIRE WALL.  WIRES 112, 114, MASTER RELAY, STARTER RELAY, AMMETER, VOLTAGE REGULATOR AND ALTERNATOR WERE ALL REPLACED.  (	K)			1	H	7	1 	3O	3	O		A759    	E223				 
2006081000136	20060810	00136		2006	8	10	2006FA0000757    	4	20060804	G	2562	AK450	ELT             			CESSNA	150   	150K        	2071822	CE  	CONT  	O200  	O200*       	17020	SO  					CABIN	INOPERATIVE     	C			BI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	5896G					15071396				THIS IS ONE OF THE ELT`S THAT USES DATED FLASHLIGHT BATTERIES.  THE BATTERIES ARE STILL IN DATE BUT OFTEN WE FIND THAT T	HE BATTERIES ARE LEAKING OR DEAD BEFORE THE EXPIRATION DATE.  RECOMMEND THAT THE BATTERIES ARE CHANGED AT EACH ANNUAL TO	 CORRECT THIS PROBLEM.  BATTERIES ARE CHEAP ENOUGH.  (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2006081400071	20060814	00071	EA  	2006	8	14	2006FA0000758    	2	20060725	G	8530	TISN12OCA	CYLINDER HEAD   			PIPER 	PA25  	PA25        	7102502	SO  	LYC   	O360  	O360C2A     	41514	EA  					RT ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	17	6471Z	410  				25673	L2925936A			THIS WAS A NEW CYLINDER INSTALLED APRIL 05, AT ENGINE OVERHAUL.  THE CYLINDER COMPLETELY SEPARATED BETWEEN THE HEAD AND 	BARREL, IN FLIGHT.  THE AIRCRAFT WAS SAFELY LANDED AT HOME AIRPORT.  PN STAMPED ON CLY BASE: AEL65102, SN12.0F.  (K)					1	L	7	1 	3O	3	O		2A10    	E286				 
2006081000119	20060810	00119	EA  	2006	8	10	2006FA0000759    	2	20060802	G	7414	10357281L	CAPACITOR       	LYC         		BELL  	47    	47G4A       	1181031	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					MAGNETO	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	17	1354X				1012162	7537	L174243			LOADED HELICOPTER SAFELY LANDED AFTER MAGNETO FAILURE.  WIRE FROM CAPACITOR TO POINTS OPEN WITHIN INSULATION.  NO VISIBL	E DAMAGE, HOWEVER, MOVEMENT OF WIRE AGAINST CAPACITOR RESTORES CONTACT.  YOU CAN FEEL IT.  OPEN LOCATED WHERE WIRE ENTER	S CAPACITOR.  NO RECOMMENDATIONS.  (K)				1	G	7	1 	3O	3	O		2H3     	E304				 
2006081000132	20060810	00132	GL  	2006	8	10	2006FA0000760    	3	20060802	G	6111		SNAP RING       			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	PROP BLADES	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	965B	2976 	1066 			21061580	295027R	782194		2 SNAP RINGS FAILED ON PROPELLAR BLADES.  (K)						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
2006081000114	20060810	00114	CE  	2006	8	10	2006FA0000761    	1	20060802	G	3297	110230102	CIRCUIT BREAKER 			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	MLG	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	21EB	7567 				177RG0589	L1265751A	752186		LANDING GEAR CIRCUIT BREAKER MALFUNCTIONED.  AIRCRAFT WAS JACKED AND GEAR CYCLED SEVERAL TIMES.  COULD NOT GET THE CIRCU	IT BREAKER TO MALFUNCTION ON JACKS.  RECOMMEND THAT CIRCUIT BREAKER BE REPLACED WITH NEW.  (K)					1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
2006081000115	20060810	00115	EA  	2006	8	10	2006FA0000762    	2	20060520	G	8520	MIOP	CRANKSHAFT      			AMTR  	SISU  	SISU1A      	0780132	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	818SH					1017S1S	L1479051A			CRANKSHAFT FLANGE SEPARATED FROM CRANK AT THE LIGHTENING HOLES. AVOID GYROSCOPIC AEROBATICS USING A CRANKSHAFT FLANGE WI	TH LIGHTENING HOLES.  (K)					1	K	0	0 	  	3	O	RC	EXPA1K00	1E10				 
2006081400082	20060814	00082		2006	8	14	2006FA0000764    	2	20060701	G	8530	AEL65102	CYLINDER HEAD   			PIPER 	PA18  	PA18A       	7101804	SO  										ENGINE	SEPARATED       	B			OF1R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			EA	17	3885Z	413  				187700				DURING NORMAL CRUISE FLIGHT, PILOT EXPERIENCED ENGINE ROUGHNESS AND A LOSS OF ENGINE OIL OUT OF THE SIDE COWLING, CAUSIN	G AN UNEVENTFUL OFF AIRPORT LANDING.  ROUGHNESS AND OIL LOSS WERE DUE TO NR 3 CYL HEAD SEPARATING FROM THE CYLINDER BARR	EL AT THE 3RD COOLING FIN FROM BOTTOM OF THE HEAD.  ALTHOUGH THIS CYLINDER ECI PN IS SAME PN LISTED IN AD, THIS WAS TITA	N STYLE CYL, NOT CLASSIC CAST AS INDICATED BY NR CAST INTO CYL HEAD.  THESE LATER TITAN CYL UNAFFECTED BY AD, MAY BE EXP	ERIENCING SAME FAILURES THAT THE EARLIER CAST CYL THAT ARE AFFECTED BY AD WERE EXPERIENCING.  (K)		1	H	7	1 	3O				1A2     					 
2006081400125	20060814	00125	SO  	2006	8	14	2006FA0000765    	1	20060808	G	3211	67042013	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	571ER	3394 				4496147				DURING MAINTENANCE INSPECTION OF THE GEAR, THE MECHANIC FOUND THE AFT MAIN GEAR TRUNNION CRACKED.  DYE PENETRANT CONFIRM	ED CRACK.  CAUSE IS UNDETERMINED BUT THE AIRCRAFT IS USED FOR FLIGHT TRAINING.					1	L	7	2 	3O				A19S0   					 
2006081400134	20060814	00134		2006	8	14	2006FA0000766    	4	20060731	G	3497	311601	WIRE HARNESS    			CESSNA	650   	650         	2076802	CE  											DAMAGED         	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	13	96MT					6507065				DUAL TRANSPONDER FAILURE IN HEAVY PRECIPITATION. NO FAILURE INDICATION ON SPZ8000 SYSTEM.  CENTER REQUESTED RESET OF TRA	NSPONDER, AND DIRECTED OUT OF RVSM AIRSPACE WHEN UNSUCCESSFUL.  HANGAR TESTS OF POWER OUTPUT SHOWED 40WATTS BEFORE CABLE	S REPLACED, AND 400 WATTS AFTER.				2	L	7	2 	4F				A9NM    					 
2006081400135	20060814	00135		2006	8	14	2006FA0000767    	4	20060731	G	3497	311601	WIRE HARNESS    			CESSNA	650   	650         	2076802	CE  											DAMAGED         	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	13	96MT					6507065				DUAL TRANSPONDER FAILURE IN HEAVY PRECIPITATION. NO FAILURE INDICATION ON SPZ8000 SYSTEM.  CENTER REQUESTED RESET OF TRA	NSPONDER, AND DIRECTED OUT OF RVSM AIRSPACE WHEN UNSUCCESSFUL. HANGAR TESTS OF POWER OUTPUT SHOWED 40WATTS BEFORE CABLES	 REPLACED, AND 400 WATTS AFTER.				2	L	7	2 	4F				A9NM    					 
2006082100055	20060821	00055		2006	8	21	2006FA0000768    	4	20060813	G	3416		ALTIMETER       			BOEING	777   	777         	UTILUSE	NM  											INOPERATIVE     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										CAPTAIN ALTIMETER INOPERATIVE.						2	L	7	2 	4F			RT	T00001SE					 
2006081400147	20060814	00147	EA  	2006	8	14	2006FA0000769    	2	20060320	G	7310	1560016D0155	HOSE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					FUEL SYSTEM	LEAKING         	D				K				NONE                    				K	K		FLUID LOSS                	FLUID LOSS                		IN	INSP/MAINT     	1			SW	15	3648C	1177 				R18200294	L2047940A			DURING AN ANNUAL INSPECTION THE HOSE ASSEMBLY FROM THE ELECTRIC PUMP TO THE ENGINE DRIVEN FUEL PUMP WAS FOUND TO BE LEAK	ING.  HOSE WAS INSTALLED 5-12-03 AND REMOVED 3-20-06.					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2006081400195	20060814	00195	EA  	2006	8	14	2006FA0000770    	2	20060320	G	7310	AE3663819B0190	HOSE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					FUEL SYS	LEAKING         	D				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			SW	15	3648C	1177 				R18200294	L2047940A			DURING AN ANNUAL INSPECTION THE HOSE ASSEMBLY FROM THE TEE FITTING AT CARBURETOR TO THE FIREWALL FITTING FOR FUEL PSI WA	S FOUND TO BE LEAKING.  HOSE WAS INSTALLED 5-12-03.					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2006081700172	20060817	00172	GL  	2006	8	17	2006FA0000772    	2	20060731	G	7200		COUPLING        								ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	FAILED          	B			A9UR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05							CAT90607			NR 2 COUPLING FAILURE, WHICH CAUSED A NI FAILURE, AND INNER SHAFT FAILURE, POWER TURBINE ROTOR DECOUPLING AND GAS PRODUC	ER OVERTEMP.  (K)										3	U			E1GL				 
2006081400193	20060814	00193	SO  	2006	8	14	2006FA0000773    	1	20060806	G	3222		SPRING          			MICCO 	145A  	MAC145A     	5660000	SO  										TAILWHEEL ASSY	FRACTURED       	P				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	05	121MA	700  	10   			307				TAILWHEEL SPRING FAILED ON LANDING.  BROKEN IN MULTIPLE LOCATIONS. ONE BREAK POINT SHOWS EVIDENCE OF CORROSION, THE OTHE	R DOES NOT.  CRYSTALLIZATION PRESENT AT BOTH BREAK POINTS.  CRACKS APPEAR TO HAVE BEEN COVERED BY PAINT.					1	L	7	1 	3O			RC	        					 
2006081500011	20060815	00011	SO  	2006	8	15	2006FA0000774    	1	20060806	G	3220		SPRING          			MICCO 	145A  	MAC145A     	5660000	SO  										TAILWHEEL ASSY	FRACTURED       	P				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	05	121MA	700  	10   			307				TAILWHEEL SPRING FAILED ON LANDING.  BROKEN IN MULTIPLE LOCATIONS.  ONE BREAK POINT SHOWS EVIDENCE OF CORROSION, THE OTH	ER DOES NOT.  CRYSTALLIZATION PRESENT AT BOTH BREAK POINTS.  CRACKS APPEAR TO HAVE BEEN COVERED BY PAINT.					1	L	7	1 	3O			RC	        					 
2006081500006	20060815	00006	SO  	2006	8	15	2006FA0000775    	1	20060810	G	5711	6707003	SPAR            			PIPER 	PA28  	PA28R180    	7102809	SO  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	3894T	5260 				28R30223				DURING COMPLIANCE, A CRACK WAS FOUND ON THE MAIN SPAR DIRECTLY BEHIND THE SWIVEL BOLT BRACKET AT THE IB MOUNTING NUTPLAT	E. THE CRACK IS 3 INCHES IN LENGTH AND CURVES UPWARD ON BOTH ENDS. THE CRACK WAS NOT VISIBLE UNTIL THE AREA WAS CLEANED.	 IT IS RECOMMENDED THAT THIS AREA OF THE SPAR BE CLEANED AND INSPECTED DURING COMPLIANCE OF SB.  A CRACK WAS ALSO FOUND 	ON ANOTHER PA28R-180 NEAR THE SAME LOCATION ON THE SPAR. THIS INFORMATION AND PICTURES WERE SENT TO FOR EVALUATION.			1	L	7	1 	3O				2A13    					 
2006081500001	20060815	00001		2006	8	15	2006FA0000776    	4	20060804	G	2300		ELEC CONNECTOR  			DIAMON	DA40  	DA40        	2990002	GL  										MICROPHONE	SHORTED         	B				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	05	38CF					40567				ADJACENT MIC AND PHONE JACKS SHORTED TOGETHER CAUSING SQUEAL IN AUDIO SYSTEM.						1	L	7	1 	3O			NT	A47CE   					 
2006081500009	20060815	00009	SO  	2006	8	15	2006FA0000778    	1	20060801	G	2842		TRANSMITTER     			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					FUEL SYSTEM	UNRELIABLE      	C				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	17	319RD					4636139				NEW-STYLE FUEL SENDERS UNRELIABLE.  HAVE REPLACED 3 TIMES SO FAR.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2006081500010	20060815	00010	SO  	2006	8	15	2006FA0000779    	1	20060801	G	2842		TRANSMISSION    			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ZONE 500	UNRELIABLE      	C				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	17	319RD					4636139				NEW-STYLE FUEL SENDERS UNRELIABLE.  HAVE REPLACED 3 TIMES SO FAR.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2006081500004	20060815	00004	CE  	2006	8	15	2006FA0000780    	1	20060808	G	3230	NAS464P426	BOLT            	CESSNA      		CESSNA	340   	340A        	2076405	CE  										BELL CRANK	SHEARED         	C				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			LD	LANDING        	1			SW	17	2745F	2113 				340A0949				FAILURE OF THE PIVOT BOLT ON THE RT MLG DOWNLOCK BELLCRANK (BOOMERANG) APPEARS TO HAVE RESULTED FROM SHEAR FORCES DURING	 LANDING. FORCES OF THIS NATURE EXCEEDED DESIGN LIMITS OF THIS SEGMENT OF THE LANDING GEAR SYSTEM.  THE EXACT CAUSE COUL	D NOT BE DETERMINED BUT MAY HAVE RESULTED FROM IMPROPER RIGGING TO THE SYSTEM DURING RECENT MAINTENANCE OF THE LANDING G	EAR COMPONENTS.			1	L	7	2 	3O				3A25    					 
2006081500005	20060815	00005	CE  	2006	8	15	2006FA0000781    	1	20060803	G	5544	905000377	BRACKET         			BEECH 	90    	C90         	1152913	CE  										RUDDER	UNSECURE        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	36799	200  				LJ1799				DURING THE INITIAL 200 HOUR PHASE 1 INSPECTION ON THIS AIRCRAFT, THE MOUNT BRACKETS THAT SECURE THE RUDDER SERVO BRIDLE 	CABLES AND PULLEYS WERE FOUND TO BE UNSECURED AT THE AFT ATTACH POINTS (FS 364.00) BOTH LT AND RDT BRACKETS WERE NOT ATT	ACHED. THE ASSOCIATED FUSELAGE (2 EACH BOLTS IAW SIDE WAS LOCATED IN THE AFT FUSELAGE COMPARTMENT. REVIEWED OF THE AIRFR	AME LOGBOOKS DETERMINE NO DOCUMENTED WORK HAD BEEN PERFORMED IN THE AREA OR ON THE AFFECTED COMPONENTS. RAYTHEON FIELD T	ECHNICAL SUPPORT IS CONDUCTING AN INVESTIGATION.		1	L	7	2 	3T				3A20    					 
2006082100066	20060821	00066	EA  	2006	8	21	2006FA0000782    	1	20060802	G	2810	G201G202	FITTING         			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540*      	41532	EA  					FUEL SYSTEM	UNDERTORQUED    	H				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			AL	03	753	532  				44				AS REPORTED FROM THE PILOT, THE MAINTENANCE VENDOR FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEAD	ER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME OF SERVICE 532 HOURS. PIPE THREADED FITTINGS HAD NO THREAD LUBE/SEALANT. T	HE VENDOR NOTED THAT THE FUEL FITTINGS WERE NOT PROPERLY TORQUED.  THIS MAY REPRESENT A QUALITY CONTROL ISSUE AT THE FOU	ND AIRCRAFT PRODUCTION FACILITY. AT PRESENT THE USDOI, AVIATION MANAGEMENT DIRECTORATE, IS INVESTIGATING THIS EVENT WITH	IN ITS FLEET.		1	H	7	1 	3O	3	O		A7EA    	1E4				 
2006081600265	20060816	00265	CE  	2006	8	16	2006FA0000783    	1	20060725	G	2510	07140593	SEAT            			CESSNA	182   	182R        	2072731	CE  										COCKPIT	BROKEN          	B			BIIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	9983H	4070 				18268161				INSPECTED SEATS IAW AD.  FOUND PILOTS SEAT BOTTOM ASSY BROKEN AT LT FWD ATTACH POINT AND RT FWD CRACKED.  (K)						1	L	7	1 	3O			NT	3A13    					 
2006081600302	20060816	00302		2006	8	16	2006FA0000784    	4	20060814	G	2562	300011	ELT             			CESSNA	172   	172S        	2072439	CE  										CABIN	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	5359K	1944 	1944 			9447				ELT REMOTE SWITCH FOUND TO BE INOP. ELT SENT TO SHOP FOR REPAIR, SYSTEM OPS CKD NORMAL AFTER REPAIR. THIS IS THE 4 OCCUR	RENCE OF THIS ON THIS TYPE AIRCRAFT IN THE LAST 3 MONTHS. ALL REPAIRS ARE THE SAME REPLACE FUSE F1.					1	H	7	1 	3O			NT	3A12    					 
2006081600226	20060816	00226	CE  	2006	8	16	2006FA0000785    	1	20060804	G	8011		MOTOR           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					STARTER	SHORTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	99465					17276450				LIGHT WEIGHT STARTER MOTOR FAILED (SHORTED INTERNALLY) AFTER 1.5 YEARS SERVICE.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006081700170	20060817	00170	CE  	2006	8	17	2006FA0000786    	1	20060804	G	8011	85034007	DRIVE GEAR      			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360B1E    	41514	EA  					STARTER	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	981CP					17280215				BENDIX DRIVE GEAR BROKE INTO PIECES AFTER 1 YEAR OF SERVICE.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006081600300	20060816	00300	SW  	2006	8	16	2006FA0000787    	1	20060811	G	5311	2722019045	FRAME           			SWRNGN	SA227 	SA227AC     	8780603	SW  										FUSLEAGE	CRACKED         	B			OWFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	ECIXL					AC689				DURING REPAIR OF WING SPAR SHEAR WEB IAW AD AND SRM, IT WAS FOUND THAT THE LT AND RT BELT FRAMES WERE CRACKED AT THE STR	INGER 11 CUTOUT.  THE CRACKED BELT FRAMES WILL BE REPLACED WITH NEW COMPLETION OF THE SPAR REPAIR.  AIRCRAFT IS OPERATIN	G ON THE SPANISH REGISTER.  (K)				2	L	7	2 	4T			RT	A8SW    					 
2006081800160	20060818	00160	SW  	2006	8	18	2006FA0000788    	1	20060811	G	5711	2722019046	FRAME           			SWRNGN	SA227 	SA227AC     	8780603	SW  										WING	CRACKED         	B			OWFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	ECIXL	22492				AC689				DURING REPAIR OF WING SPAR SHEAR WEB IAW AD AND SRM, IT WAS FOUND THAT THE LT AND RT BELT FRAMES WERE CRACKED AT THE STR	INGER 11 CUTOUT.  THE CRAKED BELT FRAMES WILL BE REPLACED WITH NEW UPON COMPLETION OF THE SPAR REPAIR.  AIRCRAFT IS OPER	ATING ONT HE SPANISH REGISTER AS ECIXL.  (K)				2	L	7	2 	4T			RT	A8SW    					 
2006081700173	20060817	00173	SO  	2006	8	17	2006FA0000789    	2	20060809	G	8530		CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	DAMAGED         	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	58LF					TH237	243832R			ON ANNUAL INSPECTION, WORK WAS BEING PERFORMED TO REPAIR OIL LEAK ON PUSH ROD TUBE SEALS, WHEN PUSHRODS WERE REMOVED, TH	EY WERE FOUND TO BE BENT AND GREATER THAN 50 PERCENT OF TOTAL TUBE WORN THROUGH.  FURTHER INVESTIGATION FOUND THAT SEVER	AL TUBES WERE FOUND IN SAME CODITION AND THAT ALL EXHAUST RODS WERE BENT.  THERE WERE ALSO SIGNS ON 5 PISTONS OF VALVE C	ONTACT.  FIREWALL FWD RECONDITIONED CYLINDERS AND STATED THAT VALVE GUIDES HAD COAKING ON THEM AND THAT THE PISTON RINGS	 HAD LOST THEIR TEMPER.  OWNER IS SUSPECT OF BAD PARTS FROM MFG.  (K)		1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006081700169	20060817	00169	SW  	2006	8	17	2006FA0000790    	1	20060801	G	5711	5262L	SPAR            			BBAVIA	7     	7HC         	21101PN	SW  	LYC   	O290  	O290        	41506	EA  					WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	8906R					7HC26				LONGITUDINAL CRACK FROM STRUT BOLT HOLE OB.  PROBABLE CAUSE: WING DAMAGE FROM PAST GROUND LOOPING PROPAGATING OVERTIME. 	 TIME OF INCIDENT IN LOGS, 7/17/72.  (K)					1	H	7	1 	3O	3	O		A759    	E229				 
2006082100065	20060821	00065	CE  	2006	8	21	2006FA0000791    	1	20060708	G	2720	35660033	HINGE           			BEECH 	P35   	P35         	1151530	CE  	CONT  	O470  	IO470*      	17026	SO  					RUDDERVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9520Y					D7016				FAIRLEADS IN RUDDERVATOR TRIM TAB CNTRL CABLE SYS ARE CRACKING UPON INSTALLATION, POSSIBLY DURING FLIGHT.  BUTTON-HEAD R	IVETS ARE INTERFERING WITH INSTALLATION, CAUSING CRACKS TO FORM IN (TANG) OF FAIRLEADS.  CABLE TENSION USED IN RUDDERVAT	OR TRIM TAB CABLES IS A FACTOR IN CRACKING.  A LOOSENING OF RUDDERVATOR TRIM TAB CNTRL CABLES IS NECESSARY DURING INSTAL	L, FOLLOWED BY RIGGING TO VERIFY PROPER CABLE TENSION.  A SMALL AMOUNT OF FILING ON BACK OF (TANG) OF FAIRLEAD FOR CLOSE	 TOLERANCE OF RIVETS THAT HOLD NUTPLATE FOR MOUNTING OF FAIRLEAD.  EITHER A NEW MATERIAL NEEDS TO BE EXPLORED FOR MAKING	  FAIRLEADS MORE DURABLE, OR A MAINT NOTE NEEDS TO BE MADE ON PROPER INSTALLATION OF FAIRLEADS TO PREVENT CRACKING.  (K)	1	L	7	1 	3O	3	O	RT	3A15    	E1CE				 
2006081600341	20060816	00341	CE  	2006	8	16	2006FA0000792    	1	20060728	G	3250	24670036	BUNGEE CYLINDER 			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NLG STEERING	BROKEN          	D			V36R	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	13	20CU					172RG0323				THE NOSE GEAR STEERING BUNGEE PN 2467003-6, BROKE WHILE TAXIING IN AFTER LANDING.  THE AIRCRAFT STOPPED WITHOUT INCIDENT	.  THE BREAK OCCURRED IN THE  THEADED AREA OF THE SHAFT THAT CONTAINS THE CHAIN SPROCKET.  NOTE THAT THIS SHAFT HAS THRE	ADS ON BOTH ENDS.  THE END THAT BROKE HAS THE SMALLER THREADS (.3125 INCHES) NAD IS ON THE OPPOSITE END FROM THE SPROCKE	T.  THIS FAILURE IS SIGNIFICANT BECAUSE WHEN THE BUNGEE BREAKS THE BODY, WILL PIVOT DOWN AROUND THE ATTACHMENT POINT AND	 FOUL THE ELEVATOR CONTROLS.  BUNGEE WAS REPLACED AT TACH 532 AS A RESULT OF THE AD.  THE AC HAS 8070 HRS ON IT SO THE R	EPLACEMENT PART  HAS 7538 HOURS ON IT.  (K)	1	H	7	1 	3O	3	O		3A17    	E286				 
2006081800154	20060818	00154	CE  	2006	8	18	2006FA0000793    	1	20060628	G	5711		SPAR            			BEECH 	18    	E18S        	1151006	CE  	PWA   	R985  	R985*       	52008	NE  					LT WING	CORRODED        	B			O31R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	92WA	6600 				BA379				THE DEFECT IS SEVERE CORROSION IN SPAR TUBE LT SIDE UPPER AT WING STA 90.  PROBABLE CAUSE IS EXPOSURE TO MOISTURE OVER A	N EXTENDED PERIORD OF TIMEM.  RECOMMENDATION TO PREVENT RECURRENCE WOULD BE TO SEAL AND FILL WITH LIN SEED OIL.  FURTHER	 RECOMMENDATION WOULD BE TO ADD A SPLICE TO SPARE SECTION TO PROVIDE STRUCTURE INTEGRITY.  FURTHER RECOMMENDATION WOULD 	BE TO VISUAL INSPECT AND DYE PENETRANT INSPECT THIS AREA AT 25 HOUR INTERVALS UP TO 1ST 100 HOURS.  IF NO FATIGUE OR CRA	CKS ARE NOTED THEN EXTEND VISUAL AND PENETRANT INSP TO EVERY 100 HOURS OR EACH YEAR WHICH EVER OCCURS FIRST.  SEE ATTACH	ED XRAY, PENETRANT REPORT AND ADDITIONAL AREAS OF CONCERN FOR NOTED DEFECT.  (K)	1	L	7	2 	3R	3	R		A765    	5E1				 
2006081800149	20060818	00149	EA  	2006	8	18	2006FA0000794    	1	20060708	G	3210	A153034	LEG ASSY        			GRUMAN	SA16  	G64         	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT MLG	FAILED          	D			NHXG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	9965					1362	21758	BUA20843		THE RT MAIN GEAR LEG (SPRING GEAR STYLE) FAILED AT THE UPPER END, JUST OB OF THE CLAMP BAV.  THIS IS AN AREA OF MAJOR FL	EX OF THE GEAR LEG AND IT IS THE THICKEST PART OF THE LEG.  IN 25 YEARS WORKING ON THIS TYPE OF AIRCRAFT, I HAVE NEVER S	EEN A FAILURE OF THE MAIN GEAR LEGS.  THIS SET OF GEAR WAS INSTALLED ON THE AIRCRAFT 4/22/02 AND WAS MAGNAFLUXED, SANDBL	ASTED, AND PAINTED PRIOR TO INSTALLATION.  THE GEAR LEGS WERE A USED SET AT THAT TIME AND THE TT ON THE PAIR IS UNKNOWN.	  THE TIME SINCE MAGNAFLUX AND INSTALLATION (4/22/02) IS 1687.1 HRS.  THIS IS NOT A COMMON FAILURE AND I DO NOT BELIEVE 	THAT THERE IS A NEED FOR AN AD NOTE OR OTHER ACTION.  (K)	2	H	7	2 	4R	3	T		EXPA2H72	E4EA	6	C	P15EA	 
2006081700189	20060817	00189	NE  	2006	8	17	2006FA0000795    	1	20060524	G	6410	6516100001043	SPAR            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					T/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	229AC	39689				64018				(REF NR: MDR06-088)  IB SIDE OF SPAR ON TRAILING EDGE HAS A CRACK.  THE CRACK IS APPROX .482 INCH LONG AND RUNS FROM TIP	 END OF BLADE, DOWN INTO THE SCREW HOLE COUNTERSINK.  BLADE HAS ACCUMULATED 660.4 HOURS SINCE LAST REPAIR.  (K)					2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006081700171	20060817	00171	CE  	2006	8	17	2006FA0000796    	1	20060721	G	2910	S217840105	HYDRAULIC LINE  			CESSNA	172   	172RG       	2072438	CE  										HYDRAULIC SYS	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CE	03	5114U					172RG0243				NOSE GEAR HYDRAULIC ACTUATOR HOSE BLEW OUT OF CRIMP IN FLIGHT CAUSING LOSS OF ALL HYDRAULIC FLUID AND GEAR WOULD NOT GO 	UP OR DOWN, EVEN WITH HAND PUMP.  THE MFG HOSE WAS NOT THE AEROQUIP TYPE WITH STEEL BRADING OR THE SCREW ON ENDS.  RECOM	MEND THE AEROQUIP 303 HIGH PRESSURE HOSE COULD NOT FIND A TT ON HOSE OR A DATE CODE.  (K)				1	H	7	1 	3O				3A17    					 
2006081700183	20060817	00183		2006	8	17	2006FA0000798    	4	20060802	G	6122	210638F	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										THE GOVERNOR FAILED AFTER 106 HOURS OF OPERATION.  THIS UNIT WILL NOT PERFORM THE OVERSPEED TEST.  COMPONENT WAS OVERHAU	LED ON WO 39044 ON 5/18/06. (K)																		 
2006081700175	20060817	00175		2006	8	17	2006FA0000799    	4	20060804	G	6122	8210024H	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										THE GOVERNOR FAILED AFTER 772.1 HOURS OF OPERATION.  PROPELLER SYNCHRONIZATION FUNCTION IS INOPERATIVE.  COMPONENT WAS O	VERHAULED ON WO 39914 ON 07/06/2006.  (K)																		 
2006081700180	20060817	00180		2006	8	17	2006FA0000800    	4	20060527	G	6122	210638	GOVERNOR        																	PROPELLER	UNKNOWN         	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										DOCUMENTATION RECEIVED WITH COMPONENT AFTER REPAIR DOES NOT SHOW TIME SINCE OVERHAUL. (K)																			 
2006081700185	20060817	00185		2006	8	17	2006FA0000801    	4	20060413	G	6122	8210406H	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 291 HOURS AFTER INSTALLATION	. (K)																		 
2006081700184	20060817	00184		2006	8	17	2006FA0000802    	4	20060207	G	6122	210638F	FASTENER        																	PROP GOVERNOR	LOOSE           	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										COMPONENT RECEIVED FROM OVERHAUL SHOP WITH HARDWARE LOOSE ON CONNECTOR.  (K)																			 
2006081700186	20060817	00186		2006	8	17	2006FA0000803    	4	20060221	G	6122	8210406	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										GOVERNOR WOULD NOT PASS TEST AFTER INSTALLATION.  PROPELLER RPM DOES NOT DECREASE TO 1150 RPM WHEN TEST SWITCH ACTIVATED	.  UNIT WILL ALSO NOT PASS PY SHIFT TEST.  (K)																		 
2006081700188	20060817	00188		2006	8	17	2006FA0000804    	4	20060620	G	6122	8210406H	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										BETA VALVE STICKING, CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 171 HOURS AFTER INSTALLATIO	N.  (K)																		 
2006081700177	20060817	00177		2006	8	17	2006FA0000805    	4	20060629	G	6122	8210406H	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 302.6 HOURS AFTER INSTALLATI	ON.  (K)																		 
2006081700181	20060817	00181		2006	8	17	2006FA0000806    	4	20060502	G	6122	210638F	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										GOVERNOR WOULD NOT ACTIVATE USING TEST SWITCH ON INSTALLATION AFTER OVERHAUL. (K)																			 
2006081700178	20060817	00178		2006	8	17	2006FA0000807    	4	20060207	G	6122	8210406	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										GOVERNOR WOULD NOT PASS TEST AFTER INSTALLATION.  PROPELLER RPM DOES NOT DECREASE TO 1150 RPM WHEN TEST SWITCH ACTIVATED	.  (K)																		 
2006081700174	20060817	00174		2006	8	17	2006FA0000808    	4	20060207	G	6122	82100224H	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										BETA VALVE STICKING WHEN ENGINE POWER IS REDUCED CAUSING AIRCRAFT TO YAW.  GOVERNOR FAILED 222 HOURS OF OPERATION AFTER 	OVERHAUL.  (K)																		 
2006081700179	20060817	00179		2006	8	17	2006FA0000809    	4	20060519	G	6122	82130391	GOVERNOR        																	PROPELLER	MISMANUFACTURED 	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										COMPONENT RECEIVED WITH INCORRECT ARM INSTALLED ON BETA VALVE.  ATTACHMENT HOLE FOR LINKAGE WAS TOO SMALL.  (K)																			 
2006081700176	20060817	00176		2006	8	17	2006FA0000810    	4	20060620	G	6122	58210007	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										PROPELLER GOVERNOR FAILED AFTER 2.5 HOURS OF OPERATION AFTER OVERHAUL. (K)																			 
2006081700182	20060817	00182		2006	8	17	2006FA0000811    	4	20060616	G	6122	210638F	GOVERNOR        																	PROPELLER	OUT OF ADJUST   	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										DURING TEST AFTER INSTALLATION, PROPELLER DROPS TO 1800 RPM.  GOVERNOR SET TO INCORRECT LIMIT.  (K)																			 
2006081700187	20060817	00187		2006	8	17	2006FA0000812    	4	20060613	G	6122	8210406H	GOVERNOR        																	PROPELLER	FAILED          	B			IG0R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 36 HOURS AFTER INSTALLATION.	 (K)																		 
2006082500024	20060825	00024	CE  	2006	8	25	2006FA0000816    	1	20060815	G	2810		O-RING          			CESSNA	182   	182D        	2072710	CE  										FUEL CAP	SPLIT           	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	05	8916X	300  				18253316				THE RT FUEL TANK CAP O-RING SPLIT AND FUEL SIPHONED OUT OF THE RT TANK DURING FLIGHT.						1	H	7	1 	3O			NT	3A13    					 
2006082100057	20060821	00057	SO  	2006	8	21	2006FA0000817    	2	20060816	G	7414	6310	MAGNETO         			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  					LT ENGINE	SEPARATED       	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	13	1850F	1600 				TE1195				LT ENGINE OB MAGNETO IMPULSE COUPLING FROZE UP, CAUSING MAGNETO HOUSING TO COMPLETELY SEPARATE FROM ENGINE.						1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006082500033	20060825	00033	SO  	2006	8	25	2006FA0000819    	2	20060709	G	8530	656612	EXHAUST VALVE   			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C9012F      	17009	SO  					NR 4 CYLINDER	BROKEN          	B			AWOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	4715E	1350 				7EC59	42615012			WHEN THE NR 4 CYLINDER WAS REMOVED, THE EXHAUST VALVE HEAD WAS FOUND TO BE BROKEN OFF, ABOUT .5 INCH FROM THE FACE OF TH	E VALVE, CAUSING FAILURE OF THE PISTON AND FAILURE OF THE INTAKE VALVE.  THE CIRCUMSTANCES OF THE FAILURE CAUSED A LOSS 	OF ENGINE POWER AND A FORCED LANDING IN A FIELD.  THE PILOT WAS UNHARMED.  (K)				1	H	7	1 	3O	3	O		A759    	E252				 
2006082500047	20060825	00047	CE  	2006	8	25	2006FA0000820    	1	20060706	G	2910	511700712	TUBE            			CESSNA	425   	425         	2076018	CE  										HYD SYSTEM	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	05										TUBE FAILED ON LOWER ATTACHMENT, ALL FLUID LOST, CAUSE UNKNOWN.  (K)						1	L	7	2 	3T			RT	A7CE    					 
2006082500021	20060825	00021	CE  	2006	8	25	2006FA0000821    	1	20060726	G	5200		HINGE           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					DOOR	CORRODED        	B			AW4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	485DS	4783 				421C0459				TO FIND USED SERVICEABLE HINGES AND HINGE SUPPORT FITTINGS FROM AC SALVAGE COMPANIES, EVERY HINGE THAT WAS RECEIVED, SAM	E TYPE OF CORROSION,  BEARING AND BUSHINGS WERE RUSTED TO HINGE BOLT.  BUSHINGS AND BEARING ARE PRESS FIT INTO HINGE SO 	AS TO ALLOW HINGE ASSY TO ROTATE ON BOLT.  WHEN BOLT FREEZES TO BEARING AND BUSHINGS,  BOLT THEN ROTATES IN SOFT ALUMINU	M SUPPORT FITTING WHICH ALLOWS HOLES IN FITTING TO ELONGATE.  IT WOULD APPEAR THAT THIS IS A CHRONIC PROBLEM.  AS NOTED 	IN ORIGINAL MD PROBLEM SEEMS TO BE RELATED TO FACT THAT SUPPORT FITTINGS CAN RETAIN WATER.  THERE IS NO SPECIFIC INSPECT	ION REQUIREMENT TO CHECK THESE HINGES FOR CORROSION AND SO CONDITION REMAINS UNDETECTED UNTIL BOLTS HAVE TO BE REMOVED.	1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006082500042	20060825	00042	SO  	2006	8	25	2006FA0000822    	1	20060303	G	3220	9617800	SPRING          			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	UNKNOWN         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	210SK					347250307				WHEN COMPARING THE NEW SPRING TO OLD SPRING, USING A FISH SCALE, THE NEW TOOK 12 LBS TO OFFSET THE COILS THE OLD ONLY TO	OK 7LBS.  THIS IS BELIEVED TO CONTRIBUTE TO NOSE GEAR COLLAPSE.  (K)					1	L	7	2 	3O	3	O		A7SO    	1E10				 
2006082500043	20060825	00043	SO  	2006	8	25	2006FA0000823    	1	20060303	G	3220	400890AN2340A	BOLT            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG DOWNLOCK	BENT            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	210SK					347250307				THIS WITH OTHER PROBLEMS LEAD TO SLOP IN THE DOWNLOCK OF THE NOSE GEAR.  THIS CONTRIBUTED TO THE COLLAPSE OF THE NOSE GE	AR.  BOLT REPLACED WITH NEW.  (K)					1	L	7	2 	3O	3	O		A7SO    	1E10				 
2006082500022	20060825	00022	SO  	2006	8	25	2006FA0000824    	1	20060303	G	3230	9506189	BUSHING         			PIPER 	PA34  	PA34200     	7103405	SO  										NLG DOWLOCK	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	210SK					347250307				INSPECTION REVEALED END OF BUSHING HAD BROKE OFF.  REPLACE WITH NEW.  THIS CONTRIBUTED TO SLOP IN NOSE GEAR DOWNLOCK MEC	HANISM AND GEAR COLLAPSE.  (K)					1	L	7	2 	3O				A7SO    					 
2006083100029	20060831	00029	CE  	2006	8	31	2006FA0000825    	1	20060804	G	2730	MS21251B6L	TURNBUCKLE      			BEECH 	B300  	B300        	1159232	CE  										ELEVATOR	MISMANUFACTURED 	B			E81R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	8YN	697  				FL417				WHEN THE PART WAS MFG, THE SAFETY SLOT DID NOT LIME UP WITH THE END SLOTS.  THIS DID NOT CAUSE A PROBLEM EITHER OPERATIO	NALLY, OR IN THE PROCESS OF SAFETYING THE TURNBUCKLE.  (K)					2	L	7	2 	4T			RT	A24CE   					 
2006083100007	20060831	00007	CE  	2006	8	31	2006FA0000826    	1	20060727	G	2710	05010105364	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LT AILERON	FRAYED          	B			7TFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	533BM					172S8340				DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE LT AILERON  CROSSOVER CABLE WAS FRAYED AT THE ABBRASSI	ON STRIP.  THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE ABBRASION BLOCK.  A POSSIBLE SOLUTION IS TO MAKE THE ABBR	ASION BLOCK OUT OF A SOFTER MATERIAL.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006082500054	20060825	00054	CE  	2006	8	25	2006FA0000827    	1	20060727	G	2710	05010105362	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					RT WING	UNSERVICEABLE   	B			7TFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	533BM	5687 				172S8340				DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FUND THAT THE RT AILERON DIRECT CABLE WAS FRAYED AT THE FAIRLEAD ASSE	MBLY.  THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE FAIRLEAD ASSY.  A POSSIBLE SOLUTION IS TO MAKE THE FAIRLEAD A	SSY OUT OF A SOFTER MATERIAL.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006083100006	20060831	00006	CE  	2006	8	31	2006FA0000828    	1	20060727	G	2710	05010105365	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  										RT AILERON	FRAYED          	B			7TFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	533BM	5687 				172S8340				DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE RT AILERON CROSSOVER CABLE WAS FRAYED AT THE FAIRLEAD 	ASSY.  THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE FAIRLEAD ASSY.  A POSSIBLE SOLUTION IS TO MAKE THE FAIRLEAD A	SSY OUT OF A SOFTER MATERIAL.  (K)				1	H	7	1 	3O			NT	3A12    					 
2006082500045	20060825	00045	SO  	2006	8	25	2006FA0000829    	2	20060809	G	7414	6320	POINTS          	SLICK       		AMTR  	LANCAR	LC41550FG   	5150001	GL  	CONT  	O550  	TSIO550C    		SO  					MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	400UK				653280	41062	802709			MAGNETO FAILURE, ON ECR ON INSP RT MAGNETO POINT HAD BROKEN IN HALF.  (K)						1	L	7	1 	3O	3	O	RT	EXPA1L71	E5SO				 
2006082500055	20060825	00055	CE  	2006	8	25	2006FA0000830    	1	20060807	G	3246	MS20002C6	WASHER          			RAYTHN	390   	390         	7150030	CE  										MLG WHEEL	MISINSTALLED    	B			E81R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	03	390JV				0453	RB129				DURING WHEEL DISASSEMBLY FOR TIRE REPLACEMENT FOUND WHEEL TIE BOLT CHAMFERED WASHERS INSTALLED INCORRECTLY, WITH CHAMFER	ED SIDES TOWARDS WHEEL HALF.  NOTED WASHERS TO BE BENT, WHEEL TIE BOLT HEADS UNDERSIDE RADIUSES DAMAGED.  SUSPECT TECHNI	CIAN ASSEMBLING WHEELS AT PREVIOUS TIRE CHANGE AT ANOTHER FACILITY DID NTO FULLY FOLLOW COMPONENT MM AND WAS NOT FAMILIA	R WITH INSTALLATION OF MS20002 SERIES CHAMFERED WASHERS.  (K)			1	7		2 	3F			RT	A00010WI					 
2006083100028	20060831	00028	CE  	2006	8	31	2006FA0000831    	1	20060807	G	3246	MS20002C6	WASHER          			RAYTHN	390   	390         	7150030	CE  										WHEEL	MISINSTALLED    	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	390JV	284  				RB129				DURING WHEEL DISASSEMBLY FOR TIRE REPLACEMENT FOUND WHEEL TIE BOLT CHAMFERED WASHERS INSTALLED INCORRECTLY, WITH CHAMFER	ED SIDES TOWARDS WHEEL HALF.  NOTED WASHERS TO BE BENT, WHEEL TIE BOLT HEADS UNDERSIDE RADIUSES DAMAGED.  SUSPECT TECHNI	CIAN ASSEMBLY WHEELS AT PREVIOUS TIRE CHANGE AT ANOTHER FACILITY DID NOT FULLY FOLLOW COMPONENT MM AND WAS NOT FAMILIAR 	WITH INSTALLATION OF MS20002 SERIES CHAMFERED WASHERS.  (K)			1	7		2 	3F			RT	A00010WI					 
2006082500025	20060825	00025	CE  	2006	8	25	2006FA0000832    	1	20060726	G	3234	1SX1T	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  										MLG SELECTOR	DAMAGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	334SR	3446 				RK129				DURING SCHEDULED INSPECTION, FOUND LANDING GEAR WARNING HORN WOULD NOT OPERATE WITH LT POWER LEVER RETARDED.  FOUND THRO	TTLE QUADRANT SWITCHES S25 AND S26 TO HAVE HIGH INTERNAL RESISTANCE.  REPLACED SWITCHES AND ADJUSTED AS REQUIRED IAW MM.	  LANDING GEAR WARNING SYSTEM TESTS NORMAL.  TYPICAL FAILURE MODE FOR THIS TYPE SWITCH USED ON THROTTLE LEVERS FOR VARIO	US FUNCTIONS.  RECOMMEND A MORE EXTENDED LIFE SWITCH BEING UTILIZED, OR ESTABLISH A SCHEDULED 2600 HR REPLACEMENT SCHEDU	LE (IN CONJUNCTION WITH REPLACEMENT SCHEDULE (IN CONJUNCTION WITH ADDITIONAL C-INSPECTION/COMPONENT REPLACEMENT ITEMS). 	 (K)	2	H	7	2 	4F			RT	A16SW   					 
2006082500040	20060825	00040	CE  	2006	8	25	2006FA0000833    	1	20060718	G	3240	5010614	BRAKE           			BEECH 	MU300 	400A        	1155402	CE  										MLG	SEIZED          	B			E81R	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	03	476LX					RK376				DURING INITIAL TAKEOFF ROLL, FOLLOWING POSITIVE PARKING BRAKE RELEASE CHECK, LT MAIN WHEEL BRAKE LOCKED-UP.  TAKEOFF ABO	RTED DUE TO SLOW ACCELERATION, POOR DIRECTIONAL CONTROL.  UNABLE TO MOVE AIRCRAFT UNTIL RT BRAKE APPLIED AND RELEASED, T	HEN TAXI-IN NORMAL.  REPLACED LT MAIN WHEEL BRAKE.  ALSO REPLACED PN 4500A2 PARKING BRAKE VALVE ASSY.  AS A PRECAUTION I	AW OPERATOR REQUEST.  REPLACED LT MAIN WHEEL ASSY.  DUE TO FLAT-SPOTTED TIRE.  AT THIS TIME SUSPECTED FAULT IS IN LT BRA	KE ASSY, BRAKE ASSY.  QUARANTINED BY OPERATOR FOR FURTHER EVALUATION.  (K)		2	H	7	2 	4F			RT	A16SW   					 
2006082500050	20060825	00050	NE  	2006	8	25	2006FA0000834    	2	20060728	G	7322	D8531	LINK            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					THROTTLE ARM	SEPARATED       	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	07	494SH	486  				10878	3043948A			ON 7/26/06 PILOT REPORTED THAT WHILE FLYING THROTTLE CONTROL BECOME INEFFECTIVE.  AIRCRAFT LANDED SAFELY AT AIRFIELD AND	 PUSHED TO HANGAR.  INSPECTED THROTTLE CONTROL ATTACHMENT AT ENGINE THROTTLE BODY AND FOUND UPPER ROD END OF LINK, PN D8	531 SEPARATED.  PHOTOGRAPH TAKEN AND SENT OT MFG, IAW INSTRUCTION , LINK PN B5642 ORDERED AND RETURNED THE SEPARATED LIN	K PN D8531 TO MFG FOR FURTHER INVESTIGATION.  (K)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006082500044	20060825	00044	EA  	2006	8	25	2006FA0000835    	1	20060811	G	2500	SPH1606B3	INVERTER        			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF341A      	 	NE  					STATIC FREQUENCY	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NE	05	372G					5351				THIS STATIC FREQUENCY INVERTER WAS INSTALLED IN THE STATED AIRCRAFT ON JUNE 2, 2006.  AT THE TIME OF INSTALLATION, THE P	ART HAD BEEN OVERHAULED BY CONSOLIDATED AC SUPPLY CO, INC.  UNDER WO NR 7314, DATED MAR 14,2006.  THE STATIC FREQUENCY I	NVERTER FAILED ON AUGUST 8, 2006.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006082500049	20060825	00049	EA  	2006	8	25	2006FA0000836    	1	20060811	G	2130		UNKNOWN         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					CABIN PRESSURE	UNKNOWN         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	373G					5556				REASON REMOVED, PRESSURIZATION CLIMBS AFTER T/O UP TO 2000 FPM.  THEN CATCHES AND WORKS DURING FLIGHT.  PRIOR TO INSTALL	ATION IN THE AIRCRAFT, THIS COMPONENT WAS INSPECTED, UNDER WO NR U22732, DATED MAR 30, 2006.  COMPONENT WAS INSTALLED ON	 06/09/2006.  (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006082500056	20060825	00056	CE  	2006	8	25	2006FA0000837    	1	20060607	G	2612	22412886	FIRE LOOP       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RT NACELLE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	172GA					UB11	PS32232			PILOT EXPERIENCED A FIRE WARNING ANNUNCIATION DURING TAKEOFF ROLL.  PILOT ABORTED TAKEOFF.  MAINTENANCE FOUND THAT ONE F	IRELOOP HAD FAILED AND CAUSED THE FALSE FIRE INDICATION.  (K)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006082500053	20060825	00053		2006	8	25	2006FA0000839    	1	20060822	G	3213	3581525115	BRACE           	RAYTHN      																MLG STRUT	MISDRILLED      	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	09					072					THIS IS A NEW PART PURCHASED THRU MFG (RAPID).  BRACE ASSEMBLY HAS 4 BOLT HOLES THAT ARE NOT DRILLED TO THE REQUIRED SIZ	E TO ACCOMMODATE THE BOLT THAT IS TO BE INSTALLED.  HOLE I.D. SIZE IS 0.185.  BOLT O.D. SIZE IS 0.310.																		 
2006082500028	20060825	00028	CE  	2006	8	25	2006FA0000840    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE INBOARD GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODE	LS AND BEECH HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PART NUMB	ERS.  THE NEW PART NUMBER PARTS ARE MADE FROM .050" ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCHES ALUMINU	M.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006082500029	20060825	00029	CE  	2006	8	25	2006FA0000841    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -	24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO FACT THAT MFG HAS CHANGED DESIGN OF THE IB 	GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS AC	KNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MA	DE FROM .050 INCH ALUMINUM WHILE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTE	D AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006082500030	20060825	00030	CE  	2006	8	25	2006FA0000842    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AN	D MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PART NUMBERS.  T	HE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS	 COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006082500031	20060825	00031	CE  	2006	8	25	2006FA0000843    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AN	D MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN 	PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EAS	ILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006082500037	20060825	00037	CE  	2006	8	25	2006FA0000847    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	45MS	360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AN	D BEECH HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW P	N PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD E	ASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006082500038	20060825	00038	CE  	2006	8	25	2006FA0000848    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	45MS	360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AN	D MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN 	PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EAS	ILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006082500039	20060825	00039	CE  	2006	8	25	2006FA0000849    	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	45MS	360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AN	D MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN 	PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EAS	ILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006091300398	20060913	00398	CE  	2006	9	13	2006FA0000851    	1	20060812	G	3231	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  										NLG DOOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		1461 								THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)						2	L	7	2 	4F			RT	A22CE   					 
2006091500133	20060915	00133	CE  	2006	9	15	2006FA0000852    	1	20060712	G	5280	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  										NOSE GEAR DOORS	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		3016 								THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)						2	L	7	2 	4F			RT	A22CE   					 
2006083100002	20060831	00002	CE  	2006	8	31	2006FA0000853    	1	20060718	G	3231	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  										NLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		4646 								THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)						2	L	7	2 	4F			RT	A22CE   					 
2006092700019	20060927	00019	CE  	2006	9	27	2006FA0000854    	1	20060718	G	3231	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  										NLG DOORS	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		4182 								THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)						2	L	7	2 	4F			RT	A22CE   					 
2006092600251	20060926	00251	CE  	2006	9	26	2006FA0000855    	1	20060720	G	3231	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  										NOSE GEAR DOORS	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										THE NOSE LANDING GEAR DOOR TORQUE TUBE RECEIVED NEW FROM MFG HAS THE ATTACHMENT ARMS MISALIGNED.  HOLE FOR THE LINKAGE A	TTACHMENT BOLT HAS BEEN DRILLED WITH LESS THAN ALLOWABLE EDGE DISTANCE TO COMPENSATE FOR THE MISALIGNED ARMS.  (K)					2	L	7	2 	4F			RT	A22CE   					 
2006091300397	20060913	00397	CE  	2006	9	13	2006FA0000856    	1	20060712	G	3231	55421029	TORQUE TUBE     			CESSNA	500   	560CESSNA   	2076750	CE  										NLG DOOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		1615 								THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)						2	L	7	2 	4F			RT	A22CE   					 
2006092700020	20060927	00020	CE  	2006	9	27	2006FA0000857    	1	20060718	G	3240	169580001143	LINE            			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1A    	41514	EA  					BRAKE SYSTEM	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	824BA					MC533				AIRCRAFT LEAKING HYDRAULIC FLUID.  INSP FOUND RT BRAKE LINE  LEAKING APPROX 8 INCHES FWD OF WING SPAR.  FOUND ALUMINUM B	RAKE LINE CHAFING AGAINST WIRE REINFORCED HEATING DUCT.  ALSO, EVIDENCE OF CORROSION FROM CONTACT WITH DISSIMILAR METALS	.  CUT OFF DAMAGED AREA AND REPLACED WITH NEW MATERIAL AND ON UNION.  ADDED NYLON SPIRAL WRAP FOR CHAFE PROTECTION.  (K)				1	L	7	1 	3O	3	O		A1CE    	1E10				 
2006092600254	20060926	00254	GL  	2006	9	26	2006FA0000858    	1	20060718	G	7810	14836001	MUFFLER         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					LT, RT EXHAUST	DAMAGED         	B			QRQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	948AH					0329				LT AND RT MUFFLER FLAME ARRESTERS FOLDED OVER FROM EXHAUST GAS HEAT COMPOUNDED OVER THE 609 HOURS OF THEIR SERVICE LIFE.	  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006082800001	20060828	00001	CE  	2006	8	28	2006FA0000859    	1	20060817	G	2720		SERVO           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RUDDER TRIM	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	719D	1494 				5250075				TECH WAS IN TAILCONE AREA AND NOTICED METAL SHAVINGS UNDER RUDDER SERVO ASSY.  INVESTIGATION REVEALED THAT THE SERVO DRU	M  CABLE WAS CUTTING THROUGH THE DRUM GROOVES ARE TO SEVERE SIDE LOADING ON THE CABLE.  SUSPECT THAT THE SEVERE SIDE LOA	D CONDITION RESULTED FROM IMPROPER PLACEMENT OF SERVO CABLE TO MAIN SYSTEM CABLE CLAMP.  ROTATION OF THE CLAMP ON THE MA	IN RUDDER SYSTEM CABLE INDUCED THE SIDE LOAD.  THIS AC WAS NOT IN FOR AN INSPECTION AND THE TECH FOUND THIS CONDITION BY	 CHANCE.  (K)		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006092600071	20060926	00071	EA  	2006	9	26	2006FA0000860    	2	20060623	G	8520	LW12581	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	4095L					318152178	L816261A			PILOT REDUCED POWER FOR LANDING, PUSHED NOSE OF AC OVER TO DESCEND, LF ENGINE RPM INCREASED.  PULL NOSE OF AC UP, RPM DE	CREASED.  THEN PILOT REPORTED SLIGHT VIBRATION AND THE BANG.  LT ENGINE WAS SHUTDOWN.   AIRCRAFT LANDED WITHOUT INCIDENT	.  INSPECTION OF LT ENGINE WAS PERFORMED AND FOUND THAT THE FRONT 2 CYLINDERS WERE THE ONLY ONES STILL ATTACHED TO THE F	RONT THIRD OF THE CRANKSHAFT (THE CRANKSHAFT WAS IN (3) PIECES).  (K)			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006083100003	20060831	00003	SO  	2006	8	31	2006FA0000861    	1	20060729	G	2910		HYDRAULIC LINE  			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					HYDRAULIC SYS	CHAFED          	B				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	01	401PJ					274112				AIRCRAFT SUFFERED HYDRAULIC PRESSURE LOSS, FOUND LT RUDDER CABLE CHAFED THRU PRESSURE LINE BEHIND PILOTS LT SIDE WALL, A	REA IS DIFFICULT TO INSPECT DUE TO SIDE WALL/INSULATION.  LINE REPLACE, SYSTEM SERVICED OPERATES NORMAL.  PLEASE FIND BE	LOW ADDITIONAL ITEMS DISCUSSED IAW TELECOM DATED 8/15/2006.  PROBLEM WITH THE CABLE CHAFING THROUGH THE PRESSURE LINE HA	S BEEN IDENTIFIED ONE TIME PREVIOUS TO THIS INCIDENT.  BOTH OCCURRENCES HAPPENED BETWEEN 6000-7000 AC HOURS.  PROBLEM IN	 BOTH CASES WAS NOT IDENTIFIED UNTIL HYDRAULIC LEAK WAS DETECTED.  MECHANIC REPOSITIONED THE NEW LINE TO ALLEVIATE THE P	ROBLEM.  (K)	1	L	7	2 	3O	3	O		1A10    	1E4				 
2006092600057	20060926	00057	SO  	2006	9	26	2006FA0000862    	1	20060828	G	3097		WIRE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  						BROKEN          	D				C	H			ABORTED TAKEOFF         	DEACTIVATE SYST/CIRCUITS			R	N		PARTIAL RPM/PWR LOSS      	FALSE WARNING             		TO	TAKEOFF        	1			EA	35	160TR	4327 				31T7920036	51943			RTBETA-LIGHT CAME ON DURING TAKE-OFF ROLL. PROPELLER RPM DROPPED HEAVILY. PULLED CIRCUIT BREAKER. RPM RETURNED TO NORMAL	.  FOUND ALL SINGLE WIRE INSULATIONS IN WIRE BUNDLE TOENGINE/PROP SWITCHES, INCLUDING DE-ICE WIRES AT REDUCTION GEAR BOX	 HARDENED AND BROKEN, MAKING CONTACT.  WIRE BUNDLE RUNS UNDERNEATH EXHAUST FLANGE.  NO OTHER DAMAGE DUE TO FAST PULLING 	CIRCUIT BREAKER, IF THIS HAPPENS DURING FLIGHT, IT COULD LEAD TO A DANGEROUS SITUATION.  REPLACED ALL WIRING.			1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2006092200083	20060922	00083	CE  	2006	9	22	2006FA0000863    	1	20060718	G	7810	15501261	CLAMP           			CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360GB     	17025	SO  					EXHAUST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	1258S	39   				33701894				WHILE DOING A PRE-TOW WALKAROUND INSPECTION, NOTICED THE FRONT ENGINE EXHAUST TAIL PIPES WERE LOOSE AND SUPPORT CLAMPS P	N 15501261 BROKEN ON BOTH LT AND RT SIDES.  BOTH CLAMPS HAD BOTH OUTER EARS BROKEN OFF AT WELDMENT.  PREVIOUS CLAMPS FAI	LED AFTER EXHAUST SYSTEM OVERHAUL AFTER 191 HOURS.  SUSPECT THAT FAILURES MAY BE DUE TO EXCESS VIBRATION FROM MUFFLE BAL	L JOINT CLAMPS INSTALLED TOO TIGHTLY.  (K)			1	H	7	2 	3O	3	O		A6CE    	E1CE				 
2006092700005	20060927	00005	EA  	2006	9	27	2006FA0000864    	2	20060807	G	7414	M3548	ROTOR           	SLICK       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	9286M				02110612	288616044	RL681539A			ROTOR SHAFT BROKEN AT CAM SLOT.  REMOVED AND INSPECTED MAGNETO DUE TO 5 PERCENT TIMING DISCREPANCY.  INSTALLED NEW MAGNE	TO.  (K)					1	L	7	1 	3O	3	O		2A13    	E274				 
2006092200058	20060922	00058	SO  	2006	9	22	2006FA0000865    	1	20060226	G	3213	1180500	STRUT           			PIPER 	PA17  	PA17        	7101702	SO  	CONT  	A65   	A65*        	17003	SO  					LANDING GEAR	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	4879H	725  				17178				WHEN CHANGING SHOCK CORDS ON THIS AC, NOTICED A DISCOLORATION OF THE INNER STRUT TUBE (LONGER ONE, SUB PN 1180400) AND R	EMOVED IT FROM THE OUTER TUBE (SHORTER, SUB PN 1180300) ONE OF THE INNER STRUT TUBES WAS CORRODED APPROX 50 PERCENT OF C	IRCUMFERENCE.  THE OTHER INNER STRUT HAD MULTIPLE CORROSION HOLES THROUGH ALL THE METAL.  BOTH SHORT TUBES (OUTER) SHOWE	D OVAL ELONGATION AT THE ENDS INDICATING FLEXING/BENDING OF THE ASSY DURING LANDINGS AND TAKEOFF.  RELATIVELY NEW (HOURS	) BUNGEES KEPT THIS GEAR FROM FINAL FAILURE AND RESULTANT GROUND LOOP.  THE BUNGEE CORDS, WHEN INSTALLED, COVER THIS ARE	A AND ALSO USUALLY HAVE A CLOTH OR ALUMINUM FAIRING OVER THEM.  DETECTION OF THIS REQUIRES REMOVAL OF THE FAIRINGS AT A 	1	H	7	1 	3O	3	O		A805    	E205				 
2006092700011	20060927	00011	CE  	2006	9	27	2006FA0000866    	1	20060821	G	3246	50300001087	WHEEL           			BEECH 	90    	C90A        	1152911	CE  										MLG	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	304TC	214  				LJ1719				AFTER SEVERAL ATTEMPTS TO FIND SOURCE OF ONGOING TIRE LEAKAGE, WHEEL ASSEMBLY WAS REMOVED FROM AIRCRAFT AND NSPECTED.  F	OUND 2 CRACKS OPPOSITE OF (1) OTHER ALONG INNER RADIUS OF INNER WHEEL HALF.  DURING DISASSEMBLY IT WAS NOTED THAT WHEEL 	ASSEMBLY TIE BOLT NUTS DID NOT HAVE ANY SELF LOCKING FEATURE.  WHEEL WAS ORIGINAL EQUIPMENT WITH ONLY (1) TIRE CHANGE SI	NCE NEW.  (K)			1	L	7	2 	3T			RT	3A20    					 
2006083100004	20060831	00004	CE  	2006	8	31	2006FA0000867    	1	20060818	G	2400	635A050	SUPPORT BRACKET 			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					ATTENUATOR	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	719D					5250075				FOUND THE LT AND RT ATTENUATOR ACTUATOR LOWER SUPPORT BRACKETS TO BE CRACKED.  THESE BRACKETS HAVE BEEN REPLACED BY ACCO	MPLISHMENT OF SB AT PRIOR DATE.  WE HAVE REPEATEDLY FOUND THESE BRACKETS.  CRACKED AGAIN AND AGAIN AFTER THEY ARE REPLAC	ED BY THE SB.  CUSTOMERS OF HAVEING CHANGE THE BRACKETS OVER AND OVER WHEN THE SB WAS SUPPOSED TO BE ADDRESSING THE PROB	LEM WITH NEWER, IMPROVED BRACKETS.  RECOMMEND THE OEM STRENGTHEN THE REPLACEMENT BRACKETS.  (K)			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006092700010	20060927	00010	CE  	2006	9	27	2006FA0000868    	1	20060720	G	2840	62266502	SWITCH          			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL LOW LEVEL	MISMANUFACTURED 	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	17	993LC					6500027				AFTER ARRIVAL, FOUND FUEL LEAK NEAR IB END OF RT WING.  INVESTIGATION SHOWED THE LOW LEVEL FUEL LIMIT SWITCH WAS NOT ASS	EMBLED.  THE FLOAT, PN L15F2, WAS NOT ATTACHED TO THE MOUNT ASSY PN 62266503.  THIS ALLOWED FUEL TO LEAK FROM THE WING. 	 SWITCH WAS ASSEMBLED, REINSTALLED AND LEAK CHECKED.  NO FURTHER LEAKS NOTED.  (K)				2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2006083100001	20060831	00001	CE  	2006	8	31	2006FA0000869    	1	20060315	G	5500	35405130	FITTING         			BEECH 	35    	35BEECH     	1151502	CE  	CONT  	E185  	E185*       	17014	SO  					STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	4473V	4329 				D1291				STABILIZER FITTING REMOVED FROM AC TO BE CHECKED IAW AD76-05-04.  DYE PENETRANT INSPECTION REVEALED (2) CRACKS RADIATING	 FROM THE LOWER BOLT HOLE ATTACHMENT POINTS AS DEPICTED IN DWG.  PROBABLE CAUSE COULD BE FROM IMPROPER TORQUE OF ATTACHM	ENT BOLTS AT PREVIOUS INSPECTION.  THIS PART IS TO BE INSPECTED EACH 1,000 HRS TIME IN SERVICE.  SUGGEST PROPER TORQUE B	E APPLIED DURING INSTALLATION OR UPGRADE OLD FITTING TO THE NEW STYLE FITTING PN 35405130.  (K)			1	L	7	1 	3O	3	O		A777    	E246				 
2006091400196	20060914	00196	GL  	2006	9	14	2006FA0000870    	2	20060819	G	7323	21722	GOVERNOR        			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	564WP		1003 			0564E	CAE837044			PILOT OBSERVED ENGINE RPM DROOPED TO APPROX 98 PERCENT N2 AND WOULD NOT BEEP UP.  THIS CAUSING LOW ROTOR WARNING TO ILLU	MINATE, AS WELL AS AUDIO WARNING TO SOUND.  PILOT ENTERED AN AUTO ROTATION AND OBSERVED THE ENGINE SURGING AS HE APPROAC	HED THE GROUND.  NORMAL AUTO ROTATION LANDING WAS MADE WITH NO DAMAGE TO AIRCRAFT OR INJURY TO PERSONS.  FOR TROUBLESHOO	TING PURPOSE MAINTENANCE CONDUCTED AN ENGINE START AND OBSERVED THE ENGINE WOULD NOT BEEP ABOVE 98 PERCENT N2 AND MINOR 	SURGING OF THE ENGINE.  MAINTENANCE REPLACED THE PT GOVERNOR.  ENGINE AND AIRCRAFT PERFORMED NORMAL.  AIRCRAFT RETURNED 	TO SERVICE FOLLOWING OPS FLIGHT CHECK.  (K)	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092600168	20060926	00168	EA  	2006	9	26	2006FA0000871    	2	20060819	G	7322	30804	FLOAT           	PRECISION   		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					CARBURETOR	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	95429		732  		DT21385	15285892				AIRCRAFT NOTED AS HAVING FUEL DRIPPING FROM BOTTOM COWL, FOUND CAR LEAKING FUEL WHILE SITTING STATIC, REMOVED AND CHECKE	D CARBURETOR.  DETERMINED (1) OF THE (2) PONTOONS OF THE PLASTIC FLOAT WAS FULL OF FUEL, CONTACT MADE WITH MFG WHO SUGGE	STED THEY WERE AWARE OF THE PROBLEM AND HAVE SUPERSEDED THE FLOAT TO A NEWER VERSION, REPLACED THE FLOAT WITH THE 30-864	 AND 29-184 FLOAT VALVE CLIP, OPS CHECKED OK.  (K)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006091400028	20060914	00028	EU  	2006	9	14	2006FA0000872    	1	20060804	G	2760	65WE0103036	PUMP            			HWKSLY	DH1254	HS125400F   	230145 	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					SPOILERS	FAILED          	A			IAVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	4QB					25255	84435			NR 1 HYDRAULIC SYS FAILURE RESULTING IN LOSS OF HYDRAULIC FLUID.  IN FLIGHT DIVERT AFTER DEPARTURE, AFTER ALTERNATE LAND	ING GEAR/ FLAP EXTNESION.  LT HYDRAULIC SYSTEM PRESSURE LOW LIGHT ILLUMINATED ON TAKEOFF AFTER 80 KTS, CONTINUED TAKEOFF	.  AFTER COMPLETING HYDRAULIC FAILURE CHECK LIST, DETERMINED THERE WAS A HYDRAULIC LEAK.  DECLARED AN EMERGENCY AND DIVE	RTED.  COMPLETED THE HYDRAULIC LOSS CHECKLIST, WHICH BASICALLY INVOLVED PUMPIN GHE LANDING GEAR DOWN AND FLAPS TO POSITI	ON.  LANDED WITHOUT INCIDENT, STOPPED ON THE RUNWAY.  REPLACED 2 PASSENGERS, PINNED THE LANDING GEAR AND TOWED THE AC TO	 THE FBO RAMP.   (K)	2	L	7	2 	3F	4	F	RT	A3EU    	E6WE				 
2006092700022	20060927	00022	CE  	2006	9	27	2006FA0000874    	1	20060130	G	8011	PM1201H	STARTER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	70323					17267200				PM1201-H STARTER FAILED TO ENGAGE.  INSTALLED DIFFERENT MFG STARTER.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006092700029	20060927	00029	CE  	2006	9	27	2006FA0000878    	1	20060207	G	8011		PINION GEAR     			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	510LP					172S9510				PINION GEAR WOULD NOT ENGAGE RING GEAR.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006092700023	20060927	00023	CE  	2006	9	27	2006FA0000879    	1	20060630	G	8011		PINION GEAR     			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	510LP					172S9510				PINION GEAR NOT ENGAGING RING GEAR COMPLETELY.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006092200119	20060922	00119	CE  	2006	9	22	2006FA0000880    	1	20060830	G	2821	075601011	PLUNGER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					FUEL STRAINER	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	5067H	4170 				17265326				FUEL STRAINER WOULD NOT DRAIN WHEN ACTUATED. INVESTIGATION REVEALED THAT THE RUBBER NIPPLE HAD SEPARATED FROM THE PLUNGE	R, (P/N 0756010-11). THE FUEL SUMP DRAIN ON THE LT WING ALSO LEAKED AND WAS REPLACED. THE AC HAD RECENTLY BEEN PURCHASED	 AND IT WAS NOTED THAT AUTO FUEL HAD BEEN USED IN THE PAST. AN STC WAS SECURED AND INSTALL IT ON THE AIRCRAFT. IT IS MY 	OPINION THAT AN AUTO FUEL WITH ETHANOL ALCOHOL HAD BEEN USED, IN THAT THE PLUNGER NIPPLE WAS (ROCK) HARD AS WAS THE FUEL	 SUMP DRAIN SEAL. ALL MECHANICS NEED TO MAKE NOTE AS THIS COULD HAVE CAUSED ALL THE FUEL TO LEAK OUT IN FLIGHT AND CAUSE	D AN OFF FIELD LANDING OR WORSE. IF YOU SMELL AUTO FUEL GO AS DEEP AS NECESSARY TO DETERMINE THE SERVICEABILITY OF THE S	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006092500165	20060925	00165		2006	9	25	2006FA0000881    	2	20060830	G	7261	537650	COVER           			BLANCA	17    	1730A       	1220433	GL  										OIL SUMP	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	15	711LA	2100 	200  			30411				5 INCH SPANWISE CRACK, 10 INCHES AFT OF FORWARD EDGE OF OIL SUMP COVER.						1	L	7	1 	3O				A18CE   					 
2006092700025	20060927	00025	EA  	2006	9	27	2006FA0000884    	2	20060829	G	7322	30804	FLOAT           	LYC         	MA4SPA105217	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	CARBURETOR BOWL	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	3066H				DC43329	287916219	LW1498739A	A60546		ON SHUTDOWN, THE RPM INCREASED 400 RPM.  ON IDLE, THE ENGINE WOULD IDLE AT 600 RPM, THEN DROP TO 300 RPM THEN DIE.  ON O	PENING THE CARBURETOR, HALF OF THE WHITE PLASTIC FLOAT WAS 80 PERCENT FULL OF FUEL.  IT DID NOT LEAK OUT OVER NIGHT.  (K	)				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006091300396	20060913	00396	SO  	2006	9	13	2006FA0000885    	1	20060812	G	7820		MUFFLER         			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					EXHAUST SYS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4418Z	81   				188753				DURING ANNUAL INSP FOUND CRACK AT END OF ONE SUPPORT BRACE WITH EVIDENCE OF EXHAUST LEAK.  ADVISED OWNER, HE SAID HE HAD	 EXPERIENCED EXHAUST LEAKAGE WITH MILD NOSE AND LEAKAGE.   REPAIRED MUFFLER AND RETURNED TO US AND MUFFLER WAS REINSTALL	ED.  (K)				1	H	7	1 	3O	3	O		1A2     	E274				 
2006091300258	20060913	00258		2006	9	13	2006FA0000886    	1	20060830	G	8011		STARTER         																	ENGINE	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		45   								STARTER, WILL NOT SPIN ON LOAD.																			 
2006092200089	20060922	00089	EU  	2006	9	22	2006FA0000887    	1	20060815	G	7797		CONNECTOR       			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TORQUE IND	CONTAMINATED    	B			HXSR	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			AL	05	57954					1127	501			DEPARTED BASE, HEADED FOR THE GLACIER, EN ROUTE THE PILOT NOTICED HIS TORQUE READING WAS FLUCTUATING.  THE PILOT RETURNE	D TO BASE AND THE MECHANIC FOUND THAT THE ENGINE DECK PLUG HAD WATER IN IT FROM THE HEAVY RAINS WE HAVE BEEN ENDURING.  	THE MECHANIC CLEANED OUT THE PLUG AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER AN OPERATIONS CHECK WAS COMPLETED.  (K)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006091300384	20060913	00384	EA  	2006	9	13	2006FA0000888    	1	20060608	G	6210	234R0001	BLADE           			BOEING	234   	234         	1385049	EA  										MAIN ROTOR	DEBONDED        	B			CHIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CFHFB					MJ005				ROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329, APPROXIMATEL	Y 475-500 SQUARE INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE.  UNBONDED SKIN WAS RE	MOVED TO EXPOSE HONEYCOMB CORE FOR INSPECTION.  HONEYCOMB WAS OIL FREE AND APPEARED TO BE IN GOOD CONDITION.  THE ROTOR 	BLADE WILL UNDERGO FURTHER INVESTIGATION TO DETERMINE THE PROBABLE CAUSE AND REPAIR SCHEME IF POSSIBLE.  THE MANUFACTURE	R HAS BEEN NOTIFIED.  (K)		2	G	7	2 	4U				H9EA    					 
2006091300395	20060913	00395	GL  	2006	9	13	2006FA0000889    	1	20060829	G	7920		UNION           			AMTR  	LANCAR	LC41550FG   	5150001	GL  	CONT  	O550  	TSIO550C    		SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	999GL	251  				41034	802678			THE AN911-1J UNION THAT SUPPLIES OIL TO THE OIL PRESSURE TRANSDUCER, THE HOBBS PRESSURE SWITCH, AND THE OIL FEED LINE, A	T THE BASE OF THE OIL COOLER, ON THE BACK OF THE ENGINE, WAS CRACKED AT THE PIPE THREADS, AND THEN BROKE IN THE PROCESS 	OF REMOVING THE PART.  THE WEIGHT OF THE FITTINGS ATTACHED TO THE UNION HANGING OUT AS FAR AS THEY ARE, AND THE VIBRATIO	N OF THE ENGINE, MAY HAVE CAUSED THE UNION TO CRACK AT THE PIPE THREADS.  THE HARDNESS OF THE STAINLESS STEEL PART COULD	 ALSO HAVE BEEN PART OF THE PROBLEM.  THE AC WAS SCHEDULED THAT DAY BUT AN OIL LEAK WAS NOTICED AND INVESTIGATED BEFORE 	THE FLIGHT, WHICH WOULD HAVE ENDED WITH A CATASTROPHIC FAILURE OF THE ENGINE DUE TO OIL LOSS.  THE TEMPORARY RECOMMENDAT	1	L	7	1 	3O	3	O	RT	EXPA1L71	E5SO				 
2006091300364	20060913	00364	CE  	2006	9	13	2006FA0000890    	1	20060824	G	2730		CONTROL CABLE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR	OUT OF ADJUST   	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	405DD					LJ1748				DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTIONS NOTED ELEVATOR CONTROL SYSTEM CABLE TENSIONS OUT OF MM SERVICE LIMI	TS.  FOUND ELEVATOR NEUTRAL POSITIONS OUT OF LIMITS FOLLOWING CABLE TENSION ADJUSTMENTS (WITH FORWARD AND AFT RIG PINS I	NSTALLED).  FOUND FORWARD BELLCRANK DOWN STOP BOLT CLEARANCE PAST SERVICE LIMIT AND ADJUSTED.  FOUND ELEVATOR BOBWEIGHT 	CLEARANCE GAP EXCESSIVE.  REQUIRED ADJUSTING THE  FORWARD PUSHROD ASSY AND ADDING WASHERS TO OBTAIN BOBWEIGHT CLEARANCE 	WITHIN SERVICE LIMITS.  AIRCRAFT HAD BEEN SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MANUFACTURE LOGB	OOK RECORDS.  RECOMMEND FOLLOW-UP INVESTIGATION BY MFG ON OTHER AC.  (K)	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006092700043	20060927	00043	CE  	2006	9	27	2006FA0000891    	1	20060824	G	3350	8751062	POWER SUPPLY    			BEECH 	MU300 	400A        	1155402	CE  										EMERGENCY LIGHTS	INOPERATIVE     	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	45RK	3957 				RK43				DURING SCHEDULED 12 MONTH/200 HR INSPECTION OF AIRCRAFT SERVICES EMERGENCY LIGHTING SYS INSTALLED UNDER STS ST00344AT FO	UND AFT POWER INSTALLED UNDER STC ST00344AT FOUND AFT POWER SUPPLY TO HAVE NO OUTPUT.  VERIFIED POWER SUPPLY RECEIVING B	ATTERY CHARGING VOLTAGE AND BATTERY FULLY CHARGED.  REPLACED POWER SUPPLY WITH NEW UNIT, SYSTEM TESTS SATISFACTORY IAW M	ANUAL INSPECTION GUIDE.  (K)			2	H	7	2 	4F			RT	A16SW   					 
2006091300362	20060913	00362		2006	9	13	2006FA0000892    	4	20060824	G	2215	6225735002	MOUNT           			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RUDDER SERVO	DISTORTED       	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	405DD	201  				LJ1748				DURING FIRST SCHEDULED 1ST AND 2ND PHASE INSPECTIONS NOTED SQUEAKING AND METAL TO METAL CONTACT NOISES WHEN RUDDER MOVED	 SIDE TO SIDE.  FOUND RUDDER SERVO CABLE RUBBING ON SMT-65 SERVO MOUNT CABLE DRUM COVER.  REPLACED SMT-65 UNIT AND REINS	TALLED, RIGGED SERVO CABLE.  RUDDER OPERATIONS NOW NORMAL, AUTOPILOT OPERATIONAL CHECKS OK.  SUSPECT SMT -65 SERVO MOUNT	 EITHER DISTORTED FROM PRIOR HANDLING OR NOT ASSEMBLED CORRECTLY.  (K)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006091300363	20060913	00363	CE  	2006	9	13	2006FA0000893    	1	20060824	G	2720		FASTENER        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RUDDER SYS	OVERTORQUED     	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	405DD					LJ1748				FOUND OTHER LT SIDE RUDDER CONTROL ATTACHING HARDWARE TIGHT OR OVERTIGHTENED.  EXAMINED LT RUDDER CONTROL SYSTEM HARDWAR	E FOR SERVICEABILITY AND REINSTALLED AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED 	WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED.  REPLACED PILOT`S OB PUSHROD ASSY BEARINGS AND R	EINSTALLED.  NOSEWHEEL STEERING AND RUDDER OPERATIONS FOUND NORMAL AFTER REASSEMBLY.  SUSPECT HARDWARE POSSIBLY OVERTIGH	TENED DURING INITIAL AC ASSY, AIRCRAFT WAS ALSO SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MFG.  RECO	MMENDED FURTHER INVESTIGATION BY MFG TO DETERMINE IF A ONE-TIME SB.  (K)	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006091300361	20060913	00361	CE  	2006	9	13	2006FA0000894    	1	20060824	G	2720	139909B47	BOLT            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RUDDER SYS	OVERTORQUED     	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	405DD					LF1748				DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTION INVESTIGATED PILOT COMPLAINT OF STIFF NOSEWHEEL STEERING.  VERIFIED 	COMPLAINT, FOUND NOSEWHEEL STEERING STIFF AND LOUD POPPING NOISES COMING FROM COCKPIT UNDER FLOOR AREA WHEN TAXIED FROM 	COPILOTS POSITION.  ACCESSED COCKPIT AREA RUDDER CONTROL SYSTEM AND FOUND PILOTS SIDE OB RUDDER CONTROL PUSHROD TO HAVE 	EXCESSIVE PLAY.  UPON REMOVING OB PUSHROD ASSY.  BEARINGS FELL OUT OF ROD END BEARING ASSY.  FURTHER INVESTIGATION SHOWE	D PN 50-5244553 LT SIDE RUDDER BELLCRANK ASSY OPERATION TIGHT, FOUND  PN 139909B47 PIVOT BOLT OVERTIGHTENED.  ALSO FOUND	 LT TO RT RUDDER CONTROLS INTERCONNECT TUBE ATTACHING HARDWARE OVERTIGHTENED.  (K)	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006091400152	20060914	00152	EU  	2006	9	14	2006FA0000896    	2	20060824	G	7250	1975M84P01	RETAINER        			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					ENGINE	DISLODGED       	W			QEMY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	SPLKC	29341					857849			(REF: 2006FA00008996) DURING STRIP OF ENGINE 857819 FOR SCHEDULED LLP REPLACEMENT IT WAS NOTED THAT THE HPT FORWARD BLAD	E RETAINER HAD LIBERATED 2 SECTIONS OF MATERIAL, ONG 3.5 INCHES X .8750 INCH AND 1) 2 INCH X .8750 INCH.  THE LIBERATED 	MATERIAL HAD CAUSED MINOR LPT AND HPT IMPACT DAMAGE.  MFG HAS BEEN ASKED TO INVESTIGATE THIS DEFECT.  (K)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006091300394	20060913	00394	EA  	2006	9	13	2006FA0000897    	2	20060825	G	8530	AEL65102	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	SEPARATED       	D				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	733EN	206  				17268239				PILOT EXPERIENCED A NOTICEABLE POP SOUND IN ENGINE COMPARTMENT FOLLOWED BY ROUGHNESS.  SOON AFTER THE ENGINE OIL PRESSUR	E STARTED TO DETERIORATE AND PILOT ELECTED TO SHUTDOWN ENGINE AND STOPPED PROPELLER FROM TURNING BY PUTTING AIRCRAFT IN 	NOSE HIGH ATTITUDE.  HE MANAGE TO GLIDE TO MAJOR AIRPORT AND DEAD STICK LAND SUCCESSFULLY WITHOUT ACCIDENT.  INVESTIGATI	ON SHOWED THAT THE NR 1 CYLINDER HEAD SEPARATED FROM BARREL.  THIS CYLINDER WAS REPLACED 206 HOURS PRIOR WHEN ENGINE WAS	 OVERHAULED.  THE CYLINDER WAS PURCHASED NEW.  NEW CYLINDER WAS INSTALLED AND ENGINE RAN NORMALLY WITH NO ADVERSE PROBLE	MS NOTED.  THE SEPARATION OF CYLINDER IS THOUGHT TO BE STRESS CRACKING DUE TO THREADS CUT IN CYLINDER HEAD HAVING LITTLE	1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2006091300399	20060913	00399	GL  	2006	9	13	2006FA0000898    	1	20060818	G	3213	21410103	AXLE            			BOMBDR	BD700 	BD7001A10   	1390006	GL  										LT MLG	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	700ML	2175 				9043				LT MLG TRAILING ARM AXLE FOUND TO HAVE CORROSION ON TAPERED WASTELAND AREAS AT BOTH WHEEL POSITIONS.  (K)						2	L	7	2 	4F			RT	T00003NY					 
2006091300393	20060913	00393	SW  	2006	9	13	2006FA0000899    	1	20060809	G	3230	ED10055	BOLT            			GULSTM	690TP 	690C        	7630517	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					NLG	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	777NV	4937 				11680				DURING ROUTINE INSPECTION FOUND NOSE GEAR LOWER DRAG BRACE BOLT SHEARED AT JUNCTION OF REDUCED DIAMETER BOLT HAD NOT YET	 CAME OUT OF ITS BORE AND THEREFORE THE GEAR DID NOT COLLAPSE.  BUT IT WAS READY TO.  (K)					1	H	7	2 	3T	3	T		2A4     	E2WE				 
2006092500160	20060925	00160	WP  	2006	9	25	2006FA0000900    	1	20060901	G	6720	HS10537	CABLE           			HILLER	UH12  	UH12E       	4360122	WP  										TAIL ROTOR	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			AG	AGRICULTURE    	1			SW	11	8402D	250  				1093				LT TAIL ROTOR CABLE FAILED. OPERATOR OPERATES IN VERY DUSTY ENVIRONMENT. BUILD UP OF DUST AND OILY SUBSTANCE FROM PRODUC	T FOR SPRAYING CAUSE A FINE ABRASIVE SUBSTANCE ON CABLES AT PULLEYS. CABLE NEEDS PROTECTION FROM ENVIRONMENT AND MORE FR	EQUENT INSPECTION AND/OR REPLACEMENT.				1	G	7	1 	3O				4H11    					 
2006091500020	20060915	00020	CE  	2006	9	15	2006FA0000901    	1	20060912	G	2497	1N6391	DIODE           	CESSNA      		CESSNA	172   	172S        	2072439	CE  										BUSS BAR	FAULTY          	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	452ER	48   	48   			172S10255				ON A RECENT LOCAL FLIGHT, ONE OF THESE AIRCRAFT EXPERIENCED THE LOSS OF THE MFD, OR RT DISPLAY AS WELL AS THE COMM 2, NA	V 2, AUDIO PANEL AND TRANSPONDER. THE CREW ELECTED TO MAKE A PRECAUTIONARY LANDING AT THE NEAREST AIRPORT. ON INSPECTION	, IT WAS DISCOVERED THAT THE POWER TO BUSS 2 WAS NOT PRESENT. THE BUSS 2 CIRCUIT BREAKER WAS REPLACED AND THE SYSTEM FUN	CTIONED PROPERLY. SHORTLY AFTER, THE MFD FAILED AGAIN. AFTER CLOSER INSPECTION THE WIRE PROVIDING POWER TO THE MFD BREAK	ER WAS FOUND LOOSE ON THE TERMINAL. THIS WIRE WAS SECURED AND THE AIRCRAFT INCURRED NO FURTHER PROBLEMS. A FLEET INSPECT	ION OF THE BUSS WIRING FOR THE ESSENTIAL BUSS, BUSS 1 AND BUSS 2 WAS COMMENCED. ADDITIONAL LOOSE WIRE TERMINALS WERE FOU	1	H	7	1 	3O			NT	3A12    					 
2006092600050	20060926	00050	SO  	2006	9	26	2006FA0000902    	2	20060729	G	8530	649543	CYLINDER        			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300*      	17022	SO  					ENGINE	SEPARATED       	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	11	6793E	3    	3    			56293	121479C			NR (5) CYLINDER SEPARATED FROM THE CRANK-CASE IN FLIGHT RESULTING IN ENGINE FAILURE AND AN UN-PLANNED, SAFE LANDING OF T	HE AIRCRAFT.					1	H	7	1 	3O	3	O		3A17    	E298				 
2006091800010	20060918	00010	CE  	2006	9	18	2006FA0000903    	1	20060913	G	2497	1N6391	DIODE           			CESSNA	172   	172S        	2072439	CE  										NR 1 BUSS	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	465ER	38   				172S10290				THIS OPERATOR HAS A FLEET OF 16 CESSNA 172S NAVIII AIRCRAFT.  DUE TO SOME OPERATIONAL DIFFICULTIES WHERE BUSS WIRING DIS	CREPANCIES WERE FOUND, A FLEET WIDE INSPECTION OF THE BUSS WIRING, TERMINAL CONNECTIONS AND WIRE ROUTING WAS ACCOMPLISHE	D.  THE FOLLOWING WAS FOUND ON THIS AIRCRAFT: REMOVED CIRCUIT BREAKER PANEL AND FOUND LOOSE WIRES COMING FROM DIODES, GO	ING TO DIFFERENT CIRCUIT BREAKER BUSSES.  TIGHTENED LOOSE NUTS AND CHECKED ALL OTHER WIRE CONNECTIONS, NONE NOTED.  REMO	VED SPARE WIRES LOOPED THRU OPEN BREAKER MOUNTING HOLE AND SECURED TO WIRE BUNDLE.  CHECKED J-BOX FOR LOOSE CONNECTIONS,	 NONE NOTED.  REINSTALLED BREAKER PANELS AND SECURED ALL WIRES AND FITTINGS.	1	H	7	1 	3O			NT	3A12    					 
2006092100249	20060921	00249	EA  	2006	9	21	2006FA0000904    	2	20060914	G	7313	LW15472	PUMP            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					FUEL SYSTEM	LEAKING         	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	7103W	2900 				28890	L505536			UPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF	.  NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING	 FROM THE FUEL PUMP VENT LINE.  THIS APPEARED TO BE A MIX OF GAS AND OIL. IT IS ESTIMATED 3-4 QUARTS DRAINED FROM THE VE	NT BEFORE STOPPING. THE OIL PAN WAS DRAINED AND WAS FOUND TO CONTAIN 8-10 QUARTS OF GAS/OIL MIX. THE OIL FILTER WAS OPEN	ED AND NO METAL WAS FOUND. THE OLD PUMP HAS NOT YET BEEN OPENED AND WAS OPERATING SUFFICIENTLY FOR THE ENGINE TO RUN, BU	T IT IS PRESUMED THE PUMP DIAPHRAGM HAD RUPTURED CAUSING FUEL TO LEAK INTO THE ENGINE CRANKCASE. NO EVIDENCE OF THE PUMP	1	L	7	1 	3O	3	O		2A13    	E286				 
2006092200042	20060922	00042	EA  	2006	9	22	2006FA0000905    	2	20060914	G	7314		DIAPHRAGM       	AC          		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					FUEL PUMP	RUPTURED        	P				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			GL	03	7103W					28890	L505536			UPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF	.  NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING	 FROM THE FUEL PUMP VENT LINE.  THIS APPEARED TO BE A MIX OF GAS AND OIL. IT IS ESTIMATED 3-4 QUARTS DRAINED FROM THE VE	NT BEFORE STOPPING. THE OIL PAN WAS DRAINED AND WAS FOUND TO CONTAIN 8-10 QUARTS OF GAS/OIL MIX. THE OIL FILTER WAS OPEN	ED AND NO METAL WAS FOUND. THE OLD PUMP HAS NOT YET BEEN OPENED AND WAS OPERATING SUFFICIENTLY FOR THE ENGINE TO RUN, BU	T IT IS PRESUMED THE PUMP DIAPHRAGM HAD RUPTURED CAUSING FUEL TO LEAK INTO THE ENGINE CRANKCASE. NO EVIDENCE OF THE PUMP	1	L	7	1 	3O	3	O		2A13    	E286				 
2006092700028	20060927	00028	SO  	2006	9	27	2006FA0000906    	2	20060823	G	8520	TCM536379	BOLT            								CONT  	O550  	TSIOL550A   	 	SO  					CRANKSHAFT GEAR	SHEARED         	B			VA1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19		58   					800554			CRANKSHAFT GEAR BOLTS SHEARED/BROKE CAUSING ENGINE FAILURE.  (ENGINE FIALED ON GROUND, DURING STARTING) (K)											3	O			E4SO				 
2006092700030	20060927	00030	CE  	2006	9	27	2006FA0000907    	1	20060822	G	3230	99100023	MOTOR           			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470*      	17026	SO  					MLG	FAILED          	B			E81R	L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			GL	03	7940Q					310Q0623				LANDING GEAR WOULD NOT EXTEND ELECTRICALLY ON APPROACH.  OPERATIONS NORMAL WHEN LANDING GEAR EXTENDED WITH MANUAL EMERGE	NCY EXTENSION SYS. FOUND LANDING GEAR ACTUATOR MOTOR INOPERATIVE.  WOULD MAKE NOISE BUT NOT ROTATE.  REPLACED MOTOR WITH	 OVERHAULED REPLACEMENT UNIT; LANDING GEAR SYS OPERATIONS NORMAL.  CLEANED CORROSION FROM BATTERY TERMINALS, SUSPECT VOL	TAGE DROP UNDER  LANDING GEAR OPERATIONS LOAD MAY HAVE CONTRIBUTED.  TRANSIENT AC, RECORDS NOT AVAILABLE TO VERIFY MOTOR	 TIME IN SERVICE.  (K)		1	L	7	2 	3O	3	O		3A10    	E1CE				 
2006092600238	20060926	00238	CE  	2006	9	26	2006FA0000908    	1	20060817	G	3230	MS250261	SWITCH          			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					MLG	FOULED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	515EK					EA440				LANDING GEAR WOULD NOT EXTEND ELECTRICALLY UPON APPROACH TO RFD.  MANUAL EXTENSION OPERATIONS NORMAL.  TROUBLESHOT LANDI	NG GEAR ELECTRICAL SYS.  FOUND S45 LANDING GEAR ACTUATOR DYNAMIC BRAKE DOWNLIMIT SWITCH OIL SOAKED AND FOULED BY LINT, F	UZZ, ETC.  CLEANED DOWNLIMIT SWITCH AS REQUIRED AND CYCLED LANDING GEAR ELECTRICALLY; OPERATION NORMAL.  SUSPECT OIL AND	 LINT BLOCKING FULL SWITCH TRAVEL AND/OR CAUSING HIGH RESISTANCE IN S45 SWITCH.  DYNAMIC BRAKE LIMIT SWITCHES SHOULD BE 	INSPECTED CLOSELY AND CLEANED IF REQUIRED EACH 100 HR OR ANNUAL INSPECTION.  THIS AREA CAN BE PRONE TO ATTRACTING DIRT A	ND UPHOLSTERY (FUZZ).  (K)	1	L	7	1 	3O	3	O		3A15    	E7CE				 
2006092700026	20060927	00026	GL  	2006	9	27	2006FA0000909    	1	20060907	G	7120		BELT            			AMTR  	WOODY 	WOODYPUSHER 	       	GL  	CONT  	A65   	A65*        	17003	SO  					REDUCTION BRACK	FRACTURED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	56JH	191  				JEH2				ULTRALIGHT FRACTURED ENGINE BELT REDUCTION BRACKET CAUSING IN-FLIGHT SHUTDOWN AND EMERGENCY LANDING.  PROBABLE CAUSE: EN	GINE BELT REDUCTION BRACKET STRESS/FATIGUE CRACK CAUSING HEAVY ENGINE VIBRATION AND SHUTDOWN.  (K)					1	H	7	1 	3O	3	O		EXPA1H71	E205				 
2006092700024	20060927	00024	CE  	2006	9	27	2006FA0000910    	1	20060626	G	3000	991240217	SHUTOFF VALVE   			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ANTI-ICE SYS	MISINSTALLED    	B			EBVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	993LC					6500027				DETERMINED THE PRESSURE REGULATOR SHUTOFF VALVE WAS LEAKING.  FOUND THE REGULATOR HAD BEEN INSTALLED WITHOUT GASKETS.  T	HE PARTS MANUAL DOES NOT CLEARLY IDENTIFY THAT GASKETS ARE REQUIRED TO BE INSTALLED WITH THIS SPECIFIC PN OF VALVE.  CON	TACTED AND CONFIRMED THAT GASKET PN 24096-150C IS REQUIRED TO BE INSTALLED ON THIS VALVE.  MAINTENANCE PERSONNEL INSTALL	ED GASKETS, PERFORMED LEAK CHECK, AND DETERMINED LEAKAGE PROBLEM HAD BEEN CORRECTED BY INSTALLATION OF GASKETS.  (K)			2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2006092700033	20060927	00033	EA  	2006	9	27	2006FA0000911    	2	20060828	G	7314	RGRG0957OK1	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					ENGINE FUEL	LEAKING         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	788  				85002	RL2155648A			PILOT REPORTED A STRANGE ODOR AFTER THEY PUT THE GEAR UP, WHILE TROUBLESHOOTING MECHANIC FOUND ENGINE FUEL PUMP LEAKING 	FROM PRESSURE ADJUSTMENT SCREW.  NO PROPABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2006092700021	20060927	00021	CE  	2006	9	27	2006FA0000912    	1	20060817	G	3610	AA3216CW	SHAFT           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					AIR PUMP	SHEARED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8240T	173  				CE1542	830141R			PILOT REPORTED INSTRUMENT AIR PRESSURE WENT TO -0- IN FLIGHT, PILOT THEN SELECTED STANDBY PUMP AND RETURNED TO BASE.  UP	 ON TROUBLESHOOTING THE MECHANIC REMOVED THE AIR PUMP AND FOUND THE SHAFT WAS SHEARED.  NO PROBABLE CAUSE OR RECOMMENDAT	IONS AT THIS TIME.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006092700032	20060927	00032	CE  	2006	9	27	2006FA0000913    	1	20060817	G	3610	AA3216CW	SHAFT           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					AIR PUMP	SHEARED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8240T	173  				CE1542	830141R			PILOT REPORTED INSTRUMENT AIR PRESSURE WENT TO -0- IN FLIGHT, PILOT THEN SELECTED STANDBY PUMP AND RETURNED TO BASE.  UP	ON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND FOUND THE SHAFT WAS SHEARED.  NO PROBABLE CAUSE OR RECOMMENDAT	IONS AT THIS TIME.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006092700037	20060927	00037	NE  	2006	9	27	2006FA0000914    	2	20060821	G	7261	3035890	TRANSFER TUBE   			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					ENGINE OIL	CHAFED          	B			BNGR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	19	234CW					LA236	PCE35079			IN FLIGHT NOTICED TORQUE METER WAS UNSTABLE, CHECKED OIL PRESSURE AND SAW IT DROPPING.  REDUCED POWER TO IDLE OIL PRESSU	RE WAS IN YELLOW RANGE.  SHUTDOWN ENGINE AND LANDED.  REMOVED FRONT COWLING AND FOUND INLET DEICE TUBE HAD RUBBED A HOLE	 IN THE OIL PRESSURE TRANSFER TUBE RT SIDE ON ENGINE.  CHECKED CHIP DETECTOR CHECKED OK.  CHECKED OIL FILTER CHECKED OK.	  REMOVED AND REPLACED TUBE AND RELOCATED DEICE TUBE.  SERVICED OIL SYSTEM AND GROUND RUN RECHECKED CHIP DETECTOR AND FI	LTER CHECKED OK.  RECOMMEND THAT BEFORE FRONT TOP COWLING IS INSTALLED THAT DEICE TUBES BE CHECKED FOR CLEARANCE AT OTHE	R ITEMS IN COWLING.  (K)	1	L	7	2 	4T	4	T		A31CE   	E4EA				 
2006092700015	20060927	00015	NM  	2006	9	27	2006FA0000915    	1	20060802	G	3232	273T61027	CYLINDER        	BOEING      		BOEING	767   	767*        	       	NM  										ACTUATOR	DAMAGED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01			33938		SHL1262					(REF NR: 209609/QN1) PIN HOLE THROUGH CYLINDER WALL.  PRESSURES CYCLES AND MATERIAL DEFECT. (K)						2	L	7	2 	4F			RT	A1NM    					 
2006092700044	20060927	00044	NM  	2006	9	27	2006FA0000916    	1	20060802	G	2913	65447822	HOUSING         			BOEING	737   	737*        	       	NM  										HYD PUMP	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01										(REF NR 209606/PH30) CRACK IN HOUSING.  CYCLICAL FATIGUE.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006092600134	20060926	00134	SO  	2006	9	26	2006FA0000917    	2	20060906	G	8520	653631	GEAR            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	CRANKSHAFT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	8411Q	167  				U20603271	830575R	011026		AC FLEW A SHORT LEG TO AN ISLAND 25 NM OFFSHORE.  AFTER START-UP THE PILOT HEARD AN UNUSUAL NOISE THAT SOUNDED LIKE A LO	OSE VALVE TRAIN.  THE PILOT QUICKLY SHUT THE POWERPLANT DOWN AND DECIDED IT WOULD NOT BE SAFE TO COMPLETE THE TRIP BACK 	TO MAINLAND.  MECHANIC FLEW OUT TO THE ISLAND TO DETERMINE THE SOURCE OF THIS UNUSUAL NOISE.  FURTHER INVESTIGATION REVE	ALED THAT THE SOURCE OF THE NOISE WAS 2 TEETH BROKEN OFF OF THE CRANKSHAFT GEAR.  THE IDLER GEAR AND THE STARTER ADAPTER	 GEAR WERE ALSO DAMAGED AS A RESULT OF THE INTERACTION WITH THE DAMAGED CRANKSHAFT GEAR.  THE TEETH THAT WERE BROKEN OFF	 HAVE NOT BEEN LOCATED.  METAL SLIVERS AND PIECES WERE ALSO IDENTIFIED IN THE AREA AND OIL.  THIS IS PRELIMINARY INFORMA	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2006092100246	20060921	00246	CE  	2006	9	21	2006FA0000918    	1	20060913	G	2497		JUMPER          			CESSNA	172   	172S        	2072439	CE  										CB PANEL	LOOSE           	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	458ER	15   				172S10258				DURING INSPECTION OF THE BUS WIRING, THE JUMPER WIRE BETWEEN THE ESSENTIAL BUS AND THE BUS 1 CONNECTION WAS FOUND LOOSE.	 THE REMAINDER OF THE SCREWS OF THOSE CIRCUIT BREAKERS WERE CHECKED FOR SECURITY, AND SEVERAL WERE FOUND SLIGHTLY LOOSE 	REQUIRING .2500 TURN OR MORE TO SECURE THEM.				1	H	7	1 	3O			NT	3A12    					 
2006092100252	20060921	00252	CE  	2006	9	21	2006FA0000919    	1	20060911	G	2497	1N6391	DIODE           			CESSNA	172   	172S        	2072439	CE  										ELECTRICAL	LOOSE           	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	461ER	34   				172S10281				DURING INSPECTION OF THE BUSS STRIPS, THE 2 DIODES FOR THE ALT AND WARNING CIRCUIT BREAKERS WERE FOUND LOOSE AT THEIR AT	TACH POINTS TO THE BUS. THE ATTACHING HARDWARE  (NUTS) WERE SEVERAL COMPLETE TURNS FROM BEING SECURE, OR ABOUT THE WIDTH	 OF THE NUT GAP SHOWING.				1	H	7	1 	3O			NT	3A12    					 
2006092600029	20060926	00029		2006	9	26	2006FA0000922    	4	20060915	G	2330	1F220100102	AMPLIFIER       			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					ENTERTAIN SYS	FIRE            	C				H				DEACTIVATE SYST/CIRCUITS				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			EA	17	367G					28579				WHILE MAINTENANCE PERSONNEL WERE PERFORMING A ROUTINE POST FLIGHT INSPECTION, A TECHNICIAN DISCOVERED A PROBLEM.  ACFT P	OWERED BY EXTERNAL POWER, AND CABIN ENTERTAINMENT SYS OPERATING (PLAYING A DVD MOVIE) WITH THE AUDIO SYSTEM VOLUME AT A 	LOW LEVEL.  AFTER A FEW MINUTES OF OPERATION, A TECHNICIAN NOTICED SMOKE AND FUMES COMING FROM TWO OF THE FORWARD CABIN 	SPEAKERS (LOUNGE AREA).  ONE SPEAKER EMITTED A FLAME APPROXIMATELY 2 TO 3 INCHES IN LENGTH.  THE TECHNICIAN QUICKLY SHUT	 DOWN ALL AIRCRAFT ELECTRICAL POWER, AND RETURNED TO THE DAMAGED SPEAKER AREA WITH AN ONBOARD FIRE EXTINGUISHER.  THE FL	AME HAD SELF EXTINGUISHED, HOWEVER, THE CABIN WAS VERY SMOKEY AT THAT POINT.  UPON FURTHER EXAMINATION, (2) SPEAKERS HAD	2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006092200086	20060922	00086	WP  	2006	9	22	2006FA0000923    	2	20060823	G	7261	30745732	CARBON SEAL     			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	DETERIORATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	922JW					038				(NR 4 CARBON SEAL, PN30745732, SN 010515810208),  (NR 5 CARBON SEAL, PN 30745742, SN 0119368002352) PILOTS REPORT HIGH O	IL PRESSURE.  OIL PRESSURE FOLLOWED THROTTLE HIGH GEARBOX PRESSURE CAUSED BY DETERIORATION OF NR 4 AND NR 5 CARBON SEALS	.				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2006092600241	20060926	00241	WP  	2006	9	26	2006FA0000924    	2	20060823	G	7261	30745742	CARBON SEAL     			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 5	DETERIORATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	922JW					038				(NR 4 CARBON SEAL, PN30745732, SN 010515810208) (NR 5 CARBON SEAL, PN30745742, SN 011936802352)  PILOTS REPORT HIGH OIL 	PRESSURE.  OIL PRESSURE FOLLOWED THROTTLE HIGH GEARBOX PRESSURE CAUSED BY DETERIORATION OF NR 4 AND NR 5 CARBON SEALS.  	(K)				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2006092100199	20060921	00199	CE  	2006	9	21	2006FA0000925    	1	20060917	G	5711	082260039	SPAR CAP        			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470*      	17026	SO  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	69704	5433 				310Q0930				DURING THE ANNUAL INSPECTION, FOUND UPPER AND LOWER REAR SPAR DAMAGE ON THIS AIRCRAFT. THIS DAMAGE IS DUE TO CORROSION O	N THE UPPER AND LOWER REAR SPAR CAPS.  THE UPPER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CA	P EXTENDING IB FROM UNDER RIB PN 0822175-69 AT STATION 57.50. THIS DAMAGE IS APPROX. 3 INCHES HORIZONTALLY, .7500 INCH V	ERTICALLY AND .2500 IN DEPTH.  THE LOWER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CAP EXTEND	ING OB FROM UNDER RIB PN 0822175-69 AT STATION 57.50. THIS DAMAGE IS APPROX. 6 INCHES HORIZONTALLY AND THE ENTIRE LOWER 	SPAR CAP IN THIS AREA IS ESSENTIALLY MISSING.  THE LT WING HAS BEEN REMOVED AND SENT FOR REPAIR.	1	L	7	2 	3O	3	O		3A10    	E1CE				 
2006092200047	20060922	00047	CE  	2006	9	22	2006FA0000926    	1	20060919	G	7830	HS78320009	THRUST REVERSER 			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  											CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	852QS	5855 				258452				MAJOR CORROSION ON THE THRUST REVERSER DOOR RAMP SKINS DUE TO THE PAINT MISSING FROM THE RIVET HEADS.  BY MAJOR CORROSIO	N, WE ARE BLENDING THE AREAS BELOW LIMITS AND HAVING TO SEND THEM OUT FOR REPAIR.  AREAS OF CORROSION ARE NOT ONLY BEING	 FOUND ON THE RIVET HEADS WE ARE FINDING SURFACE CORROSION ANYWHERE THE PAINT IS MISSING ON THE RAMP SKINS.				2	L	7	2 	4F			RT	A3EU    					 
2006092200048	20060922	00048	CE  	2006	9	22	2006FA0000927    	1	20060919	G	7830		SKIN            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										THRUST REVERSER	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	852QS	5855 			TECAV0114	258452				MAJOR CORROSION ON THE THRUST REVERSER DOOR RAMP SKINS DUE TO THE PAINT MISSING FROM THE RIVET HEADS.  BY MAJOR CORROSIO	N I MEAN WE ARE BLENDING THE AREAS BELOW LIMITS AND HAVING TO SEND THEM OUT FOR REPAIR.  AREAS OF CORROSION ARE NOT ONLY	 BEING FOUND ON THE RIVET HEADS WE ARE FINDING SURFACE CORROSION ANYWHERE THE PAINT IS MISSING ON THE RAMP SKINS.				2	L	7	2 	4F			RT	A3EU    					 
2006092500162	20060925	00162	NE  	2006	9	25	2006FA0000928    	2	20060919	G	7200		ENGINE          			AGUSTA	A109  	A109E       	0260119	EU  	TMECA 	ARRIUS	ARRIUS2K1   		NE  						MAKING METAL    	C				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	08	91LF					11509	33022			ENGINE CHIP LIGHT CAME ON APPROACH TO LANDING. REMOVED GAS GENERATOR MAG PLUG FOUND COVERED WITH METAL CHIPS. PROBABLE C	AUSE BEARING FAILURE.					1	G	7	2 	3U	3	U	RT	H7EU    	E34NE				 
2006092600030	20060926	00030	NE  	2006	9	26	2006FA0000929    	2	20060919	G	7200		ENGINE          			AGUSTA	A109  	A109E       	0260119	EU  	TMECA 	ARRIUS	ARRIUS2K1   		NE  						MAKING METAL    	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	91LF					11509	33022			ENGINE CHIP LIGHT CAME ON APPROACH TO LANDING. REMOVED GAS GENERATOR MAG PLUG FOUND COVERED WITH METAL CHIPS. PROBABLE C	AUSE BEARING FAILURE.					1	G	7	2 	3U	3	U	RT	H7EU    	E34NE				 
2006092100187	20060921	00187	CE  	2006	9	21	2006FA0000930    	1	20060920	G	5511	45A21146006	RIB             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	939GP					RK125	PCEJA0017			THE HORIZONTAL STABILIZER RIB (RT SIDE) LOCATED UNDER THE ROLLER BRACKET HAD A CRACK IN IT. THIS ITEM IS COVERED UNDER C	OMMUNIQU NR 70.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006092100212	20060921	00212		2006	9	21	2006FA0000931    	1	20060920	G	5511	45A211460506	RIB             								PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	27XP									THE RIBS LOCATED UNDER THE HORIZONTAL STABILIZER BRACKETS WERE CRACKED, BOTH THE LT AND RT SIDES. THIS IS COVERED UNDER 	COMMUNIQU NUMBER 70.										4	F			E25EA				 
2006092100213	20060921	00213	CE  	2006	9	21	2006FA0000932    	1	20060920	G	5511	45A211460506	RIB             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	27XP					RK266				THE RIBS LOCATED UNDER THE HORIZONTAL STABILIZER BRACKETS WERE CRACKED, BOTH THE LT AND RT SIDES. THIS IS COVERED UNDER 	COMMUNIQUE NUMBER 70.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006092100248	20060921	00248	EU  	2006	9	21	2006FA0000933    	1	20060806	G	3222	8904200484	AXLE            			SOCATA	MS894 	MS894A      	8402842	EU  	FRNKLN	6AV350	6V350*      	27043	EA  	MCAULY	2A31C	2A31C21     	GL  	NLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	17	33BF					11720				INFORMATION OBTAINED FROM OWNER AND OPERATOR ENCOUNTERED AN INCIDENT UPON LANDING. AT TOUCHDOWN PILOT REPORTED THE NOSE 	LANDING GEAR AXLE BROKE, LIBERATING THE NOSE WHEEL FROM THE AIRCRAFT. THE NOSE WHEEL CONTACTED THE RT MAIN FLAP ASSY (DA	MAGE SEVERITY UNKNOWN, REPLACEMENT APPARENTLY REQUIRED) SUBSEQUENTLY THE PROPELLER CONTACTED THE RUNWAY. PILOT REPORTED 	THE ENGINE DID NOT SUFFER SUDDEN STOPPAGE AND  THERE  WAS NO REPORTED INJURY OR DAMAGE TO AIRPORT PERSONNEL, EQUIPMENT O	R PROPERTY.		1	L	7	1 	3O	3	O		7A14    	E9EA	5	C	P919	 
2006092100319	20060921	00319	EA  	2006	9	21	2006FA0000934    	2	20060920	G	8500		ENGINE          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  						LACK OF LUBE    	D				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SO	05	5330B		2252 			83838	L1395415			LOSS OF OIL PRESSURE WHICH LED TO ENGINE FAILURE/SEIZE AND FORCED EMERGENCY LANDING ON HIGHWAY.  NO VISUAL PROBLEMS ON E	XTERNAL AREA OF ENGINE.  REMOVED ENGINE AND SENT TO MFG FOR TEARDOWN AND EVALUATION.  MFG REPORTED  THAT ENGINE SUFFERED	 OIL STARVATION.  NR 1 AND NR 3 ROD JOURNALS WERE SCORED AND HEAT CHECKED BEYOND REPAIR.  SIGNATURE'S ESTIMATION OF OIL 	STARVATION WAS CAUSED BY DETONATION IN NR 1 CYLINDER.  THE NR 1 CYLINDER DETONATION, BURNED HOLE IN THE PISTON, CAUSING 	OIL TO BE BLOWN OUT OF ENGINE VENT TUBE.  THE NR 1 CAMSHAFT INTAKE LOBE WAS SEVERELY WORN AND THE EXHAUST LOBE MODERATEL	Y WORN IN WHICH IS BELIEVED TO HAVE CONTRIBUTED TO THE NR 1 CYLINDER DETONATION PROBLEM.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006092600133	20060926	00133	CE  	2006	9	26	2006FA0000939    	1	20060913	G	3710	S2501	HOSE            			CESSNA	172   	172P        	2072436	CE  	CONT  	O470  	IO470*      	17026	SO  					VACUUM SYS	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	98264					17276271				INVESTIGATION INTO FAILED ATTITUDE INDICATOR ON LISTED AIRCRAFT FOUND APPARENT CAUSE OF FAILURE TO BE FROM CONTAMINATION	 FROM DISINTEGRATING VACUUM HOSE.  THE HOSES IN QUESTION ARE MARKED B906 AND B904 HOSE.  TO PREVENT RECURRENCE, SB SEB96	-10 SHOULD BE ACCOMPLISHED ON AIRCRAFT.  ON OTHER AIRCRAFT HOSE SHOULD BE REPLACED WITH APPROVED EQUIVALENT.  DUE TO SEV	ERITY OF POTENTIAL FOR HOSE TO CONTAMINATE, DAMAGE AND RENDER USELESS NEEDED EQUIPMENT IN IFR FLIGHT, SPECIAL CONSIDERAT	ION SHOULD BE TAKEN TO REMOVE THIS PRODUCT FROM AIRCRAFT IT MIGHT HAVE BEEN INSTALLED AS SOON AS POSSIBLE.(K)		1	H	7	1 	3O	3	O	NT	3A12    	E1CE				 
2006092700004	20060927	00004	CE  	2006	9	27	2006FA0000940    	1	20060823	G	2750		FLAP SYSTEM     			RAYTHN	390   	390         	7150030	CE  											MISRIGGED       	B			MGOR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	09	9LV					RB132				DURING PHASE INSPECTION FOUND THE LT IB AFT FLAP TRACK ATTACH BOLT CHAFED 3 LAYERS OF CARBON FIBER INTO THE FUSELAGE.  F	OUND FLAP MISRIGGED AND TOP 3 FLAP TRACK FASTENERS WORKING.  RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTA	CHING HARDWARE DURING PHASE INSPECTIONS.  (K)				1	7		2 	3F			RT	A00010WI					 
2006092700008	20060927	00008	CE  	2006	9	27	2006FA0000941    	1	20060906	G	5753	39005214110002	FLAP TRACK      			RAYTHN	390   	390         	7150030	CE  										RT WING	DAMAGED         	B			MGOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	701KB	600  				RB103				DURING 200/600 HR PHASE INSPECTION FOUND THE RT IB AFT FLAP TRACK UPPER 3 ATTACH FASTENERS PN: MS90354S0609 WORKING.  RE	COMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTIONS.  (K)					1	7		2 	3F			RT	A00010WI					 
2006092700009	20060927	00009	CE  	2006	9	27	2006FA0000942    	1	20060906	G	5753	39005214110002	FLAP TRACK      			RAYTHN	390   	390         	7150030	CE  										RT WING	DAMAGED         	B			MGOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	701KB	600  				RB103				DURING 200/600 HR PHASE INSPECTION FOUND THE RT IB AFT FLAP TRACK UPPER 3 ATTACH FASTENERS PN: MS90354S0609 WORKING.  RE	COMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTION.  (K)					1	7		2 	3F			RT	A00010WI					 
2006092700007	20060927	00007	CE  	2006	9	27	2006FA0000944    	1	20060911	G	8120	4709440029	RELIEF VALVE    			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540AK1A  		EA  					WASTEGATE	FAILED          	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	182GA	89   			ILN00185	T18208587	L1240661A			PILOT REPORTED, ON TAKEOFF ROLL, THE MANIFOLD PRESSURE WENT TO GREATER THAN 40 MP FOR 3 TO 4 SECONDS.  THE PILOT WENT BA	CK TO RUNUP AREA AND CONFIRMED THAT MP COULD GO ABOUT 40 MP, PILOT TAXIED BACK TO RAMP AND GROUNDED AIRCRAFT.  TROUBLESH	OT TURBO CHARGER SYSTEM FOUND THE TURBO CHARGER WASTEGATE CONTROLLER HAD FAILED.  REMOVED WASTEGATE CONTROLLER AND PRESS	URE RELIEF VALVE AND SENT FOR CHECKOUT.  FOUND THE WASTE CONTROLLER BAD AND THE PRESSURE RELIEF VALVE WAS FACTORY PRESEN	T TO THE INCORRECT MP PRESSURE WHICH IF SET CORRECTLY COULD HAVE PREVENTED THE ENGINE FROM OVERBOOSTING.  THIS AC ENGINE	 TURBOCHARGING SYS HAD A DUEL SYS FAILURE.  SB 369J ADDRESSES WHAT SHOULD BE DONE WHEN ENG IS OVERBOOSTED.  MFG RECOMMEN	1	H	7	1 	3O	3	O	NT	3A13    					 
2006092700012	20060927	00012	CE  	2006	9	27	2006FA0000945    	1	20060707	G	7120		MOUNT           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					RT ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	2009X					ME66				BOTH LT AND RT ENGINE MOUNT TO FIREWALL ATTACH POINTS BROKE OUT AFT OF THE FIREWALL IN THE UPPER OB POINT.  THIS BREAKAG	E IS DIFFICULT TO DETECT DUE TO VISIBILITY ACCESS.  THESE BRACKETS BROKE BECAUSE OF FLIGHT THROUGH TURBULENCE.  (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
2006092700002	20060927	00002	CE  	2006	9	27	2006FA0000946    	1	20060707	G	7120	10598000021	ATTACH ANGLE    			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					ENGINE MOUNT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	2009X					ME66				BOTH LT AND RT ENGINE MOUNTS TO FIREWALL ATTACH POINTS BROKE OUT AFT OF THE FIREWALL IN THE UPPER OB POINT.  THIS BREAKA	GE IS DIFFICULT TO DETECT DUE TO VISIBILITY ACCESS.  THESE BRACKETS BROKE BECAUSE OF FLIGHT THROUGH TURBULENCE.  (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
2006092700038	20060927	00038	GL  	2006	9	27	2006FA0000947    	2	20060908	G	7240	6870992	COMBUSTION CASE 			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	90431					1100833D	CAE830468			PILOT COMPLAINED THAT THE TOT SUDDENLY WENT 40 DEGREES C, HOT.  FOUND OUTER COMBUSTION CAN CRACKS.  REPLACED UNIT.  (K)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092600060	20060926	00060	GL  	2006	9	26	2006FA0000948    	2	20060908	G	7200	23057142	CASE            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	ERODED          	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CFASX		684  			1150D	CAE830467			FOUND CASE HALVES SHOT.  ENGINE RUNNING 35 DEGREES C, HOT. (K)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092600010	20060926	00010	EA  	2006	9	26	2006FA0000949    	1	20060907	G	5610	6003303025	WINDSHIELD      			CNDAIR	CL600 	CL6002A12   	1900304	EA  										COCKPIT	CRACKED         	B			SH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	63	150MH					3021				LT WINDSHIELD (PILOTS) OUTER-PLY CRACKED DURING FLIGHT.  NO KNOWN CAUSE AS TO THE EVENTS LEADING TO CRACK.  KNOWN TO BE 	A COMMON FAILURE ON CHALLENGER  ACRYLIC WINDSHIELD AND SIDE WINDOWS.  WHETHER DUE TO IMPACT OF SOME SORTS OR WINDSHIELD 	NEAT FAILURE OR DELAMINATION.   WINDSHIELD AND AC WAS RTSD AS AIRWORTHY.  (K)				2	L	7	2 	4F			RT	A21EA   					 
2006092600256	20060926	00256	EA  	2006	9	26	2006FA0000950    	1	20060907	G	5610	6003303025	WINDSHIELD      			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					COCKPIT	CRACKED         	B			SH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	63	500PE					5440				LT WINDSHIELD (PILOTS) OUTER-PLY CRACKED DURING FLIGHT.  NO KNOWN CAUSE AS TO THE EVENTS OF THE CRACK.  KNOWN TO BE A CO	MMON FAILURE ON CHALLENGER ACRYLIC WINDSHIELD AND SIDE WINDOWS.  WHETHER DUE TO IMPACT OF SOME SORTS OR WINDSHIELD HEAT 	FAILURE OR DELAMINATION.  WINDSHIELD WAS REMOVED AND REPLACED WITH A NEW WINDSHIELD AND AC WAS RETURNED AS AIRWORTHY.  (	K)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006092600248	20060926	00248	NE  	2006	9	26	2006FA0000951    	1	20060908	G	3213	6525108027103	AXLE            			SKRSKY	S64   	CH54B       	8142610	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					MLG	CRACKED         	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	158AC					64081				(REF NR: MDR06-091) UPON DISASSEMBLY, AXLE WAS FOUND TO BE CRACKED AND RUNS AROUND THE CIRCUMFERENCE.  THE TRACTURE APPE	ARS TO ROIGINATE IN THE WELD ON THE CENTER OF THE AXLE SHAFT.  THE AXLE WAS FRACTURED UNDER THE SOCKET, PN 6425-50202-10	1, AS EVIDENCED BY A CRACK EXTENDING AROUND THE CIRCUMFERENCE OF THE SOCKET, FROM APPROXIMATELY THE 10:00 TO 2:00 POSITI	ON.  NO RECENT EVENTS ARE KNOWN THAT MAY HAVE CONTRIBUTED TO THIS TYPE OF FAILURE.  RECOMMENDATIONS TO PREVENT RECURRENC	E:  A ONE PIECE AXLE IS AVAILABLE FOR USE IN LIEU OF THE 2 PIECE WELDED AXLE.  (K)		2	G	7	2 	4U	4	U		H6EA    	E15EA				 
2006092600132	20060926	00132	CE  	2006	9	26	2006FA0000952    	1	20060908	G	3240		LINE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BRAKE	CHAFED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	785TA					RK239				DURING A SCHEDULED INSPECTION FOUND PN 128580101-1, BRAKE LINE ASSY CHAFE DAMAGED BY EXCESS LENGTH CABIN FLOOR PANEL ATT	ACH SCREW AS DESCRIBED IN MFG SB 53-3511.  REPAIR REQUIRED SPLICING IN OF NEW BRAKE LINE SEGMENT IAW SB 53-3511.  HAVE F	OUND THIS CONDITION ON NUMEROUS OTHER AC.  RECOMMEND THAT SB 53-3511 BE CHANGED TO A MANDATORY SB DUE TO COMMON OCCURREN	CE AND POSSIBILITY FOR LOSS OF BRAKING ACTION IF TUBING CHAFED THROUGH.  ALSO RECOMMEND AN ALERT INFO BULLENTIN ON THIS 	SUBJECT.(K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006092700001	20060927	00001		2006	9	27	2006FA0000954    	4	20060907	G	3460	1017241011	CDU             			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	BURNED          	B			JGVR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CE	09	48KR					127				SMOKE EMANATING FROM NR 1 FMS CDU DURING CRUISE FLIGHT.  UNIT SMELLED OF SMOKE AND WOULD NOT POWER UP DURING INITIAL BEN	CH CHECK.  FURTHER TEARDOWN PENDING.  (K)					2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2006092600125	20060926	00125	SO  	2006	9	26	2006FA0000955    	2	20060925	G	8530	AEC631397CN2C	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					EXHAUST PORT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	4307S	133  				E675	281757			NOTED ON 6 ENGINE COMPONENTS, INC. ECI CYLINDERS WITH 133.1 SINCE NEW AND PUT IN SERVICE ON THE SAME ENGINE DECEMBER 200	4.  NR4 AND NR5 CYLINDERS WERE CRACKED IN THE EXHAUST PORT WITH A HOLE BURNED THROUGH AT THE CRACK AND WAS LEAKING EXHAU	ST GASSES OVERBOARD. NR 1, NR 2, NR 3 AND NR 6 CYLINDERS WERE CRACKED IN THE SAME LOCATION AS NR 4 AND NR 5. THE CRACKS 	ARE IB OF THE EXHAUST GUIDE BOSS. THE THICKNESS OF THE MATERIAL IN THAT AREA OF THE EXHAUST PORT APPEARS TO BE TOO THIN 	AND NOT ABLE TO WITHSTAND THE HEAT AND STRESS PRESENT DURING NORMAL ENGINE OPERATION.		1	L	7	1 	3O	3	O		3A15    	E3SO				 
2006092600247	20060926	00247	GL  	2006	9	26	2006FA0000957    	2	20060919	G	7230	6876873	IMPELLER        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DAMAGED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	511SB	289  				1090592D	CAE834272			DURING REPLACEMENT OF THE S16 SHAFT, IT WAS DISCOVERED THAT THE OUTER LAND OF THE SNAP RING GROOVE WAS VERY THIN AND THE	 INNER EDGE WAS LIFTING AND (2) .3750 INCH LONG PIECES CAME OFF OF THE LAND.  WHEN THE SNAP RING WAS REMOVED THE GROVE F	OR THE  SNAP RING SEEMS TO BE THE NORMAL DIMENSION.  (K)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092700003	20060927	00003	GL  	2006	9	27	2006FA0000958    	2	20060919	G	7250	23038241	TURBINE WHEEL   			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	511SB	12352	208  			1090592D	CAE834272			FOUND NR 1, AND NR 2 TURBINES RUBING AFTER ENGINE DISASSEMBLY FOR CHIPS.  DURING 100 HR CHIPS WERE FOUND ON THE CHIP PLU	GS.  DISASSEMBLED ENGINE AND DISCOVERED THE N1 AND N2 TURBINES WERE RUBBING, REPLACED UNIT.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092600243	20060926	00243	GL  	2006	9	26	2006FA0000959    	2	20060919	G	7210	6894171	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MAKING METAL    	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	511SB	12617	4455 			1090592D	CAE834272			FOUND PTO , PTO BALL BEARING AND TORQUEMETER SPALLED.  FOUND CHIPS ON CHIP PLUGS.  DISASSEMBLED GEAR BOX AND FOUND PTO G	EAR, TORQUEMETER GEAR AND PTO BALL BEARING SPALLED.  REPLACED GEARBOX.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006101800083	20061018	00083	SO  	2006	10	18	2006FA0000961    	2	20060919	G	8520	656935	CRANKCASE       								CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	LEAKING         	B			VA1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	19							292082			POROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG.  LEAKS OIL, MFG HAS BEEN NOTIFIED.  (K)											3	O			E7CE				 
2006101900163	20061019	00163	SO  	2006	10	19	2006FA0000962    	2	20060919	G	8550	656935	CRANKCASE       								CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	LEAKING         	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19							604918			POROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG.  LEAKS OIL.  MFG HAS BEEN NOTIFIED.  (K)											3	O			E7CE				 
2006101800046	20061018	00046		2006	10	18	2006FA0000963    	1	20060918	G	4930	38828406	FCU             	HONEYWELL   																APU FUEL	CORRODED        	B			QKPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05										FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING INSIDE 	THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL TO E	XIT THE FCU DURING OPERATION.  IF THE PROBLEM IS NOT CORRECTED IT COULD CREATE A POTENTIAL FIRE HAZZARD.  (K)																	 
2006101100147	20061011	00147	CE  	2006	10	11	2006FA0000964    	1	20060919	G	5340	AN743A	ATTACH BOLT     			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  	SNSNCH	76E	76EM8       	EA  	ALTERNATOR	WORN            	D			PVQG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	9239S					M1732	L2046036A	17458K		DURING PRE-RUNUP INSPECTION FOR ANNUAL INSPECTION ALTERNATOR BELT NOTED TO BE LOOSE.  UPON INSPECTION OF ALTERNATOR FOR 	BELT TENSION THE FOLLOWING WAS NOTED:  THE CASTLE NUT WAS BACKED OUT TO THE POINT OF CHAFING ON THE A+ WIRE, THE WIRE WA	S KEEPING THE NUT FROM BACKING ALL OF THE WAY OFF OF THIS ATTACHMENT BOLT.  THIS AIRCRAFT AND ENGINE COMBINATION HAD BEE	N INSPECTED FOR ANNUAL AIRWORTHINESS BY THE SAME INSPECTION 3 TIMES DURING THE PAST 22.1 HRS.  NOTE ENCLOSED PHOTOS.  T	HIS ENGINE HAS 237 HRS SINCE MAJOR OVERHAUL BY AN APPROVED SHOP AND WOULD ESTIMATE THAT THE NUT HAD NOT BEEN SAFTIED DUR	ING ANY OF THIS TIME AS THE NUT WOULD ACTUALLY SLIDE ACROSS THE THREADS OF THE BOLT.  (K)	1	L	7	1 	3O	3	O		A1CE    	E286	5	N	P4EA	 
2006101100183	20061011	00183	SO  	2006	10	11	2006FA0000965    	1	20060902	G	3230	211C23412	PRESSURE SWITCH 			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540AH1A  	42003	EA  					MLG PUMP	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	98LA					3257031	L992361A			AT AN ANNUAL INSPECTION IT WAS NOTED THE MAIN GEAR FAILED TO CYCLE COMPLETELY BEFORE PUMP SHUT OFF.  PUMP CYCLED ON AND 	OFF UNTIL MAINS WERE FULLY RETRACTED.  PUMP THEN REMAINED OFF.  PRESSURE SHUT OFF SWITCH WAS CHECKED WITH A HIGH PRESSUR	E GAUGE AND IT WAS FOUND TO TRIP AT 1400 LB WELL BELOW THE 1800 LG IT WAS DESIGNED FOR.  SWITCH IS ESTIMATED TO HAVE MAD	E 500 CYCLES BEFORE FAILING.  IT IS NOTED THAT THIS IS MY FIRST INSPECTION OF THIS AIRCRAFT SO THE PROBLEM MAY HAVE BEEN	 OVER LOOKED IN THE PAST.  (K)		1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2006101200073	20061012	00073	GL  	2006	10	12	2006FA0000966    	3	20060918	G	6114	C6132C67	HUB             			CESSNA	172   	T41D        	       	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	PROPELLER	CRACKED         	B			LT4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19								686342		PROPELLER RECEIVED FOR REPAIR, RED DYE OIL LEAK.  PROPELLER WAS DISASSEMBLED AND BLADE RETENSION THREADS EDDY CURRENT IN	SPECTED.  NR2 BLADE RETENTION THREAD, 4 THREADS IN AT APPROXIMATELY 7 O`CLOCK POSITION FOUND CRACKED.  HUB REMOVED FROM 	SERVICE.  (K)				1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
2006101200123	20061012	00123	CE  	2006	10	12	2006FA0000967    	1	20060922	G	5610	121140019	WINDOW          			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					REAR WINDOW	DAMAGED         	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	217DL	674  				T20608224				THE FACTORY ORIGINAL REAR WINDOW OF THIS AC BEGAN TO DEVELOP A CONCAVE AREA IN THE CENTER OF THE WINDOW.  THIS AREA WOUL	D BECOME MORE PRONOUNCED IN DIRECT SUNLIGHT.  THIS AC IS 6 YEARS OLD AD HAS ACCUMULATED 674.52 HOURS.  THE AC WAS HANGER	 KEPT MOST OF THE TIME.  THE WINDOW WAS REPLACED WITH A NEW UNIT MEASURING .250 INCH THICK.  AMPLE CLEARANCE WAS MAINTAI	NED TO PROVIDE ROOM FOR EXPANSION AND CONTRACTION YET STILL MAINTAINING ADEQUATE ENGAGEMENT OF WINDOW  INTO WINDOW RETAI	NER.  THE ORIGINAL WINDOW MEASURED .125 INCH THICK.  THIS INSTALLATION WAS PERFORMED UNDER THE FIELD APPROVAL PROCESS AN	D REQUIRED ONLY MINOR BENDING AND REFORMING OF THE RETAINER FLANGE OF THE AIRCRAFT STRUCTURE TO ACCEPT THIS NEW THICKER 	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2006101200121	20061012	00121	CE  	2006	10	12	2006FA0000968    	1	20060919	G	2435	23085001	STARTER GEN     			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LEFT	WORN            	B			AHTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	200VC	1737 	712  			FL316				IN FLIGHT THE LT SIDE STARTER/GEN AFT BEARING AT THE COOLING FAN FAILED AND THE GENERATOR FAILED.  THE AC RETURNED TO IT	S DEPARTURE TERMINAL WITHOUT INCIDENT.  THE STARTER/GEN WAS REPLACED AND THE CHARGING AND ELECTRICAL SYSTEM OPS, CHECKED	 GOOD.  NO KNOWN CAUSE, STARTER/GEN WAS WITHIN THE 1000 HRS FOR BEING OVERHAULED.  (K)				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006101200122	20061012	00122	SO  	2006	10	12	2006FA0000969    	1	20060927	G	2140	A23D04	SHUTOFF VALVE   	JANITROL    		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540*     	41532	EA  					HEATER	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	16SC	750  			1997221	31639				DURING ANNUAL INSPECTION FOUND FUEL LEAKING AROUND DIAPHRAGM JOINT.  PART MADE BY DURING FIRST QUARTER OF 2001.  PN A23D	04, 7.5 PSI, 24 VOLT.  (K)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006101800134	20061018	00134	SO  	2006	10	18	2006FA0000970    	1	20061002	G	3210	AN617	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SO	05	4093W	24842	250  			318152176				MFG SL NR 1092, DATED 06/15/2005 DEALS WITH REPLACEMENT OF RETRACTION ARMS, P/N 42042-000 OR 42042-002 AT 6000 HOURS AND	 TO PERFORM INSPECTION FOR CRACKS USING 10X MAGNIFYING GLASS AND DYE PENETRANT AFTER REACHING 1500 HOURS AND AT EACH 250	 HOURS THERE-AFTER UNTIL ACCUMULATION OF 6000 HOURS. THERE IS NO INSPECTION CRITERIA FOR INSPECTION AND REPLACEMENT OF A	TTACHING HARDWARE. ATTACHMENT BOLTS HAVE BEEN VISUALLY INSPECTED EACH 250 HOURS WHEN REMOVED TO INSPECT RETRACTION ARMS.	 HOWEVER, BOLT FAILED AND WAS FOUND BROKEN AND SHEARED OFF WITH ONLY HEAD PORTION STILL IN PLACE. IT APPEARS THAT WITH B	OLT SHEARED, THE LANDING GEAR ACTUATOR WAS PLACED IN A BIND WHICH BROKE THE BALL LINK THAT SCREWS IN THE MAIN SHAFT OF T	1	L	7	2 	3O				A20SO   					 
2006112100111	20061121	00111	SO  	2006	11	21	2006FA0000971    	2	20060926	G	7320	55P70D5E608	VALVE           			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					ENGINE FUEL	LEAKING         	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NM	09	231GR	1340 				250087	309083			THE FUEL PRIMER DIVERTER VALVE P/N 642199 (P/N 55P70D5E-608) LEAKED FUEL OVER THE TOP OF THE ENGINE IN FLIGHT, IT WAS LE	AKING SO MUCH THE ENGINE WOULD NOT KEEP RUNNING WITHOUT THE USE OF THE ELECTRIC BOOST PUMP. INITIALLY OUR MFG VENDOR GAV	E ME A REPLACEMENT P/N 633862 AND SAID NO PARTS WERE AVAILABLE. SO I CONTACTED THE MFG ENGINEERING AND SPOKE WITH THEIR 	REPAIR STATION MANAGER. HE INFORMED ME THAT THEY HAD JUST OVERHAULED A VALVE THAT HAD CAUSED AN ENGINE FIRE, AND THEY OV	ERHAUL 8-10 A YEAR. HE ALSO SAID THE OVERHAULED VALVES HAVE PMA AND WILL NEVER LEAK AGAIN. I CALLED MFG AND PASSED ON TH	E PROBLEM TO THEIR TECH REP, HE DID INFORM ME THAT THEY DO IN FACT STOCK THE NEW P/N VALVE. I CANNOT FIND ANY BULLETINS 	1	L	7	1 	3O	3	O		2A3     	E9CE				 
2006101900200	20061019	00200	SO  	2006	10	19	2006FA0000974    	1	20060929	G	2823	1138303	SELECTOR VALVE  			PIPER 	PA18  	PA18125     	7101812	SO  	LYC   	O290  	O290*       	41506	EA  					FUEL SYSTEM	FAILED          	D				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			AL	05	1896A		45   			181728				FUEL SELECTOR/SHUTOFF VALVE HANDLE MOVED BUT VALVE DID NOT SELECT FROM LT FUEL TANK TO RT FUEL TANK. ENGINE RAN OUT OF F	UEL FROM THIS AND AIRCRAFT LANDED ON ROAD. AD 60-10-08 WAS COMPLIED WITH 45 HOURS EARLIER. IA MECHANIC SUGGESTS THAT ROU	TINE CLEANING OF VALVE AND INSPECTION OF PLASTIC PLUGS AROUND SHAFT MOUNTING HOLES CRACKS OR REPLACEMENT OF PLASTIC PLUG	S WITH BRASS PLUGS. TIME IN SERVICE OF SELECTOR VALVE 11383-03 UNKNOWN.			1	H	7	1 	3O	3	O		1A2     	E229				 
2006101800050	20061018	00050	EA  	2006	10	18	2006FA0000975    	2	20061003	G	7414	1052949	DISTRIBUTOR BLK 	CONT        		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAGNETO	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8280J				4772011	0892	L1492539A			DURING 500 H0UR INSPECTION AND SERVICE THE DISTRIBUTOR BLOCK BRONZE BUSHING WAS FOUND TO BE BROKEN AND FREE TO MOVE AROU	ND.					1	G	7	1 	3O	3	O		H10WE   	E274				 
2006101200120	20061012	00120		2006	10	12	2006FA0000976    	2	20061003	G	8530	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  										ENGINE	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	253SR	50   				2034				NR 5 EXHAUST STACH/HEADER WAS FOUND TO BE CRACKED AT THE CYLINDER FLANGE AT THE WELD.						1	L	7	1 	3O			NT	A00009CH					 
2006101800032	20061018	00032	EU  	2006	10	18	2006FA0000977    	1	20061003	G	3260	803682	PROXIMITY SENSOR			AMD   	FALC50	FALCON50MYST	2730106	EU  										MLG	FAILED          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			SW	11	784B					118				GEAR SELECTED (DOWN), LT GEAR DOOR INDICATION LIGHT REMAIND RED. MANUAL GEAR PROCEDURES USED TO CLOSE DOOR.						2	L	7	3 	4F				A46EU   					 
2006101800041	20061018	00041	SO  	2006	10	18	2006FA0000979    	2	20060915	G	8530	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					NR 5	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	253SR	50   				2034				NR 5 EXHAUST HEADER CRACKED AT CYLINDER FLANGE AT THE WELD.  (K)						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006101800042	20061018	00042	SO  	2006	10	18	2006FA0000980    	2	20060929	G	7414	M3548	ROTOR           	SLICK       		PIPER 	PA18  	PA18        	7101802	SO  	CONT  	C90   	C90*        	17009	SO  					RT MAGNETO	INOPERATIVE     	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AL	03	7472D	400  			94010288	185807				PILOT NOTICED LACK OF POWER AND ROUGHNESS AFTER TAKEOFF.  RETURNED TO FIELD, DISCOVERED INOPERATIVE RT MAGNETO.  DISASSE	MBLY OF RT MAGNETO REVEALED ROTOR SHAFT HAD SHEARED FLUSH WITH BOTTOM OF CAM CUTOUT.  THE REMAINING ROTOR AND DISTRIBUTO	R BOTH ROTATED FREELY.  NO EVIDENCE OF PROBLEMS WITH EITHER GEAR.  PROBABLE CAUSE IS A DEFECT IN MFG (POSSIBLY BAD METAL	 OR STRESS CRACK FROM MACHINING CAM SLOT.  (K)			1	H	7	1 	3O	3	O		1A2     	E252				 
2006101800040	20061018	00040	NM  	2006	10	18	2006FA0000981    	1	20061006	G	2820	07166171	FUEL LINE       			UNIVAR	108   	108         	9230402	NM  										LT DOOR POST	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	933D	5401 				1082933				AILERON CABLE HAD CHAFED 90 PERCENT THRU FUEL LINE. AREA A LITTLE HARD TO SEE. FOUND BY LOOKING FOR NAV LIGHT SQUAWK THA	T LED TO THE LT UPPER DOOR POST AREA. SUGGEST THAT ALL SIMILAR STYLE MFG WITH AILERON CABLE THAT RUNS ALONG FUEL LINES T	O BE INSPECTED AND INSTALL SOME FORM OF ANTI-CHAFING MATERIAL TO THE AFFECTED AREA.				1	H	7	1 	3O				A767    					 
2006101900175	20061019	00175	CE  	2006	10	19	2006FA0000983    	1	20061009	G	7603		CONTROL CABLE   			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					CARBUETOR	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	07	9991B	84   				172RG1110	L297946A			UPON SHUTDOWN AFTER FLIGHT, PILOT PULLED ON CARBURETOR MIXTURE CABLE TO IDLE CUT-OFF. THE CABLE CAME OUT IN THE PILOTS H	AND. SUSPECT CARBURETOR MIXTURE CABLE BROKE DURING FLIGHT. SUSPECT CABLE HAS A QUALITY ISSUE. NOTE: DID NOT EFFECT OPERA	TION OF AIRCRAFT DURING FLIGHT. REPLACED CABLE WITH NEW.				1	H	7	1 	3O	3	O		3A17    	E286				 
2006102600172	20061026	00172	GL  	2006	10	26	2006FA0000984    	3	20060918	G	6114	C6132C67	HUB             	MCAULY      		CESSNA	172   	T41D        	       	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	PROPELLER	CRACKED         	B			LT4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19		3250 	1101 		686342			806058		PROPELLER RECEIVED FOR 60 MONTH OVERHAUL.  PROPELLER WAS DISASSEMBLED AND BLADE RETENTION THREADS EDDY CURRENT INSPECTED	.  NR1 BLADE RETENTION THREAD, 4 THREADS IN AT APPROX 7 TO 8 OCLOCK POSITION FOUND CRACKED.  HUB REMOVED FROM SERVICE. (	K)				1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
2006102500127	20061025	00127	SO  	2006	10	25	2006FA0000985    	2	20060922	G	7310	156F0034S0244	LINE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					ENGINE FUEL	RUPTURED        	B			SI6R	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	17	469S	1120 				421C1057	808347R			FUEL HOSE RUPTURED, SPRAYING FUEL ON THE HOT EXHAUST MANIFOLD TO TURBO CHARGER CAUSING AN ENGINE FIRE ON THE GROUND.  (K	)					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006102500128	20061025	00128	SO  	2006	10	25	2006FA0000986    	1	20060825	G	3210	ANG17	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	4093W	24842				318152176				AIRCRAFT HAD GEAR UNSAFE LIGHT AND NO LT DOWN AND LOCKED INDICATION LIGHT, AS WELL.  THE GEAR HANDLE WOULD NOT RETURN TO	 NEUTRAL POSITION.  AIRCRAFT LANDED WITHOUT INCIDENT.  WE BELIEVE THAT THE UPPER BOLT THAT RETAINS THE MAIN GEAR RETRACT	ION ARM BROKE DUE TO FATIGUE.  THIS ALLOWED THE MAIN GEAR ACTUATOR TO BIND ON THE UPPER SECTION OF THE DRAG LEG AND BROK	E THE MAIN GEAR ACTUATOR BALL END OUT OF THE MAIN SHAFT OF THE ACTUATOR.  THERE IS SL NR 1092, DATED JUNE 15TH, 2005 THA	T REQUIRES THE MAIN GEAR RETRACTION ARMS, PN 42042000 OR 42042002 TO BE INSPECTED USING A 10X MAGNIFYING GLASS AND LIQUI	D PENETRANT INSPECTION AFTER REACHING 1500 HOURS TIME IN SERVICE AND THERE AFTER AT EACH 250 HOURS UNTIL THAT PART REACH	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006101600269	20061016	00269	CE  	2006	10	16	2006FA0000987    	1	20060922	G	2820	25160281	LINE            			LEAR  	35    	31          	5170530	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					BOOST PUMP	CHAFED          	B			UO2R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	19	5VG					014				BLEED AIR CLAMP POSITIONED OB OF FUEL LINE CHAFED INTO FUEL LINE CAUSING A FUEL LEAK WITH BOOST PUMP PRESSURE.  (K)						2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
2006101600218	20061016	00218	CE  	2006	10	16	2006FA0000988    	1	20060907	G	3240	215286	BRAKE ASSY      			CESSNA	501   	551         	2076605	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT MLG	BROKEN          	D				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			GL	03	502CL		317  			5510002				DURING TAXI ON RAMP, LT BRAKE LOCKED UP (AIRCRAFT WAS MOVING AT A VERY LOW RATE OF SPEED).  AFTER REMOVAL OF LT WHEEL, F	OUND 1 STATOR BROKEN IN HALF, DROPPING DOWN ONTO WHEEL (BRAKE KEY), CAUSING WHEEL TO LOCK UP.  NO DAMAGE NOTED TO WHEEL 	OR ANY OTHER PART OF AIRCRAFT.  (K)				1	L	7	2 	4F	4	F		A27CE   	E1NE				 
2006101600290	20061016	00290	CE  	2006	10	16	2006FA0000989    	1	20060922	G	5532	4555030001803	PANEL           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					VERTICAL STAB	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	10J					063				DURING MAINTENANCE, DISCOVERED PANEL HAD 6 INCHES LONG CRACK RUNNING VERTICAL AT FWD ATTACH HOLES.  PANEL WAS REPLACED. 	 (K)					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006101800105	20061018	00105	SO  	2006	10	18	2006FA0000990    	1	20060914	G	2420	60A4111810R	BRUSH HOLDER    			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ALTERNATOR	WORN            	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	36116	637  				287816614				DURING AC OPERATION, ALTERNATION CEASED PUTTING OUT POWER.  UPON INSPECTION AFTER REMOVAL, FOUND FIELD BRUSHES PREMATURE	LY WORN, AND COCKED OVER IN BRUSH HOLDER.  (K)					1	L	7	1 	3O	3	O		2A13    	E274				 
2006102000033	20061020	00033	SO  	2006	10	20	2006FA0000991    	1	20060914	G	2420	4111810	ALTERNATOR      			PIPER 	PA28  	PA28R201    	7102816	SO  										ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	2241Q	109  				28R7737029				ALTERNATOR CEASED OPERATION WITH ONLY 109 HOURS ON IT IN LIKE NEW CONDITION.  (K)						1	L	7	1 	3O				2A13    					 
2006101800030	20061018	00030	WP  	2006	10	18	2006FA0000992    	2	20060907	G	7200		ENGINE          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 2	FAILED          	B			AN3R	A				UNSCHED LANDING         				X	T	J	ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   	WARNING INDICATION        	CR	CRUISE         	1			SO	33	800WW					258661	P107869			(REF NR:  2006-1001)  30,000 FT, ENGINE BANG, ENGINE WAS SHUTDOWN AND FLIGHT DIVERTED.  NR 2 ENGINE TURBINE WHEEL FAILUR	E, UNCONTAINED.  INITIAL VISUAL INSPECTION POSSIBLE TURBINE WHEEL FAILURE.  INVESTIGATION IN PROCESS WITH ASSISTANCE FRO	M MFG.  PORTION OF ENGINE PROTRUDED THE ENGINE THRUST REVERSER SECTION AT THE APPROXIMATE 5 OCLOCK POSITION.  ENGINE REM	OVED AND RELOCATED TO MFG. (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006102000001	20061020	00001	EA  	2006	10	20	2006FA0000993    	2	20061005	G	8530	LW19001	EXHAUST VALVE   			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	NR 5 CYLINDER	STUCK           	B			JRUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	17HP	997  				18281436	L2971648A	041547		DURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (10/80) WITH A STRONG LEAK PASSED THE EXHAU	ST VALVE.  SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN LYCOMING SB 388C REVEALED THAT THE EXHAUST VALVE WA	S PARTIALLY STUCK AND WOULD NOT FULLY CLOSE.  THE EXHAUST VALVE ALSO COULD NOT BE REMOVED FROM THE CYLINDER ONCE THE CYL	INDER WAS REMOVED FROM THE ENGINE.  LYCOMING RECOMMENDS THE FOLLOWING INTERVAL FOR INSPECTING NON-HELICOPTER ENGINES, "4	00 HOUR INTERVALS OR EARLIER IF VALVE STICKING IS SUSPECTED UNTIL EXHAUST VALVE GUIDES ARE REPLACED WITH GUIDES MADE OF 	IMPROVED MATERIAL (REFER TO LATEST REVISION OF SERVICE INSTRUCTION 1485)". 	1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2006102000039	20061020	00039	EA  	2006	10	20	2006FA0000995    	2	20060609	G	8520		CRANKCASE       			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	AEIO360A1A  	41514	EA  					ENGINE	BROKEN          	P				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			WP	09	671DB		200  			670030				WHEN OUR ENGINE NEEDED A MAJOR OVERHAUL THE CRANKCASE WAS SENT TO DIVCO IN TULSA, OKLAHOMA FOR INSPECTION AND FAA AIRWOR	THINESS CERTIFICATION.  DIVCO DID REPAIRS AND MACHINE WORK AND CERTIFIED THE CRANKCASE AS AIRWORTHY ON FAA FORM 8130 PER	 14 CFR  43.13 (B).  THE ENGINE WAS ASSEMBLED AND INSTALLED IN THE AIRPLANE.  AT JUST OVER 200 HOURS THE CRANKCASE NEAR	LY BROKE IN HALF AT DIVCO'S REPAIR.   IN A MATTER OF MINUTES THE ENGINE LOST SIX OF THE EIGHT QUARTS OF OIL IT HAD.  THE	 CRANKCASE BREAK AND A SUBSEQUENT ENGINE FAILURE COULD HAVE BEEN CATASTROPHIC!  THE TOTAL LOSS OF THE ENGINE, LOSS OF TH	E AIRPLANE AND LOSS OF LIFE OF THOSE ON BOARD AND ON THE GROUND WERE A VERY REAL POSSIBILITY.  FORTUNATELY, HAD JUST DEP	1	L	7	1 	3O	3	O		2A3     	1E10				 
2006102000036	20061020	00036	SO  	2006	10	20	2006FA0000999    	1	20061002	G	5102	34285	LINE            			BALWKS	FIRE  	FIREFLY715  	1050518	SO  										FUEL SYS	SEPARATED       	B			OG2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	2203B	2    				F7B2009				HOSE SEPARATED AT THE FUEL LINE END.  PILOT WAS INFLATING BALLOON WHEN THIS OCCURRED.  NEW HOSES WERE INSTALLED ON 7/27/	2006.  THE BALLOON HAD BEEN FLOWN TWICE, WITH A TOTAL OF 2.0 HOURS ON NEW HOSES.  (K)					1	B	0	0 	  				A14SO   					 
2006102300158	20061023	00158		2006	10	23	2006FA0001000    	2	20061009	G	7314	271T00687	PUMP            			BOEING	767   	767*        	       	NM  										ENGINE FUEL	CRACKED         	B			DM4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19										PART HAS CRACK IN FILTER BOWL PORT, UNIT LEAKING.  (K)						2	L	7	2 	4F			RT	A1NM    					 
2006102500125	20061025	00125		2006	10	25	2006FA0001001    	4	20060927	G	3417	FE422	RELAY           			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					AIR DATA	FAILED          	B			XJRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	925BC					257				LOSS OF RT AIR DATA ELECTRICAL POWER CAUSES A SNEAK PATH THROUGH THE ARTHUR Q AIR DATA REVERSION RELAYS ON RELAY CARD 41	7J.  THIS SNEAK PATH WILL CAUSE THE LT RADIO TUNING UNIT TO REVERT TO AIR DATA SOURCE NR 2.  BECAUSE AIR DATA SOURCE NR 	2 IS NOW INACTIVE, NEITHER TRANSPONDER WILL HAVE ALTITUDE ENCODING.  ALTITUDE ENCODING SOURCE SELECTION VIA THE MODE SEL	ECTOR SOURCE SELECTION WILL HAVE NO EFFECT, NOR WILL CHANGING SELECTED TRANSPONDER OR AIR DATA REVERSION SWITCH ON EITHE	R PILOTS SIDE.  THIS IS A SINGLE POINT OF FAILURE CAUSING LOSS OF ALL ALTITUDE ENCODING AND WILL ALSO CAUSE TCAS FAILURE	.  INSTALLATION OF A STEERING DIODE IN THE ARTHUR Q REVERSION RELAY CIRCUIT WILL PREVENT THIS PROBLEM FROM OCCURRING.  T	2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2006102600182	20061026	00182	CE  	2006	10	26	2006FA0001002    	1	20060906	G	3260	SR008	DOWNLOCK SWITCH 			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					RT MLG	FAILED          	C			CNQR	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CE	07	651QS	4482 				5605251	DB0515			AFTER TAKEOFF AND GEAR RETRACTION ALL GEAR LIGHTS WENT OUT.  APPROX 5-10 INTO FLIGHT, NOTICED RT GREEN GEAR LIGHT WAS ON	.  NO OTHER ABNORMAL LIGHTS NOTED.  40 MINUTES LATER LIGHT EXTINGUISHED.  TROUBLESHOT SYS BY RIGING ALL DOWN LOCK SWITCH	 WIRING AND SWITCH MOUNTED TO RT GEAR ACTUATOR AND AFTER COLD SOAKING FOUND SWITCH SR008 (DOWNLOCK SWITCH) HAD A 2.209 M	 OHM READING WHEN OPEN (SHOULD BE NO READING).  REPLACED MLG ACTUATOR WITH A RENTAL UNIT AND OPERATIONAL CHECKS WERE GOO	D.  RESERVICED EMERGENCY PNEUMATIC GEAR EXTENSION.  (K)		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006102000040	20061020	00040	CE  	2006	10	20	2006FA0001003    	1	20060919	G	2435	23085001	STARTER GEN     			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LT ENGINE	WORN            	B			AHTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	200VC	1737 	712  			FL316				IN FLIGHT THE LT SIDE STARTER/GENERATOR AFT BEARING AT THE COOLING FAN FAILED AND THE GENERATOR FAILED.  THE AC RETURNED	 TO ITS DEPARTURE TERMINAL WITHOUT INCIDENT.  THE STARTER/GENERATOR WAS REPLACED AND THE CARGING AND ELECTRICAL SYSTEM O	PS CHECKED GOOD.  NO KNOWN CAUSE, STARTER/GENERATOR WAS WITHIN THE 1000 HOURS FOR BEING OVERHAULED.  (K)				2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2006102300154	20061023	00154	WP  	2006	10	23	2006FA0001004    	2	20061009	G	7210	8964214	RESTRICTOR VALVE			MTSBSI	MU2   	MU2B26      	5780408	CE  	GARRTT	TPE331	TPE3310T    	 	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	REDUCTION GB	FAILED          	B			IZ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	392P					392SA	P105025C	CDA3129M1		FOLLOWING O/H AND INSTALLATION OF ENGINE ON AC AN IN-FLIGHT CHECK OF THE NTS SYSTEM WAS PERFORMED IAW MM INSTRUCTIONS.  	UPON ACTUATION OF THE STOP SWITCH BY THE PILOT FOR THE LT ENGINE THE AC YAWED NOSE LT APPROXIMATELY 20 TO 25 DEGREES.  A	LSO, THE ENGINE RPM HESITATED TO DECAY FOR 1 TO 2 SECONDS THEN DECAYED NORMALLY TO 35 PERCENT RPM.  TROUBLESHOOTING FOLL	OWING FLIGHT SHOWED THAT THE (TRIP) PRESSURE OF THE ENGINE WAS HIGHER THAN NORMAL AND THE DECISION WAS MADE TO REPLACE T	HE TORQUE SENSOR ASSY PN 31017263.  A SECOND IN FLIGHT CHECK OF THE NTS SYSTEM WAS PERFORMED WITH THE SAME UNSATISFACTOR	Y RESULTS.  FURTHER TROUBLESHOOTING IAW MM.  INSTRUCTION WAS CONDUCTED WITH NO DEFECTS NOTED.  ENGINE REDUCTION GEARBOX 	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2006102000097	20061020	00097	SW  	2006	10	20	2006FA0001007    	1	20060908	G	5340		TEE FITTING     			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	LOOSE           	B			B2ER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	5760Y	721  				241635				DURING ANNUAL INSPECTION, FOUND PRECISE FLIGHT SVS V, SN 17245 (T-FITTING) LOOSE IN HOUSING.  IF FITTING PULLED OUR YOU 	WOULD HAVE COMPLETE VACUUM SYS FAILURE.  (K)					1	L	7	1 	3O	3	O		2A3     	1E10				 
2006102300157	20061023	00157	EA  	2006	10	23	2006FA0001008    	1	20061002	G	2740		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	87353					7353				REPORTED IN-FLIGHT SQUAWK, (STAB TRIM FAIL IN FLIGHT) ON AC.  HSTCU WAS REMOVED AND SENT FOR TEST AND REPAIR.  DURING BE	NCH TEST/INSPECTION THE FOLLOWING ITEMS WERE NOTED.  UNIT MEMORY INDICATED (CP PITCH TRIM SWITCH JAMMED) (AC SWITCH).  D	URING AUTO TEST, (HSTCU DOOR SWITCH (PN 134-30901-005) FAILED) WAS INDICATED.  DISASSY AND INSPECTION REVEALED SMALL AMO	UNT OF CORROSION ON CIF ASSY OF HSTCU.  PROBABLE CAUSES/RECOMMENDATIONS:  KNOWN PROBLEM-UNRELIABLE TRIM SWITCH HAS A DOC	UMENT THAT ADDRESSES THIS ISSUE.  HSTCU DOOR SWITCH PROBABLY BENT AFTER INCIDENT DURING TROUBLESHOOTING, IF PRIOR TO FLI	GHT FAULT WOULD HAVE BEEN INDICATED IN COCKPIT/CAUTION MECHANICS TO AVOID BENDING SWITCH ARM DURING MAINTENANCE ACTIONS.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006102000024	20061020	00024	SO  	2006	10	20	2006FA0001009    	2	20060923	G	7322	MA35PA	CARBURETOR      			CESSNA	150   	150C        	2071808	CE  	CONT  	O200  	O200*       	17020	SO  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	7870Z					15059970	250066A48			ENGINE STOPPAGE ON FINAL DUE TO CARBURATOR FLOODING, SUSPECT STUCK FLOAT.  REMOVED UNIT AND SENT BACK TO MANUFACTURE FOR	 INSPECTION.  THIS CARBURETOR WAS (FACTORY REBUILT) 1 YEAR EARLIER AND HAD LESS THAN 55 HOURS TT.  FUEL WAS FOUND SPILLI	NG OUT OF COWLING WHEN EXITING THE AIRCRAFT, SHUT FUEL VALVE OFF.  (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
2006102000030	20061020	00030	SO  	2006	10	20	2006FA0001010    	1	20060913	G	5100	89307000	ROD END         			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					CONTROL CABLE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	55068					28R7335176	L1061351A			ROD END BROKE AT POINT OF ATTACHMENT ON SERVO ARM.  APPEARS BOLT MAY HAVE BEEN OVER TORQUED AT SOME POINT WHICH CAUSED A	 STRESS CRACK AND FAILURE OF BOLT AT POINT OF ATTACHMENT.  TORQUE BOLT AT TIME OF INSTALLATION.  (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
2006102300159	20061023	00159	SO  	2006	10	23	2006FA0001011    	2	20060925	G	8530	AEC631397CN2C	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	4307S	133  				E675	281757			THE DEFECTS WERE NOTED ON 6 ENGINE COMPONENTS, CYLINDERS WITH 133.1 SINCE NEW AND PUT IN SERVICE ON THE SAME ENGINE DECE	MBER 2004.  NR 4 AND NR 5 CYLINDERS WERE CRACKED IN THE EXHAUST PORT WITH A HOLE BURNED THROUGH AT THE CRACK AND WAS LEA	KING EXHAUST GASSES OVERBOARD.  NR1, NR2, NR3, AND NR6 CYLINDERS WERE CRACKED IN THE SAME LOCATION AS NR4 AND NR5.  THE 	CRACKS ARE IB OF THE EXHAUST PORT APPEARS TO BE TOO THIN AND NOT ABLE TO WITHSTAND THE HEAT AND STRESS PRESENT DURING NO	RMAL ENGINE OPERATION.  (K)		1	L	7	1 	3O	3	O		3A15    	E3SO				 
2006102300160	20061023	00160	EA  	2006	10	23	2006FA0001012    	2	20061011	G	8500	AEL13884	MAIN BEARING    								LYC   	O320  	O320B2B     	41508	EA  					ENGINE	FAILED          	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		251  					RL1362339A			THIS ENGINE WAS DISMANTLED DUE TO METAL CONTAMINATION.  WE DISCOVERED THAT THE REAR SURFACE OF THE BEARING WAS PEELING A	WAY.  PROBABLE CAUSES OF THIS BEARING FAILURE ARE UNKNOWN.  (K)										3	O			E274				 
2006102600184	20061026	00184	EA  	2006	10	26	2006FA0001013    	2	20061009	G	8550		VALVE GUIDE     			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	LEAKING         	B			LC1R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	07	168TA					18281068	L2822248A			OPERATOR COMPLAINED OF AN OIL LEAK.  WHEN COWL WAS REMOVED IT WAS OBVIOUS THAT THE NR3 AND NR4 EXHAUST PUSH RODS AND PUS	H ROD HOUSING WERE BENT.  SUSPECTED STICKING EXHAUST VALVES.  EXHAUST VALVE TO GUIDE CLEARANCE WAS CHECKED ON ALL CYLIND	ERS IAW SB AND THE PROBLEM CYLINDERS CHECKED OK.  CYLINDERS NR2 AND NR5 CHECKED BELOW THE SPECIFIED CLEARANCE.  INSPECTE	D THE LIFTERS ASSOCIATED THE DAMAGED PUSH RODS AND FOUND NO OTHER PROBLEMS.  ALL EXHAUST VALVE GUIDES WERE REAMED IAW SI	 1425A, AND EXHAUST VALVE STEMS WERE CLEANED PRIOR TO REASSEMBLY.  (K)		1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2006102300155	20061023	00155	SO  	2006	10	23	2006FA0001014    	1	20061011	G	2612	23454G10	FIRE LOOP       			CURTIS	C46   	C46RCURTIS  	2622710	SO  	PWA   	R2800 	R280097     	52026	NE  	HAMSTD	34E	34E60       	NE  	NR 2 NACELLE	DAMAGED         	B			EVAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	7848B					273				FIRE WARNING LIGHT NR 2 ENGINE ZONE 2 AND 3 ILLUMINATED THEN EXTINGUISHED.  VISUAL INSPECTION OF ENGINE SHOWS NO SIGN OF	 FIRE OR DAMAGE, SUSPECT FAULTY LOOP DETECTOR.  (K)					2	L	7	2 	4R	4	R		3A2     	E231	6	C	P881	 
2006102000025	20061020	00025	SO  	2006	10	20	2006FA0001015    	1	20061019	G	5320	AN78310D	TEE FITTING     			GULSTM	G1159 	G1159       	3953505	SO  										BULKHEAD	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	750RA	*    				117				UPON POST FLIGHT INSPECTION THE PILOT NOTICED SMALL AMOUNT OF HYDRAULIC FLUID SEEPING FROM THE BOTTOM OF THE RADOME.  MA	INTENANCE DETERMINED THAT THE LEAK WAS COMING FROM A BULKHEAD TEE IN THE NOSE LANDING GEAR DUMP VALVE LINE.  THE LEAK WA	S INITIALLY THOUGHT TO BE CAUSED BY A DEFECTIVE PACKING BETWEEN THE TEE AND A REDUCER INSTALLED IN THE FEMALE PORT OF TH	E TEE.  THE PACKING WAS RENEWED AND THE SYSTEM WAS LAEK CHECKED.  THE LEAK PERSISTED,THE TEE FITTING WAS REMOVED AND INS	PECTED.  A CRACK WAS FOUND ON THE INNER BORE OF THE FEMALE PORT OF THE FITTING AT THE MOLD LINE OF THE FITTING.  THE CRA	CK WAS NOT VISIBLE ON THE EXTERIOR OF THE TEE.  THE TEE WAS REPLACED.THE SYSTEM WAS LEAKED CHECKED AND THE AIRCRAFT WAS 	2	L	7	2 	4F			RT	A12EA   					 
2006102000029	20061020	00029	CE  	2006	10	20	2006FA0001016    	1	20061019	G	5710		STRUCTURE       			CESSNA	500   	550         	2076604	CE  										RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	1254X	9937 	300  			0494				DURING A PHASE NR 5 A CRACH WAS FOUND IN THE LT & RT WHEEL WELL AREA ADJACENT TO THE INSIDE CORNER OF THE OPENING AT THE	 WHEEL WELL. A REPAIR WAS DONE AS PER SERRIA INDUSTRIES WING SKIN REPAIR ENGINEERING REPORT NR 3521-36 AND A DER 8110-3.	 THIS REPAIR HAS BEEN DONE ON SEVERAL OF OUR (26) AIRCRAFT AND IS NOT UNCOMMON TO SEE IN THE FIELD. I WOULD LIKE TO SEE 	CESSNA TO COME OUT WITH A SB KIT FOR THIS FIX FOR US IN THE FIELD RATHER THAN HAVING TO GET DER SUPPORTON OUR OWN.			1	L	7	2 	4F				A22CE   					 
2006112900380	20061129	00380	SW  	2006	11	29	2006FA0001017    	1	20061020	G	5302	205030889015S	SUPPORT BRACKET 			BELL  	204   	UH1H        	1181407	SW  										TAILBOOM	LOOSE           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										TAIL BOOM ELEVATOR SUPPORT BRACKET LOOSE. (WORKING RIVETS/SITE OF PREVIOUS REPAIR WITH PULL TYPE RIVETS).						1	G	7	1 	4U				EXPA1G71					 
2006102300153	20061023	00153	SO  	2006	10	23	2006FA0001018    	1	20061020	G	2822	2B663OH	PUMP            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL BOOST	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	22GE		766  			317712091	RL1182161A			LT FUEL BOOST PUMP FAILED ON RUNUP, DEBRIS CONTAMINATED FUEL SYSTEM, DAMAGED ENGINE DRIVEN FUEL PUMP, FUEL FLOW TRANSDUC	ER, CONTAMINATION FOUND IN FUEL SERVO FUEL INLET SCREEN.  SERVO REMOVED AND SENT TO REPAIR FACILITY FOR INSPECTION AND O	R REPAIRS.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006102500126	20061025	00126	GL  	2006	10	25	2006FA0001020    	1	20061018	G	2820		LINE            			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					FUEL SYSTEM	CHAFED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	777ND					1258				FUEL LINE CHAFED, LINE REPLACED.						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2006110600055	20061106	00055	CE  	2006	11	6	2006FA0001021    	1	20061006	G	3230	991242339	VALVE           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					MLG	MALFUNCTIONED   	B			CNQ3	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	122CS					5250469				CREW REPORTED (HYDRAULIC PRESSURE ON) LIGHT STAYED ILLUMINATED AFTER LANDING GEAR RETRACTION.  REPLACED LOADING VALVE AN	D OPERATIONALLY CHECKED HYDRAULIC SYSTEM.  AIRCRAFT WAS RETURNED TO SERVICE.  (K)					1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006102600161	20061026	00161	CE  	2006	10	26	2006FA0001022    	1	20061006	G	5610	NP13972112	WINDSHIELD      			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					COCKPIT	FAILED          	B			CNQ3	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	7SB					7500209				RT WINDSHIELD OUTER PANE FAILED IN FLIGHT.  THE OUTER PANE IS NON STRUCTURAL AND DID NOT EFFECT THE INTEGRITY OF THE PRE	SSURE VESSEL.  WINDSHIELD WAS SENT TO MFG ENGINEERING FOR FAILURE EVALUATION. (K)					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2006102600160	20061026	00160	CE  	2006	10	26	2006FA0001023    	1	20061006	G	2910	991242339	VALVE           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					HYD SYSTEM	FAILED          	B			CNQ3	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	122CS					5250469				CREW REPORTED ALL HYDRAULIC SYSTEMS INOPERATIVE IN FLIGHT.  LANDING GEAR WAS EXTENDED PNEUMATICALLY AND AIRCRAFT LANDED 	WITHOUT INCIDENT.  IT WAS DETERMINED THE HYDRAULIC LOADING VALVE WAS NOT CLOSING ALLOWING HYDRAULIC PRESSURE TO BUILD.  	THE HYDRAULIC LOADING VALVE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (K)				1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006102600167	20061026	00167	WP  	2006	10	26	2006FA0001024    	2	20061002	G	7250		TURBINE WHEEL   			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 2 ENGINE	FRACTURED       	B			ROIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	6NR	679  				258701	P107953			IN FLIGHT, CREW FELT SLIGHT TO MODERATE VIBRATION FROM NR 2 ENGINE.  AFTER LANDING FURTHER INSPECTION FOUND APPROX ONE I	NCH OF ONE OF THE 3 LPT DISK BLADES MISSING.  REASON FOR FAILURE AT THIS TIME UNDER INVESTIGATION BY MFG, SB 72-3689.  (	K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006102500129	20061025	00129	NE  	2006	10	25	2006FA0001025    	2	20061003	G	7230	30B47451	COMPRESSOR WHEEL			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					LT ENGINE	CRACKED         	B			BTVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	699DA	2054 				237	PCECA0319			(REF NR: 6841.5.30) DURING A SCHEDULED INSPECTION, EDDY CURRENT NDT REVEALED A CRACK IN THE LT ENGINE HP COMPRESSOR STAG	E 1 ROTOR.  (K)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006102600178	20061026	00178	SO  	2006	10	26	2006FA0001027    	2	20061017	G	8520		ROD             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	11	640LS	907  				TH1107	827255R			CYLINDER NR 2 PISTON ROD FAILED WHILE AIRCRAFT WAS IN CRUISE FLIGHT. PROP WAS FEATHERED. AIRCRAFT LANDED WITHOUT INCIDEN	T. (K)					1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006102600159	20061026	00159	CE  	2006	10	26	2006FA0001028    	1	20060912	G	6100	A4564	BEARING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	324SJ	1898 				208B0908		010761		UPON DISASSEMBLY OF THIS PROPELLER IAW WITH MFG TECH REPORT NR940. IT WAS DISCOVERED THAT THE PITCH CHANGE LINK BUSHINGS	, P/N A4564, ON BLADES NR 2 AND NR 3 WERE BROKEN AND PARTIALLY MISSING. AT LEAST 50 PERCENT OF THE BUSHINGS WERE NOT IN 	THE LINK. THE THICKNESS OF BUSHING WOULD ALLOW THE BLADE ANGLES OF TWO OF THE THREE BLADES TO BE MUCH DIFFERENT ANGLE TH	AN THEY SHOULD BE, LEADING TO EXCESSIVE VIBRATION AND LOSS OF EFFICIENCY. (THIS WAS THE REASON FOR THE HIGHER VIBRATIONS	 REPORTED BY THE FLIGHT CREWS). SB137AB HAS A MANDATORY SPECIFIED TIME BETWEEN OVERHAULS FOR THIS PROPELLER OF 4000 HOUR	S OR 72 CALENDAR MONTHS, WHICHEVER COMES FIRST. THIS PROPELLER WAS REMOVED DUE TO A CALENDAR CHANGE, NOT DUE TO HOURS IN	1	H	7	1 	3T	3	T		A37CE   	E2NE	5	C	P60GL	 
2006102600163	20061026	00163	CE  	2006	10	26	2006FA0001029    	1	20061009	G	5280	634100616	STUD            	CESSNA      		CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					MLG DOOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	902GW	488  				5250553				COMPONENT STUD APPEARS TO HAVE BEEN CRACKED FOR SOME TIME, RUST EVIDENT HALF WAY THRU BOLT CROSS SECTION AT THE START OF	 THE THREADED AREA, NEAR CENTER OF THE STUD. COULD POSSIBLY HAVE BEEN CAUSED BY MFG FLAW, OVER TORQUEING OF SAFETY JAMB 	NUTS, TO OVER RIGGING OF MLG DOOR (TOO TIGHT), IN THE GEAR UP POSITION. WHEN THIS LINK BREAKS, THE DOOR DROPS FURTHER TH	AN THE GEAR ALLOWING IT TO COME INTO CONTACT WITH THE GROUND DAMAGING THE GEAR DOOR, WHICH UNDER THE RIGHT CIRCUMSTANCE 	COULD CAUSE EXTENSIVE DAMAGE TO THE WING. (K)		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006102600165	20061026	00165	EA  	2006	10	26	2006FA0001030    	2	20061019	G	8530	LW19001	EXHAUST VALVE   								LYC   	O320  	O320E2D     	41508	EA  					CYLINDER NR 3	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		1606 								HEAD OF THE NR 3 EXHAUST VALVE BROKE OFF DURING ENGINE OPERATION. THE BROKEN PIECES DAMAGED THE PISTON AND CYLINDER HEAD	 AS WELL AS THE LOWER SPARK PLUG. SMALL PIECES FOUND IN THE OTHER 3 CYLINDERS AS WELL. (K)										3	O			E274				 
2006103100156	20061031	00156	CE  	2006	10	31	2006FA0001031    	1	20060803	G	7430	A5109	IGNITION SWITCH 			CESSNA	172   	172S        	2072439	CE  										INSTRUMENT PANEL	INTERMITTENT    	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	03	656SJ	1098 				172S8656				DURING A GROUND OUT CHECK OF THE IGNITION SWITCH, THE ENGINE CONTINUED TO RUN.  REPEATED TESTS DUPLICATED CONDITION 4 OU	T OF 10 TIMES.  UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE RT MAGNETO CONTINUED TO RUN WHEN THE FAULT OCCURRED.  R	EPLACED THE MAGNETO/STARTER SWITCH.  MAGNETO SWITCH, MODEL NR A-510-9.  AC PN C292501-0107, CAGE NR 65873.				1	H	7	1 	3O			NT	3A12    					 
2006103100164	20061031	00164	CE  	2006	10	31	2006FA0001032    	1	20061025	G	3240	656120011	TIE ROD         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					LEFT	CHAFED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	221VP	2161 				5600585				LT BRAKE TIE-ROD CHAFING ON COCKPIT DEFROST DUCT APPROX 6 INCHES ABOVE COCKPIT FLOOR, ROD WORN APPROX .030 INCHES.  NO R	ELOCATION OF COMPONENTS POSSIBLE TO ALLEVIATE CHAFING.  REPLACEMENT PART RECEIVED FROM MFG IS DIFFERENT PN AND SMALLER D	IAMETER.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006103100165	20061031	00165	CE  	2006	10	31	2006FA0001033    	1	20061030	G	7160	NONEREADABLE	AIR FILTER      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DETERIORATED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2108L	66   	39   			172S9605				METAL PIECES COMING OFF AIRFILTER (AIR FILTER P/N: CPE1173, PREVIOUSLY INSTALLED IAW STC NR SA01669CH. THE METAL PIECES 	THAT ARE COMING A PART ARE LOCATED ON THE TOP, FRONT AND REAR OF THE FILTER ASSEMBLY.  AN FAA-PMA STAMP COVERS THE PN ON	 THE FILTER. THE ONLY IDENTIFYING FEATURES ON THE FILTER IS A K&N STAMP, AND A MESSAGE TO SERVICE AT 50,000 MILES.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006103100169	20061031	00169	SO  	2006	10	31	2006FA0001034    	2	20061027	G	8550	ES48108	OIL FILTER      			CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512F      	17008	SO  					ENGINE	CONTAMINATED    	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CE	07	72951	2    				10149				DURING CRUISE FLIGHT, OIL PRESSURE DROPPED TO BELOW MINIMUM REDLINE.  PRECAUTIONARY LANDING WAS MADE.  ON INSPECTION, DI	SCOVERED RECENTLY INSTALLED (2 HOURS IN SERVICE) OIL FILTER HAS DESIGN AND/OR MANUFACTURING DEFECT ALLOWING AN INTERNAL 	SEAL TO BE DAMAGED DURING MFG SUCH THAT RUBBER SEAL MATERIAL IS RELEASED FROM THE FILTER INTO THE ENGINE OIL.  LOW OIL P	RESSURE CONDITION WAS DUE TO A CHUNK OF THIS MATERIAL FOULING THE SEAT OF THE OIL PRESSURE REGULATING VALVE, KEEPING THE	 VALVE PARTIALLY OPEN.  THE FILTER HAS BEEN DISSECTED AND I HAVE DIGITAL PHOTOS OF THE PARTS IN QUESTION AS WELL AS THE 	DEBRIS FOUND IN THE OIL SYSTEM.  I WILL RETAIN CUSTODY OF THE PARTS, BUT I CAN MAKE THEM AVAILABLE FOR INSPECTION AT THE	1	H	7	1 	3O	3	O	NC	A768    	E233				 
2006103100170	20061031	00170	SO  	2006	10	31	2006FA0001035    	2	20061027	G	8550	ES48108	OIL FILTER      			CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512F      	17008	SO  					ENGINE	CONTAMINATED    	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CE	07	72951	2    				10149				DURING CRUISE FLIGHT, OIL PRESSURE DROPPED TO BELOW MINIMUM REDLINE.  PRECAUTIONARY LANDING WAS MADE.  ON INSPECTION, DI	SCOVERED RECENTLY INSTALLED (2 HOURS IN SERVICE) OIL FILTER HAS DESIGN AND/OR MANUFACTURING DEFECT ALLOWING AN INTERNAL 	SEAL TO BE DAMAGED DURING MFG SUCH THAT RUBBER SEAL MATERIAL IS RELEASED FROM THE FILTER INTO THE ENGINE OIL.  LOW OIL P	RESSURE CONDITION WAS DUE TO A CHUNK OF THIS MATERIAL FOULING THE SEAT OF THE OIL PRESSURE REGULATING VALVE, KEEPING THE	 VALVE PARTIALLY OPEN.  THE FILTER HAS BEEN DISSECTED AND I HAVE DIGITAL PHOTOS OF THE PARTS IN QUESTION AS WELL AS THE 	DEBRIS FOUND IN THE OIL SYSTEM.  I WILL RETAIN CUSTODY OF THE PARTS, BUT I CAN MAKE THEM AVAILABLE FOR INSPECTION AT THE	1	H	7	1 	3O	3	O	NC	A768    	E233				 
2006110100095	20061101	00095	SW  	2006	11	1	2006FA0001036    	1	20061031	G	6320	206033426001	SUPPORT         	BELL        		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAILBOOM	CRACKED         	B			SL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	812TV	3622 	50   		AO1402	51185				CRACK FOUND AT TAIL ROTOR GEARBOX AFT LT MOUNTING HOLE ON TAILBOOM CASTING. REPLACED GEARBOX SUPPORT CASTING.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006111700146	20061117	00146	EA  	2006	11	17	2006FA0001037    	2	20061101	G	8530	LW19001	EXHAUST VALVE   			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	ENGINE	STUCK           	B			JRUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	311HP	673  				18280919	RL2144048A	002157		DURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (5/80) WITH A STRONG LEAK PASSED THE EXHAUS	T VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN SB 388C REVEALED THE CYLINDER DID NOT MEET THE MEASUR	EMENT CRITERIA FOR THE EXHAUST VALVE GUIDE. THE MEASUREMENT TAKEN BEFORE REAMING (IAW SB388C) WAS .007 INCH.  THE EXHAUS	T VALVE WAS REMOVED FROM THE CYLINDER (WITH THE CYLINDER INSTALLED) AND EXHAUST VALVE GUIDE WAS REAMED. A COMPRESSION CH	ECK WAS TAKEN AGAIN ON CYLINDER NR 5 AND COMPRESSION AFTER REAMING WAS 77/80.  MEASUREMENT AFTER REAMING WAS .0175 INCH.	 THE PERMISSIBLE RANGE IS .015 TO .030 INCH.  CYLINDER NR 3 ALSO FAILED THE MEASUREMENT CRITERIA OF SB 388C. THIS EXHAUS	1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2006110700065	20061107	00065	CE  	2006	11	7	2006FA0001039    	1	20061011	G	3233	99121202	SWITCH          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NOSE GEAR ACTUAT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	61	94TX	3104 				5600247				NOSE GEAR ACTUATOR JAMMED IN THE EXTENDED POSITION.  WOULD NOT RETRACT.  FOUND ACTUATOR FAULTY INTERANA SWITCH.  REPLACE	D NOSE GEAR ACTUATOR.  ACTUATOR PARET NR 15232005, SN 842.  (K)					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006110700066	20061107	00066	NE  	2006	11	7	2006FA0001040    	2	20061005	G	7320	310033501	SENSOR          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT ENGINE N1	DAMAGED         	B			AHTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	827SB	8181 	406  			RK2	PCE100183			IN NORMAL FLIGHT, THE EFC OFF(ELECTRONIC FUEL CONTROL) ANNUNCIATOR LIGHT ILLUMINATED.  THE PILOTS ATTEMPTED TO RESET THE	 EFC SEVERAL TIMES, FAILING AT EVERY ATTEMPT.  TROUBLESHOOTING REVEALED DAMAGE TO THE N1 SENSOR PROBE CAUSED BY THE N1 P	ICK-UP, AT 24 EQUALLY-SPACED TOOTHED WHEEL INTEGRAL TO THE COMPRESSOR SHAFT.  MINUTE DAMAGE WAS INFLICTED ON THE PROBE, 	CONSISTING OF AN EXTREMELY SHALLOW GROOVE CUT INTO THE END OF THE PROBE.   THE TOOTHED WHEEL DID NOT APPEAR DAMAGED.  TH	E PROBE WAS PROBABLY DAMAGED DUE TO THE IMPROPER INSTALLATION.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006110700064	20061107	00064	SW  	2006	11	7	2006FA0001041    	1	20061006	G	6200	069A5512	DRIVE BELT      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					MAIN ROTOR	STRETCHED       	B			HA4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	17535					0225				NEW DRIVE BELTS WERE INSTALLED, STRETCHED FOR 24 HOURS, AND RE-ADJUSTED IAW MM.  THE AIRCRAFT WAS RETURNED TO SERVICE AN	D .5 HOUR INTO THE FIRST FLIGHT THE PILOT NOTICED THE MAIN ROTOR RPM DECAYING AND ENGINE RPM INCREASING.  A STEEP DESCEN	T WITH POWER WAS PERFORMED AND THE AIRCRAFT LANDED SAFELY.  A SUBSEQUENT MAINTENANCE INSPECTION REVEALED THAT THE BELTS 	HAD CONTINUED TO STRETCH AFTER THE AIRCRAFT WAS RETURNED TO SEVERICE CAUSING THE CLUTCH ACTUATOR TENSION TO BECOME EXCES	SIVELY LOOSE.  THIS ALLOWED THE BELTS TO SLIP ON THE DRIVE PULLEYS AND ALLOWED THE MAIN ROTOR RPM TO DROOP.  (K)		1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2006110700057	20061107	00057	NM  	2006	11	7	2006FA0001042    	1	20061015	G	5330		SKIN            			BOEING	727   	727191      	1384063	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 360 S24-26R	CORRODED        	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	502MG					19391				CORROSION ON FUSELAGE SKIN AT BS 360 CIRCUMFERENTIAL SKIN JOINT BETWEEN STR 24R AND STR 26R.  (K)						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006110700068	20061107	00068	NM  	2006	11	7	2006FA0001043    	1	20061015	G	5330		SKIN            			BOEING	727   	727191      	1384063	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 441 S17R	CORRODED        	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	502MG					19391				CORROSION ON FUSELAGE SKIN AT BS 441, STR 17R.  (K)						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006110700058	20061107	00058	NM  	2006	11	7	2006FA0001044    	1	20061015	G	5511	65174375	RIB             			BOEING	727   	727191      	1384063	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					HORIZONTAL STAB	CRACKED         	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	502MG					19391				LT HORIZONTAL STABILIZER ELEVATOR HINGE SUPPORT RIB CRACKED (2.5 INCHES) ON OB, UPPER, AFT SIDE OF RIB AT ELEV STA 99.79	.  (K)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006110700060	20061107	00060	NM  	2006	11	7	2006FA0001045    	1	20061015	G	5511	651742812	RIB             			BOEING	727   	727191      	1384063	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					HORIZONTAL STAB	CRACKED         	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	502MG					19391				RT HORZ STAB ELEVATOR HINGE SUPPORT RIB CRACKED (2.5 INCH) ON UPPER FLANGE AT ELEV STA 17.20.  (K)						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006110700061	20061107	00061	NM  	2006	11	7	2006FA0001046    	1	20061015	G	5330		SKIN            			BOEING	727   	727191      	1384063	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 480 S7-8L	CORRODED        	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	502MG					19391				EXTERNAL FUSELAGE SKIN CORRODED AT STA 480, STR 7L TO STR 8L, CIRCUMFERENTIAL JOINT.  (K)						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006110700067	20061107	00067	NM  	2006	11	7	2006FA0001047    	1	20061015	G	5330		SKIN            			BOEING	727   	727191      	1384063	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 480 S9-10L	CORRODED        	B			KO0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	502MG					19391				EXTERNAL FUSELAGE SKIN CORRODED AT STA 480, STR 9L TO STR 10L, CIRCUMFERENTIAL JOINT.  (K)						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006110700042	20061107	00042	SW  	2006	11	7	2006FA0001048    	1	20061003	G	3220	540004	LEG ASSY        			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					NLG ASSY	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	78880					2895				NOSE GEAR COLLAPSED UPON LANDING.  INITIAL INSPECTION FOUND BOTH TUBES ON THE NOSE GEAR LEG ASSEMBLY BROKEN.  RETRACT ME	CHANISM TUBES BENT.  UNABLE TO DETERMINE WHICH COMPONENTS WERE DAMAGED PRIOR TO THE INCIDENT.  PILOT REPORTED THAT THE L	ANDING GEAR WAS HARDER THAN NORMAL TO RETRACT DURING THE LAST TAKEOFF AND EASIER TO EXTEND THAN NORMAL DURING THIS LANDI	NG.  (K)			1	L	7	1 	3O	3	O		2A3     	E286				 
2006110700056	20061107	00056	GL  	2006	11	7	2006FA0001049    	1	20061010	G	2810	C36L	CAP             			DIAMON	DA40  	DA40        	2990002	GL  										FUEL TANK	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	416FP	40   				40FC016				UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 TO 3 SUMP GLASSES WERE FIL	LED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN.  FURTHER INSPECTION OF 9 OTHER AIRCRAFT OF THE SAME MAKE AND MODEL F	OUND 2 OTHER AIRCRAFT WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS.  ALL 3 OF THESE AIRCRAFT WERE TIED DOWN OUTSIDE 	DURING WEATHER ABOVE STATED.  INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSEMBLY OF ALL TWELVE AIRCRAFT REVEALED THE SAME	 LOOSE FUEL CAP CONDITION.  ALL AIRCRAFT FUEL CAPS WERE TIGHTEN AS A PRECAUTION.  THE O-RING SEALS DID NOT APPEAR TO BE 	DAMAGED.	1	L	7	1 	3O			NT	A47CE   					 
2006110700054	20061107	00054	EA  	2006	11	7	2006FA0001050    	2	20061025	G	8597	DA424064100	WIRE HARNESS    			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					ALT/CB	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	417FP	69   				40FC017				TOTAL ELECTRICAL SYSTEM FAILURE IN FLIGHT.  INSPECTION REVEALED THAT THE MAIN POWER WIRES RING TERMINAL TO THE ALTERNAT	OR HAD FAILED CAUSING ARCING WHICH SHORTED THE ALTERNATOR OUT AND CAUSED THE MAIN AND ESSENTIAL BUSS CIRCUIT BREAKERS TO	 POP.  POSSIBLE CAUSE IS TOO SHORT OF A WIRE HARNESS WHICH DOES NOT ALLOW FOR ENGINE VIBRATION.  REMEDIED WITH NEW ALTER	NATOR AND NEW ALTERNATOR CABLE ASSY PROVIDED BY MFG.  THE NEW CABLE ASSY IS A COUPLE OF INCHES LONGER TO PREVENT THIS FR	OM OCCURRING.  (K)		1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2006110700055	20061107	00055	GL  	2006	11	7	2006FA0001051    	1	20061010	G	2701	D4122131200	CONTROL STICK   			DIAMON	DA40  	DA40        	2990002	GL  										CONTROL COLUMN	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	418FP	34   				40FC018				PILOTS CONTROL STICK GRIP BECAME LOOSE AND WOULD, IF PULLED ON, COULD BECOME DETACHED FROM THE CONTROL ASSEMBLY.  CHECK 	BOTH CONTROL GRIPS FOR LOOSE INSTALLATION AND REATTACH WITH APPROVED ADHESIVE.  (K)					1	L	7	1 	3O			NT	A47CE   					 
2006110700053	20061107	00053	GL  	2006	11	7	2006FA0001052    	1	20061010	G	2810	C36L	CAP             			DIAMON	DA40  	DA40        	2990002	GL  										WING FUEL TANK	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	420FP					40FC020				UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 OR 3 SUMP GLASSES WERE FIL	LED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN.  FURTHER INSPECTION OF 9 OTHER AC OF THE SAME MAKE AND MODEL FOUND 2	 OTHER AC WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS.  ALL 3 OF THESE AC WERE TIED DOWN OUTSIDE DURING WEATHER ABO	VE STATED.  INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSY ON ALL 12 AIRCRAFT REVEALED THE SAME LOOSE FUEL CAP CONDITION.	  ALL AC FUEL CAPS WERE TIGHTENED AS A PRECAUTION.  THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED.  (K)		1	L	7	1 	3O			NT	A47CE   					 
2006110700062	20061107	00062	GL  	2006	11	7	2006FA0001053    	1	20061010	G	2810	C36L	CAP             			DIAMON	DA40  	DA40        	2990002	GL  										WING FUEL TANK	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	423FP	38   				40FC023				UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 OR 3 SUMP GLASSES WERE FIL	LED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN.  FURTHER INSPECTION OF 9 OTHER AC OF THE SAME MAKE AND MODEL FOUND 2	 OTHER AC WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS.  ALL 3 OF THESE AC WERE TIED DOWN OUTSIDE DURING WEATHER ABO	VE STATED.  INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSY ON ALL 12 AC REVEALED THE SAME LOOSE FUEL CAP CONDITION.  ALL 	AC FUEL CAPS WERE TIGHTENED AS A PRECAUTION.  THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED.  (K)		1	L	7	1 	3O			NT	A47CE   					 
2006110700063	20061107	00063		2006	11	7	2006FA0001055    	2	20061025	G	8550	83278	PRESSURE SWITCH 			CESSNA	172   	172R        	2072401	CE  										ENGINE OIL	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	24352	2618 				17280835				AC WAS MAKING AN APPROACH AND HAD OIL SPLASH ON THE WINDSHIELD.  PILOT MADE A FULL STOP AND TAXIED BACK TO RAMP.  OIL PR	ESSURE AND TEMPERATURE STAYED IN THE GREEN.  UPON INVESTIGATION, FOUND THE CAUSE OF THE OIL LEAK TO BE THE (SENSOR-OIL P	RESSURE (HOBBS-SWITCH) PN 83278 TO BE THE SOURCE OF THE LEAK.  THE SENSOR HAD FAILED INTERNALLY AND THE OIL WAS COMING F	ROM AROUND THE PRONGS INSIDE THE CONNECTOR AREA.  PROBABLE CAUSE-BAD DESIGN.  PREVENT REOCCURRENCES-UNKNOWN.  (K)			1	H	7	1 	3O			NT	3A12    					 
2007060500213	20070605	00213	CE  	2007	6	5	2006FA0001056    	1	20061022	G	5100		PIN             			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					ACTUATOR	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	5274S					R18201534				LOCKDOWN PINS BROKE AT GROOVE FOR ROLL PINS.  THIS ALLOWED THE PINS TO MOVE OUT OF ACTUATOR BEARING END AND JAM THE ACTU	ATOR.  IN THE UNLOCKED POSITION, SEB95-20 ACTUATOR DOWNLOCK PIN.  INSPECTION SAYS TO CHECK FOR LOOSE PINS.  THESE PINS W	ERE NOT LOOSE IN THE END BEARING UNTIL THE PART WAS THOROUGHLY CLEANED.  THERE ARE INDICATIONS THAT THE PINS WERE MOVING	 BUT COULD NOT BE MOVED.   THE NEW ASSEMBLIES USE A PIN THROUGH THE PINS INSTEAD OF A GROVE CUT IN THE CIRCUMFERENCE OF 	THE LOCKDOWN PIN.  SUGGEST THAT ANY ACTUATORS THAT ARE STILL OUT THERE BE REMOVED AND CLEANED TO DETERMINE  THAT THE PIN	S ARE BROKEN OR LOOSE.  (K)	1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2006120500296	20061205	00296	SO  	2006	12	5	2006FA0001057    	1	20061025	G	7830	1159SCP40211RW	ACTUATOR        			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					THRUST REVERSER	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	01	595PE	143  	143  			1373	16871			APPROXIMATELY 20 MINUTES INTO THE FLIGHT, THE CREW NOTIFIED MAINTENANCE THAT THEY HAD A (T/R REV UNLOCK) LIGHT.  THE CRE	W BROUGHT BACK POWER AND THE LIGHT EXTINGUISHED, CREW THEN SELECTED (EMERGENCY STOW) AND RETURNED TO DEPARTURE WITHOUT I	NCIDENT.  AS THE AIRCRAFT ROLLED UP WITH ENGINES RUNNING, MAINTENANCE NOTED THE LT T/R DROOPED APPROX .1250 INCH, BUT ST	ILL NOT ON THE SECONDARY LOCK (S HOOKS).  THIS ACTUATOR HAD BEEN INSTALLED IN FEB 2006.  A NEW REPLACEMENT ACTUATOR PN: 	1159CP402-11, SN 2268 HAS BEEN INSTALLED WITH NO FAULTS NOTED AND THE AC HAS BEEN RETURNED TO SERVICE.  (K)		2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2006111700166	20061117	00166	CE  	2006	11	17	2006FA0001058    	1	20061018	G	3411	0800106379	PITOT LINE      			CESSNA	310   	T310Q       	2074244	CE  	CONT  	O520  	TSIO520*    	17040	SO  						CORRODED        	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	17	87JV					310Q0206				DURING A ROUTINE PITOT/STATIC TEST, FOUND THAT THE PITOT SYSTEM WAS LEAKING BEYOND LIMITS.  THE LEAKAGE WAS DETERMINED T	O BE IN THE TUBING FROM THE PITOT TUBE TO THE FORWARD CABIN BULKHEAD FITTING.  UPON REMOVING THE TUBE (PN 0800106-379) S	EVERE CORROSION WAS FOUND AT THE AFT  END, NEAR THE FITTING.  THIS PORTION WAS FOUND HALF BURIED IN THE OUTER INSULATION	 OF A HEAT DUCT ON THE LT OB SIDE, ALLOWING MOISTURE TO BE TRAPPED.  THIS AREA IS DIFFICULT TO INSPECT AND DAMAGE TO THE	 TUBE COULD GO UNDISCOVERED UNTIL A LEAK TEST IS PERFORMED.  IT IS RECOMMENDED THAT OPERATORS OF AC HAVE THIS LINE INSPE	CTED, AND THAT CHAFE AND CORROSION PROTECTION BE APPLIED TO THE TUBE WHERE IT CONTACTS THE INSULATION OF THE HEAT DUCT. 	1	L	7	2 	3O	3	O		3A10    	E8CE				 
2006120500309	20061205	00309	EA  	2006	12	5	2006FA0001059    	2	20061020	G	8520	72877	LIFTER          			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	BROKEN          	B			JUJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	1102N		1800 			3240756	L1236848			LIFTER BROKE. (K)						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2006120500310	20061205	00310	EA  	2006	12	5	2006FA0001060    	2	20061020	G	8520	72877	LIFTER          			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	BROKEN          	B			JUJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	9581V	1138 				18280257	L2639348A			LIFTER BROKE.  (K)						1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2006120500311	20061205	00311	EA  	2006	12	5	2006FA0001061    	2	20061020	G	8520	AEL72877	LIFTER          			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	BROKEN          	B			JUJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	146DG	1400 				4636066	L975261A			LIFTER BROKE.  (K)						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2006120500312	20061205	00312	EA  	2006	12	5	2006FA0001062    	2	20061003	G	8520	1382712170	CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CORRODED        	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	987WU	2216 				17280550	L170551A			INSIDE DIAMETER WAS FOUND TO BE PITTED AFTER REMOVAL OF THE COATING CALLED URETHABOND 104.  THIS COATING WAS APPLIED BY 	MFG.  THE SURFACE APPEARED TO BE VERY ROUGH, ALMOST THREADED.  THE CAUSE FOR THE CORROSION IS UNCERTAIN.  A SUGGESTION F	OR PREVENTION IS NOT POSSIBLE.  MY SPECULATION WOULD BE THAT THE COATING IS NOT ADEQUATELY SEALING THE SURFACE FROM MOIS	TURE.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006120500315	20061205	00315	CE  	2006	12	5	2006FA0001063    	1	20061011	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	01	686SP					172S8097				BENDIX GEAR FAILS DURING START OPERATION.  INSTALLED ON 3/10/04, REMOVED ON 8/16/04.  (K)						1	H	7	1 	3O			NT	3A12    					 
2006120500316	20061205	00316	EA  	2006	12	5	2006FA0001064    	2	20061012	G	8530	17F19357	ROCKER          			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					NR 4 CYLINDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	776SH		5    			3552				NR 4 CYLINDER INTAKE ROCKER ARM CRACKED/SPLIT INTO 2 PIECES.  CRACK/ SPLIT RUNS CROSS-WAYS NEAR ROCKER BOSS ON VALVE STE	M SIDE OF ROCKER ARM.  AGGRESSIVE MACHINING OF ROCKER ARM AND OR ROCKER ARM INCORRECTLY CONTACTING KEEPER SPRING ASSEMBL	Y.  (K)				1	G	7	1 	3O	3	O		H10WE   	E286				 
2007011800030	20070118	00030		2007	1	18	2006FA0001065    	4	20060918	G	2564	46FASA631201	LIFE RAFT       																	CABIN	PARTIAL INFLATE 	D			WV1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	35										LIFE RAFT PARTIALLY INADVERTENTLY DEPLOYED IN CUSTOMERS AIRCRAFT CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIB	LY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED	 IN-FLIGHT.  THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZ	ING THE POSSIBILITY OF SEVERE DAMAGE.  (K)																 
2006111500310	20061115	00310		2006	11	15	2006FA0001066    	4	20060926	G	2564	46FASA2303603	LIFE RAFT       																	CABIN	PARTIAL INFLATE 	C			WV1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	35										LIFE RAFT PARTIALLY INADVERTENTLY INFLATED IN CUSTOMERS AIRCRAFT CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIB	LY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED	 IN-FLIGHT.  THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZ	ING THE POSSIBILITY OF SEVERE DAMAGE.  (K)																 
2006120500317	20061205	00317	EA  	2006	12	5	2006FA0001067    	2	20060926	G	8530	SI74673	COMPRESSION RING			GULSTM	G44   	G44         	3951502	SO  	LYC   	O480  	GO480B1C    	41527	EA  					PISTON	IMPROPER        	D			AV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	645DH					1329	L29228			SUPERIOR COMPRESSION RINGS PN 74673 WERE INSTALLED DURING OVERHAUL, AFTER 3.0 HRS OF RUNNING A BORE SCOPE INSPECTION REV	EALED SOME STRANGE BLACKENING OF THE CYLINDER WALLS.  A CYLINDER WAS REMOVED TO INVESTIGATE AND THE TOP (2) COMPRESSION 	RINGS ONLY SHOWED CONTACT ON THE BOTTOM HALF INDICATING THAT THE BEVEL ON THE FACE OF THE RING WAS FACING THE WRONG WAY 	FOR A COMPRESSION RING.  AFTER COMPARING THIS SUPERIOR RING TO A MFG RING IT APPEARS THE SUPERIOR RING IS DEFECTIVE, NUM	BERED WRONG, BUT DOES NOT MATCH THE SHAPE OF THE RING AND INFORMATION OBTAINED FROM MFG TECH SUPPORT.  SUBSEQUENTLY ALL 	CYLINDER HAVE BEEN REMOVE TO REPLACE THESE RINGS.  RECOMMEND THAT ALL RINGS FROM MFG BE RECALLED FROM THE SYSTEM FOR SAF	1	H	7	2 	3I	3	O	O	A734    	E275				 
2006111500306	20061115	00306	SO  	2006	11	15	2006FA0001068    	1	20061103	G	7921	20017A	OIL COOLER      			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  						LEAKING         	B				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			GL	21	287ND	2365 	3    			2844036	L1731751A			PILOT REPORTED FLICKERING OIL PRESSURE ANNUCIATOR DURING TAKE-OFF. LANDED AND FOUND OIL LEAKING FROM OIL COOLER AREA. UP	ON CLOSER EXAMINATION BY A&P DETERMINED COOLER WAS LEAKING IN BETWEEN THE COOLING FINS. COOLER WAS REPLACED RUN UP AND L	EAK CHECKED GOOD. OIL LEVEL NEVER EXCEDED MINIMUM QUANTITY.				1	L	7	1 	3O	3	O		2A13    	1E10				 
2006111500330	20061115	00330	EA  	2006	11	15	2006FA0001069    	2	20061109	G	8530	LW19001	EXHAUST VALVE   			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	ENGINE CYLINDER	STUCK           	B			JRUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	715HP	501  				18280921	RL2126148A	060202		STUCK EXHAUST VALVES ON NR 3 CYLINDER FOUND DURING PHASE 2 INSPECTION.  						1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2006120500318	20061205	00318	CE  	2006	12	5	2006FA0001070    	1	20060223	G	8011	646275	BEARING         			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					STARTER MOTOR	SEIZED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	6622N					21063125				OVERHAULER W/O NR 84062, O/H DATE 10/06/2006.  STARTER BEARING SEIZED AFTER INSTALLATION STARTER MOTOR FAILED.  (K)						1	H	7	1 	3O	3	O		3A21    	E8CE				 
2006120500319	20061205	00319	CE  	2006	12	5	2006FA0001071    	1	20061028	G	5720	1011200953	WEB             			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT WING	CRACKED         	B			B92R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	828FM					BB1069				DURING PHASE 1 THROUGH 4 INSPECTION, AFTER REMOVING MOVING ALL WING INSPECTION PANELS.  4 (EA) CRACKS NOTICED IN WEB FLA	NGE COMMON TO AND EMITTING FROM RIVETS ON LT IB WING BOX AREA, BL-65.50, (2EA) CRACKS AT WS 65, (1EA) CRACK AT WS 56.  (	K)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006111700049	20061117	00049	SO  	2006	11	17	2006FA0001072    	1	20060904	G	2710	6271605	SHAFT           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					AILERONS	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	4112R					3240431				THE HOLE IN THE SHAFT WAS MISDRILLED WHERE THE TAPER PIN ATTACHES IT TO THE SPROCKET, WHICH IS PART OF THE AILERON CONTR	OL SYSTEM.  THE MISDRILLED HOLE ALLOWED THE PIN TO BREAK FREE OF THE SHAFT.  THIS FAILURE CAUSED THE SEPARATION OF THE R	T CONTROL WHEEL FROM THE AIRPLANE FLIGHT CONTROL SYSTEM.  THIS PROBLEM WAS FOUND WHILE CONDUCTING OTHER MAINTENANCE ON T	HE AIRCRAFT.  THE PART IS AVAILABLE FOR INSPECTION.  PHOTOS OF THE PART ARE AVAILABLE VIA E-MAIL. (K)			1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2006120500320	20061205	00320	CE  	2006	12	5	2006FA0001073    	1	20061029	G	3220	08424008	BRACKET         			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470*       	17026	SO  					NLG	FAILED          	D				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			WP	07	5166D	5400 				51266				DURING LANDING ROLL OUT THE NOSE GEAR BEGAN TO SHIMMY UNTIL NOSE GEAR FAILURE.  AN INSPECTION SHOWN, A FAILURE OF THE NO	SE GEAR SHIMMY DAMPER BRACKET ON HOUSING.  PART ORIGINAL TO 1958 INSTALLATION.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2006120500237	20061205	00237	SW  	2006	12	5	2006FA0001074    	1	20061031	G	3250	350501	SERVO           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313U    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG STEERING	MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	247ML					TC247				AIRCRAFT PULLS TO THE RT.  OPERATOR REMOVED AND REPLACED NOSE STEERING SERVO, FLUSHED OUT LINES AND REPLACED FILTER.  OP	S CHECK GOOD IAW MFG MM.  (K)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2006120500321	20061205	00321	CE  	2006	12	5	2006FA0001075    	1	20061011	G	8011	PM2401H	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	01	686SP	177  				172S8097				THE BENDIX GEAR CRACKED/SHATTERED DURING START OPERATION.  NO DAMAGE TO RING GEAR.  PART INSTALLED ON 6/23/2006.  PART R	EMOVED ON 10/11/2006.  THIS IS BECOMING A VERY BIG PROBLEM WITH THESE STARTERS.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007013100255	20070131	00255		2007	1	31	2006FA0001076    	2	20061030	G	8520		CONNECTING ROD  			AMTR  	RWEXEC	ROTORWAY162F	       	GL  										ENGINE	FAILED          	G				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SW	11	162HM					6135				ENGINE FAILED ON CIRCLING CLIMB FROM AIRPORT.  ROD CAME THRU ENGINE BLOCK.  (INCIDENT ISW1107003) (K)						1	G	7	1 	3O				EXPA1G71					 
2006120500259	20061205	00259	SO  	2006	12	5	2006FA0001077    	2	20060928	G	8530	SA10200A1	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 3	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	714DG	1100 				15079092				OIL LEAK LEAD TO FINDING CYLINDER BARREL CRACKED, MID SECTION IN COOLING FINS, .7500 WAY AROUND BARREL.  (K)						1	H	7	1 	3O	3	O		3A19    	E252				 
2007011800033	20070118	00033	SO  	2007	1	18	2006FA0001078    	1	20061031	G	3213	65489000	STRUT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MLG	DEPARTED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	5513V					287716181	L802639A			WHILE PRACTICING TAKEOFF AND LANDINGS, THE TOWER INFORMED PILOT THERE WAS A PROBLEM WITH LEFT LANDING GEAR.  THE INSTRUC	TOR ELECTED TO RETURN TO TAKEOFF AIRPORT.  UPON LANDING THE BRAKEHOSE SEPARATED, AND THE WHEEL, BRAKE ASSY, STUB AXEL AN	D OLEO PISTON DEPARTED WHEN LANDING WAS MADE ON BOTTOM OF LT GEAR CYLINDER.  PROBABLE CAUSE IS NUMEROUS HARD LANDINGS WI	TH STUDENTS FLYING. (K)			1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006120500322	20061205	00322	GL  	2006	12	5	2006FA0001079    	1	20061005	G	2434	653344	ALTERNATOR      			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	ENGINE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	01	269CD	940  				1204	357442	EF282B		DURING FLIGHT, PILOT NOTICED A LOUD BANGING NOISE FROM UNDER ENGINE COWLING PILOT PROCEEDED TO LAND.  AFTER LANDING, MAI	NTENANCE DEPARTMENT.  REMOVED COWLING TO FIND THIS ALTERNATOR SEPARATION/ FAILURE.  NO OTHER COMPONENTS WERE DAMAGED.  I	NSPECTION PRIOR TO THIS FAILURE SHOWED NO DEFECT TO THIS COMPONENT.  (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2006121200288	20061212	00288		2006	12	12	2006FA0001080    	1	20061016	G	2750	790231509	CONTROL VALVE   																	T/E FLAP	DEFECTIVE       	B			W6NR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	25										PART HAD OVERHAULED TAG INSTALLED SEPT 2004.  THE PART WAS INSTALLED ON A COMMANDER AND STILL HAD THE SAME PROBLEM OF DR	OOPING FLAPS.  WE SENT THE UNIT BACK AND THEY SAID IT NEEDED REPAIRED AND ADDITIONAL SERVICED PERFORMED.  THE UNIT WAS S	ENT BACK TO US JULY 2005 AND THE INSTALLED ON ANOTHER AIRCRAFT IN JULY 2006 AND THE SAME PROBLEM OCCURRED WE HAD ON THE 	PREVIOUS AC.  THIS UNIT WAS NOT ON THE AIRCRAFT LONG ENOUGH TO DO ANY KIND OF DAMAGE.  WE RAN THE FLAP SYSTEM 1 TIME AND	 STILL SAME PROBLEM.  WE SENT THE PART BACK AGAIN AND THEY SAID IT NEEDED OVERHAULED THIS TIME.  WE INSTALLED A NEW FLAP	 VALVE ON THE AIRCRAFT AND THE PROBLEM IS GONE.  (K)														 
2007010800147	20070108	00147	SO  	2007	1	8	2006FA0001081    	1	20061101	G	2510	8994406	SEAT BACK       			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	812MB					4636111				CREW SEAT BACK FRAME CROSS SUPPORT BREAKS AT WELDED JOINT ON EITHER SIDE AND OR BOTH.  (K)						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2007011600012	20070116	00012	EA  	2007	1	16	2006FA0001082    	2	20061108	G	7220	10991004933	TUBE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					INLET	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	200HV					LJ1478				THE TUBES ARE CRACKING ALONG THE WELDS, WHICH CONNECT THEM TO THE INLET LIP ASSEMBLY.  REQUIRES REMOVAL OF INLET LIP ASS	Y AND REPAIR OF THE CRACKED WELDS.  (K)					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2007011800056	20070118	00056	NM  	2007	1	18	2006FA0001083    	1	20061002	G	3230	65446924	HOUSING         			BOEING	737   	737*        	       	NM  										MLG VALVE	CRACKED         	C			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01										REF (211263/KS2) HOUSING CRACKED IN VALVE BORE. CYCLIC STRESS. REDESIGN HOUSING. (K)						2	L	7	2 	4F			RT	A16WE   					 
2006111700138	20061117	00138	NM  	2006	11	17	2006FA0001084    	1	20061006	G	2913	65447822	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										VALVE	ERODED          	D			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					1795					(REF: 211704/QN1) PIN HOLE ERODED IN NR 2 PORT HEEL.  MATERIAL DEFECT/ TIME.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2007010900006	20070109	00006	GL  	2007	1	9	2006FA0001085    	2	20061103	G	7260	23034787AL	BEARING         	ALLSN       		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	SPALLED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGPHC				CAG35789	180257D	CAE830015			VISIBLE LINE FOUND ON 2.5 BEARING ROLLERS MATCHING SPALLING FOUND ON SAG SHAFT (SDR DATED 3/NOV/2006).  GEARBOX INSTALLE	D 6/SEPT/2006.  TIME IN SERVICE FOR GEAR BOX, 105.1 HOURS.  2.5 BEARING INSTALLATION TIMES NUT SHOWN ON ENGINE CARDS.  2	.5 BEARING IS A PMA PART ALCOR.  (K)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007010800172	20070108	00172	WP  	2007	1	8	2006FA0001086    	1	20061004	G	5300	369A75058	SUPPORT         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ANTITORQUE PEDAL	CORRODED        	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	511SB					1090592D				DURING ANNUAL INSPECTION PEDAL SUPPORT WAS FOUND WITH CORROSION ON LOWER BOLT PADS BEYOND REPAIRABLE LIMITS.  REPLACED S	UPPORT BRACKET WITH SERVICEABLE PART.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007011600054	20070116	00054	GL  	2007	1	16	2006FA0001087    	2	20061103	G	7230	E23031922C	SHAFT           	ALLSN       		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR ASSY	SPALLED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGPHC				CAC362283	180257D	CAE830015			FOUND SPALLING ON BEARING RACE AT 2.5 BEARING CONTACT POINT.  FOUND VISIBLE LINE ON 2.5 BEARING ROLLERS MATCCHING SPALL 	LINE ON SAG SHAFT.  COMPRESSOR ASSY INSTALLED ON AC 6/SEPT/2006, TIME IN SERVICE SINCE INSTALLATION OF COMPRESSOR ASSY 1	05.1 HOURS, 220 CYCLES.  INSTALLATION TIMES NOT SHOWN ON ENGINE CARDS FOR SAG SHAFT.  SAG SHAFT IS A PMA PART-EXTEX.  (K	)			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007010400063	20070104	00063	SW  	2007	1	4	2006FA0001088    	1	20061119	G	6200	2040408123	ADAPTER         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	DAMAGED         	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGREU					30011				DURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS A	CCOMPLISHED AND IT WAS DISCOVERED THAT THERE WAS NO TORQUE, THAT THE BREAKER BAR`S WEIGHT BROKE THE BOLT LOOSE, REMOVED 	THE ADAPTOR AND FOUND WEAR ON THE ADAPTOR FLANGE AND IT WAS BEYOND LIMITS IAW TECH BULLETIN.  REPLACED PART.  (K)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006111700133	20061117	00133	CE  	2006	11	17	2006FA0001089    	1	20061115	G	5210	MS203922C63	HINGE PIN       			BEECH 	35    	V35B        	1151548	CE  										CABIN DOOR	LOOSE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	66WC	2540 				D10199				CABIN DOOR TOP HINGE PIN KEEPER COTTER PIN FAILED. THE PIN, A CLEVIS BOLT, WAS INSTALLED FROM THE BOTTOM DUE TO STRUCTUR	AL DESIGN LIMITATIONS. THE FAILURE OF THE COTTER PIN ALLOWED THE CLEVIS PIN THE PARTIALLY FALL OUT OF PLACE ALLOWING THE	 DOOR TO MOVE. COMPLETE LOSS OF THE PIN MIGHT HAVE ALLOWED THE DOOR TO SEPARATE FROM THE AIRCRAFT IN FLIGHT. POSSIBLE IM	PACT WITH THE RT RUDDERVATOR. CLOSER INSPECTION AT ANNUAL AND INSTALLING THE PIN FROM THE TOP WOULD HELP AVOID THE PROBL	EM.		1	L	7	1 	3O				3A15    					 
2006111700134	20061117	00134	EA  	2006	11	17	2006FA0001090    	2	20061115	G	7414	6393	MAGNETO         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	FAILED          	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			GL	13	15FG	630  	140  			277554112	L1313448A			PILOT REPORTED THAT HE STARTED LT ENGINE AND THEN ATTEMPTED TO START RT ENGINE ON THE GROUND.  RT ENGINE WOULD NOT FIRE.	  TROUBLESHOT AND TRACED PROBLEM TO LT MAGNETO OF RT ENGINE.  REMOVED LT MAGNETO FROM ENGINE.  UPON REMOVAL, LOOSE PARTS	 COULD BE HEARD INSIDE OF MAGNETO.  MAGNETO WAS DISASSEMBLED.  THE WEDGES HOLDING THE COIL IN PLACE WERE FOUND TO BE DIS	LODGED AND THE COIL HAD SHIFTED AND TAB WAS NOT MAKING CONTACT WITH DISTRIBUTOR BRUSH.  MAGNETO WAS INSPECTED AND ALL OT	HER PARTS WERE FOUND TO BE SERVICEABLE.  A NEW COIL AND WEDGES WERE INSTALLED AND THE MAGNETO WAS REINSTALLED ON THE ENG	INE AND OPERATED SATISFACTORILY.  THIS MAGNETO WAS NEW AT ENGINE INSTALLATION 630 HOURS AGO AND HAD BEEN DISASSEMBLED AN	1	L	7	2 	3O	3	O		1A10    	1E4				 
2006111700137	20061117	00137	CE  	2006	11	17	2006FA0001093    	1	20061115	G	5210	MS203922C63	HINGE PIN       			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520*      	17032	SO  					CABIN DOOR	LOOSE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	66WC	2540 				D10199				CABIN DOOR TOP HINGE PIN KEEPER COTTER PIN FAILED. THE PIN, A CLEVIS BOLT, WAS INSTALLED FROM THE BOTTOM DUE TO STRUCTUR	AL DESIGN LIMITATIONS. THE FAILURE OF THE COTTER PIN ALLOWED THE CLEVIS PIN THE PARTIALLY FALL OUT OF PLACE ALLOWING THE	 DOOR TO MOVE. COMPLETE LOSS OF THE PIN MIGHT HAVE ALLOWED THE DOOR TO SEPARATE FROM THE AIRCRAFT IN FLIGHT. POSSIBLE IM	PACT WITH THE RT RUDDERVATOR. CLOSER INSPECTION AT ANNUAL AND INSTALLING THE PIN FROM THE TOP WOULD HELP AVOID THE PROBL	EM.		1	L	7	1 	3O	3	O		3A15    	E5CE				 
2006112900376	20061129	00376	EA  	2006	11	29	2006FA0001094    	2	20061116	G	7414	M3548	ROTOR           	SLICK       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAGNETO	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		549  			04081167					RT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE PLASTIC ROTOR GEAR.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006120400106	20061204	00106	EA  	2006	12	4	2006FA0001095    	2	20061116	G	7314	M3548	ROTOR           	SLICK       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAGNETO	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		549  			04081167					RT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE PLASTIC ROTOR GEAR.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006120500251	20061205	00251	SO  	2006	12	5	2006FA0001096    	1	20061106	G	7120	102460036	MOUNT           			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	5215U	757  				4697068				CUSTOMER REPORTED THAT HYDRAULIC PUMP KENP CYCLING.  INSPECTED LANDING GEAR ACTUATORS FOR LEAKS.  FOUND NLG ACTUATOR ATT	ACH CRACKED ON ENGINE MOUNT.  INSTALLING NEW ENGINE MOUNT IAW SB 1154A WILL SOLVE MALFUNCTION. (K)					1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2006120500246	20061205	00246	CE  	2006	12	5	2006FA0001097    	1	20060815	G	3250	2609	SPRING          			BBAVIA	11    	11AC        	0191102	CE  	CONT  	A65   	A65*        	17003	SO  					TAIL STEERING	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	3799E					11ACS18				TAIL WHEEL SPRING STRETCHED AT HOOK CPVSWG PILOT TO LOOSE RUDDER CONTROL PAD DEPART TAXIWAY.  (K)						1	H	7	1 	3O	3	O		A761    	E205				 
2006120500249	20061205	00249	CE  	2006	12	5	2006FA0001098    	1	20061107	G	2820	LW120981116	PRIMER LINE     			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					NR 3 CYLINDER	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			EA	23	2059E					17271137				NOTED FUEL SPRAYING OUT WHEN TRYING TO PRIME ENGINE FOR START.  FOUND LINE CRACKING AT WELDED TIP AREA.  ON PRIMER LINE,	 WHERE IT ATTACHES TO CYLINDER FITTING.  THIS IS A BAD TYPE END ON LINE.  SUGGEST MORE SECURITY OF PRIMER LINES AT MORE 	PLACES, TO MINIMIZE VIBRATIONS. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006120500239	20061205	00239	CE  	2006	12	5	2006FA0001099    	1	20061107	G	2497		WIRE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					ALTERNATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	2059E					17271137				ALTERNATOR FAILED AND MAIN POWER BUS FEED WIRE BROKEN FROM ALTERNATOR.  TERMINAL ENDS, PROBABLY DUE TO VERY TIGHT AREA A	ND VIBRATION.  PREVENTION MIGHT BE TO ENLARGE AREA WHERE WIRES PASS THRU BAFFLING TO LIGHTEN VIBRATION AND STRESS ON WIR	ES BEING BENT TO FIT IN THIS AREA.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007011100143	20070111	00143	CE  	2007	1	11	2006FA0001100    	1	20061025	G	2810	128920185609	FUEL TANK       			BEECH 	MU300 	400A        	1155402	CE  										AUX	DEBONDED        	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	45RK	5423 				RK43				INVESTIGATED REPORTS OF IN-FLIGHT POPPING NOISES FROM UNDER FLOOR AREA ADJACENT TO CABIN DOOR.  FOUND FORWARD LT AUXILLA	RY TANK STRUCTURE UNDERSIDE HONEYCOMB PANELS DISBONDED FROM TANK STRUCTURE SHEETMETAL.  NO CORROSION NOTED, HONEYCOMB MA	TERIAL APPEARS TO HAVE SEPARATED FROM SHEETMETAL AT ADHESIVE BOND LINE.  SLIGHT DEFORMATION OF CURVED UNDERSIDE OF FUEL 	TANK STRUCTURE NOTED.  INFORMATION FORWARDED TO MFG FOR FOLLOW-UP INVESTIGATION.  POSSIBLE CAUSE IS VACUUM IN FUEL TANK 	DUE TO VENTING PROBLEM CAUSING TANK DEFORMATION AND/OR HONEYCOMB ADHESIVE FAILURE.  (K)		2	H	7	2 	4F			RT	A16SW   					 
2007011200001	20070112	00001	NE  	2007	1	12	2006FA0001101    	2	20061108	G	7321	0164248850	FUEL CONTROL    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	680CH	2352 				3540	9798			(4TH FLIGHT OF THE NIGHT) AFTER START UP, ALL SYSTEMS NORMAL, UPON LIFT OFF THE TURBINE AND ROTOR RPM SIMULTANEOUSLY DEC	REASED.  PILOT REDUCED PITCH AND LANDED ON PAD WITHOUT INCIDENT RPM RETURNED TO 100 PERCENT.  PILOT AND COPILOT CROSS CH	ECKED INSTRUMENTS AND CONTROLS POSITIONS, FOUND NORMAL.  A SECOND ATTEMPT WAS MADE WITH THE SAME RESULTS.  BOTH NEEDLES 	STAYED TOGETHER DURING EACH EVENT.  THE TURBINE AND ROTOR SPEED RETURNED TOT HE NORMAL RANGE UPON THE COLLECTIVE BEING R	ETURNED TO THE LOCKED POSITION.  AIRCRAFT WAS REMOVED FROM SERVICE.  MAINTENANCE PERFORMED VISUAL INSPECTIONS AND GROUND	/FLIGHT OPERATIONAL CHECKS AND FOUND NO DEFECTS COULD NOT DUPLICATE.  MFC/GOV RETURNED TO MFG FOR EVALUATION.  (K)	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007010900062	20070109	00062	NM  	2007	1	9	2006FA0001102    	1	20060904	G	5754	69738243	BOLT            			BOEING	737   	737322      	1384676	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					SLAT TRACK	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	354UA					24360				(REF NR: ATC0712) DURING AN A-CHECK INSPECTION OF RT WING LEADING EDGES.  THE OB TRACK ATTACHMENT BOLT ON THE NR 6 SLAT 	WAS FOUND TO BE LOOSE AND ALSO THE SPLIT PIN WAS MISSING.  A NON ROUTINE CARD, WO 3956/06 HAS BEEN RAISED TO FIT THE SPL	IT PIN AND RECTIFY THE DEFECT.  A CONFIDENCE CHECK HAS BEEN CARRIED OUT ACROSS ALL THE LEADING EDGE ATTACHMENTS FOR THE 	FLAP TRACKS.  IN ADDITION ALL FLYING CONTROLS AND TRAILING EDGE FLAPS HAVE BEEN INSPECTED FOR CORRECT LOCKING AND FITMEN	T.  NO OTHER LOCKING OR ASSY DEFECTS WERE FOUND.  (K)		2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2007010800004	20070108	00004		2007	1	8	2006FA0001104    	1	20061016	G	3242	50030967	BRAKE ASSY      																	LANDING GEAR	MISREPAIRED     	C			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21										SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT RETURN PINS WERE INSTALLED.  SHOULD BE PN 5001421, INST	ALLED WERE PN 9535044.  SWAGE ADJUSTER ASSEMBLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE.  THE SWAGES WERE SET AT	 A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE.  (K)																	 
2007010800007	20070108	00007		2007	1	8	2006FA0001105    	1	20061016	G	3242	50030967	BRAKE ASSY      																	LANDING GEAR	MISREPAIRED     	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21										SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT RETURN PINS WERE INSTALLED.  SHOULD BE PN 5001421, INST	ALLED WERE PN 9535044.  SWAGE ADJUSTER ASSEMLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE.  THE SWAGES WERE SET AT 	A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE.  (K)																	 
2007010800002	20070108	00002		2007	1	8	2006FA0001106    	1	20061016	G	3242	50030967	BRAKE ASSY      																	LANDING GEAR	MISREPAIRED     	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21										SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT RETURN PINS WERE INSTALLED.  SHOULD BE PN 5001421, INST	ALLED WERE PN 9535044.  SWAGE ADJUSTER ASSEMBLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE.  THE SWAGES WERE SET AT	 A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE.  (K)																	 
2007010800003	20070108	00003		2007	1	8	2006FA0001107    	1	20061016	G	3242	50030964	BRAKE ASSY      																	LANDING GEAR	MISREPAIRED     	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21										UPON CONDUCTING REPAIR TO REPLACE THE MISSING RETURN SPRING ASSEMBLY.  FOUND THAT THE SPACER TUBES (PN 5012941) WERE MIS	SING FROM THE REMAINING 3 RETURN SPRING ASSEMBLIES.  (K)																		 
2007010800001	20070108	00001		2007	1	8	2006FA0001109    	1	20061016	G	3242	50030967	BRAKE ASSY      																	LANDING GEAR	MISREPAIRED     	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21										SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT PRESSURE PLATE INSTALLED ON BRAKE ASSY.  SHOULD PN 5006	890, INSTALLED WAS PN 5005117.  PN 5006890 MEASURES .240 INCH THICK, PN 5005117 MEASURES .210 INCH THICK.  INCORRECT WEA	R PAD WAS INSTALLED ON PRESSURE PLATE.  SHOULD BE PN 5007328, INSTALLED WAS 5005119. YOU CAN TELL THE DIFFERENCE BECAUSE	 PN 5007328 DOES NOT HAVE A MILLED OUT AREA FOR STRUT CLEARANCE.  INCORRECT STATIONARY DISK INSTALLED ON BRAKE ASSY.  SH	OULD BE PN 5006892, INSTALLED WAS PN 9544028.  PN 5006892 MEASURES .240 INCH THICK, PN 9544028 MEASURES .210 INCH THICK.	  INCORRECT INSULATORS WERE INSTALLED IN PISTONS.  SHOULD BE PN 50068951.  (K)														 
2007011600070	20070116	00070	WP  	2007	1	16	2006FA0001110    	2	20060907	G	7250	30607881	BLADE           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					LPT3	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	800WW					258661	107869			THE INFLIGHT SHUTDOWN OCCURED ON SEPT 7, 2006, AFTER LEVELING OFF AT 30,000 FT THE CREW REPORTED A LOUD BANG FROM THE NR	 2 ENGINE.  THE CREW SECURED THE ENGINE, DIVERTED AND LANDED WITHOUT INCIDENT.  VISUAL INSPECTION OF THE AC REVEALED DIS	PLACED MATERIAL ON THE AIRCRAFT NACELLE, DUCTING.  ENGINE EXHAUST DUCT AND TURBINE SECTION IN THE FORM OF A UNCONTAINED 	MALFUNCTION.  THE ENGINE WAS RETURNED TO MFG FOR DISASSEMBLY AND INSPECTION.  DISASSEMBLY FINDINGS REVEALED MATERIAL LOS	S ON THE LPT3 WHEEL BLADES IN THE FORM OF MID SPAN BLADE FRACTURES.  (K)		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007010800283	20070108	00283	CE  	2007	1	8	2006FA0001111    	1	20061121	G	7810	227450	CLAMP           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					TAIL PIPE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01		1371 				1249				PN 2274-50 (ALSO PN NH1000897-50) CLAMP HOLDING TAILPIPE TO THE TURBO CRACKED LENGTHWISE ALONG THE CIRCUMFERENCE OF THE 	CLAMP.  TOTAL LENGTH OF THE CRACK IS 3 INCHES.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006112900198	20061129	00198	SO  	2006	11	29	2006FA0001112    	1	20061126	G	3213	7873803	AXLE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DMS       	EA  	LANDING GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	2525Y	14786				288516075				DURING A SCHEDULED 100 HOURS INSPECTION OF THE LANDING GEAR, THE MECHANIC FOUND A CRACK ON RT MAIN LANDING GEAR UPPER PA	RT. IT IS SUSPECTED THE FATIGUE OR STRESS CORROSION CRACKING COULD BE THE CAUSE. ANOTHER REASON WHY MOST OF RT MAIN LAND	ING GEAR WERE FOUND CRACKED IS PROBABLY THE DIFFERENCE OF STRUCTURAL STRENGTH BETWEEN RT AND LT WING. RT WING IS SLIGHTL	Y STRONGER THAN LT WING BECAUSE IT HAS A (WING WALK PANEL) WHICH DOES NOT ALLOW TRANSFER ALL THE LOADS OCCURRING ON LAND	INGS TO THE MAJOR MASS (ENGINE), THIS THEORY IS JUST A STRUCTURAL ANALYSIS BASE ON EXPERIENCE BUT IT NEED BE TESTED AND 	PROVED.	1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007011600077	20070116	00077	WP  	2007	1	16	2006FA0001118    	2	20061116	G	7200		ENGINE          								GARRTT	ATF3  	ATF36       	29002	WP  						FIRE            	D				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			WP	07							P21210C			ENGINE FIRE DURING MAINTENANCE GROUND RUN ON 10/2/2006, PERFORMED TO DETERMINE THE CAUSE OF FLUCTUATING OIL PRESSURE.  P	ROBABLE CAUSE OF FIRE FOUND TO BE MISSING ROLL PIN FROM ATOMIZER, FUEL, INTEGRAL FLOW DIVIDER. MISSING PIN PERMITTED ATO	MIZER SHROUD TO MOVE, DEFLECTING FUEL FLOW AWAY FROM COMBUSTION CHAMBER UPSTREAM IN THE ATOMIZER.  HOT GASSES FROM COMBU	STION CHAMBER WERE PERMITTED TO FLOW INTO THE CAVITY BETWEEN ATOMIZER AND ATOMIZER SHROUD CAUSING FUEL TO IGNITE IN THE 	ATOMIZER.  FIRE BURNED THROUGH FUEL ATOMIZER PILOT DIAMETER AND THROUGH THE COMBUSTOR CASE.  MISSING ROLL PIN LOCATION I	N THE ENGINE ASSY IS FULLY CAPTURED BY FUEL ATOMIZER SLEEVE PN 3002830-1. NO EVIDENCE OF THE MISSING WAS FOUND DURING DI						4	F			E7WE				 
2006120400001	20061204	00001		2006	12	4	2006FA0001119    	2	20061020	G	7414	6324	MAGNETO         																	ENGINE	FAILED          	B			PX2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07										MAGNETO IS DEAD.  (K)																			 
2006121200315	20061212	00315		2006	12	12	2006FA0001120    	1	20061110	G	8011	PM2401	STARTER         																	ENGINE	FAILED          	B			PX2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07		151  								STARTER SPINS, BENDIX DOES NOT ENGAGE RING GEAR.  (K)																			 
2006121200318	20061212	00318		2006	12	12	2006FA0001121    	1	20061110	G	8011	ES6462382	STARTER         																	ENGINE	MALFUNCTIONED   	B			PX2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07										STARTER WILL NOT DISENGAGE.  (K)																			 
2006121200316	20061212	00316		2006	12	12	2006FA0001122    	2	20061114	G	8530	EC636122ST	CYLINDER        																	ENGINE	MISMANUFACTURED 	B			PX2R	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CE	07										INSTALLED CYLINDER ASSEMBLE ON NEWLY OVERHAULED ENGINE.  DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RU	N.  REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED.  THERE IS NO RADIUS AT THE AREA WHE	RE THE O-RING SEAL IS TO SEAT.  THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE.  USED RADIUS GAUG	ES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER.  (K)																 
2006121200314	20061212	00314		2006	12	12	2006FA0001123    	2	20061114	G	8530	EC636122ST	CYLINDER        																	ENGINE	MISMANUFACTURED 	B			PX2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07										INSTALLED CYLINDER ASSEMBLY ON NEWLY OVERHAULED ENGINE.  DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RU	N.  REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED.  THERE IS NO RADIUS AT THE AREA WHE	RE THE O-RING SEAL IS TO SEAT.  THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE.  USED RADIUS GAUG	ES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER.  (K)																 
2006121200317	20061212	00317		2006	12	12	2006FA0001124    	2	20061114	G	8530	EC636122ST	CYLINDER        																	ENGINE	MISMANUFACTURED 	B			PX2R	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CE	07										INSTALLED CYLINDER ASSEMBLY ON NEWLY OVERHAULED ENGINE.  DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RU	N.  REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED.  THERE IS NO RADIUS AT THE AREA WHE	RE THE O-RING SEAL IS TO SEAT.  THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE.  USED RADIUS GAUG	ES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER.  (K)																 
2007010800141	20070108	00141	NM  	2007	1	8	2006FA0001125    	1	20061101	G	2100		CONTROL UNIT    			PIPER 	PA60  	PA60602P    	7106015	NM  										AUTOPILOT	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	64715					608365003				AC WAS ACQUIRED IN AN OVERHAULED CONDITION FROM AUTO PILOTS CENTRAL.  THIS UNIT WAS AN EXCHANGE UNIT WITH AN OVERHAUL DA	TE OF APPROX, JUNE 2004.  THE KI-256 WAS INSTALLED AND MARRIED TO THE EXISTING FACTORY INSTALLED AUTOPILOT SYS IAW INSTA	LLATION/ SYS MM.  AC WAS RETURNED TO SERVICE AFTER A SUCCESSFUL FLIGHT CHECK.  ALL AUTOPILOT/ FLIGHT DIRECTOR MODES WERE	 CHECKED.  SINCE THEN THIS FD/HORIZON HAS BEEN REMOVED AND RETURNED TO OVERHAULER NO LESS THAT 3 TIMES.  HORIZON HAS BEE	N RESPONSIBLE FOR AN ABRUPT AND ERRATIC PURPOSE.  THIS UNIT HAS ALWAYS FAILED IN AUTOPILOT PITCH MODE.  EACH TIME OVERHA	ULER FINDS A NEW PROBLEM IN PITCH CIRCUITS.  THESE PROBLEMS ARE RELATED TO THE AUTOPILOT IN THE PITCH AXIS, BUT EACH TIM	1	M	7	2 	3O			RT	A17WE   					 
2006112900216	20061129	00216	NE  	2006	11	29	2006FA0001126    	2	20061128	G	7314	378200	PUMP            								PWA   	JT8   	JT8D15A     	52051	NE  					FUEL SYSTEM	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99			5360 							UNIT RECEIVED ON 13 NOV 2006.  UNIT PROCESSED ON A REPAIR WORKSHOP IAW CUSTOMER REQUIREMENTS.  PUMP FAILED AS RECEIVED B	ENCH TEST FOR LOW FUEL FLOWS.  PUMP DISASSEMBLED IAW CMM REF 73-11-1 TO INVESTIGATE INCOMING TEST FINDINGS.  DISASSEMBLY	 OF FUEL PUMP REVEALED EXTENSIVE DAMAGE TO IMPELLER ASSY. PN 216916.  DAMAGE WAS CAUSED AS A RESULT OF QTY 2 NUTS ENTERI	NG FUEL PUMP FROM AN UNKNOWN EXTERIOR SOURCE.								4	F			E2EA				 
2006112900274	20061129	00274	CE  	2006	11	29	2006FA0001127    	1	20061127	G	5344	6511695204	HINGE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					UNKNOWN	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	1200N					0494				AT INSPECTION THE HINGE WAS FOUND CORRODED AND THE PINS WORN PAST LIMITS. A FACTORY NEW HINGE ASSY WAS ORDERED AND INSTA	LLED. UPON COMPLETION OF THE WORK THE AIRCRAFT WAS PRESSURIZED AND THE HINGE ASSY WAS FOUND TO BE LEAKING. UPON CLOSER I	NSPECTION THE SKIN THAT ATTACHES TO THE HINGE WAS NOT SEALED. MFG WAS CONTACTED WITH THE REQUEST TO PAY FOR THE SEALANT 	AND MAGNESIUM RIVETS. WE WERE INFORMED THAT MFG WILL NOT PAY FOR THESE PARTS UNLESS WE RETURNED THE HINGE ASSY. DUE TO T	HE AMOUNT OF TIME TO INSTALL AND FIT THIS HINGE WE DECLINED. MFG NEEDS TO INSPECT MORE CLOSELY THERE PARTS OR BE ABLE TO	 WORK BETTER WITH THEIR CUSTOMERS.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007011800019	20070118	00019	CE  	2007	1	18	2006FA0001128    	1	20061108	G	3020	10991004933	TUBE            			BEECH 	90    	C90         	1152913	CE  										DUCT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	39FB					LJ1165				THE LIP-ASSY IS CRACKED AROUND THE WELDS FOR THE INLET AND OUTLET TUBES.  REQUIRES REMOVAL OF INLET LIP ASSY AND REPAIR 	OF CRACKED WELDS.  (K)					1	L	7	2 	3T				3A20    					 
2007011600069	20070116	00069	EA  	2007	1	16	2006FA0001129    	2	20061114	G	8530	MS139973	KEEPER          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					EXHAUST VALVE	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	59987	1550 				317552081	L170168A			FOUND VALVE KEEPER BROKEN ON ROUTINE VALVE INSPECTION IAW SB 388C.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007011800077	20070118	00077	EA  	2007	1	18	2006FA0001130    	2	20061114	G	8530	72050	KEEPER          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					INTAKE VALVE	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	59987	1550 				317552081	L170168A			FOUND NR 6 CYLINDER VALVE KEEPER BROKEN ON ROUTINE VALVE INSPECTION IAW SB 388C.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007011600078	20070116	00078	CE  	2007	1	16	2006FA0001131    	1	20061030	G	2720	002524040	RUDDER PEDAL    			BEECH 	36    	A36         	1151604	CE  										RUDDER	LOOSE           	B			AKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	304E	1015 				E3433				UPON INVESTIGATING LOOSE RUDDER PEDALS, THE ASSEMBLY WAS DISASSEMBLED AND IT WAS NOTED THAT THE SHAFT HAD BEEN DOUBLE DR	ILLED WITH THE HOLES OVERLAPING.  THE AIRCRAFT WAS CERTIFICATED JANUARY 2002; THE AIRCRAFT NOW HAS 1015.4 HOURS, TIME IN	 SERVICE.  (K)				1	L	7	1 	3O				3A15    					 
2007010400022	20070104	00022	WP  	2007	1	4	2006FA0001132    	2	20061026	G	7200	TPE3316	ENGINE          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	RIGHT	FAILED          	D			GSTR	O				OTHER                   				T			ENGINE CASE PENETRATION   			IN	INSP/MAINT     	1			SW	13	93WT	4839 				BE80	P27168	CDA3823		DURING GROUND RUN FRO A POSSIBLE GENERATOR PROBLEM.  WITH THE ENGINE AT FLIGHT IDLE AND SPEED LEVERS FORWARDTHE RT ENGIN	E HAD A UNCONTAINED ENGINE FAILURE.  2 PIECES OF THE ENGINE PENETRATED THE RT FUSELAGE SKIN ADJACENT TO THE CO PILOT POS	ITION.  (K)				1	L	7	2 	4T	4	T		A14CE   	E4WE	6	C	P40EA	 
2007011800075	20070118	00075	CE  	2007	1	18	2006FA0001133    	1	20061114	G	3230	508100398	DRAG BRACE      			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG	MISMANUFACTURED 	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	14	690GT	268  				LJ1727				UPPER DRAG BRACE PN 50-8100398 RUBBED AGAINST THE LOWER DRAG BRACE PN 508100404 AT THE KNUCKLE.  THIS REMOVED ABOUT .062	5 OF AN INCH OF METAL ABOUT .0625 OF AN INCH LONG ON THE TOP SIDE OF BOTH ENDS OF THE KNUCKLE.  THE CAUSE IS IMPROPER MA	CHINING OF THE PART AT MANUFACTURE.  PARTS AFFECTED MUST BE REPLACED.  (K)				1	L	7	2 	3T	3	T		3A20    	E2NE				 
2007011600052	20070116	00052	EA  	2007	1	16	2006FA0001134    	2	20061120	G	7322		FLOAT           	FACET       		AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360*       	41514	EA  					CARBURETOR	DAMAGED         	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	45343	400  			75115812	AA5B1265				ENGINE IDLE AND LOW POWER PERFORMANCE WAS ERRATIC.  UPON ENGINE SHUTDOWN FUEL WAS NOTED DRIPPING FROM CARB/INDUCTION AIR	BOX.  CARB WAS DISASSEMBLED AND INSPECTED.  FOUND PLASTIC TO HAVE PARTIALLY BECOME UNBONDED FROM LOWER SECTION ALLOWING 	FUEL TO BEGIN LEAKING INTO ASSEMBLY.  AS THE FLOAT LOST ITS BOUYANCY IT COULD NO LONGER RESTRICT FUEL SOURCE.  POOR RUNN	ING ENGINE AND A FIRE HAZZARD WERE THE RESULTS.  RECOMMEND THE MFG PROCESS (BONDING) OF THE FLOAT BE IMPROVED.  IN THE M	EANTIME, ALL FLOATS MFG IN THE SAME BATCH SHOULD BE REMOVED FROM SERVICE.  (K)		1	L	7	1 	3O	3	O		A16EA   	E286				 
2007012500301	20070125	00301	NE  	2007	1	25	2006FA0001135    	1	20061006	G	6320	SB21511	BEARING         			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					M/R GEARBOX	CRACKED         	C			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	247AC	1085 			A6011	60452				(REF NR:MDR06-090)   MAIN GEARBOX PN 6435-20400065, SN A6-011 WAS REMOVED DUE TO FINDINGS OF FERROUS METAL IN THE OIL SC	REEN AND FILTER.  UPON DISASSEMBLY AND TEAR DOWN, THE SOURCE OF THE FERROUS METAL WAS DISCOVERED TO BE COMING FROM GHE S	ECOND STAGE INPUT ALIGNMENT BEARING PN SB 2151-1, SN EAC18170.  THE SB2151-1 BEARING CRACKED THROUGH THE ENTIRE INNER RA	CE AND CAUSED SUBSEQUENT CONTAMINATION OF THE MAIN GEARBOX, AND DAMAGE TO THE SECOND STAGE PINION PN 6435-20457-104, SN 	333 ALIGNMENT BEARING JOURNAL.  THE CRACKED INNER RACE WAS SENT TO THE MFG.  PROBABLE CAUSE: UNKNOWN.  (K)		2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2007011800076	20070118	00076	NE  	2007	1	18	2006FA0001136    	1	20061006	G	6520	SB21541	BEARING         			SKRSKY	S64   	S64F        	8142610	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					GEARBOX	CRACKED         	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	229AC	958  			EAC19192	64018				(REF NR MDR06-089)  THE IGB CHIP DETECTOR INDICATED A CHIP LIGHT.  IGB WAS REMOVED AND THE INNER RACE WAS FOUND TO BE CR	ACKED THROUGH AND SPALLED.  PROBABLE CAUSE: UNKNOWN. (K)					2	G	7	2 	4U	4	U		H6EA    	E15EA				 
2006121200399	20061212	00399	NE  	2006	12	12	2006FA0001137    	2	20061106	G	7250	597602	TURBINE BLADES  			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					NR 2 ENGINE	FRACTURED       	B			JYDR	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			NM	09	CFCRN	2946 				64061				(REF NR: MDR06-092)  VIBRATION FELT BY CREW, UPON LANDING, MAINTENANCE PERSONNEL FOUND METAL PARTICLES IN NR 2 ENGINE EX	HAUST.  UPON CLOSER EXAMINATION, A 2ND STAGE TURBINE BLADE WAS FOUND TO BE FRACTURED APPROXIMATELY 1 INCH FROM THE ROOT.	  THE FRACTURED PIECE BROKE OFF AND CAUSED SOME ADDITIONAL DAMAGE TO THE 2ND STAGE TURBINE BLADES AND EXTENSIVE DAMAGE T	O THE FREE TURBINE AS IT DEPARTED.  (K)			2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006121200400	20061212	00400	NM  	2006	12	12	2006FA0001138    	1	20061031	G	2750	65446321	HOUSING         			BOEING	737   	737*        	       	NM  										T/E FLAP	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		53778								(REF NR: 212286/ FXS)  HOUSING CRACKED INSIDE THE (P) PORT.  CYCLIC STRESS.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006121200268	20061212	00268	EU  	2006	12	12	2006FA0001139    	1	20061101	G	2497		WIRE            			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					ENGINE	CHAFED          	B			YLMR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	794TK					373				AIRCRAFT ARRIVED WITH INOPERATIVE STRATER-GENERATOR.  TROUBLESHOOTING REVEALED INOPERATIVE GENERATOR, FAILED GENERATOR C	ONTROL UNIT, AND FAILED CONTROL RELAY.  FURTHER TROUBLESHOOTING FOUND (A) AND (D) LEADS TO STARTER-GENERATOR AT ENGINE W	IRING WAS BRITTLE AND HAD BARE SPOT CHAFFED TO ENGINE INLET MOUNTING STRUT.  THIS ISSUE SHOULD BE CONSIDERED FOR ALL GEN	ERAL AVIATION AIRCRAFT, NOT JUST THIS MFG.  WE HAVE NOTED CONDITION ON SEVERAL AIRCRAFT.  THIS IS THE FIRST INCIDENT, HO	WEVER, THAT HAD CHAFFING AND A CIRCUIT SHORT.  RECOMMEND INSPECTION AT NEXT ACCESS FOR ALL GENERAL AVIATION TURBOJET AIR	CRAFT AS THIS WIRING IS LOCATED IN EXTREME ENVIRONMENTAL CONDITIONS, WITHIN THE ENGINE COWLING.  (K)	2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007011800094	20070118	00094	CE  	2007	1	18	2006FA0001140    	1	20061107	G	2612	24412886	FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RT ENGINE	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	534M					UE333	PCEPS0246	HJ1616		ON 10/4/2006, AFTER DEPARTING, APPROXIMATELY 30 MINUTES INTO THE FIRST LEG OF THE DAYS TRIP, THE PILOT REPORTED GETTING 	A RT ENGINE FIRE INDICATION.  FOLLOWING PROCEDURE, THE PILOT PULLED THE T-HANDLE AND BLEW THE FIRE BOTTLE, SHUTTING DOWN	 THE ENGINE.  THE PILOT DIVERTED TO AIRPORT AND LANDED SAFELY.  THE PILOT STATED THAT HE HAD NOT NOTICED ANY UNUSUAL REA	DINGS FROM ANY OF THE GAUGES.  A MAINTENANCE CREW WAS SENT TO INVESTIGATE AND FOUND THAT THERE WERE APPROXIMATELY 3 QUAR	TS OF OIL LEFT IN THE ENGINE.  IT WAS DECIDED TO PULL THE ENGINE AND SEND IT FOR TESTING.  IT WAS ASSUMED THAT AN OIL SE	AL HAD MALFUNCTIONED AND THE SUBSEQUENT OIL LOSS CAUSED THE ENGINE TO OVERHEAT AND ACTIVATE THE ENGINE FIRE DETECTION LO	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007011800037	20070118	00037	SO  	2007	1	18	2006FA0001141    	1	20061120	G	2140	3716725	LINE            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O520  	TSIO520E    	17040	SO  					CABIN HEATER	LEAKING         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4566Q					347770241				PILOT REPORTED FUEL SMELL IN THE CABIN WHEN CABIN HEATER IS ON.  FURTHER INVESTIGATION REVEALED A PIN HOLE CAUSED BY COR	ROSION IN THE CABIN HEATER FUEL LINE JUST AFT OF THE AFT SPAR CARRY THRU.  (K)					1	L	7	2 	3O	3	O		A7SO    	E8CE				 
2007011800038	20070118	00038	CE  	2007	1	18	2006FA0001142    	1	20061115	G	2731	NAS302665170	CONTROL CABLE   			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELEVATOR TRIM	KINKED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	400BX					LJ686				INVESTIGATED ELEVATOR TRIM OPERATIONS COMPLAINT.  FOUND FORWARD ELEVATOR TRIM CABLE, PN NAS302-66-5170, LOOSE AND OFF PU	LLEYS UNDER LT CABIN FLOOR AREA.  CABLE ASSY DAMAGED BY KINKING AND FRAYING FROM CONTACT WITH PULLEY SUPPORTS AND ADJACE	NT STRUCTURE.  ALSO FOUND PN 4000524-8508 ELEVATOR TRIM SERVO DAMAGED AND OPERATIONS ERRATIC.  MAINTENANCE RECORDS NOT M	ADE AVAILABLE, UNABLE TO DETERMINE PREVIOUS MAINTENANCE HISTORY FOR ELEVATOR TRIM SYSTEM.  HAVE NOTED SIMILAR DAMAGE IN 	OTHER SERIES AIRCRAFT.  USUALLY CAUSED BY CABLE MISROUTING OR LOW CABLE TENSION FOR AN EXTENDED PERIOD OF OPERATIONS.  (	K)	1	L	7	2 	3T	3	T		3A20    	E2NE				 
2007011600064	20070116	00064	CE  	2007	1	16	2006FA0001143    	1	20061109	G	3260	1CH25	DOWNLOCK SWITCH 			BEECH 	300   	300BEECH    	1152930	CE  										MLG	INOPERATIVE     	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	8YN					FL417				INVESTIGATED RED WARNING LIGHT ILLUMINATED IN LANDING GEAR CONTROL HANDLE WITH LANDING GEAR DOWN AND LOCKED.  FOUND NLG 	DOWNLOCK SWITCH.  S508 INOPERATIVE PN 101-3646289, MICROSWITCH-FREEPORT PN 1CH25.  REPLACED SWITCH AND ADJUSTED IAW MM. 	 LANDING GEAR POSITION/WARNING SYSTEM FUNCTIONAL TESTS NORMAL.  (K)				2	L	7	2 	4T				A24CE   					 
2007011600065	20070116	00065	SO  	2007	1	16	2006FA0001144    	1	20061110	G	7820		MUFFLER         			MAULE 	M7235 	M7235C      	5460110	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	CRACKED         	B			FTUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	65	55105	165  				25104C	L3069248A	DY6641B		AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION.  UPON VISUAL INSPECTION FOUND A CRACK ADJACENT TO THE WELD ON THE	 GUSSET/DOUBLER LOCATED ON THE LOWER PORTION OF THE MUFFLER AT THE EXHAUST OUTLET.  THE MUFFLER WAS PRESSURIZED AND VERI	FIED THAT THE CRACK HAD EXTENDED INTO THE CAN.  MOST LIKELY CAUSED BY THE NORMAL FLEX AND ROTATION OF ENGINE OPERTATIONS	.  COUPLED WITH THE METHOD OF ATTACHMENT OF THE EXHAUST PIPE.  (K)			1	H	7	1 	3O	3	O	NC	3A23    	1E4	5	C	P25EA	 
2007010900044	20070109	00044	SO  	2007	1	9	2006FA0001145    	1	20061101	G	3213	30A04000091	DRAG LINK       			MAULE 	M7235 	M7235C      	5460110	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	RT MLG	MISINSTALLED    	B			FTUR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	65	55105					25104C	L3069248A	DY6641B		AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER INSTALLATION.  ON INSPECTION FOUND MAIN GEAR DRAG LINK HAD NOT BEEN PROPERLY SEA	LED AT THE LOWER END ALLOWING WATER TO ENTER THE ASSEMBLY.  BECAUSE OF THE SEALANT WE ARE UNABLE TO TELL IF THE INSIDE O	F THE TUBE HAS SOME SORT OF CORROSION PROTECTION.  MAY WANT TO CONSIDER DOING AWAY WITH THE SEALANT AND APPLYING A CORRO	SION PREVENTATIVE COMPOUND COUPLED WITH RECURRENT INSPECTION AND REAPPLICATION OF CPC.  (K)			1	H	7	1 	3O	3	O	NC	3A23    	1E4	5	C	P25EA	 
2007011600075	20070116	00075	SO  	2007	1	16	2006FA0001146    	1	20061101	G	2810	2117X16	FUEL TANK       			MAULE 	M7235 	M7235C      	5460110	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	RT WING	LEAKING         	B			FTUR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	65	55105	1655 				25104C	L3069248A	DY6641B		AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION, THE OWNER OPERATOR REPORTED FUEL STAINING ON THE RT WING, ON INSP	ECTION THE FUEL TANK WAS FOUND TO BE LEAKING.  THE TANK WAS REMOVED AND UPON CLOSER INSPECTION 2 PIN HOLES WERE FOUND IN	 THE WELD SEAM, ONE BEING A LIGHT SEEP, THE OTHER LARGE ENOUGH TO PRODUCE A VISIBLE STAIN.  RECOMMEND THAT ALL FUEL TANK	S BE PRESSURIZED AND LEAK CHECKED , AND THAT AN INSPECTOR PLACE THEIR (STAMP) INDICATING COMPLIANCE.  (K)			1	H	7	1 	3O	3	O	NC	3A23    	1E4	5	C	P25EA	 
2007011800126	20070118	00126	CE  	2007	1	18	2006FA0001147    	1	20061112	G	2797		WIRE            			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE7313     	01518	WP  					PITCH SERVO	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	550AK					045				AIRCRAFT ABORTED TAKEOFF DUE TO BOTH STALL WARNINGS ILLUMINATED ON DEPARTURE ROLL.  C/B LEFT AND RIGHT STALL C/B POPPED.	  AUTOPILOT, FLIGHT DIRECTOR AND PRIMARY YAW DAMPER INOPERATIVE.  (K)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007011800127	20070118	00127	CE  	2007	1	18	2006FA0001148    	1	20061030	G	2510	551900921	SEAT FRAME      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	550RB					5500117				UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  CHAI	R WAS REPAIRED IAW STCC ST01042W STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007011800128	20070118	00128	SO  	2007	1	18	2006FA0001149    	1	20061101	G	2910	21A09000204	HOSE            			MAULE 	M7235 	M7235C      	5460110	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	HYD SYSTEM	MISMANUFACTURED 	B			FTUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	65	55105	86   				25104C	L3069248A	DY6641B		AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION.  ON INSPECTION HYDRAULIC FLUID WAS FOUND TO BE COMING FROM THE FO	RWARD FUSELAGE DRAIN.  UPON REMOVAL OF THE FLOOR THE INSULATION WAS FOUND TO BE SATURATED WITH HYDRAULIC FLUID.  THE SYS	TEM WAS REFILED AND TROUBLESHOT, THE LEAK WAS TRACKED TO A HOSE.  INSPECTION OF THE HOSE REVEALED THAT THE HOSE END WASN	`T PROPERLY INSTALLED RESULTING IN THE FLUID LEAK.  THIS WAS A RESULT OF IMPROPPER ASSEMBLY OF THE HOSE BY MFG AND SHOUL	D HAVE BEEN CAUGHT DURING PRESSURE TESTING AFTER INITIAL ASSY.  (K)		1	H	7	1 	3O	3	O	NC	3A23    	1E4	5	C	P25EA	 
2006121200320	20061212	00320	CE  	2006	12	12	2006FA0001150    	1	20061017	G	3230	998100227	LOCK PLATE      	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	MISINSTALLED    	D			PFBV	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	27	528WG					BB151				DURING POST ACCIDENT INSPECTION OF RT AND LT MAIN LANDING GEAR DRAG LEGS, LOCK PLATES WERE FOUND MOUNTED WITH THE BEVEL 	AT THE NOSE OF THE PLATE FACING UP.  INSPECTION OF 5 OTHER AC FOUND THE BEVEL FACING DOWN.  REVIEW OF CURRENT REPS COMPO	NENT MM IS INCONCLUSIVE.  (K)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006120800182	20061208	00182	CE  	2006	12	8	2006FA0001151    	1	20061207	G	5314	60410025601	KEEL            			BEECH 	60    	B60         	1153605	CE  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3876C	3004 				P513				DURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT S	TATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES.  REMOVAL OF THE STIF	FENER ALLOWED FURTHER INSPECTION OF THE KEEL PART NUMBER 60-410025-601, WHICH REVEALED CRACKS IN THE WEB WHICH WERE PREV	IOUSLY OBSCURED BY THE INSTALLED STIFFENER.  THE MIRROR IMAGE STIFFENER PART NUMBER 60-410025-49 ON THE LEFT SIDE OF THE	 AIRCRAFT REVEALED SIMILAR CRACKS WITH NO DAMAGE TO THE KEEL.		1	L	7	2 	3O				A12CE   					 
2006121200299	20061212	00299	WP  	2006	12	12	2006FA0001152    	2	20061108	G	7230	30721631	DAMPER          			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					NR 1 ENGINE	BROKEN          	B			UO2R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	19	573RL					153	P74494			AIRCRAFT ARRIVED 10/31/2006 TO TROUBLESHOOT A RUMBLE FROM THE NR 1 ENGINE.  UPON INVESTIGATION, FOUND 1 FAN BLADE TO HAV	E A BROKEN MIDSPAN DAMPER. (K)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006120800183	20061208	00183	CE  	2006	12	8	2006FA0001153    	1	20061207	G	5314	6041002551	STIFFENER       			BEECH 	60    	B60         	1153605	CE  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3876C	3004 				P513				DURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT S	TATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES.  REMOVAL OF THE STIF	FENER ALLOWED FURTHER INSPECTION OF THE KEEL PART NUMBER 60-410025-601, WHICH REVEALED CRACKS IN THE WEB WHICH WERE PREV	IOUSLY OBSCURED BY THE INSTALLED STIFFENER.  THE MIRROR IMAGE STIFFENER PART NUMBER 60-410025-49 ON THE LEFT SIDE OF THE	 AIRCRAFT REVEALED SIMILAR CRACKS WITH NO DAMAGE TO THE KEEL.		1	L	7	2 	3O				A12CE   					 
2006121200313	20061212	00313	NE  	2006	12	12	2006FA0001154    	2	20061113	G	7250	RB211524G19	DISC            								RROYCE	RB211 	RB211524G19 	 	NE  					ENGINE	WORN            	B			QEMY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35		57350	7399 				13048			(REF NR: MDR/004/06) STRIP EXAMINATION REVEALED HEAVY RUBS TO THE LP1 TURBINE DISC AND TO THE LP1 AND LP2 TURBINE BLADES	.  INITIAL EXAMINATION HAS FAILED TO IDENTIFY THE CAUSE OF THE BLADE AND DISC CONTACT ALL SETTINGS APPEARING NORMAL  A R	EVIEW OF SERVICE OPERATION HAS FAILED TO IDENTIFY ANY INCREASE IN VIBRATION IN SERVICE.  (K)									4	F			E30NE				 
2006121200304	20061212	00304	WP  	2006	12	12	2006FA0001155    	1	20061009	G	5311		FRAME           			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB21122*    	54555	NE  					FUSELAGE	CRACKED         	B			RJAY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	753DA					193W1189				(REF NR: 06DA063)  DURING C-CHECK, MAINTENANCE TASK 53-02-1000 INSP FS 983 FRAME.  A CRACK, 3 INCHES) FOUND AT LT, BY A 	CLOSE VISUAL INSP AND CONFIRMED BY NDT.  NRC NR 546 RAISED FOR CORRECTIVE ACTION.  (K)					2	L	7	3 	4F	4	F		A23WE   	A12EU				 
2006121200273	20061212	00273	CE  	2006	12	12	2006FA0001156    	1	20061117	G	2750		FITTING         			BEECH 	65    	A65         	1152803	CE  										T/E FLAP	SHEARED         	B			YCYR	O				OTHER                   				F			FLT CONT AFFECTED         			UK	UNKNOWN        	1			SO	19	V2LDO					LC291				(REF NR: MOR NR OCC442)  OPERATED FLIGHT NR 101, VFR CONDITIONS, FLIGHT AND APPROACH LANDING WAS NORMAL.  AFTER LANDING,	 ROLLOUT FLAPS WERE RETRACTED.  WHEN EXITING THE AC IT WAS NOTICED THAT THE INNER FLAP ON THE PORT SIDE WAS STILL DOWN. 	 THE FLAP WAS MANUALLY RESET TO ZERO, AND THE AIRCRAFT WAS FLOWN BACT TO DEPARTURE AIRPORT.  A FLAPLESS LANDING WAS CARR	IED OUT.  MAINTENANCE FOUND THAT THE LT IB FLAP DRIVE ASSY HAD FAILED.  THE 2 LUGS THAT TRANSFER CABLE MOVEMENT 90 DEGRE	ES INTO ACTUATOR MOVEMENT HAD SHEARED.  THE LT IB FLAP COULD BE DEPLOYED FROM THE (UP) TO THE (DOWN) POSITION, BUT HAD T	O BE RESET TO THE (UP) POSITION MANUALLY.  THE LT OB, RT IB AND OUB FLAP DRIVE ASSY`S, FLAP GEAR BOX AND DRIVE  ASSY, PN	1	L	7	2 	3O				3A20    					 
2006121200295	20061212	00295	EU  	2006	12	12	2006FA0001157    	1	20060524	G	2822	SC402	PUMP            			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305       	 	NE  					FUEL SYSTEM	FAILED          	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	46WC		247  			259028				THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PART NUMBER, ORDERED FROM THE SAME VENDER HAVE FAILED AFTER SHORT T	IME ON SAME AIRCRAFT USED ON LT AND RT SIDES. 1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247	 HOURS.  2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS.  3) FUEL BOOST PUMP OVERHAULE	D CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS.  (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2006121200293	20061212	00293	EU  	2006	12	12	2006FA0001158    	1	20060511	G	2822	SC402	PUMP            			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305       	 	NE  					FUEL SYSTEM	FAILED          	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	46WC	232  								THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PN, ORDERED FROM SAME VENDOR HAVE FAILED AFTER SHORT TIME ON SAME A	IRCRAFT USED ON LT AND RT SIDES.  1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS.  2) 	FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS.  3) FUEL BOOST PUMP OVERHAULED CONDITION 	SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS.  (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2006121200301	20061212	00301	EU  	2006	12	12	2006FA0001159    	1	20061117	G	2822	SC402	PUMP            			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305       	 	NE  					FUEL SYSTEM	FAILED          	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	46WC					259028				THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PN, ORDERED FROM THE SAME VENDOR HAVE FAILED AFTER SHORT TIME ON SA	ME AIRCRAFT USED ON LT AND RT SIDES.  1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS. 	 2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS.  3) FUEL BOOST PUMP OVERHAULED CONDIT	ION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS.  (K)			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2006121300061	20061213	00061	WP  	2006	12	13	2006FA0001160    	1	20061104	G	6210		HOUSING         	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	424SH	1353 			1989C	10877				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010400074	20070104	00074	WP  	2007	1	4	2006FA0001161    	1	20061109	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					MAIN ROTOR BLADE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	424SH	1353 			1989C	10877				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010900045	20070109	00045	CE  	2007	1	9	2006FA0001163    	1	20060823	G	5260	12115041	CABLE           			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					PAX DOOR STEP	BROKEN          	H				O				OTHER                   				S			AFFECT SYSTEMS            			LD	LANDING        	1			WP	17	6169N	1000 				21062940				THE PILOT EXTENDED THE LANDING GEAR PRIOR TO LANDING, AND THE NOSEGEAR WOULD NOT EXTEND INTO THE DOWN-AND-LOCKED POSITIO	N (THE MAINS LOCKED).  DURING LANDING, THE NOSEGEAR COLLAPSED.  POST INCIDENT INSPECTION SHOWED THAT THE PASSENGER STEP 	CABLE BROKE AT THE FORWARD PULLEY AND INTERTWINED WITH THE NOSE GEAR LINKAGE, NOT ALLOWING IT TO LOCK.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007010400075	20070104	00075	WP  	2007	1	4	2006FA0001164    	1	20061204	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					MAIN ROTOR BLADE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	424SH	1408 			1989C	10877				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010800174	20070108	00174	WP  	2007	1	8	2006FA0001165    	1	20061203	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	424SH	1353 			1989C	10877				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010800176	20070108	00176	WP  	2007	1	8	2006FA0001166    	1	20061104	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	424SH	1353 			1989C	10877				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010800179	20070108	00179	WP  	2007	1	8	2006FA0001167    	1	20061204	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					M/R BLADE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	424SH	1408 			1905C	10877				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010800183	20070108	00183	WP  	2007	1	8	2006FA0001168    	1	20061204	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	511CC	54   			3424	10173				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010800184	20070108	00184	WP  	2007	1	8	2006FA0001169    	1	20061204	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	511CC	54   			3425	10173				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007010800190	20070108	00190	WP  	2007	1	8	2006FA0001170    	1	20061117	G	5340	269A5472	BRACKET         	HUGHES      		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360C1A   	41514	EA  					FUSELAGE	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	11047	2701 	29   			211031	L2209751A			ONE OF THE BELT DRIVE CLUTCH ACTUATION SYSTEM CABLE PULLEY BRACKETS (1 OF 2 P/N 269A5472) BROKE CLEAN ACROSS BETWEEN THE	 PULLEY AND ITS FRAME MOUNT HOLES DURING THE PROCESS OF ENGAGING THE ROTOR SYSTEM. DURING THE SUBSEQUENT ATTEMPTED TAKEO	FF THE OPERATOR NOTED THAT ROTOR RPM WOULD BLEED OFF RAPIDLY DUE TO DRIVE BELT SLIPPAGE WHEN THE COLLECTIVE CONTROL WAS 	RAISED. THE OPERATOR ABORTED THE TAKEOFF ATTEMPT, SHUTDOWN THE AIRCRAFT, AND INVESTIGATED THE PROBLEM THEN NOTIFIED REPA	IR PERSONNEL. THE BRACKET AND THE PULLEY (P/N MS20219-4) WERE THE ONLY PARTS DAMAGED IN THIS ASSEMBLY AS A RESULT OF THI	S FAILURE.	1	G	7	1 	3O	3	O		4H12    	1E10				 
2007010900030	20070109	00030	WP  	2007	1	9	2006FA0001171    	1	20061204	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540*       	41532	EA  					M/R BLADE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	7133E	408  			5068A	0573				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2007010900031	20070109	00031	WP  	2007	1	9	2006FA0001172    	1	20061204	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540*       	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	7133E	408  			5073A	0573				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2007010900052	20070109	00052	WP  	2007	1	9	2006FA0001173    	1	20061203	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1A5    	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	69KA	191  			4272A	1182				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2007010900053	20070109	00053	WP  	2007	1	9	2006FA0001174    	1	20061203	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1A5    	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	69KA	191  			4268A	1182				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2007010900054	20070109	00054	WP  	2007	1	9	2006FA0001175    	1	20061203	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1A5    	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	69KA	191  			4268A	1182				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2007020500053	20070205	00053	WP  	2007	2	5	2006FA0001176    	1	20061203	G	6210	C1561	BOOT            	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1A5    	41532	EA  					M/R BLADE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	05	69KA	191  			4268A	1182				FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2007010400062	20070104	00062	SO  	2007	1	4	2006FA0001177    	1	20061130	G	5711		STRUT           			PIPER 	J3    	J3          	7100502	SO  										RIGHT WING	CORRODED        	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	05										RT STRUT WAS DAMAGED FROM LOWERING A BI-FOLD HANGER DOOR ON THE WING TIP.  THE STRUT WAS MANUALLY SEPARATED WERE EXTENSI	VE CORROSION WAS FOUND INSIDE THE WING STRUT.  THE PLANE HAS SET IDLE FOR 3 YEARS OUT OF ANNUAL INSPECTION. THE LAST ANN	UAL INSPECTION PERFORMED INCLUDED COMPLYING WITH AD 99-01-05 WITH NO DISCREPANCIES NOTED.				1	H	7	1 	3O				ATC660  					 
2007010800142	20070108	00142	CE  	2007	1	8	2006FA0001178    	1	20061212	G	8120	227450	CLAMP           			CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					TURBOCHARGER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		1366 								DURING PROGRESSIVE INSPECTION FOUND LT ENGINE TURBOCHARGER TO TAILPIPE CLAMP CRACKED ALONG CIRCUMFERENCE, APPROX. 4 INCH	 CRACK.  FOUND SAME PN CLAMP ON THE RT ENGINE OF THIS AIRCRAFT TO BE CRACKED 7 HOURS PREVIOUSLY.  					1	L	7	2 	3O	3	O	RT	A7CE    	E7CE				 
2007010800173	20070108	00173	EA  	2007	1	8	2006FA0001179    	2	20061205	G	8530		CONNECTING ROD  			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	FAILED          	C				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			GL	27	2148N	1965 				32R7985069	1892548A			INTERNAL ENGINE FAILURE, CYLINDERS 2 AND 4 CONNECTING RODS FAILED. ENGINE WAS ORIGINAL TO THE AIRCRAFT (1979).						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2007010800305	20070108	00305	NM  	2007	1	8	2006FA0001180    	1	20061207	G	7900	30C208301	TRANSDUCER      			AMD   	FALC50	FALCON2000  	2730170	NM  	PWA   	306   	PW306B      	 	NE  					RT ENGINE OIL	FALSE INDICATION	C				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	07						028	CF0088			RT ENGINE OIL TRANSDUCER FAILURE WHICH GAVE FALSE ENGINE OIL INDICATION WHICH CAUSED BY AIRCRAFT OPERATIONS MANUAL CHECK	 LIST ENGINE SHUTDOWN AND SINGLE ENGINE LANDING.					2	K	7	2 	4F	4	F	RT	A50NM   	E35NE				 
2007010800314	20070108	00314	NM  	2007	1	8	2006FA0001181    	1	20061212	G	8011	3617712	HOUSING         			DOUG  	MD80  	MD83        	3023681	NM  										STARTER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05										STARTER HOUSING FOUND CRACKED DURING DYE PENETRANT INSPECTION.						2	L	7	2 	4F			RT	        					 
2007010800318	20070108	00318	GL  	2007	1	8	2006FA0001182    	3	20061213	G	6114		HUB             			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170*      	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	2112K	1839 				287990234	L2600423A	RK022		DURING ANNUAL INSPECTION FOUND CRACK EXTENDING THROUGH THE HUB AT ONE OF THE MOUNTING BOLT HOLES.  CRACK GOES COMPLETLEY	 THROUGH THE HUB TO THE INNER BORE OF THE HUB. NO HISTORY OF PROP STIKE OR ANY OTHER VISUAL DAMAGE TO THE PROPELLER. THI	S PROPELLER INSTALLED WITH STC NR SA779NE. PROPELLER REMOVED FROM AIRCRAFT AND SENT FOR FURTHER STUDY IAW MFG REQUEST.				1	L	7	1 	3O	3	O		2A13    	E286	5	N	P857	 
2007010800327	20070108	00327	EU  	2007	1	8	2006FA0001183    	1	20061208	G	2510	76201113	BRACKET         			EXTRA 	EA300 	EA300       	70218DI	EU  	LYC   	O540  	AEIO540*    		EA  					SEAT BACKREST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	497AF	1600 	44   			072				DURING A ROUTINE INSPECTION IT WAS NOTICED THE 76201.113 TOUNGE BRACKETS LT AND RT WHICH ATTACH THE REAR SEAT BACKREST T	O THE LOWER SEAT ASSEMBLY WERE CRACKED THRU THE BOLT HOLES ATTACHING TO THE BACKREST. FURTHER CLOSE EXAMINATION (REMOVED	 UPHOLSTERY)OF THE REMOVED BACKREST ASSEMBLY REVEALED THE SEAT BACK WAS SIGNIFICANTLY CRACKED IN THE AREA OF THE UPPER B	ACKREST WHERE THE SEAT BACKREST ANGLE CAN BE ADJUSTED.  RECOMMEND CLOSER INSPECTION OF THE AFFECTED PARTS BE ADDED TO TH	E 100HR AND 1000HR INSPECTION CHECKLISTS.		1	M	7	1 	3O	3	O	NC	A67EU   	1E4				 
2007010800343	20070108	00343	NE  	2007	1	8	2006FA0001184    	2	20061129	G	7323		SPRING          	WOODWARD    							GE    	CF6   	CF650*      	30018	NE  					GOVERNOR	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99					WYG13493					COMPRESSOR DISCHARGE PRESSURE RESTORING SPRING P/N 3018-248 HAS FRACTURED CLOSE TO THE SPRING SEAT 9.											4	F			E23EA				 
2007010800346	20070108	00346	NE  	2007	1	8	2006FA0001185    	2	20061129	G	7323		SPRING          	WOODWARD    							GE    	CF6   	CF650*      	30018	NE  					GOVERNOR	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99					WYG13493					COMPRESSOR DISCHARGE PRESSURE RESTORING SPRING P/N 3018-248 HAS FRACTURED CLOSE TO THE SPRING SEAT 9.											4	F			E23EA				 
2007010900046	20070109	00046	SO  	2007	1	9	2006FA0001186    	1	20061213	G	2150		TURBINE WHEEL   			GULSTM	G1159 	GIV         	3980115	SO  										ACM	SEIZED          	C				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			LD	LANDING        	1			WP	23	596CW	4541 				1145				AIR CYCLE MACHINE TURBINE WHEEL HAS SEIZED CAUSING INOPERATIVE AIR CONDITIONING SYSTEM.						2	L	7	2 	4F			RT	A12EA   					 
2007010900051	20070109	00051	EU  	2007	1	9	2006FA0001188    	1	20061202	G	5530		RIVET           			SOCATA	TB9   	TB9         	8680694	EU  	CONT  	C125  	C125*       	17011	SO  					VERTICAL STAB	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	557J					1326				DURING THE PRE-FLIGHT INSPECTION FOR A LOCAL TRAINING FLIGHT, THE BLIND RIVETS LOCATED HALFWAY UP VERTICAL FIN WERE FOUN	D TO BE MAKING ALUMINUM OXIDE (DIRT TRAILS) ON BOTH SIDES OF THE VERTICAL FIN.  THIS CONDITION IS INDICATIVE OF A POTENT	IALLY LOOSE RIVET OR CRACKED INNER RIB.  MFG SB 10-083 REQUIRES THIS TYPE OF RIVET (CHERRY-MAX) AT THIS LOCATION.  SUSPE	CT OTHER AIRCRAFT HAVE SAME ISSUE.			1	L	7	1 	3O	3	O	NT	AS1EU   	E236				 
2007010900057	20070109	00057	GL  	2007	1	9	2006FA0001189    	1	20061212	G	7921	P010904	OIL COOLER      			AMTR  	AMD   	ALARUSCH2T  	0033001	GL  	LYC   	O235  	O235*       	41505	EA  						LEAKING         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			GL	13	216LF	60   				201034				OWNER REPORTED THAT AFTER FLYING AIRCRAFT, THERE APPEARED TO BE OIL LEAKING FROM UNDER COWLING.  OIL LEVEL WAS CHECKED A	ND FOUND TO BE DOWN TO ONLY 3 QUARTS LT.  AFTER REMOVAL OF COWLING AND INSPECTION, IT WAS FOUND THAT MOST OF THE OIL LEA	KAGE APPEARED TO BE AROUND THE OIL COOLER. OIL COOLER LINES WERE DISCONNECTED AND OIL COOLER WAS PRESSURIZED WITH ABOUT 	30 PSI OF AIR PRESSURE.  A SMALL HOLE WAS FOUND IN THE UPPER RT EDGE OF OIL COOLER AT A WELD SEAM.  THIS AIRCRAFT HAS ON	LY ABOUT 60 HOURS TOTAL TIME SINCE NEW.  AN ANNUAL INSPECTION ABOUT 2 HOURS AGO DID NOT REVEAL ANY OIL LEAKAGE.  IT APPE	ARS THAT THE CAUSE WAS A DEFECTIVE WELD IN THE MANUFACTURING OF THE OIL COOLER.	1	L	7	1 	  	3	O		EXPA1L71	E223				 
2007010900058	20070109	00058	EU  	2007	1	9	2006FA0001190    	1	20061202	G	5751		RIB             			SPHRTH	CIRRUS	CIRRUS      	38019VC	EU  										AILERON	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	5557	8255 				37				DURING PRE-FLIGHT INSPECTION FOR TRAINING FLIGHT, IDENTIFIED CRACKS ON OUTER RIB CAPS ON BOTH AILERONS.  CRACKS APPEAR T	O BE ORIGINATING AT THE ATTACHMENT RIVETS LOCATED AT THE EDGE OF THE AILERONS.					1	K	0	0 	  				G19EU   					 
2007010900049	20070109	00049	SO  	2007	1	9	2006FA0001192    	2	20061213	G	8530	TISN712BCA221	CYLINDER        			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	4155A	652  				340A1001	509812			COMPLIANCE WITH ENGINE COMPONENTS, INC. MANDATORY SB06-2 DISCLOSED CRACKED CYLINDER IN RT ENGINE WITH OBVIOUS LEAKAGE.						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P25EA	 
2007010800192	20070108	00192	CE  	2007	1	8	2006FA0001193    	1	20061218	G	2140	70893	PUMP            	JANITROL    	B4500       	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					HEATER	BURNED OUT      	B				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	25	870JA	1935 				TH2036				SMOKE IN THE COCKPIT, AND ELECTRICAL BURNING SMELL WERE OBSERVED AFTER TAKEOFF, AFTER THE GEAR WAS RETRACTED. THE HEATER	 HAD BEEN IN OPERATION APPROXIMATELY 30 MINUTES BEFORE TAKEOFF, WITH NO SMOKE OR SMELL OBSERVED.  THE HEATER WAS TURNED 	OFF, AND THE SMOKE DISSIPATED. THE AIRCRAFT RETURNED TO LAND.  THE HEATER FUEL PUMP, LOCATED IN THE NOSE GEAR WELL, WAS 	FOUND TO BE CHARRED.  WHEN THE GEAR IS RETRACTED AND THE GEAR DOORS ARE CLOSED, THERE WOULD BE DIFFERENT AIR-FLOW IN THE	 GEARWELL, POSSIBLY CAUSING A HIGHER PRESSURE IN THE GEARWELL AND FORCING AIR INTO THE CABIN, PAST THE BOOTS FOR THE NOS	E GEAR RETRACT ROD AND STEERING LINKAGES.  THIS IS AT LEAST THE THIRD OCCURRENCE OF A BURNED PUMP IN A FLEET OF 11 LIKE 	1	L	7	2 	3O	3	O		3A16    	E3SO				 
2007011800123	20070118	00123	NE  	2007	1	18	2006FA0001195    	1	20061128	G	6220	641026000042	DAMPER          			SKRSKY	S64   	S64E        	8142604	NE  											BROKEN          	B			JYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CGESG					64065				(REF: MDR06-093) DAMPER WAS REMOVED FROM THE AIRCRAFT DUE TO, THE PISTON PN 6410-26005-104, SN 550 FOUND BROKEN AFTER SH	UTDOWN OF HELICOPTER.  THE PISTON ROD BROKE NEAR THE FORK ASSEMBLY, PN 6410-26211-041 AND APPEARS TO BE BROKEN AT THREAD	S.  DAMPER WAS INSTALLED ON MRH PN 6410-20004-033, SN A2-013.  (K)				2	G	7	2 	4U				H4EA    					 
2007011600013	20070116	00013	CE  	2007	1	16	2006FA0001196    	1	20061129	G	2910	90E551701064	LINE            	CESSNA      		CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					BRAKE ASSY	CORRODED        	B			AKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	501LH					5000342				INVESTIGATING SOFT BRAKE CONDITION IT WAS NOTED THAT BRAKE FLUID WAS LEAKING FROM AROUND THE BELLY BEACON AND THE BEACON	 LENS WAS FULL OF FLUID.  REMOVED THE INTERIOR AND THE CENTER AISLE FLOOR PANELS.  HYDRAULIC FLUID WAS NOTED DRIPPING FR	OM RIDGE BRAKE LINE TO THE RT BRAKE.  PN 90E5517010-64 AT FS248.1.  MFG INSTALLED AIR-CONDITIONING COLD AIR DUCT IS TY-R	APED TO THE BRAKE FLUID LINES.  BELLY BEACON IS DIRECTLY BELOW THE CORROSION AND THE BRAKE FLUID LEAKAGE.  THE AIRCRAFT 	IS NOT EQUIPPED WITH BELLY DRAINS.  THE CONDENSATION LIES IN THE BELLY OF THE AIRCRAFT AND THE BEACON CREATES HEAT AND T	HE HUMIDITY CAUSES CORROSION ON COMPONENT PARTS IN THE UNDER FLOOR AREA.  MFG PROBABLY SHOULD ENGINEER A DRAINAGE SYSTEM	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007011600016	20070116	00016	CE  	2007	1	16	2006FA0001197    	1	20060918	G	5343		TRUSS           			AYRES 	S2    	S2R         	7630202	CE  										MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	32LF	9000 				5089R				UPPER TRUSS TO SHOCK STRUT BROKE OFF GEAR LEG, ALLOWING LANDING GEAR TO COLLAPSE.  THIS AIRCRAFT HAS BEEN USED FOR FUEL 	HAULING AND IS LANDING WITH HEAVY LOADS.  IT APPEARS A SMALL CRACK IN 1 TRUSS TUBE DEVELOPED AND EVENTUALLY FAILED, CAUS	ING TOTAL FAILURE OF THE LANDING GEAR LEG.  RECOMMEND DYE PENETRANT INSPECTION OF GEAR LEGS ON AIRCRAFT CONSISTANTLY LAN	DING WITH HEAVY LOADS EVERY 200 TO 300 HOURS.  (K)			1	L	7	1 	3R			NC	A4SW    					 
2007011600014	20070116	00014	NM  	2007	1	16	2006FA0001198    	1	20060912	G	5540	173A01038	RUDDER          			BOEING	737   	73776N      	13844CH	NM  	GE    	CFM56 	CFM56*      	13802	NE  						DAMAGED         	B			I6XR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	279AT					32666				RUDDER DAMAGED DUE TO LIGHTENING STRIKE WHILE AIRCRAFT WAS ON GROUND.  DETAILED INFORMATION CONCERNING THIS REPAIR CAN B	E FOUND ON (NR 10981-3600-0001). (K)					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007011600019	20070116	00019	EA  	2007	1	16	2006FA0001199    	2	20061003	G	8520	STD21C7	SCREW           			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A     	41532	EA  					IDLR GEAR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	5097P					24107	L11240			A POST ACCIDENT INVESTIGATION IDENTIFIED THAT THE CRANKSHAFT IDLER GEAR WAS MISSING SEVERAL TEETH.  FURTHER EXAMINATION 	REVEALED THAT THE SCREWS HOLDING THE CRANKSHAFT IDLER GEAR SHAFT HAD FAILED.  (K)					1	L	7	1 	3O	3	O		1A15    	E295				 
2007010900005	20070109	00005	CE  	2007	1	9	2006FA0001200    	1	20061205	G	5330	030A326633	ACCESS PANEL    			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					FUSELAGE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	215MH					1544SA				DRAIN HOLE IN COVER NOT BEING LOCATED PROPERLY CAUSES WATER TO LAY IN AFT.  FLANGE OF NEXT FRAME FWD CAUSING CORROSION. 	 (DRAIN HOLE NEEDS TO BE IN FRAME RADIUS.  (PRIMARY STRUCTURE).  (K)					1	H	7	2 	3T	3	T	RT	A10SW   	E2WE				 
2007011600074	20070116	00074	CE  	2007	1	16	2006FA0001201    	1	20060630	G	8120	C2950010101	TURBOCHARGER    			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	FAILED          	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	6363L	32   				21064703				NEW TURBO ASSY WAS INSTALLED 3/27/2006.  (3) MONTHS LATER ON 6/30/06 (32 HOURS TT) THE TURBO SHAFT TIGHTENED UP ENOUGH T	O NOT PRODUCE TAKEOFF POWER ON NEXT FLIGHT.  OIL PRESSURE AND OIL VOLUME DELIVERED TO TURBO BEARINGS WAS VERIFIED TO BE 	ADEQUATE.  CUSTOMER PROCEDURES FOR COOL DOWN/ SPOOL DOWN OF TURBO AFTER TAXI WERE VERIFIED TO BE CONSISTENT WITH MFG POH	 RECOMMENDED PROCEDURES.  NEW TURBO WAS INSTALLED AND (4) MONTHS (41 HOURS TURBO TT) LATER IT DID THE SAME THING.  M OR 	D REPORT SUBMITTED THIS DATE ALSO.   (K)		1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007011600068	20070116	00068	CE  	2007	1	16	2006FA0001202    	1	20061006	G	8120	C2950010101	TURBOCHARGER    			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  						FAILED          	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	6363L	41   				21064703				NEW TURBO ASSY WAS INSTALLED 6/30/06.  FOUR MONTHS LATER ON 10/6/06 (41 HOURS TT) THE TURBO SHAFT TIGHTENED UP ENOUGH TO	 NOT PRODUCE TAKEOFF POWER ON NEXT FLIGHT.  OIL PRESSURE AND OIL VOLUME DELIVERED TO TURBO BEARINGS WAS VERIFIED TO BE A	DEQUATE.  CUSTOMER PROCEDURES FOR COOL DOWN/SPOOL DOWN OF TURBO AFTER TAXI WERE VERIFIED TO BE CONSISTENT WITH POH RECOM	MENDED PROCEDURES.  THIS IS THE (2ND) TURBO IN 7 MONTHS TO DEVELOP THIS PROBLEM.  MFG HAS NUMEROUS REPORTS OF THIS SAME 	PROBLEM.  IT WOULD SEEM APPROPRIATE TO RE-EVALUATE THE ENGINEERING AND OR MFG OF THE SHAFT, BEARINGS, CLEARANCES, ETC OF	 THE TURBO.  (K)	1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007011800093	20070118	00093	SW  	2007	1	18	2006FA0001203    	1	20061007	G	3213	109152	STRUT           			AIRPTS	A     	A9B         	0144206	SW  	LYC   	O540  	TIO540*     	41532	EA  					MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	7638V					1366				THIS PART FAILED AT THE WELD THAT ATTACHES PN 12020( UNIVERSAL) TO THE LANDING GEAR SHOCK STRUT.  THIS PART IS LOCATED A	T THE POINT WHERE THE SHOCK STRUT ATTACHES TO THE LANDING GEAR TO FUSELAGE SUPPORT TUBE AT THE FRONT OF THE RT WING MAIN	 SPAR.  THIS PART FAILED DURING A NORMAL TAKEOFF.  THE PART BROKE AT THE WELD BREAKING THE WELD ON ONE SIDE.  THE WELD  	DID NOT APPEAR TO HAVE COMPLETE PENETRATION.  INTERNAL CORROSION MAY HAVE BEE A FACTOR.  THIS PART APPEARS TO BE THE WEA	KEST PART OF THE ENTIRE SHOCK STRUT SYSTEM.  I WOULD RECOMMEND THAT THIS PART BE MADE OF THICKER MATERIAL UTILIZING A MO	RE EXTENSIVE WELD WITH GOOD PENETRATION.  (K)	1	L	7	1 	3O	3	O		A758    	E14EA				 
2007010900003	20070109	00003	CE  	2007	1	9	2006FA0001204    	1	20061118	G	3230	12838002115	RELEASE CABLE   			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT MLG	FRAYED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	95GK	7502 				RK27				DURING SCHEDULE (A) AND (B) INSPECTION FOUND LT MLG EMERGENCY UPLOCK RELEASE CABLE ASSY.  SEVERLY FRAYED AND CABLE FUNCT	ION COMPROMISED AT UPLOCK ATTACH CLEVIS END.  THIS SB 32-3200.  SB 32-3200 IS A RECOMMENDED SB ONLY, COMPLIANCE RECOMMEN	DED WHEN CABLE ASSY REPLACEMENT REQUIRED.  NO RECORD OF PREVIOUS COMPLIANCE ON THIS AIRCRAFT.  (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007012200186	20070122	00186	CE  	2007	1	22	2006FA0001205    	1	20061120	G	5511	45A21104012	RIB             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	311HS	2142 				RK296				DURING AN A, B, AND C INSPECTION, FOUND THE HORIZONTAL STABILIZER MOUNTING FACES NOT PARALLEL WITH THE VERTICAL STABILIZ	ER, HORIZONTAL STABILIZER ROLLER CLEARANCE CHECKS IAW MM 27-40-00 OUT OF SERVICE LIMITS.  INSPECTED STABILIZER IAW MFG C	OMMUNIQU NR 70 AND FOUND RT HORIZONTAL STABILIZER RIB, PN 45A21104012, CRACKED.  REPLACED RIB AND REINSTALLED STABILIZE	R, HORIZONTAL STABILIZER ROLLER CLEARANCE CHECKS NOW WITHIN SERVICE LIMITS.  IAW COMMUNIQU NR 70, ROLLER GAP DIMENSIONS	 OUT OF SERVICE LIMITS MAY BE CONTRIBUTING TO PROBLEM.  AFFECTED STRUCTURE HAS NOT YET BEEN INCLUDED IN SCHEDULED INSPEC	TIONS GUIDE.  (K)	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007011600071	20070116	00071	SO  	2007	1	16	2006FA0001206    	1	20061206	G	5711	202394	NUT             			AYRES 	S2    	S2RRESTD    	0970101	SO  	PWA   	R1340 	R1340*      	52016	NE  					WING SPAR	DAMAGED         	D			PWWG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	8960Q					2450R				WHILE PERFORMING (SPLICE BLOCK) MAINTENANCE A NEW TUBE NUT HAD ITS THREADS PULLED OUT BEFORE REACHING TORQUE.  THE FOLLO	W ON PART WAS EXAMINED AND WAS FOUND TO BE LOOSE ON THE BOLT, EVEN THE USED TUBE NUT WAS TIGHTER.  SUSPECT PANTS HAVE NO	 PN OR STAMP, ALSO NO INDENTATIONS ON FACE OF THE NUT (NOT VISIBLE WHEN INSTALLED).  ALMOST MADE TORQUE.  (K)				1	L	7	1 	3R	3	R		A4SW    	5E2				 
2007011600047	20070116	00047	SO  	2007	1	16	2006FA0001207    	2	20061122	G	8500		CASE            			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	205DB					D8060	1207758A			ENGINE LT CASE, MALT DEVELOPED HOLE APPROX 6 INCHES X 4 INCHES AS ROD-PISTON APPEARS TO BE MISSING FOR NR 4 CYLINDER.  E	NGINE OPERATED:  (104 HOURS - 2004), (14 HOURS - 2005), (12 HOURS - 2006).  PROPELLER RECENTLY SHIMMED BLADE NR 3, RED D	YE AROUND PROP SEAL.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007011600057	20070116	00057	EA  	2007	1	16	2006FA0001208    	2	20061010	G	7320		LINE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					ENG FUEL	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	6879A		2    			277954104				FUEL LEAKING, TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2007011600048	20070116	00048	EA  	2007	1	16	2006FA0001209    	2	20061010	G	7310	RG17980YM	LINE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					TURBOCHARGER	LEAKING         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	01	6879A		2    			277954104				FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2007011600072	20070116	00072	EA  	2007	1	16	2006FA0001210    	2	20061010	G	7310	RG179803M	TURBOCHARGER    			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					LT ENGINE	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	6879A		2    			277954104				FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2007011600063	20070116	00063	EA  	2007	1	16	2006FA0001211    	2	20061010	G	7310	RG17980JM	LINE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					FUEL SYSTEM	LEAKING         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	01	6879A		2    			277954104				FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2007011600076	20070116	00076	CE  	2007	1	16	2006FA0001212    	1	20061122	G	5520	50524414	BELLCRANK       			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720A1B    	41546	EA  					RT ELEVATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	44MA					LD412	L15595YA			A CRACK WAS FOUND ON THE RT BELLCRANK SUPPORT ASSY.  DURING A MANDITORY 5 YEAR INSPECTION IAW MSB 2231 REV 1. (K)						1	L	7	2 	3O	3	O		3A20    	1E15				 
2007010400061	20070104	00061	CE  	2007	1	4	2006FA0001213    	1	20060407	G	8011	PM2401H	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	65647	23   				172S9778				STARTER WOULD NOT STAY ENGAGED.  STARTER ONLY HAS 23.4 HR.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800153	20070108	00153	CE  	2007	1	8	2006FA0001214    	1	20061221	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	STUCK           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05						172S9778				STARTER STUCK IN ENGAGED MODE						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800154	20070108	00154	CE  	2007	1	8	2006FA0001215    	1	20060306	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	259TA	1585 				172S9225				STARTER WILL NOT STAY ENGAGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800155	20070108	00155	CE  	2007	1	8	2006FA0001216    	1	20061221	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	MALFUNCTIONED   	G			GBMS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	879LB	289  				172S9879				STARTER SPINS BUT WILL NOT ENGAGE.						1	H	7	1 	3O			NT	3A12    					 
2007010800162	20070108	00162	CE  	2007	1	8	2006FA0001217    	1	20060810	G	8011	PM2401H	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G			GBMS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	65647	240  				172S9778				STARTER FAIL, WOULD NOT ENGAGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800163	20070108	00163	CE  	2007	1	8	2006FA0001218    	1	20061207	G	8011	PM2401H	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G			GBMS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	65647	146  				172S9778				STARTER WOULD NOT ENGAGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800177	20070108	00177	CE  	2007	1	8	2006FA0001219    	1	20061221	G	8011		STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	MALFUNCTIONED   	G			GBMS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	879LB	231  				172S9879				STARTER WOULD NOT ENGAGE.						1	H	7	1 	3O			NT	3A12    					 
2007010800180	20070108	00180	CE  	2007	1	8	2006FA0001220    	1	20061020	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G			GBMS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	259TA	68   				172S9225				STARTER SPINS BUT WILL NOT ENGAGE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800181	20070108	00181	CE  	2007	1	8	2006FA0001221    	1	20060909	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	259TA	142  				172S9225				STARTER SPINS BUT WILL NOT ENGAGE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010800182	20070108	00182	CE  	2007	1	8	2006FA0001222    	1	20061221	G	8011	PM2401	STARTER         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	MALFUNCTIONED   	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	2019V	269  				18281699				STARTER STUCK IN ENGAGED MODE.						1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007010800185	20070108	00185	CE  	2007	1	8	2006FA0001223    	1	20061221	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	259TA	126  				172S9225				STARTER BENDIX FAILED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010900041	20070109	00041	CE  	2007	1	9	2006FA0001225    	1	20061003	G	8011	PM2401H	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	65647	115  				172S9778				STARTER WOULD NOT ENGAGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007010900059	20070109	00059	CE  	2007	1	9	2006FA0001226    	1	20060924	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	LOCKED          	G			GBMS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	65831	1157 				172S9796				STARTER STUCK ENGAGED AND LOCKED PROP.						1	H	7	1 	3O			NT	3A12    					 
2007010900060	20070109	00060	CE  	2007	1	9	2006FA0001227    	1	20061212	G	8011	PM2401H	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	65647	11   				172S9778				STARTER WOULD NOT ENGAGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007011800039	20070118	00039	GL  	2007	1	18	2006FA0001228    	3	20061222	G	6110	D68315A	CLAMP           													HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER BLADE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								H632		DURING A ROUTINE PRE-FLIGHT INSPECTION OF PROPELLER ASSY, A CRACK WAS IDENTIFIED ON BLADE CLAMP PN D-6831-5A, REV K, SN 	3194A.  PROP WAS REMOVED FROM AC FOR FURTHER INSPECTION.  INSPECTION CONFIRMED OPERATOR IDENTIFIED DEFECT AND PART FORWA	RDED FOR FURTHER EVALUATION.  THIS PART IS A TERMINATING ACTION FOR AD NOTE 97-18-02.  (K)														5	C	P24EA	 
2007011800131	20070118	00131	SO  	2007	1	18	2006FA0001229    	2	20061122	G	8550	LPMILH50555	LINE            			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE OIL	BROKEN          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	11	205DB					D8060	1207758A			STARFLEX 193, LOW PRESSURE HOSE, LP MIL-H-50555 WAS USED TO CONNECT OIL COOLER TO FIREWALL FITTING.  OIL PRESSURE WILL R	UN BETWEEN 50-100 PSI IN LINE.  HOSE BROKE AT FITTING AT OIL COOLER OUTLET,  ALL OIL WAS PUMPED OUT OF ENGINE CAUSING RO	D TO BE RAMMED THROUGH LT CASE HALF. (NORMAL TSO AS1072 HOSE IS INSTALLED IN THIS POSITION.  STARFLEX 2650).  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007011600066	20070116	00066	CE  	2007	1	16	2006FA0001230    	1	20061214	G	2497	501122804	WIRE            			LEAR  	35    	35A         	5170602	CE  											MISINSTALLED    	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	421SV					660				CELL DIP SWITCH INSTALLED 180 DEGREES OUT.  CELL WIRING MISROUTED AND IMPROPER GAUGE WIRE.  MULTIPLE COLD CRACKED SOLDER	 JOINTS BROKEN AND POORLY REPAIRED TRACES.  BATTERY T3 AND P3 ARE BROKEN.  UNIT SENT BACK, AS CORE SEEMS TO BE A WORKMAN	SHIP ISSUE. (K)				2	L	7	2 	4F				A10CE   					 
2007011800133	20070118	00133	CE  	2007	1	18	2006FA0001231    	1	20061130	G	3411	E420191	STATIC PORT     			RAYTHN	DH125 	DH125       	4230106	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUSELAGE	MISINSTALLED    	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	700VT					257158				ROSEMOUNT STATIC PORTS DO NOT FIT CONTOUR OF AIRCRAFT SKIN. PORTS ARE NOT UNIFORM IN THICKNESS.  CAN NOT INSTALL NEW POR	T AND MATCH STEP HEIGHT TO MEET ORIGINAL RVSM CERTIFICATION.  OTHER ISSUES: WHEN PORT IS INSTALLED, PORT CAUSE STRESS.  	AC SKIN DO TO CONTOUR FIT.  INSTALLATION OF PORT ALSO PUTS STRESS ON PLATE TO HEATER BLOCK AND CAUSES CRACKING IN THE MA	TING SURFACE CAUSING PORT TO HAVE STATIC SYSTEM LEAK.  (K)			2	L	7	2 	4J	4	F	RT	A3EU    	E6WE				 
2007011100146	20070111	00146	CE  	2007	1	11	2006FA0001233    	1	20061209	G	2497	AE776L845	CONNECTOR       			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					MAIN BATTERY	SHORTED         	B			CNQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	913QS	6798 				7500113				BATTERY OVERTEMP INDICATED R-RED CAS MESSAGE IN FLIGHT.  FOUND SPLICE AT THE BATTERY TEMP SENSOR CONNECTOR PY044 BROKEN.	  ALSO CONNECTOR WAS FOUND BADLY CORRODED INSIDE OF CONNECTOR.  REPLACED CONNECTOR PY044 AND REPLACED WIRES IAW CE750 WI	RING MANUAL 20-10-06.  THE INCIDENT WAS AN INDICATION PROBLEM ONLY AND BOTH AIRCRAFT BATTERIES WERE FOUND TO BE NORMAL (	AIRWORTHY) WITH NO ACTION REQUIRED.  (K)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007011800072	20070118	00072	EA  	2007	1	18	2006FA0001234    	2	20061202	G	8520		PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					NR 3 CYLINDER	STUCK           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	94286	8774 	1762 			15285639	L2404715			ENGINE QUIT IN FLIGHT, FOUND NR 3 CYLINDER PISTON NOT MOVING IN CYLINDER WHEN TURNING PROP.  (K)						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007010900010	20070109	00010	EA  	2007	1	9	2006FA0001235    	2	20061227	G	8530	LW19001	VALVE GUIDE     			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  						STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	19HP	1300 	200  			18281266	L2895948B			PERFORMED COMPRESSION CHECK ON ENGINE AND HAD 5/80 PSI ON NR 6 CYL, STAKED EXHAUST VALVE AND GOT 78/80. PERFORMED SB 388	C AND HAD TO REAM VALVE GUIDES TO GET WITH-IN LIMITS OF SB.  IT WAS ONLY 200 HRS SINCE LAST SB COMPLIANCE.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2006091400168	20060914	00168		2006	9	14	2006FAA0901      	4	20060906	G	2210	841341	AUTOPILOT SYS   			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  						BURNED OUT      	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	42	71562					4697081				THE COMPLAINANT NOTED SMOKE IN THE COCKPIT.THE SOURCE OF THE SMOKE WAS THE FAILURE OF A FILTER CAPACITOR, C20 (P/N 11310	13-106035,) ON THE POWER SUPPLY BOARD (P/N 71115-05.) IT HAD BURNED OUT CAUSING THE SMOKE.  IT IS A FILTER CAPACITOR FOR	 THE -15V SIDE OF THE DC TO DC CONVERTER.  THE PART WAS INSTALLED CORRECTLY (POLARITY), AND NONE OF THE SURROUNDING DEVI	CES WERE ABNORMAL.  IT WAS A PART THAT HAS HISTORICALLY GIVEN US THIS TYPE OF FAILURE, ALTHOUGH WEVE NEVER HAD ISSUE WI	TH THE PART LOCATED HERE.  IT APPEARS TO BE A ONE TIME DEFECTIVE DEVICE.		1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2007012500139	20070125	00139	NE  	2007	1	25	2007FA0000000    	2	20061201	G	7200		ENGINE          			CNDAIR	CL600 	CL6002A12   	1900304	EA  	GE    	CF34  	CF341A      	 	NE  					RIGHT	FAILED          	Z				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			WP	01	388DB	6080 	380  			3016	350152			RT ENGINE FAILURE AT T/O. ALL INDICATIONS WERE NORMAL ON ENGINE START AND TAXI. UPON THRUST ADVANCEMENT FOR TAKEOFF, AT 	APPROXIMATELY 60 PERCENT N1 WE HEARD AND FELT A COMPRESSOR STALL. THE THRUST LEVER WAS IMMEDIATELY RETARDED TO IDLE AND 	TEMPERATURES WERE NOTED TO BE IN THE RED(APPROX 950 DEGREESC). WE SHUT DOWN THE ENGINE AND OBSERVED THE TEMPERATURES REM	AINING IN THE RED FOR APPROXIMATELY 6 TO 8 SECONDS AFTER SHUTDOWN. WE TAXIED BACK TO BOMBARDIER AND REPORTED THIS INCIDE	NT. SUBSEQUENT EXAMINATION REVEALED DAMAGE IN THE FORWARD AND AFT SECTIONS OF THE ENGINE.  ENGINE REMOVED & ROUTED TO FO	R REPAIR.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007011800097	20070118	00097	EU  	2007	1	18	2007FA0000002    	1	20061206	G	5302		DOUBLER         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	110E	1065 				3322				FOUND CRACKS 2 EA ON LT OUTSIDE DOUBLER ASSY.  2 RIVETS WERE POPED OUT.  DAMAGE VISIBLE ONLY AFTER REMOVAL OF TAIL ROTOR	 GEARBOX COWLING.  FOUND DURING 100 HR INSP.  (K)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007011600067	20070116	00067	EU  	2007	1	16	2007FA0000003    	1	20061110	G	3600	1U478003	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					ENGINE	OUT OF LIMITS   	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	52   				85004				PILOT REPORTED SUCTION INDICATOR WAS BELOW LIMITS, AC RETURNE TO BASE.  UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE A	IR PUMP AND NOTICED THE SHAFT WAS VERY EASY TO ROTATE, HAD NO RESISTANCE TO IT.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT	 THIS TIME.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2007011800036	20070118	00036	EU  	2007	1	18	2007FA0000004    	1	20061026	G	3710	1U478	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					VACUUM SYS	WEAK            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF					85004	RL2802548			IN FLIGHT, THE INSTRUMENT VACUUM SYSTEM WOULD NOT PUT OUT PROPER SUCTION AND CAUSED THE ATTITUDE INDICATOR TO TUMBLE.  T	HE AC RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM  FOUND THAT THE PUMP WAS WEAK.  PUMP WAS REMOVED AND A NEW	 PUMP INSTALLED.  OPERATIONAL CHECK OF THE SYSTEM CHECKED NORMAL.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2007011600073	20070116	00073	EU  	2007	1	16	2007FA0000005    	1	20060922	G	3700	1U478	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					VACUUM SYSTEM	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF					85002	RL2515648A			DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING TECHICIAN FOUND THE ENGINE DRIVEN	 DRY AIR PUMP SHAFT HAD BROKEN.  PROBABLE CAUSE COULD BE FROM ENGINE VIBRATION OR  POOR PARTS.  RECOMMENDATION AT THIS T	IME IS FOR THE MFG TO INVESTIGATE WHY PUMP IS FAILING SO EARLY.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2007011600011	20070116	00011	EU  	2007	1	16	2007FA0000006    	1	20060926	G	3700	1U478	SHAFT           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					AIR PUMP	BROKEN          	B			VJ3R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	865AF	194  				85005				DURING ENGINE START, SUCTION PRESSURE WAS READING ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN DRI	VEN DRY AIR PUMP HAD A BROKEN SHAFT.  PROBABLE CAUSE COULD BE FROM VIBRATION OR HARD START.  NO RECOMMENDATION AT THIS T	IME.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2007012500110	20070125	00110	EU  	2007	1	25	2007FA0000007    	1	20061030	G	3710	1U478	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540*    		EA  					VACUUM SYS	WORN            	C			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	109  				85005				DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN AIR	 PUMP WAS NOT PRODUCTING ENOUGH SUCTION.  PROBABLE CAUSE COULD BE FROM PISTION WEARING INSIDE OF PUMP.  RECOMMENDATION A	T THIS TIME IS FOR THE MFG TO INVESTIGATE WHY PUMP PISTON IS FAILING.  (K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2007010900002	20070109	00002	SO  	2007	1	9	2007FA0000008    	1	20061214	G	5711	6207006	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG	LOOSE           	B			A5OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	15715	3501 				287325144				DURING AN ANNUAL INSPECTION OF THE LT MAIN LANDING GEAR ASSY PN 35644-902, IT WAS FOUND TO BE LOOSE IN THE MAIN WING SPA	R.  THE LT MAIN LANDING GEAR WAS REMOVED FOR FURTHER INSPECTION OF THE LT MAIN WING SPAR ASSY GEAR ATTACHING BOLT HOSES 	AND ATTACH POINTS.  CLOSE INSPECTION FO THE WING SPAR SHOWED THAT THE LOWER (4) BOLT HOLES HAD BEEN ELONGATED.  IT APPEA	RED THAT ALL BOLTS WERE TIGHT AND THIS CONDITION HAD BEE LOOSE FOR SOME TIME.  RECOMMEND CLOSE INSPECTION OF LANDING GEA	R ATTACH POINTS DURING ALL INSPECTIONS.  (K)		1	L	7	1 	3O	3	O		2A13    	E274				 
2007011100137	20070111	00137	GL  	2007	1	11	2007FA0000009    	1	20061218	G	8011	642083	DRIVE ASSY      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					STARTER	CRACKED         	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	249CK					0766	9117066			STARTER DRIVE WAS REMOVED FROM AIRCRAFT DUE TO SLIPPING.  INSPECTION AFTER REMOVAL FOUND A CRACK EMANATING FROM THE STUD	 BOSS LOCATED AT APPROXIMATELY THE 7:00 POSITION.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007011100138	20070111	00138		2007	1	11	2007FA0000010    	4	20061218	G	2562		BATTERY         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ELT	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	11	910JR				040334	0142				DURING ANNUAL INSPECTION, FOUND BATTERY COMPARTMENT CONTAMINATED BY LEAKAGE FROM D CELLS AND BATTERY TERMINALS CORRODED.	  BATTERIES FOUND DEAD.  BATTERIES WERE INSTALLED MARCH 2004 AND HAVE A EXPIRATION DATE OF MARCH 2008.  THE MODEL ELT IS	 CERTIFIED BY THE MFG TO USE THE BATTERY EXPIRATION DATES FOR SERVICE RATHER THAN A LIMITED CALENDAR TIME SUCH AS THE TY	PICAL 24 MONTHS.  THIS INSPECTOR HAS RECENTLY FOUND OTHER ELTS OF THE SAME TYPE IN THE SAME CONDITION.  RECOMMENDATION T	HA THE SERVICE LIFE OF THE BATTERIES BE LIMITED TO 24 MONTHS.  (K)		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007011600062	20070116	00062	WP  	2007	1	16	2007FA0000011    	2	20060929	G	7250	30606852	RETAINER        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LPT 2	CORRODED        	F				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	VH5QR	4660 				45195	P111119C			MATERIAL LOSS ON THE LPT2 NOZZLE RETAINER WITH DISLODGED PINS THAT LIKELY LED TO DOWN STREAM LPT3 BLADE MID SPAN FRACTUR	ES AND DISPLACED MATERIAL IN THE FORM OF IMPACT DAMAGE.  THIS ENGINE WAS PRESERVICE  BULLETIN 72-5165 AND ADDRESSES THIS	 ISSUE.  (K)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007011800129	20070118	00129		2007	1	18	2007FA0000012    	4	20061220	G	2564	57FASA2321325	LIFE RAFT       			ISRAEL	GALAXY	GALAXY      	4500307	EU  										CABIN	MISRIGGED       	B			JG1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	889G					046				THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC.  MOORING THE LINE (FIRING LINE) WAS FOUND RIGGED	 WRONG.  LINE WAS TIED TO LIFE RAFT FIRST AND THEN TO THE PULL CABLE.  THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST A	ND THEN TO THE LIFE RAFT.  RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE	 FIRED.  (K)			2	L	7	2 	4F			RT	A53NM   					 
2007011100144	20070111	00144		2007	1	11	2007FA0000013    	4	20061220	G	2564	57FASA2321315	LIFE RAFT       			ISRAEL	GALAXY	GALAXY      	4500307	EU  											MISRIGGED       	B			JG1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	889G					046				THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC.  MOOORING LINE (FIRING LINE) WAS FOUND RIGGED WR	ONG.  LINE WAS TIED TO THE RAFT FIRST AND THEN TO PULL CABLE.  THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN 	TO THE LIFE RAFT.  RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED. 	 (K)			2	L	7	2 	4F			RT	A53NM   					 
2007011100145	20070111	00145		2007	1	11	2007FA0000014    	4	20061220	G	2564	57FASA2321315	LIFE RAFT       			ISRAEL	GALAXY	GALAXY      	4500307	EU  											MISRIGGED       	B			JG1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	889G					046				THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC.  MOORING LINE (FIRING LINE) WAS FOUND RIGGED WRO	NG.  LINE WAS TIED TO LIFE RAFT FIRST AND THEN TO THE PULL CABLE.  THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND T	HEN TO THE LIFE RAFT.  RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIR	ED.  (K)			2	L	7	2 	4F			RT	A53NM   					 
2007011600056	20070116	00056		2007	1	16	2007FA0000015    	1	20061214	G	3500	4357B	VALVE           																	OXYGEN SYS	LEAKING         	B			WP1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										OXYGEN VALVE HAD A FUNCTIONAL TEST, ON 06/07/2006.  THE WORK WAS ACCOMPLISHED ON WO 06-5301.  THIS COMPONENT LEAKED OXYG	EN WHEN INSTALLED.  (K)																		 
2007011800078	20070118	00078		2007	1	18	2007FA0000016    	1	20061214	G	3500	4357B	VALVE           																	OXYGEN SYSTEM	LEAKING         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	WP1R									OXYGEN VALVE HAD A FUNCTIONAL TEST ON 09/25/2006.  THE WORK WAS ACCOMPLISHED ON WO 06-5970.  THIS COMPONENT LEAKED OXYGE	N WHEN INSTALLED.  (K)																		 
2007011800092	20070118	00092		2007	1	18	2007FA0000019    	1	20061214	G	3500	29909256B	VALVE           																	OXYGEN SYSTEM	LEAKING         	B			WP1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										OXYGEN VALVE HAD A FUNCTIONAL TEST ON 06/07/2006.  THE WORK WAS ACCOMPLISHED ON WO 06-5775.  THIS COMPONENT LEAKED OXYGE	N WHEN INSTALLED.  (K)																		 
2007011800125	20070118	00125		2007	1	18	2007FA0000020    	1	20061214	G	3500	4357B	VALVE           																	OXYGEN SYSTEM	LEAKING         	B			WP1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										OXYGEN VALVE WAS INSPECTED ON 10/09/2006.  THE WORK WAS ACCOMPLISHED ON WO 066023.  THIS COMPONENT LEAKED OXYGEN WHEN IN	STALLED.  (K)																		 
2007011600034	20070116	00034	EU  	2007	1	16	2007FA0000021    	1	20061127	G	5100		PIN             			AIRBUS	A340  	A340*       	       	EU  											MISMANUFACTURED 	B			VS6Y	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35						VARIOUS				TWO OCCURRENCES OF A RETAINING PIN HOLDING THE UNIVERSAL-JOINT TOGETHER, HAVING INSUFFICIENT PEENING TO RETAIN THE PIN, 	HAS BEEN IDENTIFIED IN BUILD OF THE UNIT BY THE ACTUATOR/DRIVE SHAFT MFG.  THE PIN IS THEREFORE NOT SUFFICIENTLY RETAINE	D AND MAY WALK OUT OF THE UNIVERSAL JOINT UNDER ACTUATION LOADS.  THREE POTENTIALLY HAZARDOUS CONDITIONS HAVE BEEN IDENT	IFIED.  1) THERE WILL BE A NR OF METAL PARTS FREE IN THE FUEL TANK- LIGHTNING STRIKE.  2) THE JOINT WILL FAIL AND PREVEN	T TRANSMISSION OF DRIVE THROUGH THE SHAFT TO THE ACTUATED VALVE.  THE ACTUATED VALVE WILL FAIL TO OPERATE, BUT A POSITIV	E ACTUATION WILL BE INDICATED TO THE FLIGHT CREW.  MONITORING OF THE FUEL CONTENTS WILL BE REQUIRED TO VERIFY THAT THE C	2	L	7	4 	4F			RT	A197    					 
2007011800095	20070118	00095	SW  	2007	1	18	2007FA0000024    	1	20061130	G	5520	F3114	BEARING         			MOONEY	M20   	M20G        	5870316	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ELEVATOR ROD END	FROZEN          	B			DPPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	684MA					680005	RL2292836A			ELEVATOR PUSH ROD END BEARING (PHF31-14, FOUND TO BE FROZEN FROM RUST AND GRIME.  ROD END BEARING BROKE AT THREADED PORT	ION DUE TO LACK OF MOVEMENT.  AD 73-21-01 ADDRESSES LUBRICATION OF ALL CONTROL AND LANDING GEAR ROD END BEARINGS BUT DOE	S NOT ADDRESS INSPECTION OF OPERATION AND FREEDOM OF MOVEMENT.  SERVICE INSTRUCTION M20-106 GIVES A GOOD INSPECTION OF P	RIMARY FLIGHT CONTROL/ JOINTS.  THAT SHOULD BE INCORPORATED INTO THE INSPECTION MANUAL AND/OR AD.  (K)			1	L	7	1 	3O	3	O		2A3     	E286	5	C	P920	 
2007011600053	20070116	00053	CE  	2007	1	16	2007FA0000025    	1	20060725	G	2510	07140593	SEAT BACK       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					COCKPIT	BROKEN          	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	733BE	4070 				17268161				INSPECTED SEATS IAW AD 87-20-03R2 FOUND PILOTS SEAT BOTTOM ASSY BROKEN AT LEFT FWD ATTACH POINT AND RT FWD CRACKED.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007011100139	20070111	00139	SO  	2007	1	11	2007FA0000026    	1	20061211	G	8011	MZ6222	STARTER         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	BROKEN          	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	9089N	600  				2816003	L1624939A			WHEN STARTING AIRCRAFT, MADE LOUD NOISE AT STARTER.  INSPECTED AND FOUND BENDIX SHATTERED.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2007011200002	20070112	00002	EA  	2007	1	12	2007FA0000027    	2	20061204	G	8530		PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NR 3 CYLINDER	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	94286	1762 				15285639	L2404715	VH43067		NR 3 CYLINDER PISTON DOES NOT MOVE IN CYLINDER WHEN YOU TURN PROPELLER.  (K)						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007011100141	20070111	00141	SO  	2007	1	11	2007FA0000028    	2	20061229	G	8550	6566161	DIPSTICK        			AMTR  	LANCAR	LC41550FG   	5150001	GL  	CONT  	O550  	TSIO550C    		SO  					ENGINE	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	442TA	189  				41532	802791			THE OIL GAGE ASSEMBLY (DIPSTICK) SEPARATED AT THE UPPER SWEDGED JOINT.  (K)						1	L	7	1 	3O	3	O	RT	EXPA1L71	E5SO				 
2007011100140	20070111	00140	SO  	2007	1	11	2007FA0000029    	1	20061219	G	3210	AN411A	BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	70C	70CM6       	EA  	MLG	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	8156T	8236 				288016219	L9820394	A549B2		WHILE WASHING AC, SCRUB BRUSH NOCKED OFF NUT AND ENGAGED PORTION OF ONE OF THE (AN4-11A) BOLTS THAT SECURES THE RT MLG A	SSY TO THE RT WING.  BOLT WAS CORRODED ALL THE WAY ACROSS ITS CROSS SECTION.  SUGGESTIONS: PERIODICALLY CHECK TORQUE ON 	THESE BOLTS TO ENSURE BOLT NOT CORRODED THROUGH LIKE THIS ONE.  REPLACE THES BOLTS PERIODICALLY TO PRECLUDE CORROSION FA	ILURE.  (K)			1	L	7	1 	3O	3	O		2A13    	E274	5	N	P28NE	 
2007011100134	20070111	00134	CE  	2007	1	11	2007FA0000030    	1	20061215	G	2140	83D59	VALVE           	JANITROL    		BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					CABIN HEATER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	3845L					TC2378				FOUND THERMOSTAT WORKING, BUT FUEL SOLENOID NOT STOPPING FUEL DELIVERY EVEN WITH POWER TO VALVE DISTUPTED.  CABIN HEATER	 ONLY SHUTDOWN WHEN OVERHEAT SWITCH OPENED.  VALVE INFO:  MODEL NR 4400B.					1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2007012500199	20070125	00199	CE  	2007	1	25	2007FA0000033    	1	20061219	G	8011	MZ4220	STARTER         			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					ENGINE	INTERMITTENT    	B			BIIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	60156	39   				ME147	L56171A			REPEATED TRYS, BENDIX FAILED TO ENGAGE.  LUBRICATED AND INSPECTED BENDIX, FAILS TO ENGAGE EVERY OTHER TIME.  IT STARTS (	1) TIME THEN FAILS.  (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
2007012500200	20070125	00200	CE  	2007	1	25	2007FA0000034    	1	20061124	G	8011	9301001	DRIVE GEAR      	LAMAR       		CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	856SP				85007449	172S8124				STARTER WAS REMOVED AFTER THE DRIVE GEAR BROKE INTO PIECES AND JAMMED STARTER FROM TURNING.  COMPLETE STARTER WAS REPLAC	ED WITH REBUILT ASSEMBLY.  SUB-PART (BENDIX DRIVE) IS PN 9301001.  THIS MECHANIC HAS SEEN THIS FAILURE 4 TO 5 TIMES.  BO	TH 12 AND 24 VOLT UNITS.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007012500196	20070125	00196	CE  	2007	1	25	2007FA0000035    	1	20061203	G	3350	645402500	RHEOSTAT        			LEAR  	35    	36LEAR      	5170601	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	SHORTED         	D			ESPR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SO	11	71PG					013				SOON AFTER TAKEOFF, THE CREW DETECTED A AN ELECTRICAL SMELL.  AFTER ATTEMPTING AND FAILING TO ISOLATE SOURCES.  THEY ELE	CTED TO RETURN TO DEPARTURE.  AIRPORT, AND LANDED UNEVENTFULLY.  THERE WAS NO EMERGENCY DECLARED.  MAINTENANCE REPLACED 	EL RHEOSTAT IAW MM.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007012600008	20070126	00008	NE  	2007	1	26	2007FA0000037    	2	20060915	G	7250	3360097050	SHAFT           	CFMINT      		AIRBUS	320   	A320211     	3930320	EU  	GE    	CFM56 	CFM565A     	13802	NE  					LP TURBINE	SEIZED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	SUPBD				55X31147					ENGINE WAS REMOVED FROM AC, ENG POSITION 1 FOR A SUSPECTED LPT SHAFT FAILURE.  ENG FAILED ON 9/15/2006 AND WAS REMOVED O	N 12/3/2006.  ENG WAS INPUT ON 1/2/2007 FOR DISASSEMBLY.  ON RECEIPT OF ENG, IT WAS NOT POSSIBLE TO CARRY OUT A BORESCOP	E INSP OF CORE AS IT WAS SEIZED AND WAS UNABLE TO ROTATE.  ON ROTATION OF FAN LPC SYSTEM IT WAS FOUND THAT LPT SYSTEM WA	S NOT ROTATING.  DUE TO EXTENT OF DEBRIS FOUND IN LPT FROM FAILED LPT ROTOR BLADES AND VANES, IT WAS ALSO NOT POSSIBLE T	O ROTATE IT INDEPENDENTLY.  ENG HAD SUFFERED MAJOR FAILURES ON FOLLOWING COMPONENTS:  LPT SHAFT, NR 4 BRG, CENTER VENT T	UBE, HPT BLADES, LPT STAGE 1 VANES, LLPT ROTOR BLADES AND VANES ALL STAGES.  FURTHER DISASSEMBLY OF MODULES WILL EXPOSE 	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007012200047	20070122	00047		2007	1	22	2007FA0000044    	4	20061109	G	3417	702490031304	ADC             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					COCKPIT	DEFECTIVE       	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	1140A					35045				DURING PREFLIGHT THE PILOTS ALTIMETER WAS FLAGGED.  THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS TEST	ED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91 AND TO REMAIN RVSM COMPLAINT.  THERE HAS BEEN ONE PRIOR FAILURE REPORTE	D ON THIS SYSTEM REPORTED ON 11-11-2005.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007012200048	20070122	00048		2007	1	22	2007FA0000045    	4	20061116	G	3417	8220839429	ADC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					LT AFT AVIONICS	MALFUNCTIONED   	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	160AN					126				THE FLIGHTCREW REPORTED INTERMITTENT LOSS OF ADC INFORMATION ON THE CAPTAIN`S PFD.  THE PRIMARY AIR DATA COMPUTER WAS FO	UND TO BE DEFECTIVE AND WAS REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED IAW MM AND WAS FOUND TO COMPLY WITH FAR 91.41	1, PART 43 AND RVSM ADC INSPECTIORS.  THE AIRCRAFT REMAINS RVSM COMPLAINT.  (K)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007012500240	20070125	00240	NM  	2007	1	25	2007FA0000053    	1	20061128	G	3250	4I29R12	HOUSING         	SARGENT     		BOEING	737   	737*        	       	NM  										STEERING VAVLE	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					1106					(REF NR: 213227/FXS)  BODY CRACKED IN CHECK VALVE PORT.  OVERPRESSURE/ CYCLIC STRESS, REDESIGN BODY.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2007012500035	20070125	00035	CE  	2007	1	25	2007FA0000055    	1	20061212	G	2910	1114174S0102	HYDRAULIC LINE  			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540*       	41532	EA  					NLG	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			SO	03	5091S					R18201503				HYDRAULIC HOSE ON RETRACT SIDE OF NOSE GEAR ACTUATOR FAILED AS AIRCRAT WAS ON APPROACH AND GEARDOWN WAS SELECTED.  RESUL	TED IN AIRCRAFT MAKING AN EMERGENCY GEARUP LANDING.  AFTER AC WAS RECOVERED, INSPECTION OF HYDRAULIC SYSTEM REVEALED; TE	FLON HYDRAULIC HOSE HAD COMPLETELY BLOW-OUT OF SWEDGED FITTING.  NO SIGNS OF HOSE LEAKING PRIOR TO INCIDENT.  (K)				1	H	7	1 	3O	3	O		3A13    	E295				 
2007012500145	20070125	00145	SO  	2007	1	25	2007FA0000060    	1	20061228	G	2913	HYC5005	PUMP            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					HYDRAULIC SYS	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	2PW					447995087	L10677T			UPON EXAMINATION OF THE AIRCRAFT IN QUESTION ON THE RUNWAY (AIRPORT MANAGER) TO TAKE PHOTOS OF THE INTERIOR OF THE AIRCR	AFT SO AS TO RECORD THE POSITIONS OF ENGINE, GEAR AND CIRCUIT BREAKERS.  PIC SO THEY COULD BE RECORDED BEFORE BEING REPO	SITIONED FOR SAFETY PURPOSES.  AFTER THAT WAS DONE, THE EMERGENCY GEAR KNOB AND PULLED THE LANDING GEAR HYDRAULIC CB.  T	HE AC WAS THEN HOISTED UP BY CRANE AND SLING AND THE GEAR CAME DOWN.  WHILE THE AC WAS HOISTED, EXAMINED THE LAND GEAR D	OWN LOCKS.  ALL (3) WERE IN THE (DOWN AND LOCKED) POSITION. THE AC WAS THEN TOWED TO OUR HANGER WITHOUT ANY PROBLEMS.  J	ACKED UP AC AND REPOSITIONED THE CONTROLS FOR A RETRACT TEST OF THE LANDING GEAR.  UPON S3WITCHING BATTERY POWER TO (ON)	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007012500130	20070125	00130		2007	1	25	2007FA0000061    	1	20061228	G	8011	ES6462751	STARTER         																	ENGINE	LEAKING         	B			WS9R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		2    								STARTER LEAKING OUT OF REAR OF STARTER PLATE.  (K)																			 
2007012500341	20070125	00341	NE  	2007	1	25	2007FA0000062    	2	20061004	G	7250	30606852	RETAINER        			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					TURBINE	SEPARATED       	D				O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			WP	07	1125S	2445 				134	P113218			ON 10/4/2006, 4TH AIRCRAFT EXPERIENCED A LT ENGINE EXHAUST FIRE AFTER ENGINE START AND PRIOR TO DEPARTURE.  ENGINE WAS R	EMOVED AND RETURNED TO MFG FOR REPAIR.  ENGINE WAS DISASSEMBLED IAW LMM 72-03-06, REV 8 FOR ENGINEERING INVESTIGATION.  	DISASSEMBLY FINDINGS REVEALED PINS SECURING THE DEFLECTOR SHROUD TO THE RETAINER RING OF THE LPT2 STAGE NOZZLE RETAINER 	BECAME DISLODGED AND EXHIBITED CONTACT FRETTING WITH MATERIAL LOSS ON THE OUTER RETAINER.  THE ENGINE FIRE MAY HAVE RESU	LTED FROM THE LPT2 STAGE RETAINER PINS DISLODGING WHICH MAY HAVE LOCCKED UP THE N1 ROTATING GROUP AND PREVENTED THE N1 G	ROUP FROM OBTAINING GROUND IDLE WITH EXCESSIVE RAW FUEL.  SB INCORPORATED IMPROVED HARDWARE AND PROVIDES INSTRUCTIONS FO	2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2007013100115	20070131	00115		2007	1	31	2007FA0000066    	4	20060501	G	2330	1302045100	MONITOR         																	CABIN	MALFUNCTIONED   	B			BT7Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35										POTENTIAL FOR SMOKE IN THE CABIN CAUSED BY FAILURE OF ELECTRONIC COMPONENT WITHIN IFE SCREENS.  WHILE CARRYING OUT THE R	EPAIR OF 6.4 LCD IN ARM AND SEAT BACK UNITS, WORKSHOP TECHNICIANS NOTED DAMAGE TO A CAPACITOR (LABELED AS C100) ON THE C	IRCUIT CARD ASSY (CCA) WITHIN THE LCD.  ALTHOUGH THE UNIT WAS NOT REMOVED FROM AC FOR THIS DEFECT AND THE FAILURE OF THE	 COMPONENT DOES NOT APPEAR TO HAVE A DETRIMENTAL AFFECT TO THE PERFORMANCE OF THE UNIT, IT IS CONSIDERED THAT THE DAMAGE	 TO THE CCA IS SEVERE ENOUGH TO POTENTIALLY CAUSE SMOKE IN THE CABIN.  AT THE TIME IT WAS CONSIDERED A ONE-OFF INCIDENT 	AND THE WHOLE CCA WAS CHANGED.  THE THE CCA PN AFFECTED 1302160-102 AND 1302160-103.  NO DETAILED CIRCUIT DIAGRAMS OF TH														 
2007013100007	20070131	00007		2007	1	31	2007FA0000067    	4	20060501	G	2330	1302046100	MONITOR         																	CABIN	MALFUNCTIONED   	B			BT7Y	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35										POTENTIAL FOR SMOKE IN THE CABIN CAUSED BY FAILURE OF ELECTRONIC COMPONENT WITHIN IFE SCREENS.  WHILE CARRYING OUT THE R	EPAIR OF 6.4 LCD IN ARM AND SEAT BACK UNITS, WORKSHOP TECHNICIANS NOTED DAMAGE TO A CAPACITOR (LABELED AS C100) ON THE C	IRCUIT CARD ASSY (CCA) WITHIN THE LCD.  ALTHOUGH THE UNIT WAS NOT REMOVED FROM AC FOR THIS DEFECT AND THE FAILURE OF THE	 COMPONENT DOES NOT APPEAR TO HAVE DETRIMENTAL AFFECT TOT HE PERFORMANCE OF THE UNIT, IT IS CONSIDERED THAT THE DAMAGE T	O THE CCA IS CONSIDERED A ONE-OFF INCIDENT AND THE WHOLE CCA WAS CHANGED.  THE CCA PN AFFECTED 1302160-102 AND 1302160-1	03.  NO DETAILED CIRCUIT DIAGRAMS OF THE CCA ARE AVAILABLE AS IT IS DEEMED TO BE A NON REPAIRABLE ITEM BY THE OEM.  AS A														 
2007013100081	20070131	00081	GL  	2007	1	31	2007FA0000068    	1	20060521	G	3230	194652	SPRING          			BLANCA	17    	1731A       	1220435	GL  	LYC   	O540  	IO540K1E5   	41532	EA  					NLG	WEAK            	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	15	14746	1944 				7532156	L1214948			AFTER AN INFLIGHT LANDING GEAR POWER PACK FAILURE, THE PILOT WAS UNABLE TO PERFORM AN EMERGENCY NOSE GEAR EXTENSION EVEN	 THOUGH THE MAIN GEAR WAS SAFELY EXTENDED.  DURING LANDING ROLLOUT, THE NOSE GEAR FOLDED CAUSING DAMAGE TO THE PROPELLER	 AND ENGINE.  AN UNSAFE NOSE GEAR INDICATION WAS SHOWN IN THE COCKPIT PRIOR TO LANDING.  PILOT STATES HE DID NOT DO (SHA	RP PULLUPS) AS CALLED OUT IN THE FLIGHT MANUAL IN AN ATTEMPT TO DOWNLOCK THE GEAR.  A NEW POWER PACK WAS INSTALLED, THE 	AIRCRAFT WAS PLACED ON JACKS AND NUMEROUS NORMAL AND EMERGENCY EXTENSIONS WERE PERFORMED, ALL WITHOUT INCIDENT, A COMPLE	TE CHECK WAS MADE OF THE GEAR RIGGING AND WAS FOUND CORRECT IAW MM.  THE NOSE GEAR EXTENSION SPRING WAS REMOVED AND THE 	1	L	7	1 	3O	3	O		A18CE   	1E4				 
2007012900358	20070129	00358	EU  	2007	1	29	2007FA0000069    	1	20061226	G	2400	ZN7168752608	RELAY           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540*      	41532	EA  					ELECTRICAL SYS	FAILED          	D			VJBS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	1913S	8    				1913				IT SEEMS THAT THE DEMAND OF THIS RELAY IN THE LANDING GEAR SYSTEM IS GREATER THAN THE DESIGNED LOAD USEAGE OF THE CURREN	T RELAY.  WOULD RECOMEND A HEAVIER DUTY RELAY, WHICH MFG HAS SINCE MADE AVAILABLE.  (K)					1	L	7	1 	3O	3	O	RT	A51EU   	1E4				 
2007022000014	20070220	00014	SO  	2007	2	20	2007FA0000093    	2	20061225	G	8520		CRANKSHAFT      			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	13	14690					7430637	224035R			CRANKSHAFT IS BROKEN IN AREA OF NR6, NR5 ROD JOURNAL.  CRANKSHAFT BROKE ON APPROACH TO LANDING AS PROP RPM CONTROL WAS A	DVANCED ON SHORT FINAL.  ENGINE POWER UNDER VERY LOW POWER.  ENGINE HAS NOT BEEN DISASSEMBLED YET.  THERE IS ALREADY AN 	AD NOTE TO TAKE THESE SHAFTS OUT OF SERVICE.  IT WAS A NON VAR SHAFT.  (K)				1	L	7	1 	3O	3	O		A18CE   	E5CE				 
2007021400057	20070214	00057		2007	2	14	2007FA0000094    	4	20060929	G	3417	702490031304	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FWD AVIONICS BAY	FAILED          	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	813AS					167				WHILE ENROUTE, THE PILOTS ALTIMETER FLAGGED AND OVERSPEED HORN TRIGGERED.  THE ADC BEGAN TO WORK AGAIN AT THE END OF THE	 FLIGHT.  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 HAS BEEN 2 PRIOR REPORTED FAILURES OF ADC`S IN THIS AIRCRAFT DA	TED MAY 6, 2005 AND NOV 21, 2005. (K)			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007013100064	20070131	00064	CE  	2007	1	31	2007FA0000097    	1	20061201	G	5520	243400018	ELEVATOR        			LEAR  	35    	36LEAR      	5170601	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RIGHT	SEPARATED       	C				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	21	26FN	12042				011				RT ELEVATOR DEPARTED THE AIRCRAFT AS THE AIRCRAFT EXPERIENCED AND APPROXIMATELY 70 DEGREE BANK, 50-60 DEGREE NOSE DOWN T	URN.  THE PILOT WAS FLYING IN A FORMATION AND WAS BLINDED BY THE SUN AND TURNED AWAY FROM OTHER AIRCRAFT.  AS THE ELEVAT	OR CAME OFF OF THE HORIZONTAL STABILIZER IT TOOK BOTH HINGE BRACKETS AND THE BELLCRANK ASSY WHERE THE PUSHROD TUBE ATTAC	HES.  BOTH THE HORIZONTAL SKIN AT THE OB END AND THE VERTICAL CAP WHERE BELLCRANK ASSY IS LOCATED ARE TORN AND DAMAGED. 	 FURTHER INVESTIGATION IS IN PROGRESS INCLUDING AN ALIGNMENT AND SYMMETRY INSPECTION OF THE AIRCRAFT. STRESS WILL BE EVA	LUATING THESE NR TO DETERMINE THE CAUSE AND THE VIABILITY OF THE AIRFRAME FOR REPAIR.  ATTACHED IS THE IRREGULARITY REPO	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007013100105	20070131	00105	SO  	2007	1	31	2007FA0000098    	1	20061130	G	2710	6755000	SUPPORT BRACKET 			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					RT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	4509X	9000 				28R7635067				CRACKS IN AILERON BELLCRANK LOWER SUPPORTS BOTH LT AND RT.  LOOK REAL CLOSE ON INSPECTION BECAUSE NUT AND WASHER COVER A	REAS.  (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
2007021300177	20070213	00177		2007	2	13	2007FA0000099    	1	20061109	G	6100	16160DTM	PROPELLER       													MCAULY	1C160	1C160DTM    	GL  		CRACKED         	B			F3PR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15			4818 					726964		CRACK DETECTED LENGTHWISE AT 9 INCH STATION.  LATEST LOGBOOK ENTRY FOR TSOH, DATED 7-28-2005.  (SW15200706340)  (K)																5	N	P910	 
2007021300160	20070213	00160	CE  	2007	2	13	2007FA0000100    	1	20061204	G	3210	ART73	ROD END         			MTSBSI	MU2   	MU2B36A     	5780413	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					MLG	BROKEN          	B			IZ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	777LP	10166				719SA				DURING GEAR EXTENSION FOR LANDING, A LOUD BANG WAS NOTICED BY THE PIVOT AND UNSAFE LIGHT STAYED ON.  AIRCRAFT WAS ROUTED	 TO MAINTENANCE AFTER LANDING.  MAINTENANCE FOUND ROD END ART -7E ON SHAFT HAD COME APART ANDALLOWED DOORS TO BECOME DIS	CONNECTED FROM ACTUATOR.  (SW15200706339)  (K)				1	H	7	2 	3T	3	T		A10SW   	E2WE				 
2007021300059	20070213	00059	NE  	2007	2	13	2007FA0000110    	1	20061125	G	5410	26007	STUD            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					RT NACELLE DOOR	BROKEN          	D				K				NONE                    				D	C		INFLIGHT SEPARATION       	F.O.D.                    		IN	INSP/MAINT     	1			EA	25	88CP	310  				760500	20542			ON POST-FLIGHT INSPECTION, MAINTENANCE CREW FOUND NR 2 ENGINE COMPRESSOR FOD.  WE DISCOVERED A MISSING COWL FASTENER STU	D IPC ITEM 16 FIG 53-20-03 PAGE 0.  WHEN FASTENER FAILS, THE LOCKING TAIL OF STUD FALLS INSIDE THE ENGINE AIR PLENUM AND	 THEN INGESTED BY ENGINE.  THIS TYPE OF FASTENER SYSTEM IS USED THROUGH OUT S76 ENGINE AIR PLENUM AREA.  THIS IS OUR 4TH	 EVENT OF THIS TYPE OF FAILURE CAUSING ENGINE FOD.  SUGGEST A BETTER QUALITY FASTENER THAT REMAINS INTACT UPON FAILURE, 	TO HELP PREVENT ENGINE FOD.  (K)		1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2007021300058	20070213	00058	NE  	2007	2	13	2007FA0000111    	1	20061215	G	2497	SPC38G	CAP             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					INVERTER FILTER	BURNED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	88CP	3240 				760500				INVERTER WIRING:  THE CREW REPORTED THE NR 1 INVERTER CAUTION LIGHT WOULD NOT COME ON WHEN THE INVERTER WAS SELECTED OFF	.  AFTER VERIFYING THE PROPER VOLTAGE AT THE RDAU THE AIRCRAFT WAS RAN AGAIN AND THE INVERTER CAUTION LIGHT WAS FUNCTION	ING NORMAL.  UPON AIRCRAFT RETURN FROM A TRIP THE CREW REPORTED THE NR 2 INVERTER WAS FAILED BUT STILL SHOWED VOLTAGE IN	DICATION ON THE DISPLAY.  AFTER TROUBLESHOOTING THE PROBLEM A SEVERELY BURNED AND MELTED WIRE WAS FOUND IN THE AC JUNCTI	ON BOX.  UPON REMOVAL OF THE AC JUNCTION BOX THE FOLLOWING WIRES WERE REPLACED.  (THIS WAS THE SEVERELY BURNED WIRE).  T	HE OTHER 2 WIRES LISTED WERE REPLACED DUE TO COLLATERAL DAMAGE FROM WIRE NR W1-036-0-22N THE INSULATION ON THESE 2 WIRES	1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2007021300090	20070213	00090	WP  	2007	2	13	2007FA0000116    	2	20060828	G	7250	31081251	TURBINE BLADES  								GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE	SEPARATED       	B				O				OTHER                   				A	J		FLAME/FIRE                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07		349  					P44616C			ENGINE WAS REPORTED TO HAVE FLAMES OUT OF TAILPIPE.  TEARDOWN OF ENGINE SHOWS THAT A TURBINE BLADE HAD SEPARATED AT THE 	FIRTREE.  BLADE DEBRIS CAUSED DAMAGE TO TURBINE OIL LINE, RESULTING IN A LEAK.  TURBINE DISC WAS REBLADED AT LAST MAINTE	NANCE EVENT.  TURBINE DISC/BLADES WERE PROVIDED TO MFG PROJECT ENGINEERING FOR MATERIAL ANALYSIS.  (K)									4	T			E4WE				 
2007021300137	20070213	00137	NM  	2007	2	13	2007FA0000123    	1	20060918	G	5320	6517684	INTERCOSTAL     			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 303 S10L	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				CABIN STA 303.9 JUST ABOVE STRINGER 10L.  INTERCOSTAL OUTER CHORD ANGLE, CRACKED.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300142	20070213	00142	NM  	2007	2	13	2007FA0000124    	1	20060926	G	5330	654577266	SKIN            			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 860-885	GOUGED          	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				UPPER FUSELAGE, STA 860 THRU 885, LBL 8 THRU RBL 8, UNDER DORSAL FIN BLADE SEAL, SKIN IS GOUGED.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300136	20070213	00136	NM  	2007	2	13	2007FA0000125    	1	20060926	G	5311	654653146	FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS500A S8-9R	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				UPPER FUSELAGE, BS 500A, BETWEEN STR 8R AND STR 9R, FRAME IS CRACKED AT PSU MOUNT.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300135	20070213	00135	NM  	2007	2	13	2007FA0000126    	1	20060927	G	5311	65465251	FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 727 S14L	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				FRAME IS CRACKED AT BODY STAION 727, STRINGER 14L.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300140	20070213	00140	NM  	2007	2	13	2007FA0000127    	1	20060918	G	5311	6546533	FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 500A S8-9L	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				MID CABIN, STA 500A FRAME, BETWEEN STRINGER 8 AND 9L, CRACKED AT PSU MOUNT RAIL ATTACH POINT.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021500201	20070215	00201	NM  	2007	2	15	2007FA0000128    	1	20060927	G	5330	6552988	SKIN            			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 727 S14L	DENTED          	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				BODY STATION 915 ABOVE STRINGER 25L LAP JOINT FUSELAGE SKIN HAS DENT.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100216	20070301	00216	NM  	2007	3	1	2007FA0000129    	1	20060924	G	5315	BAC1518399	FLOORBEAM       			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	GOUGED          	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				CABIN FLOORBEAM, STA 827, WL 203.6, RBL 10, LOWER T-CAP, AFT FLANGE, GOUGED.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300141	20070213	00141	NM  	2007	2	13	2007FA0000130    	1	20060918	G	5311	69353521	FRAME           			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 400 S8R	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				MID CABIN, STATION 400 FRAME AT STRINGER 8R, CRACKED AT PSU RAIL OUNT ATTACH POINT.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300139	20070213	00139	NM  	2007	2	13	2007FA0000131    	1	20060918	G	5310	65807351	CREASE BEAM     			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 947-992 S17R	CORRODED        	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				AFT GALLEY DOOR CREASE BEAM INNER CHORD ANGLE, BS 947 TO 992, STRINGER 17R, WL 208, CORROSION OUT OF LIMITS.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300161	20070213	00161	NM  	2007	2	13	2007FA0000132    	1	20060817	G	5315	BAC1518399	FLOORBEAM       			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 312	CORRODED        	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				CABIN BS 312, FROM LBL 55 TO RBL 55 WL 208, FLOORBEAM HAS LIGHT CORROSION.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007022000179	20070220	00179	NM  	2007	2	20	2007FA0000133    	1	20060924	G	5311	65465935	FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				CABIN, BS 787, FRAME AT STR 8R, CRACKED AT STOW BIN ATTACH BRACKET.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007022000180	20070220	00180	NM  	2007	2	20	2007FA0000134    	1	20060924	G	5312	6545409245	PRESSURE PANEL  			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				MID CABIN BS 663, LBL 31, WHEEL WELL PRESSURE DECK WEB, CRACKED.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007022700080	20070227	00080	NM  	2007	2	27	2007FA0000135    	1	20060927	G	5311	65465251	FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 727 S4L	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				FRAME IS CRACKED AT BODY STATION 727, STRINGER 14L.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100206	20070301	00206	NM  	2007	3	1	2007FA0000136    	1	20060924	G	5320	6580736689	FITTING         			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CORRODED        	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				DOOR 1R, BS 306-312, WL 248-249, LBL 57-63, SERPENTINE PLATE CASTING CORRODED AROUND FASTENER HOLES.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100209	20070301	00209	NM  	2007	3	1	2007FA0000137    	1	20060918	G	5340	693535214	STRINGER CLIP   			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US					23931				PASSENGER CABIN, STATION 639 AT STRINGER 4L, STRINGER CLIP, CRACKED.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100213	20070301	00213	NM  	2007	3	1	2007FA0000138    	1	20060918	G	5311		FRAME           			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US	53459				23931				MID CABIN, STATION 480 FRAME, AT STRINGER 8L, CRACKED AT PSU MOUNT RAIL ATTACH POINT.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100218	20070301	00218	NM  	2007	3	1	2007FA0000139    	1	20060918	G	5311	6546533	FRAME           			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US					23931				MID CABIN, STATION 500A FRAME, BETWEEN STRINGER 8 AND 9L, CRACKED AT PSU MOUNT RAIL ATTACH POINT.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100217	20070301	00217	NM  	2007	3	1	2007FA0000140    	1	20060918	G	5210	69773671	SUPPORT         			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					R2 DOOR	CRACKED         	B			I6XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	586US					23931				AT FWD CABIN STA 328+6, DOOR 2R AFT STOP FTG INTERCOSTAL TEE SUPPORT, CRACKED.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007030100203	20070301	00203	CE  	2007	3	1	2007FA0000142    	1	20061126	G	5210	MJV3	VALVE           			CESSNA	500   	550         	2076604	CE  										CABIN DOOR	OUT OF POSITION 	E			ON0A	B				EMER. DESCENT           				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	50NF					5500636				AT G; 390 15A, -12 DEGREES CABIN DOOR SEAL DEFLATED NECESSATING AN EMERGENCY DESCENT TO 10,000 FT.  AFTER 5-8 MINUTES, D	OOR SEAL RE-INFLATED OPERATION WAS NORMAL, CONDITION DID NOT REOCCUR.  FOUND DOOR SEAL VALVE WARM AIR TUBE BLAOCKED BY T	APE AND OUT OF POSITION.  REMOVED TAPE, POSITIONED WARM AIR TUBE PROPERLY.  (K)				1	L	7	2 	4F				A22CE   					 
2007022600154	20070226	00154	CE  	2007	2	26	2007FA0000143    	1	20061126	G	2720	0510105207	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					RUDDER	BROKEN          	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SO	19	1653V	4993 				17263703				RUDDER CONTROL CABLE BRAKES DURING FLIGHT TRAINING WHILE PERFORMING FORWARD SLIP MANEUVER ON FINAL APPROACH.  INITIAL IN	SPECTION SHOWS CABLE BROKE JUST FORWARD OF TERMINAL END AT THE LOWER BELL CRANK.  FURTHER INSPECTION REVEALED THE CAUSE 	OF FAILURE TO BE CORROSION INSIDE THE STEEL CABLE (PN 0510105207).  SINCE THE LOWER RUDDER BELLCRANK AREA IS EXPOSED TO 	THE ELEMENTS OUTSIDE OF THE AIRCRAFT, RECOMMENDATIONS IS TO REPLACE THE RUDDER CONTROL CABLE WITH STAINLESS STEEL TYPE (	PN 0510105305) AVAILABLE FROM THE OEM.  (K)		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007030900334	20070309	00334	SO  	2007	3	9	2007FA0000152    	2	20061020	G	8530	SA52006A1	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  						CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		900  								PRESSURE TESTED AT 90 PSI WITH SOAPY WATER APPLIED TO EXHAUST SIDEWALL.  AIR LEAKAGE NOTED BETWEEN FINS 19/20 & 20/21.  	(K)					1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2007030900335	20070309	00335	SO  	2007	3	9	2007FA0000153    	2	20061020	G	8530	SA52006A1	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  						CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		900  								PRESSURE TESTED AT 90 PSI WITH SOAPY WATER APPLIED TO EXHAUST SIDE WALL.  AIR LEAKAGE NOTED BETWEEN FINS 19/20 AND 20/21	.  (K)					1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2007030900336	20070309	00336	SO  	2007	3	9	2007FA0000154    	2	20061020	G	8530	SA52006A1	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  						CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										PRESSURE TESTED AT 90 PSI WITH SOAP WATER APPLIED TO EXHAUST SIDEWALL.  AIR LEAKAGE NOTED BETWEEN FINS 19/20 AND 20/21. 	 (K)					1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2007030100241	20070301	00241	CE  	2007	3	1	2007FA0000160    	1	20061216	G	5514	45A21085003	BRACKET         	BEECH       		BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZ STAB	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	93XP	7251 				RK74				DURING INSPECTION OF HORIZONTAL STABILIZER ROLLER BRACKETS AND STRUCTURE IAW COMMUNIQU NR 70, FOUND LT HORIZONTAL STABI	LIZER FWD ROLLER BRACKET, PN 45A21085-003, AND LT AFT ROLLER BRACKET, PN 45A21086-003, BOTH CRACKED.  MFG AC TECH SUPPOR	T BELIEVES IMPROPER VERTICAL STABILIZER TO ROLLER GAP CLEARANCES MAY BE CONTRIBUTING TO PROBLEM.  INSPECTION AREA NOT CU	RRENTLY NOTED ON MM AND 5-20-02 INSPECTION GUIDES, REQUIRES BORESCOPE TO INSPECT UNDERLYING STRUCTURE.  RECOMMEND A 1-TI	ME SB AND/OR SAIB.  SHOULD BE ADDED TO INSPECTION GUIDES.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007030100251	20070301	00251	CE  	2007	3	1	2007FA0000161    	1	20061213	G	3310		TRANSISTOR      			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					COCKPIT	SHORTED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	66AM	2398 				5250160				INVESTIGATED COCKPIT OVERHEAD FLOODLIGHTS TRIPPING ASSOCIATED CB WHEN BATTERY POWER APPLIED TO AIRCRAFT.  FOUND ATTACHIN	G SCREW FOR QC001 TRANSISTOR SHORTING TO AIRFRAME.  ALSO, FOUND RESISTOR NR150 ON THRUST ATTENTUATOR PC BOARD NZ017 BURN	ED.  REPAIRS REQUIRED REPLACING QC001 TRANSISTOR AND BASE, INSULATING QC001 ATTACHING SCREW, REPLACING DIODE DC046, AND 	REPLACING PC BOARD JC045.  RECOMMENDED FURTHER INVESTIGATION TO DETERMINE IF A FLEET PROBLEM REQUIRING MODIFICATIONS TO 	PREVENT TRANSISTOR ATTACHING SCREW FROM SHORTING TO AIRFRAME.  (K)		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2007030900169	20070309	00169		2007	3	9	2007FA0000197    	4	20060904	G	2565	BACR12BU9B	RING            	AIRCRUISERS 		BOEING	727   	72722C      	138400F	NM  										EVAC SLIDE	ELONGATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	942UP				1128	19101				DURING ROUTINE C-CHECK INSPECTION OF FORWARD DOOR EMERGENCY ESCAPE SLIDE, THE SLIDE BUSTLE LATCH CHAIN WAS FOUND DETACHE	D FROM THE SPLIT RING.  THE SPLIT RING HAD BECOME ELONGATED AND THE RING COILS HAD SEPARATED THUS ALLOWING THE CHAIN TO 	DETACH.  THE SLIDE WOULD NOT HAVE INFLATED IF REQUIRED.  THE SPLIT RING HAS BEEN REPLACED.  (K)				2	L	7	3 	4F				A3WE    					 
2007040200220	20070402	00220	CE  	2007	4	2	2007FA0000198    	1	20060726	G	5210	511150480	BOLT            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					PAX DOOR	CORRODED        	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	485DS	4783 				421C0459				DURING ACCOMPLISHMENT OF ANNUAL INSPECTION, EXCESSIVE PLAY WAS NOTED AT AFT HINGE POINT OF UPPER MAIN CABIN DOOR.  INVES	TIGATION REVEALED THAT HINGE BOLT WAS BROKEN, HEAD OF BOLT COULD BE TURNED, BUT END WITH NUT WOULD NOT FOLLOW.  TRIED TO	 REMOVE BOLT BUT WAS UNABLE TO REMOVE EITHER PIECE.  ATTEMPTED TO REMOVE FORWARD BOLT AS THE WHOLE DOOR ASSY HAD TO BE R	EMOVED FOR FURTHER INSPECTION, BUT WERE UNABLE TO REMOVE IT EITHER.  HAD TO FINALLY REMOVE HINGES FROM DOOR AND REMOVE H	INGE SUPPORTS FROM THE FUSELAGE STRUCTURE.  FOUND THAT THE BOLTS AND BUSHINGS IN THE HINGES WERE EXCESSIVELY CORRODED WH	ICH PREVENTED THEM FROM BEING REMOVED.  IN ORDER TO DISASSEMBLE THE FWD HINGE, IT WAS NECESSARY TO HACKSAW OFF THE HEAD 	1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007030900044	20070309	00044	EA  	2007	3	9	2007FA0000213    	2	20060627	G	8520	LW18372	CRANKCASE       	LYC         	O320D3G     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	8391Y	4648 	280  		RL1519539A	288116235	RL1519539A			DURING 100 HOUR INSPECTION A CRACK WAS DISCOVERED ON RT CRANKCASE HALF.  THE CRACK (APPROXIMATELY 1 INCH) ORIGINATED FRO	M A LOWER PARTING FACE BOLT HOLE AND SHOWED EVIDENCE OF OIL LEAKAGE ONTO MUFFLER SHROUD (BURNED OIL).  SPECIFIC CAUSE OF	 CRACK UNKNOWN.				1	L	7	1 	3O	3	O		2A13    	E274				 
2007030900337	20070309	00337	SO  	2007	3	9	2007FA0000216    	2	20060821	G	8530	SA52006A1	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  						CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		690  								PENETRANT TEST INDICATES CRACKS BETWEEN FINS 20/21 ADJACENT TO THE EXHAUST SEAT AND BETWEEN 19/20 NEARER TO THE UPPER SP	ARK SPLUG SIDE OF THE EXHAUST CHAMBER.  (K)					1	H	7	1 	3O	3	O		A16CE   	E5CE				 
2007032200074	20070322	00074	SW  	2007	3	22	2007FA0000239    	1	20061020	G	3300	1220	LIGHT           			AIRTRC	AT802 	AT802       	0390305	SW  											FAILED          	F				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AG	AGRICULTURE    	1			NM	09										PULSELIGHT UNIT FAILED.  EVALUATION OF FAILED UNIT REVEALED HIGH HEAT GENERATED WITHIN UNIT AND SIGNIFICANT BURNING.						1	L	7	1 	3T			NC	A19SW   					 
2007032600099	20070326	00099	NM  	2007	3	26	2007FA0000248    	1	20061216	G	2497		WIRE HARNESS    			DOUG  	MD80  	MD83        	3023681	NM  										BS 905	CHAFED          	G				A				UNSCHED LANDING         				A			FLAME/FIRE                			CL	CLIMB          	1			GL	03										MAIN CABIN AT RT STATION 905 WIRING BUNDLE CHAFED THROUGH ON PARTITION CAUSING FIRE AND SMOKE DAMAGE.  THE PARTITION AND	 THE WIRING BUNDLE LOCATIONS WERE INSTALLED AND POSITION AS PART OF AN EXECUTIVE CABIN INTERIOR MODIFICATION.  50 + WIRE	S, INTERIOR PANELS, INSULATION BLANKETS AND ONE CEILING RAIL WERE DAMAGED.				2	L	7	2 	4F			RT	        					 
2007050700008	20070507	00008	CE  	2007	5	7	2007FA0000347    	1	20061203	G	3220	3A07000001	SCREW           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG	DEPARTED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	8JZ					U20602326				AIRCRAFT HAD GEAR UP LANDING, FOUND SCREW PN AN503-8-4 HAD FALLEN OUT.  SCREW WAS TO BE SAFTIED, NO SAFETY WIRE FOUND.  	ONCE SCREW FELL OUT THE POWER PISTON HOUSING PN 3A07402-002 WAS ALLOWED TO FLEX DURING SUB CYCLES ALLOWING THE SCREW TO 	TEAR THE ORING ON THE HOUSING FLANGE AND PUMP ALL THE HYD (5606) FLUID OVERBOARD AND NOT ALLOWING THE MAIN GEAR THE EXTE	ND.  THE SCREW HOLE WHERE THE SCREW FELL OUT ON THE PISTON HOUSING TORE OUT.  REPLACED THE PISTON HOUSING PN 3A07000-001	, ALL ORINGS AND INSTALLED NEW SCREWS PN AN503-8-4 AND SAFTIED.  SWING LDG 6X`S AND RELEASED AIRCRAFT.  (K)		1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007050400167	20070504	00167	CE  	2007	5	4	2007FA0000376    	1	20060907	G	7810	02R3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		11322	431  				PCE85195			WHILE PERFORMING SCHEDULED MAINTENANCE,REMOVED LT ENGINE EXHAUST STACK TO FACILITATE INSPECTING THE EXHAUST DUCT. FOUND 	CRACK FOLLOWING THE CIRCUMFERENCE OF THE SKI SLOPE. THE EXHAUST DUCT HAD PWA SB 3380 COMPLIED WITH 431 HOURS EARLIER.  P	OWER SECTION WAS REMOVED AND SENT FOR REPAIR.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300222	20070613	00222	CE  	2007	6	13	2007FA0000407    	1	20060904	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		13769	657  							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				 
2007061300224	20070613	00224	CE  	2007	6	13	2007FA0000409    	1	20060812	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		14327	979  							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				 
2007060400002	20070604	00002	WP  	2007	6	4	2007FA0000418    	1	20060501	G	6210	C0165	BLADE           			ROBSIN	R44   	R44RAVENII  	7640122	WP  										MAIN ROTOR	DEBONDED        	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			SW	99	CFICL	5    	1    							IN FLIGHT BREAK UP. HELICOPTER CRASHED KILLED 2 HUMANS. NO REACTION TIME TO LAND SAFELY, PILOT WAS EJECTED OUT OF SEAT B	Y BLADE, KILLED INSTANTLY.					1	G	7	1 	3O				H11NM   					 
2007061300219	20070613	00219	CE  	2007	6	13	2007FA0000424    	1	20060820	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		13926	2030 							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				 
2007061300213	20070613	00213	CE  	2007	6	13	2007FA0000432    	1	20060705	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		11753	431  							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 BEEN COMPLIED WITH 515.2 HOURS PRIOR.POWER SECTION WAS REMOVED FOR REPAIR	.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300220	20070613	00220	CE  	2007	6	13	2007FA0000441    	1	20060908	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		16012	660  							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				 
2007061300169	20070613	00169	WP  	2007	6	13	2007FA0000449    	1	20060501	G	6210	C0165	BLADES          			ROBSIN	R44   	R44RAVENII  	7640122	WP  										MAIN ROTOR	DEBONDED        	C				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			O			OTHER                     			CR	CRUISE         	1			SW	99	CFICL	5    	1    							IN FLIGHT BREAK UP. HELICOPTER CRASHED KILLED 2 HUMANS. NO REACTION TIME TO LAND SAFELY, PILOT WAS EJECTED OUT OF SEAT B	Y BLADE KILLED INSTANTLY.					1	G	7	1 	3O				H11NM   					 
2007060500214	20070605	00214	CE  	2007	6	5	2007FA0000452    	1	20061212	G	3600	IU478003	PISTON          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					AIR PUMP	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	9899Q	65   				17265843	L42B2427A			INSTALLED A PISTON AIR PUMP (PN IU478-003, SER NR T568A) ON AUG 25, 2005.  THE PUMP DRIVE COUPLING FAILED BY 12/06 WITH 	LESS THAN 66 HOURS ON IT.  COUPLING FAILED INTERNALLY IN PUMP, WITH PLASTIC/SILICON DEBRIS IN ENG/DRIVE INTERFACE. (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007080800059	20070808	00059	CE  	2007	8	8	2007FA0000663    	1	20061121	G	5740	187504	CONTROL ARM     			BEECH 	18    	RC45J       	1151021	CE  	PWA   	R985  	R985*       	52008	NE  					ELEVATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	145J	9544 				51233				DURING COMPLIANCE WITH AD 77-19-07 PARA B, DYE PENETRANT INSPECTION REVEALED 2 POSSIBLE DEFECTS, 0.75 INCH AND 0.5 INCH 	LONG.  BOTH INDICATIONS RADIATING FROM THE TAPERED PIN ON THE STARBOARD SIDE OF THE CONTROL ARM.  INDICATIONS CONTINUED 	TO APPEAR AFTER REPEATED SURFACE POLISHING AND DYE PENTRANT, ALTHOUGH NO DEFINITIVE.  OTHER DEFECTS AND/OR INDICATIONS O	BSERVED.  INDICATIONS MAY NOT ACTUALLY HAVE BEEN A CRACK, THE INTERMITTENT LINES MAY BE OLD SURFACE FLAWS.  HOWEVER, IT 	WAS DECIDED THAT THE BEST COURSE OF ACTION WAS TO REPLACE PART.  OLD PART DID HAVE THE SMALLER AN 386-3-18 TAPERED PINS,	 INSTEAD OF THE LARGER, AN 386-5-18 PINS USED ON THE LATER MFG ELEVATOR CONTROL ARMS, THIS MAY HAVE BEEN A CONTRIBUTING 	1	L	7	2 	3R	3	R		A765    	5E1				 
2007090600042	20070906	00042	SW  	2007	9	6	2007FA0000734    	1	20060724	G	2424	800397501	VOLT REGULATOR  			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  						FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	999JW	296  				290293				THE INABILITY OF THE VOLTAGE REGULATOR (PN 800397-501, SN 0165) TO CONTROLTHE OUTPUT OF THE ALTERNATOR WHEN THE BATTERY 	SWITCH WAS TOGGLED BETWEEN THE NR1 AND NR 2 BATTERY, IN FLIGHT.  (K)					1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2007091700073	20070917	00073		2007	9	17	2007FA0000756    	4	20061112	G	2565	46FASA0303603	LIFE RAFT       			AMD   	FALC20	FALCON      	2720302	EU  	GARRTT	TFE731	TFE73160    	 	NE  						PARTIAL INFLATE 	B			QLCR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	11	191MC					282				THE LIFE RAFT VACUUM BAG INFLATED DUE TO CYLINDER LEAKAGE BETWEEN THE CYLINDER HEAD AND LIFE RAFT CYLINDER.  THE AC WAS 	CRUISING AT 40,000 FT WHEN THE PILOT HEAR A LOUD POP.  UPON INVESTIGATION, THE PILOT HAD DISCOVERED THE LIFE RAFT HAD AN	 UNCOMMANDED INFLATION.  THE BANDS AROUND THE LIFE RAFT CONTAINER HELD THE LIFE RAFT TOGETHER AND IT WAS LATER REMOVED F	ROM UNDER THE COUCH.			2	L	7	2 	4F	4	F		A7EU    	E1NM				 
2007091700068	20070917	00068		2007	9	17	2007FA0000757    	4	20061016	G	2565	46FASA2311323	LIFE RAFT       																		PARTIAL INFLATE 	B			QLCR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11										LIFE RAFT PARTIALLY INADVERTENTLY INFLATED IN CUSTOMERS AC CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAU	SED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FL	IGHT.  THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING TH	E POSSIBILITY OF SEVERE DAMAGE.  IT WAS DETERMINED THAT THE INFLATION CYLINDER HEAD WAS LEAKING AT THE POINT WHERE  IT A	TTACHES TO THE INFLATION CYLINDER.  THIS LIFE RAFT WAS NOT COVERED UNDER THE MFG SIL (SIL001STS) DATED 11/21/2005.  (K)															 
2007120400106	20071204	00106	CE  	2007	12	4	2007FA0000993    	1	20060828	G	2750	SM50D7	RELAY           			BEECH 	200   	B200        	1152922	CE  										TE FLAP MOTOR	INTERMITTENT    	D				O				OTHER                   				S			AFFECT SYSTEMS            			DE	DESCENT        	1			WP	19	185XP	514  				BB952				DURING FLIGHT WHEN THE FLAPS SELECTED DOWN & DID NOT RESPOND.  AIRCRAFT LANDED IN A FLAPS UP CONDITION & DELIVERED TO MA	INTENANCE. INVESTIGATION REVEALED THE FLAP MOTOR POWER RELAY WAS OPERATING INTERMITTENTLY.  A NEW FLAP MOTOR RELAY, PROC	URED FROM RAPID (RAYTHEON PARTS INVENTORY AND DISTRIBUTION SYSTEM) WAS INSTALLED AND THE MALFUNCTION WAS RESOLVED.  THE 	REMOVED / FAILED RELAY HAD BEEN IN SERVICE 22 MONTHS AND 514.5 FLIGHT HOURS.			1	L	7	2 	4T				A24CE   					 
2006071100107	20060711	00107	EA  	2006	7	11	2050506          	2	20060621	G	7414		BUSHING         	LYC         	IO360A3B6D  	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					MAGNETO DRIVE	LACK OF LUBE    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	386OH				568	241044	L2178051A			CRANKCASE WAS FIELD REPAIRED BY INSTALLING A BUSHING IN THE MAGNETO DRIVE GEAR BOSS. IT APPEARS THE OIL SUPPLY HOLE WAS 	NOT DRILLED IN THE BUSHING. THE BUSHING WAS STARVED FOR OIL AND METAL WAS FOUND IN THE OIL AND FILTER, THE BUSHING WAS L	OOSE AND DAMAGED FROM OIL STARVATION.				1	L	7	1 	3O	3	O		2A3     	1E10				 
2006051200063	20060512	00063	CE  	2006	5	12	21200003AD       	1	20060510	G	2730	083200054	HINGE           			CESSNA	421   	421B        	2076014	CE  										ELEVATOR	DAMAGED         	B				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			SW	99	1944G	8307 				421B0844				CUSTOMER REPORTED VIBRATION AT HIGH SPEEDS. INSPECTED AIRCRAFT AND FOUND CENTER ELEVATOR HINGE INBOARD AND OUTBOARD BRAC	KETS ELONGATED ON THE RIGHT ELEVATOR. INSTALLED CESSNA SERVICE KIT SK421-130B REPLACING ALUMINUM ELEVATOR HINGE BRACKETS	 WITH STAINLESS STEEL BRACKETS.				1	L	7	2 	3O				A7CE    					 
2006080300060	20060803	00060	GL  	2006	8	3	25869            	3	20060725	G	6110		STRUCTURE       	MCAULY      		CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	PILOT BORE	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	428DW	2099 			TI014	172S8708		TI014		PROPELLER PILOT BORE FOUND CRACKED BY PENETRANT INSPECTION BEING PERFORMED DURING OVERHAUL						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006051600091	20060516	00091	CE  	2006	5	16	314901           	1	20060511	G	3246	314901	WHEEL           			CESSNA	500   	550         	2076604	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										FINDING FATIGUE CRACKS FORMING AT THE INTERSECTION OF THREADED HOLE AND DRILLED PASSAGE OF FUSE PLUG HOLE AND VALVE STEM	 HOLE.					1	L	7	2 	4F				A22CE   					 
2006032100210	20060321	00210	CE  	2006	3	21	3969             	1	20060224	G	2820	00292000051	LINE            			BEECH 	58    	58          	1152740	CE  										ZONE 600	CHAFED          	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	6458C	7236 				TH1495				DURING SCHEDULED INSPECTION FOUND FUEL CROSSFEED LINE IN RT WHEEL WELL CHAFED 75 PERCENT THROUGH BY LANDING GEAR RETRACT	 ROD.					1	L	7	2 	3O				3A16    					 
2006031500138	20060315	00138	SO  	2006	3	15	4381             	1	20060207	G	2420	51530007B	GCU             			PIPER 	PA30  	PA30        	7103002	SO  										LT GEN	INOPERATIVE     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	1509					30798				AIRCRAFT CAME IN FOR GENERATOR PARALLELING.  LEFT GENERATOR CONTROL UNIT NEEDED REPLACEMENT.  INSTALLED OVERHAULED GCU S	/N 10853A; GCU FAILED ON INITIAL RESET.  INSTALLED SECOND GCU S/N 9183; GCU FAILED ON INITIAL RESET. (BOTH ABOVE GCU'S H	AD JUST BEEN OVERHAULED BY PRECISION ELECTRONICS, INC., ATLANTA, GA FOR THE SAME INITIAL FAILURE PROBLEM).  INSTALLED A 	THIRD GCU S/N 9657; WHICH FUNCTIONED CORRECTLY.  (ALSO OVERHAULED BY PRECISION ELECTRONICS, INC.)			1	L	7	2 	3O				A1EA    					 
2006031500174	20060315	00174	CE  	2006	3	15	4381002          	1	20060207	G	2420	51530007B	GCU             			BEECH 	200   	B200        	1152922	CE  										LT GEN	MALFUNCTIONED   	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	1509G					BB1308				AIRCRAFT CAME IN FOR GENERATOR PARALLELING.  LEFT GENERATOR CONTROL UNIT NEEDED REPLACEMENT.  INSTALLED OVERHAULED GCU S	/N 10853A; GCU FAILED ON INITIAL RESET.  INSTALLED SECOND GCU S/N 9183; GCU FAILED ON INITIAL RESET.  BOTH ABOVE GCU'S H	AD JUST BEEN OVERHAULED BY PRECISION ELECTRONICS, INC., ATLANTA, GA FOR THE SAME INITIAL FAILURE PROBLEM.  INSTALLED A T	HIRD GCU S/N 9657; WHICH FUNCTIONED CORRECTLY, ALSO OVERHAULED BY PRECISION ELECTRONICS, INC.			1	L	7	2 	4T				A24CE   					 
2006051200128	20060512	00128	SO  	2006	5	12	4437811          	1	20060418	G	7160	P151936	AIR FILTER      			PIPER 	PA32  	PA32R301T   	7103220	SO  										ENGINE	DEBONDED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	30538					3257343				PN P560007-3, GASKET HAD SEPERATED FROM FILTER ON ONE SIDE AND WAS PULLED INTO THE AIR STREAM ON THE ENGINE SIDE OF THE 	FILTER.  INSTALLED NEW FILTER.					1	L	7	1 	3O				A3SO    					 
2006102500106	20061025	00106	EA  	2006	10	25	5292S1006        	2	20061013	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CE	07	5292S					2826923				PILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND	 ENGINE FAILURE.  PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY.  NO DAMAGE TO AIRCRAFT UPON L	ANDING. UPON EXAMINATION OF THE ENGINE, FOUND NR 3 CYLINDER EXHAUST VALVE HEAD FAILURE AND FRAGMENTS OF FAILED EXHAUST V	ALVE HEAD FOUND IN INDUCTION SYSTEM.			1	L	7	1 	3O	3	O		2A13    	E274				 
2006041300260	20060413	00260	SO  	2006	4	13	5784607          	1	20060215	G	2720	63457003	ARM             			PIPER 	PA32  	PA32300     	7103212	SO  										RUDDER CONTR	BROKEN          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	19	4209R	5100 				3240574				ONE OF THE THE CLIPS (PIPER PN 62832-000) IN THE RUDDER TRIP TUBE YIELDED AND SLIPPED OVER THE END OF THE SPRING. THIS C	AUSED THE RUDDER TRIM SPRING TO BIND IN ITS TUBE, RESULTING IN THE RUDDER CONTROL ARM (PIPER PN 63457-003) BREAKING WHER	E THE TRIM ATTACHES. THIS CAUSED LOSS OF RUDDER TRIM AND NOSE-WHEEL CENTERING. RUDDER CONTROL AND NOSEWHEEL STEERING WER	E UNAFFECTED.I HAVE PHOTOS OF THE FAILED PARTS I CAN EMAIL IF SOMEONE LET'S ME KNOW WHERE TO SEND THEM.			1	L	7	1 	3O				A3SO    					 
2006072400030	20060724	00030	GL  	2006	7	24	60806            	3	20060608	G	6111	FC7663R	BLADE           	HARTZL      							LYC   	O540  	IO540K1K5   	41532	NE  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		854  	854  		EL223A	1800		EL223A		CRACKED BLADE SHANK.											3	O			1E4	5	C	P25EA	 
2006072400022	20060724	00022	GL  	2006	7	24	608062           	3	20060608	G	6111	D68315A	CLAMP           	HARTZL      		GULSTM	500   	500         	0141K02	SW  	LYC   	O540  	O540*       	41532	EA  	HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		1008 			HWA49	791		HWA49		BLADE CLAMPS CRACKED.						1	H	7	2 	3O	3	O	RT	6A1     	E295	5	C	P24EA	 
2006072400024	20060724	00024	GL  	2006	7	24	608063           	3	20060608	G	6111	D68315A	CLAMP           	HARTZL      		GULSTM	500   	500         	0141K02	SW  	LYC   	O540  	O540*       	41532	EA  	HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		1008 			HWA49	791		HWA49		BLADE CLAMP CRACKED.						1	H	7	2 	3O	3	O	RT	6A1     	E295	5	C	P24EA	 
2006051800180	20060518	00180	SW  	2006	5	18	77669            	1	20060301	G	6100		HUB             	HARTZL      	HCB3Z302    	GULSTM	680   	680F        	0141606	SW  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CORRODED CLAMP ASSEMBLY, PN 838-17, SN J4324, U4701, U4646.  CORRODED BLADES MODEL NR 9349, SN A41967, A41996, A41251.						1	H	7	2 	3O				2A4     		5	C	P907	 
2006051200048	20060512	00048	GL  	2006	5	12	77670            	3	20060213	G	6110		CLAMP           			GULSTM	680   	680F        	0141606	SW  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER ASSY	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CORRODED CLAMP ASSEMBLY PN 838-17, SN U5211, U5188, U5109.						1	H	7	2 	3O				2A4     		5	C	P907	 
2006051800179	20060518	00179	GL  	2006	5	18	78978            	3	20060306	G	6114	D7292C203	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CORRODED HUB.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
2006051200068	20060512	00068	GL  	2006	5	12	79965            	3	20060404	G	6114	E71693	HUB             			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										HUB CORRODED BEYOND REPAIR IAW MFG OVERHAUL MANUAL.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
2006022400158	20060224	00158	CE  	2006	2	24	8862             	1	20060115	G	3246	50107201	WHEEL           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT MLG	MISOVERHAULED   	B			YGJR	C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			GL	17	234DK		24   			RK182				LT MAIN TIRE DISINTEGRATED ON T/O ROLL. AFTER REMOVING WHEEL ASSY, DISCOVERED WHEEL HALVES O-RING EXPOSED BY VALUE STEM.	 UPON INVESTIGATION DISCOVERED WHEEL WAS NOT OVERHAULED IAW A/C BRAKING SYSTEMS COMPONENT MM.  INBOARD WHEEL HALF WAS NO	T REMARKED IAW TEMPORARY REVISION NO. 32-6 TO COMPONENT MM MAIN WHEEL ASSY 5010720. UPON INVESTIGATION DISCOVERED THAT T	HE OTHER MAIN WHEEL INBOARD WHEEL WAS NOT REMARKED EITHER. THE SPARE WHEEL WHICH WAS OVERHAULED BY THE SAME REPAIR STATI	ON WAS NOT MARKED EITHER.		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006032400004	20060324	00004	CE  	2006	3	24	8921             	1	20060303	G	2897	281810613	RELAY           			LEAR  	35    	31          	5170530	CE  										FUEL PANEL	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	00	XAJYC					30				LEFT ENGINE WOULD NOT START.  TROUBLESHOT TO SHORTED RELAY ON FUEL RELAY PANEL.						2	L	7	2 	4F			RT	A10CE   					 
2006061900238	20060619	00238	EU  	2006	6	19	AACSDR061006B    	1	20060610	G	2150		LINE            	AIRCOM      		AGUSTA	A109  	A119        	0261102	EU  										AIR CONDITIONER	MAINT ERROR     	B			DT1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	119RW					14508				AIR CONDITIONING SYSTEM STC NR SR00463DE UTILIZES RIGID FREON LINES RUNNING FORE AND AFT ON THE ENGINE DECK.  AT THE FOR	WARD END, THESE LINES CONNECT TO FLEX LINES. AT THIS CONNECTION THE LINES WERE SWAPPED. THE CONNECTIONS ARE LOCATED RIGH	T NEXT TO EACH OTHER AND THE LINES RUN PARALLEL, MAKING THIS A VERY EASY MISTAKE. THESE LINES SHOULD UTILIZE DIFFERENT F	ITTINGS TO PREVENT THIS FROM HAPPENING.			1	G	7	2 	3U				H7EU    					 
2007051100154	20070511	00154	SW  	2007	5	11	AACSDR121406     	1	20061214	G	5302	3P5340A11951	LONGERON        			AGUSTA	AB139 	AB139       	0260110	SW  	PWA   	PT6   	PT6*        	52043	EA  					TAILBOOM	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	805HD					31051				DURING INSPECTION OF THE TAILBOOM ATTACHMENT POINTS, A CRACK ABOUT 1.5 INCHES LONG WAS DISCOVERED ON THE TOP LT LONGERON	 AT STA 8700MM.					2	G	7	2 	6U	3	T		R00002RD	E2NE				 
2006071100108	20060711	00108		2006	7	11	AACSDR61006      	1	20060610	G	5302	1090371231	LONGERON        	AGUSTA      																TAILBOOM	CRACKED         	B			DT1R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	17	45HV	1900 			A7093					DURING FLIGHT A BANG WAS HEARD, AIRCRAFT SHUDDERED MOMENTARILY, PILOT SUSPECTED BIRD STRIKE. FLIGHT CONTINUED TO LANDING	 SITE. AIRCRAFT WAS INSPECTED FOR DAMAGE, NO EVIDENCE OF BIRD STRIKE OR ANY DAMAGE WAS NOTED. DURING A SUBSEQUENT AIRFRA	ME INSPECTION LT UPPER TAILBOOM TO FUSELAGE FITTING WAS FOUND CRACKED.  A/C AND COMPONENT TOTAL TIME APPROXIMATELY 1900.	0 HRS.																 
2007051100152	20070511	00152	SW  	2007	5	11	AACSDR61606      	1	20060616	G	6510		DRIVE SHAFT     			AGUSTA	AB139 	AB139       	0260110	SW  										TAIL ROTOR	UNBONDED        	B			DT1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	XA001	13   				31047				NEW AIRCRAFT WAS BEING ASSEMBLED AFTER SHIPPING. DURING ASSEMBLY TAIL ROTOR DRIVESHAFT WAS FOUND SCORED AROUND UPPER FLA	NGE ATTACHMENT AREA. THIS WAS DIRECTLY BELOW THE TAILROTOR GEARBOX, AT THE TOP OF THE VERTICAL FIN.  SCORING WAS CAUSED 	BY A (CLICK-BOND) TYPE FASTENER/STANDOFF USED TO SECURE A WIRE HARNESS. THE FASTENER CAME UNBONDED FROM THE FUSELAGE AND	 ALLOWED THE WIRE HARNESS TO CONTACT THE DRIVESHAFT. THE CLAMP AND SCREW CAUSED THE SCORING ON THE DRIVESHAFT FLANGE.			2	G	7	2 	6U				R00002RD					 
2007010800138	20070108	00138		2007	1	8	AFASVRA335       	4	20061201	G	2562		G SWITCH        	DORNEMARGLN 																ELT	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03		9331 			4959					ANNUAL INSPECTION TESTING OF ELT IAW AC 43.13-1B, CHAPTER 12, PARA 12-22C.   THE G-SWITCH WOULD NOT ACTIVATE. THE NORMAL	 ON FUNCTIONED SATISFACTORY.  WHEN THE ELT WAS AT ROOM TEMPERATURE, G-SWITCH FUNCTIONED PROPERLY BUT WHEN COLD SOAKED IN	 THE HANGER IT WOULD NOT ACTIVATE.  TRIED THE G-SWITCH NUMERIOUS TIMES AND IT WOULD NOT ACTIVATE WHEN COLD.  BATTERY EXP	IRATION DATE MAR 2007.																 
2006051800269	20060518	00269		2006	5	18	AMCR200600001    	4	20060405	G	2562	MN1300	BATTERY         	ACK         	E01         	CIRRUS	SR    	SR22        	2130001	GL  										ELT	CORRODED        	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	679DV	420  			041133	0196				DURING ANNUAL INSP, ELT DID NOT TEST. FOUND 2 D-CELL BATTERIES CORRODED. THESE 2 BATTERIES WERE AT THE BOTTOM OF THE STA	CK AND THE CORROSION WAS NOT EVIDENT AT FIRST. THERE WERE 2 YEARS REMAINING BEFORE BATTERY REPLACEMENT WAS DUE. THESE AR	E THE ORIGINAL BATTERIES SINCE NEW (APRIL 2002).  RECOMMEND BATTERIES BE REMOVED COMPLETELY AT EACH ANNUAL AND INSPECTED	.			1	L	7	1 	3O			NT	A00009CH					 
2006092600128	20060926	00128		2006	9	26	AMCR200600002    	4	20060925	G	3414	EA517245CES	INDICATOR       			CESSNA	208   	208B        	2073701	CE  										AIRSPEED	LEAKING         	B			AMCR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	09	479DV	129  				208B1169				PILOT REPORTED AN AIRSPEED SPLIT BETWEEN THE 2 INDICATORS. MAINTENANCE FOUND THE CO-PILOTS INDICATOR LEAKING INTERNALLY.	 FOUND INDICATOR TO BE AN OLDER, SUPERSEDED TYPE. LATEST UNIT IAW IPC INSTALLED. MFG P/N C661064-0237.					1	H	7	1 	3T				A37CE   					 
2006111500178	20061115	00178	EU  	2006	11	15	AMCR200600003    	1	20061107	G	3244	237K232	TIRE            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG	LEAKING         	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	527AC					NA0405				AFTER MOUNTING A NEW GOODYEAR TIRE ON AN AHA1814 WHEEL, THE TIRE FAILED THE 24 HOUR LEAK CHECK. EXCESSIVE VENTING WAS SE	EN FROM MANY VENT HOLES IN THE BEAD AREA. TWO ADDITIONAL 24 HOUR CHECKS WERE PERFORMED AND LEAK RATE WAS ABOUT 19 PERCEN	T LOSS. AGAIN, EXCESSIVE LEAKING FROM VENT HOLES. TIRE RETURNED FOR WARRANTY.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006111500321	20061115	00321	NE  	2006	11	15	AMCR200600004    	1	20061113	G	7921	6454474	QUILL           			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6*        	52043	EA  					BLOWER	WORN            	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	520AC		580  		16471	760380				DURING A POSTFLIGHT INSPECTION, MECHANIC WIGGLED THE IMPELLER OF THE LT OIL COOLER BLOWER AND NOTICED EXCESSIVE PLAY AND	 PROCEEDED TO REMOVE THE BLOWER. INVESTIGATION REVEALED THE SPLINE SHAFT TEETH OF BOTH THE BLOWER'S QUILL SHAFT AND THE 	ACCESSORY DRIVE TO BE EXCESSIVELY WORN TO THE POINT THAT FAILURE WAS IMMINENT. THE SPLINE TEETH WERE DRY SO IT IS SUSPEC	TED THAT THE LUBRICATION WAS MISSED AT LAST INTERVAL. BUT THE REPLACEMENT OIL COOLER BLOWER, WITH AN OVERHAUL TAG, WAS F	OUND TO HAVE IT'S IMPELLER INSTALLED UPSIDE DOWN. KUDO'S TO THE MECHANIC FOR THOROUGHLY CHECKING BOTH UNITS WITH UNCANNY	 ATTENTION TO DETAIL.	1	G	7	2 	4U	3	T		H1NE    	E2NE				 
2006042400152	20060424	00152	NM  	2006	4	24	AMTA200600279    	1	20060414	G	2840		FUEL TANK       			BOEING	737   	73783N      	13844HI	NM  										WING	READS HIGH      	A			AMTA	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	11	319TZ					30643				RT MAIN FUEL TANK READ 400 LBS HIGH.  FQIS TEST SHOWS NO FAULT FOR RT MAIN TANK.  CHECK GOOD, C/W FIM 28-41-00-810.  (K)						2	L	7	2 	4F			RT	A16WE   					 
2006042800116	20060428	00116	CE  	2006	4	28	AOC06001         	1	20060316	G	3230	12806005	ACTUATOR        	CESSNA      	NA          	CESSNA	210   	T210L       	2073449	CE  										NLG	BROKEN          	B			R29R	K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	19	57977	6593 				21061475				UPON LANDING, THE NOSE LANDING GEAR COLLAPSED, CAUSING MAJOR DAMAGE TO THE PROPELLER AND DAMAGE TO THE NOSE SECTION OF T	HE AIRCRAFT.  INSPECTION AFTER RECOVERY REVEALED THE THE BEARING END (P/N - 1280600-5) HAD BROKEN, ALSO SHEARING THE PIN	S (P/N - 1280209-1).  NO EVIDENCE OF A PRE-EXISTING CRACK NOTED.  PARTS SENT TO CESSNA FOR EVALUATION.				1	H	7	1 	3O				3A21    					 
2006041300257	20060413	00257	GL  	2006	4	13	ASWFSDO15OKC     	1	20060207	G	3233		ACTUATOR        			AMTR  	GAIR  	GLASAIRIII  	05691HK	GL  										NLG	WORN            	C				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			SW	99	373R									THE PILOT STATED THAT DURING ROLLOUT AFTER LANDING A HOME BUILT GLASAIR III HE APPLIED THE BRAKES AND THE NOSE GEAR COLL	APSED.  THE PILOT SAID THE LANDING GEAR POSITION INDICATOR LIGHTS WERE GREEN PRIOR TO LANDING.  THE NOSE GEAR ACTUATOR W	AS FOUND TO BE LEAKING FLUID.  DURING DISASSEMBLY OF THE ACTUATOR THE PISTON SEAL WAS FOUND TORN.  THE AIRCRAFT OWNER SU	SPECTS THAT HYDRAULIC FLUID WAS BY PASSING THE PISTON DURING OPERATION BECAUSE OF THE TORN SEAL.  THE ACTUATOR DID NOT P	RODUCE ENOUGH FORCE TO OVERCOME THE AIR LOAD ON THE NOSE GEAR TO LOCK THE NOSE GEAR DOWN.  THIS IS THE SUBJECT OF STODDA	RD-HAMILTON SERVICE BULLETIN 136.	1	L	7	1 	3O			RT	EXPA1L71					 
2006022700068	20060227	00068	NM  	2006	2	27	AUCR200600001    	1	20060201	G	5730	9006071	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	927AU	16619				151369				LT WING, STA. 82, 2.9 IN. FRACTURE IN NR 7 PLANK FORWARD TANG. FRACTURE WAS LOCATED BY ULTRASONIC INSPECTION DURING EVAL	UATION OF FUEL STAIN AT ANNUAL INSPECTION. THERE EXISTS AN APPROVED REPAIR FOR THIS DAMAGE IN THE SRM.					2	L	7	4 	4T	4	T	RT	A32NM   	E282				 
2006042700128	20060427	00128	NM  	2006	4	27	AUCR200600002    	1	20060321	G	5711	9010622	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										WING	CORRODED        	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	922A	12531				151387				UPPER REAR SPAR CAP STRESS CORROSION CRACKED IN AFT RADIUS FORWARD OF NR 4 FLAP HANGER.  DAMAGE CENTERED AT WS275.  DAMA	GE WAS INITIALLY DETECTED VISUALLY DURING SCHEDULED SPECIAL INSPECTION.  DAMAGE WAS FURTHER EVALUATED WITH EDDY CURRENT 	INSPECTION AND WAS FOUND TO EXCEED THE PARAMETERS OF THE SRM.  US TECHNICAL ENGINEERING HAS BEEN CONTRACTED TO GENERATE 	AN APPROVED REPAIR.			2	L	7	4 	4T			RT	A32NM   					 
2006051200084	20060512	00084	NM  	2006	5	12	AUCR200600003    	1	20060427	G	5730	9006051	PANEL           			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	CRACKED         	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	925AU	16997				151361				CRACKED RISER, NR 4 FUEL TANK LOWER PLANK NR 4 AT NR 27 RISER WS397R.						2	L	7	4 	4T			RT	A32NM   					 
2006051500203	20060515	00203	NM  	2006	5	15	AUCR200600004    	1	20060427	G	5730	9006041	SKIN PANEL      			LKHEED	P3A   	P3A         	5260103	NM  										LT WING	DAMAGED         	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	925AU	16997				151361				BOTTOM LT WING WS68.5, 4 FUEL BOOST PUMP SCREEN ATTACHING HOLES ELONGATED IN NR 17 AND NR 18 RISER.						2	L	7	4 	4T			RT	A32NM   					 
2006061200046	20060612	00046	NM  	2006	6	12	AUCR200600006    	1	20060531	G	5711	9010621	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										LT WING	CRACKED         	B			AUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	900AU	15902				151391				DURING SCHEDULED INSPECTION FOUND CORROSION INDUCED CRACK IN UPPER AFT SPAR CAP EXTENDING OUTBOARD FROM PREVIOUS REPAIR 	IN THE AREA OF FLAP TRACK 5, WS 346.  DURING DISASSEMBLY TO EFFECT REPAIR FOUND ADDITIONAL STRESS CORROSION FRACTURE ON 	UPPER AFT SPAR CAP AT FLAP TRACK 4, WS 275.  THE AFFECTED AREAS RECEIVE A DETAILED INSPECTION ANNUALLY.				2	L	7	4 	4T			RT	A32NM   					 
2006051200073	20060512	00073	GL  	2006	5	12	AVI000021        	1	20060419	G	5520	11626002	ELEVATOR        	CIRRUS      	10146005    	CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ELEVATOR	OUT OF TOLERANCE	D				K				NONE                    				O	O	O	OTHER                     	OTHER                     	OTHER                     	IN	INSP/MAINT     	1			SO	15	753CD	796  	796  			0090				DURING SA 06-05 ELEVATOR GAP VISUAL INSPECTION IT WAS NOTED THAT THE GAP BETWEEN ELEVATOR TIP AND HORIZONTAL STABILIZER 	WAS LESS THEN 0.10 INCH, UPON FURTHER INVESTIGATION IT WAS NOTED THAT PN 11626-002 ELEVATOR HINGE, OB WAS RUBBING ON HOR	IZONTAL STABILIZER OB HINGE. ELEVATOR WAS RE-SHIMMED BY INSTALLING SHIM PN 11508-005.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2006051800248	20060518	00248	CE  	2006	5	18	B3OR20060111     	1	20060419	G	2497		TERMINAL        			CESSNA	500   	550         	2076604	CE  										WIRING SYS	MISINSTALLED    	B			B3OR	D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	03	1200N					5500681				WIRE TERMINAL WAS IMPROPERLY CRIMPED ONTO WIRE INSULATION WITH STRIPPED END OF WIRE STRANDS CONTACTING TERMINAL SCREW AT	 VOLTAGE METER CIRCUIT BREAKER.  THIS DISCREPANCY CAUSED AN INTERMITTENT VOLTAGE METER READING FAILURE.					1	L	7	2 	4F				A22CE   					 
2006021400216	20060214	00216	EU  	2006	2	14	B3OR20060125     	1	20060126	G	6510	350A34021006	DRIVE SHAFT     			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	MISOVERHAULED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J					3118				DURING ROUTINE TBO REPLACEMENT OF TAIL ROTOR DRIVESHAFT; IT WAS DISCOVERED THAT THE FORWARD END OF THE RECENTLY OVERHAUL	ED REPLACEMENT WAS UNPAINTED CAUSING THE NR 5 BEARING FIT TOLERANCES TO BE TOO LOOSE.  MFG TECHNICAL REPRESENTATIVES VER	IFIED THAT THE DRIVESHAFT IS SUPPOSED TO BE PAINTED UP TO THE SPLINES.  PART WAS RETURNED FOR FURTHER REWORK.				1	G	7	1 	3U				H9EU    					 
2006012700067	20060127	00067	EU  	2006	1	27	B3OR20060126     	1	20060126	G	6510	350A34021006	DRIVE ASSY      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	MISOVERHAULED   	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J					3118	9318			DURING ROUTINE TBO REPLACEMENT, DISCOVERED THE NEWLY OVERHAULED TAIL ROTOR DRIVESHAFT FORWARD END WAS UNPAINTED CAUSING 	AN UNSERVICEABLY LOOSE FIT OF THE NR 5 BEARING.  MANUFACTURER TECHNICAL REPRESENTATIVES VERIFIED THAT THE AREA IN QUESTI	ON IS SUPPOSED TO BE PAINTED UP TO THE SPLINES.   PART WAS RETURNED FOR FURTHER REWORK.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007010800140	20070108	00140	CE  	2007	1	8	BIOR061211001    	1	20061211	G	5350	101420024438	FAIRING         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  						CORRODED        	B			BIOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	200MJ	9672 				BB1012				DURING A PHASE 4 INSPECTION PAINT BLISTERS WERE NOTED ON THE LT AND RT WING ROOT FAIRING LOWER AFT PANELS P/N 101-420024	-43 AND 101-420024-8. UPON FURTHER INSPECTION BOTH PANELS WERE FOUND TO BE CORRODED THRU IN SEVERAL PLACES FROM THE INSI	DE OUT.  AFTER REMOVING THE PANELS IT WAS DISCOVERED THAT THE ACOUSTIC FOAM HAD BECOME SOAKED WITH WATER OVER TIME. THIS	 SET UP CORROSION OVER THE ENTIRE AREA OF THE INSIDE OF BOTH PANELS. ALSO WHERE THIS MATERIAL CONTACTED THE FUSELAGE ON 	THE LT SIDE IT CAUSED CORROSION THRU THE PRESSURE VESSEL.  MFG HAS BEEN NOTIFIED AND SUPPLIED WITH PHOTO DOCUMENTATION.		1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006120400004	20061204	00004	WP  	2006	12	4	BS2R2120003      	1	20061117	G	6310	269A5472	PULLEY BRACKET  	HUGHES      		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					BELT DRIVE SYSTE	BROKEN          	B			BS2R	C	E			ABORTED TAKEOFF         	ENGINE SHUTDOWN         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SW	17	11047	2701 	29   			211031	L2209551A			ONE OF THE TWO BELT DRIVE CLUTCH ACTUATOR CABLE PULLEY BRACKETS BROKE CLEAN ACROSS BETWEEN THE FRAME MOUNT HOLE AND THE 	PULLEY MOUNT HOLE DURING ENGAGEMENT OF THE ROTOR SYSTEM. DURING THE SUBSEQUENT TAKE OFF ATTEMPT THE ROTOR RPM WOULD BLEE	D OFF RAPIDLY DUE TO DRIVE BELT SLIPPAGE ANY TIME THE M/R COLLECTIVE CONTROL WAS RAISED.THE AICRAFT WAS SHUT DOWN AND TH	E PROBLEM INVESTIGATED BY THE OPERATOR THEN MAINTENANCE PERSONELL WERE NOTIFIED.			1	G	7	1 	3O	3	O		4H12    	1E10				 
2006061400070	20060614	00070	EA  	2006	6	14	CA060103001      	2	20060102	G	7230		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RIGHT	FAILED          	W				A				UNSCHED LANDING         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	DE	DESCENT        	1			CA								PCE81119			AT APPROXIMATELY 09:30 THIS MORNING, THE RT ENGINE OF KING AIR 200 HAD AN IN-FLIGHT TORQUE ROLL BACK TO APPROX 200 FT LB	S, WITH A RISE IN ITT TO APPROX 680 DEG C, WITH A POPPING NOISE AND CORRESPONDING FLAMES FROM THE RT ENGINE EXHAUST.  TH	E CREW INITIATED THE ENGINE SHUTDOWN.				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061500027	20060615	00027	EU  	2006	6	15	CA060104004      	1	20060102	G	5610	01379377C405	WINDSCREEN      			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	COCKPIT	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			A			FLAME/FIRE                			CR	CRUISE         	1			CA											AT CRUISE ALT 20,000 FT, NOTICED CRACK AND SUBSEQUENT FLAME WITHIN LAYERS OF LT WINDSHIELD.  FLAME SELF EXTINGUISHED WIT	H DE-SELECTION OF WINDSHIELD HEAT.  DURING DESCENT ADDITIONAL CRACKING.  DIVERTED TO CYMM.  MX DISPATCHED, REPLACED WIND	SHIELD.  UPON MX REVIEW FOLLOWING WAS DETERMINED; THE PART WAS IN SERVICE ON THIS A/C ON REGISTER SINCE 2003 JANUARY AND	 PRIOR.  NO ABNORMALITIES OBSERVED DURING REMOVAL REGARDING INSTALLATION, EXCEPT FOR PRC APPLIED OVER EXT SCREW HEADS.  	AIRFRAME VOLTAGE AND CURRENT OUTPUT TO LT WINDOW HEAT SYS FOUND NORMAL.  NO EVIDENCE OF MISTORQUE OF SECURING SCREWS OBS	ERVED.  MX PRELIMINARY CONCLUSION, MALFUNCTION LEADING TO A SHORT CIRCUIT OF INTERNAL HEAT FILAMENTS OF WINDSHIELD.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2006061500142	20060615	00142	EU  	2006	6	15	CA060104005      	1	20060104	G	2530	820317000	OVEN            			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					FWD GALLEY	SHORTED         	W				F				ACTIVATE FIRE EXT.      				A		O	FLAME/FIRE                		OTHER                     	CR	CRUISE         	1			CA											FWD GALLEY OVEN FIRE EXTINGUISHED WITH 2 FIRE EXT BOTTLES ACTION.  FWD GALLEY NR1/NR 2 OVENS REPLACED. FUNCT CHKD SERV  	NR 1 OFF HK76R5  NR 2 OFF 8203-17-000 S/N 9403-6150.  NR 1 ON 8203-17-000, S/N 96-11-7934 NR 2 ON 568K81.					2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006061500179	20060615	00179	EU  	2006	6	15	CA060104007      	1	20060104	G	3260	201122006	UPLOCK          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER T/O ECAM L/G DOORS NOT CLOSED.  CYCLED LDG GEAR.  ECAM RE-APPEARED.  LT MAIN GEAR DOOR SHOWED PARTIALLY OPEN IN AM	BER.  GEAR DOORS SHOW CLOSED WHEN GEAR DOWN.  LT GEAR DOOR UPLOCK ASSY REPLACED AS PER TASK, 32-31-33-400-002.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2006061500181	20060615	00181	NE  	2006	6	15	CA060104008      	2	20060104	G	7530	0CFM565A5	REDUCER         			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  					P3 LINE	SHEARED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											IN CLIMB THRU FL185, ENG NR 2 PWR REDUCED TO 74.5 N1/1200 KGH FF.  ENG PARAMETERS NORMAL WHEN PWR REDUCED TO LOWER SETTI	NGS.  ENG NR 1 NORMAL THROUGHOUT.  FOUND PS3 LINE REDUCER SHEARED AS PER TSM 77-00-00-810-833.  REDUCER REPLACED AS PER 	AIRBUS STANDARD PRACTICES.  GROUND RUN CHKD SERV.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2006061500182	20060615	00182	SW  	2006	6	15	CA060104009      	1	20060104	G	7921	2660163501	SHAFT           	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					BLOWER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8292 	582  		30791					PERFORMED MAGNETIC PARTICLE INSPECTION IAW BHT-ALL-SPM, SHAFT P/N 2660-1635-01 WAS FOUND TO BE CRACKED IN KEY WAY, PART 	HAS BEEN SUBSEQUENTLY SCRAPED.  BELL HELICOPTER HAS BEEN NOTIFIED FOR INTEREST AND INFORMATION ONLY.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006061500183	20060615	00183		2006	6	15	CA060104010      	4	20060101	G	2330	50401100003	VIDEO DISPLAY   			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 20E	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											A/C WAS ON DESCENT WHEN A BURNING SMELL WAS NOTICED COMING FROM SEAT 20E VDU.  THE IFE SYSTEM WAS DEACTIVATED.  MAINTENA	NCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A C	OMPLETE TEAR DOWN REPORT WILL BE REQUESTED.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006061500184	20060615	00184	SW  	2006	6	15	CA060104011      	1	20060102	G	5610	27194423REV3	WINDSHIELD      			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											LT WINDSHIELD CRACKED WHILE AT FL250.  CREW CARRIED ON TO BASE AT LOWER ALTITUDE AND SLOWER AIRSPEED.  MAINTENANCE IS CH	ANGING WINDSHIELD.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2006061500185	20060615	00185		2006	6	15	CA060105001      	4	20060103	G	2330	50401100003	VIDEO DISPLAY   			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 6D	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											A/C WAS IN CRUISE WHEN SMOKE WAS OBSERVED COMING FROM SEAT 6D VDU.  THE IFE SYSTEM WAS DEACTIVATED.  MAINTENANCE REPLACE	D THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEA	R DOWN REPORT WILL BE REQUESTED.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006061500203	20060615	00203	CE  	2006	6	15	CA060105004      	1	20060105	G	3246	NIL	CONTROL CABLE   			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  	HARTZL	HCF3Y	HCF3YR1     	GL  	WATER RUDDER	FRAYED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			CA			1065 								WATER RUDDER STEERING CABLES ARE FRAYED WHERE IT ENTERS THE SIDE OF THE FLOAT.  THE MAIN CAUSE OF THIS IS A MISALIGNMENT	 OF THE HOLE ON THE SIDE OF THE FLOAT TO THE ACTUAL POSITIONING OF THE RUN.  IN SOME CASES, THE CABLE HAD CUT A 1/4" SLO	T ON THE FLOAT SIDE SKIN DUE TO THIS MISALIGNMENT.				1	H	7	1 	3O	3	O	RT	A4CE    	1E4	5	C	P31EA	 
2006072400076	20060724	00076	WP  	2006	7	24	CA060106001      	2	20060101	G	7200		ENGINE          			BOMBDR	BD700 	BD7001A10   	1390006	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					LEFT	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA								3030014			(CAN) ON CLIMB OUT CREW REPORTED A LOUD THUMP FOLLOWED BY A DROP IN LT ENGINE OIL PRESSURE AND AN AIRFRAME VIBRATION. CR	EW SHUT DOWN THE ENGINE DELARED AN EMERENCY AND RETURNED TO AIRPORT.  LT ENGINE REMOVED AND LOANER INSTALLED. (TC NR 200	60106001)				2	L	7	2 	4F	4	F	RT	T00003NY	E00010LA				 
2006061600051	20060616	00051	CE  	2006	6	16	CA060106003      	1	20060105	G	3297		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					UPLOCK SWITCH	DAMAGED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											UPON ARRIVAL, THE GEAR WAS SELECTED DOWN BUT NO DOWN AND LOCKED ANNUNCIATORS ILLUMINATED.  THE IN TRANSIT LIGHT WAS ALSO	 NOT ILLUMINATED SO THE PILOT DID A FLY BY OF TOWER TO CONFIRM GEAR POSITION, THEY ALSO HAD EMERGENCY SERVICES ON STANDB	Y.  AN UNEVENTFUL LANDING WAS COMPLETED.  AS THE AIRCRAFT WAS BEING SHUTDOWN THE CREW NOTICED THAT THE CB FOR THE ANNUNC	IATORS WAS POPPED.  RESET THE CB AND ALL THE ANNUNCIATORS ILLUMINATED AS REQUIRED.  A SPECIAL FERRY PERMIT WAS ISSUED TO	 RETURN THE AIRCRAFT TO A MAINTENANCE BASE.  MAINTENANCE FOUND A CHAFED WIRE ON THE HARNESS FOR THE RT UPLOCK MICROSWITC	H.  GEAR SWUNG AND AIRCRAFT RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006061600052	20060616	00052	CE  	2006	6	16	CA060106004      	1	20060105	G	5610	10138402523	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA				1234 							DEPARTING AIRPORT THE LT HEATED WINDSHIELD CRACKED.  TURNED AROUND AND MADE AN UNEVENTFUL LANDING.  THE AIRCRAFT WAS SEN	T TO MAINTENANCE WHO REPLACED THE WINDSHIELD.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006061600053	20060616	00053	EA  	2006	6	16	CA060108001      	1	20060104	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF343B1     	 	NE  					COPILOT'S	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						99307H2825					RIGHT WINDSHIELD CRACKED DURING CLIMB.  DIVERTED FLIGHT BACK TO DEPARTURE AIRPORT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061600054	20060616	00054	EA  	2006	6	16	CA060108002      	1	20060103	G	5610	NP1393211	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											DURING APPROACH, THE LEFT WINDSHIELD CRACKED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061600056	20060616	00056	WP  	2006	6	16	CA060109001      	1	20060103	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYDRAULIC	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			92   								DURING DAILY INSPECTION, NOTICEABLE AMOUNT OF HYDRAULIC FLUID LEAKING FROM SERVO.  GROUND RUN DETERMINED PILOT VALVE SOU	RCE OF LEAK.  AFT SERVO REMOVED AND RETURNED TO ROBINSON HELICOPTERS FOR WARRANTY REPAIRS.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600057	20060616	00057	NM  	2006	6	16	CA060109002      	1	20060106	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG WOW	DAMAGED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											AIR TURN BACK DUE TO NR 2 WOW CAUTION LIGHT.  NLG WOW 2 HARNESS REPLACED.  AIRCRAFT RETURNED TO SERVICE.						2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006061600060	20060616	00060	CE  	2006	6	16	CA060110001      	1	20060106	G	3310	2K40D10	RESISTOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PANEL LIGHT	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA											DURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED.  INSULATI	ON ABOVE THE RESISTOR WAS SCORCHED AND BURNED.  THE SYSTEM WAS DEACTIVATED AND DEFERRED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006061600062	20060616	00062	NM  	2006	6	16	CA060110002      	1	20060108	G	7933	MS280344	PROBE           			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	OIL TEMPERATURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA			18748								DURING CRUISE, THE LT OIL TEMPERATURE INDICATION WAS NOTICED TO BE INTERMITTENTLY FLUCTUATING AND UNSERVICEABLE.  CREW E	LECTED TO RETURN THE AIRCRAFT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT.  ENGINEERING INVES	TIGATION REVEALED THAT THE ENGINE'S OIL TEMPERATURE PROBE WAS UNSERVICEABLE.  THE PROBE IN QUESTION WAS REPLACED AND FOL	LOWING REQUIRED ENGINE RUNS AND CHECKS THE AIRCRAFT WAS RELEASED BACK TO SERVICE WITHOUT FURTHER INCIDENT.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061600108	20060616	00108	CE  	2006	6	16	CA060110003      	1	20060106	G	3310	2K40D10	RESISTOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PANEL LIGHTS	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA											DURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED.  INSULATI	ON ABOVE THE RESISTOR WAS SCORCHED AND BURNED.  THE SYSTEM WAS DEACTIVATED AND DEFERRED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006061600115	20060616	00115	EA  	2006	6	16	CA060110004      	1	20060106	G	3244	362K821	TIRE            			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF34*       	 	NE  					NR 2	SEPARATED       	W				O				OTHER                   				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			CA			1160 	504  							ON TAKEOFF, THE NR 2 MAIN TIRE RECAP DEPARTED THE TIRE CAUSING DAMAGE TO MLG SIDE STAY SPRINGS AND RETAINING PINS, INBD 	FLAP AND VANE, THE WING LOWER SKIN AFT OF THE LT GEAR BAY, AND THE INBD SPOILER FITTING ASSEMBLY.  SIGNS OF FOD NOTED IN	 THE LT ENGINE BUT DETAILED INSPECTION AND BOROSCOPE SHOWED NO DAMAGE SUSTAINED.  MAIN TIRE PRESSURES NOTED AS FOLLOWS N	R 1 198 PSI, NR 2 140 PSI, NR 3 198 PSI, NR 4 198 PSI, S/N (D) IS TIRE SERIAL NUMBER NOT ASSEMBLY, RECAPPED AT WILKERSON	.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061600116	20060616	00116	NE  	2006	6	16	CA060110005      	2	20060104	G	7230	311074102	SHROUD          								PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			746  					PCE19201			DURING A RECTIFICATION INSPECTION OF RENTAL ENGINE, CT SHROUD SEGMENT RETAINING RING OF POST SB 1627 CONFIG FOUND LOOSE 	AND MINOR SHIFTING OF CT SHROUD SEGMENT WAS NOTED.  CT SHROUD SEGMENT-RETAINING RING WAS OF POST SB 1627 CONFIG AND CT S	HROUD SEGMENTS (P/N 3053094) WERE PER SB 1628.  QTY 6-RUB SPOTS WERE NOTED ON CT SHROUD SEGMENTS WITH MINOR RUB ON CT BL	ADES.  CT SHROUD SEGMENT-RETAINING RING WAS FOUND DISTORTED AND PARTIALLY DISENGAGED FROM RETAINING GROOVE OF CT SHROUD 	HOUSING.  NO OVER HEATING/BURNING OF HOT SECTION PARTS NOTED.  INSPECT OF CT SHROUD HOUSING WAS DONE AND ROUNDNESS OF AL	L CRITICAL DIAMETERS NOTED WITHIN O/H MANUAL LIMIT.  SHIFTING OF CT SHROUD SEGMENTS WAS DUE TO PARTIAL DISENGAGEMENT OF 						3	T			E4EA				 
2006062700003	20060627	00003		2006	6	27	CA060110006      	1	20060110	G	2730	82700561003	CABLE           																	ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING CHECK , 2 CHAIN CABLE ASSY`S, P/N 82700561-003, TITLED "ELEV TRIM AND ELEV GUST LOCK CONTROL" INSPECT OF CHAINS, 	REF AD CF-2005-38, WAS FOUND INCORRECTLY ASSEMBLED AND SUPPLIED BY SPARES.  ASSY FOUND INCORRECTLY BUILT WHEN ATTEMPTING	 TO INSTALL AS PER AMM 27-36-01, PARA B, STEP 3.  SPECIFIES THAT CHAIN PLATE IS REQ`D TO BE ON INBD SIDE OF SPROCKET.  T	HIS CAN'T BE ACCOMP WITH NEW CHAIN ASSY IN ITS PRESENT CONFIG (DWG 82700561 SHOWS THE DIMENSIONS AND CORRECT ORIENTATION	 OF ASSY).   TECH HELP DESK E-MAILED, ADVISED OF ISSUE & REQUESTED TO PULL THEIR DRAWINGS TO CONFIRM OUR FINDINGS.  REQU	ESTED INSPECT EXISTING INVENTORY TO CONFIRM IF THEIR SPARES WERE ALSO AFFECTED.  REPLACEMENT CHAIN CABLE ASSY`S ORDERED 														 
2006061600117	20060616	00117	NM  	2006	6	16	CA060110007      	1	20060110	G	2530	8201170000	OVEN            			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  					AFT GALLEY	SHORTED         	W				O				OTHER                   				A			FLAME/FIRE                			CR	CRUISE         	1			CA											OVEN NR 02-02-17535 OVEN NR 3 IN AFT GALLEY EMITTED AN ELECTRIC SHOCK TO F/A UPON TOUCHING IT.  MEL ERASED IN CCS AND CB	 PULLED AND COLLARED BY FLIGHT CREW.  REPLACED NR 3 OVEN CONTROLLER FUNCTION CHECK SATISFACTORY.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2006061600118	20060616	00118		2006	6	16	CA060111001      	1	20060103	G	2400		CIRCUIT BREAKER 																		BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											AIRCRAFT HAD NR 1 AC GENERATOR INOPERATIVE (GOES OFFLINE AFTER 20 SECONDS).  INITIALLY, THE GENERATOR HAD BEEN REPLACED,	 HOWEVER, THE DISCREPANCY REMAINED.  SUBSEQUENTLY, CIRCUIT BREAKER, P/N 2TC2-5 FOUND WITH HOLE BURNT IN THE SIDE.  FOR R	ECTIFICATION PURPOSES, CONTACTOR RELAY 2421-K1 REPLACED.  RING CONNECTORS TO CB3 AND CB5 REPLACED, P/N HC-AJN022 (CONTAC	TOR RELAY), P/N 2TC2-5 (CB3) & (CB5).																 
2006061600120	20060616	00120	NM  	2006	6	16	CA060111002      	1	20060111	G	5340	69215313	BRACKET         			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					FUSELAGE	SPLIT           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											ON LANDING IN YYZ,FORWARD ATTENDANTS SEAT BELT CAME FREE OF THE ATTACH BRACKET.  UPON INVESTIGATION IT WAS FOUND THAT A 	WASHER WAS MISSING FROM THE RETAINING BOLT.  THIS MISSING WASHER WAS LEFT OFF THE BOLT AT INSTALLATION BY A PREVIOUS OPE	RATOR.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061600122	20060616	00122	GL  	2006	6	16	CA060112001      	2	20060107	G	7240	6870992	COMBUSTION CASE 			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CREW REPORTED ABNORMALLY HIGH TOT ON NR 1 ENGINE.  INVESTIGATION REVEALED A CRACK IN THE RT ARMPIT AREA OF THE OUTER COM	BUSTION CASE.  THE OUTER COMBUSTION CASE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006061600123	20060616	00123	WP  	2006	6	16	CA060112002      	1	20060111	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ROTOR FLT CONTRO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			503  								HYDRAULIC LEAK FROM SERVO.  SERVO REMOVED FOR REPAIR AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600124	20060616	00124	EA  	2006	6	16	CA060112003      	1	20060111	G	2540	601R40467239	INSULATION      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15193								BURNT INSULATION BLANKET FOUND IN CARGO UNDERFLOOR AREA ON RT SIDE OF AIRCRAFT AROUND HEATED LAV WATER SERVICE PORT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061600125	20060616	00125	WP  	2006	6	16	CA060112004      	1	20060111	G	6700	C12131	PUSH-PULL ROD   			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAST	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			503  								WHILE REMOVING A HYDRAULIC SERVO, IT WAS NOTED THAT THE PUSH PULL TUBE FROM THE SERVO TO THE SWASHPLATE WAS WEARING WHER	E IT PASSED THROUGH THE MIDDLE RIB OF THE MAST FAIRING.  THE CHAFING WAS MINOR, AND HAD ONLY GONE THOUGH THE TOP LAYER O	F PAINT, AND STARTED ON THE PRIMER.  THE ENGINEERS SUSPECT THAT THE LOWER RIBS OF THE MAST WERE NOT CENTERED PROPERLY DU	RING MANUFACTUER, AND WERE ALTERING THE POSITION OF THE MIDDLE RIB.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600150	20060616	00150	SW  	2006	6	16	CA060112005      	1	20060110	G	5280	2755001177	DOOR            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					LANDING GEAR	JAMMED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											DURING APPROACH, CREW ATTEMPTED TO EXTEND L/G AND NOTICED RT MAIN WAS NOT DOWN AND LOCKED.  IT WAS DETERMINED LANDING GE	AR WAS NOT COMING OUT OF RT W/W.  IT TOOK SEVEN ATTEMPTS TO GET LANDING GEAR TO COME DOWN AND LOCK INTO POSITION.  INSPE	CTION REVEALED RT I/B GEAR DOOR HINGES WERE WORN, ALTHOUGH NOT EXCESSIVE, THAT TWO RT MLG DOORS OVERLAPPED DURING RETRAC	TION AND DID NOT ALLOW GEAR TO COME DOWN OUT OF W/W WHEN IT WAS EXTENDED FOR LANDING.  INSPECTION OF DOOR REVEALED SOME 	DENTS AND TEARING OF SKIN EDGE ON DOOR WHERE L/G GEAR WAS HITTING DOOR DURING ATTEMPTS TO EXTEND LANDING GEAR.  LANDING 	GEAR DOOR WAS REPLACED AND DOOR AND GEAR RIGGING CHECKED.  AIRCRAFT HAS SINCE RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2006061900069	20060619	00069	GL  	2006	6	19	CA060112006      	2	20060105	G	7250	6886407	TURBINE BLADES  								ALLSN 	250C  	250C*       	 	GL  					ENGINE	BROKEN          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			C	W		F.O.D.                    	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			CA			120  					CAT32511P			TURBINE RECEIVED AT ESSENTIAL TURBINES IN A DISASSEMBLE STATE.  LOG CARDS REFLECT THAT THE TURBINE HAD BEEN INVOLVED IN 	A HARD LANDING.   IT HAD BEEN INSPECTED AND SENT TO MAC-V AVIATION WHO RE-ASSEMBLED THE ENGINE.  MAC-V STATED VIA A PHON	E CALL THAT THE HARDWARE WAS MIXED IN THE COMBUSTION SECTION AND COULD NOT FIND ALL OF THE NUTS, BOLTS ETC.  OUR INVESTI	GATION LEADS US TO BELIEVE THAT THE HARD LANDING WAS NOT A FACTOR.  THE FAILED TURBINE WHEEL WILL BE FORWARDED TO THE SA	FETY BOARD TO EVALUATE THE REASON FOR FAILURE, POSSIBLY DUE TO FOD FROM ITEM MISSED DURING RE-ASSEMBLY.							3	U			E4CE				 
2006061900072	20060619	00072	CE  	2006	6	19	CA060112007      	1	20060101	G	5340		INTERCOSTAL     			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RUDDER PEDAL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											PILOTS OUTBOARD INTERCOSTAL RUDDER PEDAL MOUNT REPAIRED DUE TO SEVERAL SMALL CRACKS.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006061900077	20060619	00077	SW  	2006	6	19	CA060112009      	1	20060112	G	7712	2719158007	INDICATOR       			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TORQUE	INOPERATIVE     	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											ON TAKEOFF, THE TORQUE INDICATOR WENT TO ZERO.  TAKEOFF ABORTED AND AIRCRAFT RETURNED TO BLOCKS.  MAINTENANCE REPLACED I	NDICATOR AND RELEASED AIRCRAFT AFTER SATISFACTORY GROUND RUN.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2006061900245	20060619	00245	WP  	2006	6	19	CA060112010      	1	20060108	G	8011	72566	RING GEAR       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			201  								STARTER RING GEAR REPLACED AFTER 201.1 HOURS.  MISSING TEETH.  AIRCRAFT TOTAL TIME 441.3.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061900246	20060619	00246	WP  	2006	6	19	CA060112011      	1	20060105	G	2913	D5001	PUMP            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					HYD SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			42   								DURING GROUND CHECK, THE PILOT NOTED PROBLEMS WITH FLIGHT CONTROL CHECK WITH HYDRAULICS.  MAINTENANCE FOUND FERROUS DEBR	IS IN THE FILTER.  THE HYDRAULIC PUMP WAS REPLACED, AND SYSTEM FLUSHED.  NO FURTHER DEFECTS FOUND.  PUMP WAS SENT BACK T	O MFG.				1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061900248	20060619	00248	EA  	2006	6	19	CA060112013      	1	20060108	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			9835 								LT WINDSHIELD FOUND CRACKED BEFORE FLIGHT.  LT WINDSHIELD REPLACED AND TESTED IAW TO AMM PROCEDURE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061900249	20060619	00249	EU  	2006	6	19	CA060116001      	1	20060112	G	2910	HTE400005	VALVE           			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			20126	20126							ON APPROACH, UPON FLAP SELECTION, NO SYSTEM HYD PRESSURE.  EMERG GEAR SELECTION USED TO EXTEND L/G, AND TO OBTAIN 10 DEG	REES FLAP.  A/C LANDED W/O INCIDENT, DUE TO LOSS OF SYS HYD PRESSURE, N/W STEERING INOP AND MAIN BRAKING WAS LIMITED.  T	OWED TO HANGAR.  MX FOUND PN HTE400005 CHECK VALVE CRACKED, WHICH RESULTED IN LOSS OF SYS HYD FLUID.  CHECK VALVE WAS RE	PLACED, SYS WAS REPLENISHED AND BLED, OPS CHECKED SERVICEABLE.  COMPANY ISSUED FLEET INSP TO DETERMINE IF A COMMON PROBL	EM WITH FACTORY INSTALLATION.  FOUND MULTIPLE A/C WITH THESE NRV'S CRACKED IN RADIUS.  (FPI,  10X MAG. GLASS REQUIRED TO	 DETECT.)  VALVE'S REPLACED AS REQ`D AND MFG TO BE CONTACTED.  DEFECTIVE VALVES TAGGED AND ON FILE FOR FURTHER INSPECT.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2006061900250	20060619	00250	GL  	2006	6	19	CA060116002      	2	20060116	G	7260	23069576	BEARING         			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12348					CAE311908			ENGINE CAE311908 CAME IN THE SHOP FOR METAL DEBRIS IN THE FILTER.  DURING ENGINE DISASSEMBLY IT WAS FOUND THAT NR 6 MID 	SPAN BEARING ASSEMBLY HAD FAILED.  MID-SPAN BEARING OUTER RACE WAS STILL IN ITS HOUSING AND ONLY 3 ROLLERS AND A PIECE O	F BEARING CAGE WERE FOUND.  THE RADIAL DRIVE QUILL SHAFT WAS FOUND BROKEN ABOVE THE SPLINES CONNECTING TO THE RADIAL DRI	VE BEVEL GEARSHAFT.  SIMILAR OCCURRENCE ON MID SPAN GEAR TRAIN SYSTEM ON OTHER ENGINES HAD CAUSE IN FLIGHT SHUTDOWN.			2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2006061900251	20060619	00251	EA  	2006	6	19	CA060116003      	2	20060106	G	8530	AEL65102	CYLINDER        			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2192 								IN RESPONSE TO AD 2005-26-10 ISSUED BY THE FAA, INSPECTED AIRCRAFT TO DETERMINE IF ANY OF SUSPECT SN CYLINDERS INSTALLED	.  FOUND 2 CYLINDERS ON LT ENGINE WERE PART OF THE AD REQUIREMENT FOR REPLACEMENT. ON CLOSER EXAMINATION OF ONE OF THESE	 CYLINDERS (NR 3), FOUND A CRACK EXTENDING FROM THE SPARK PLUG HOLE AROUND THE EXHAUST PORT AND PARTIALLY AROUND THE BAR	REL.  THERE WAS A SIGNIFICANT LEAK OF COMPRESSION.  BOTH CYLINDERS ARE PRESENTLY BEING REPLACED.  ALL OTHER CYLINDERS MA	DE BY ECI AND ON OUR AIRCRAFT WILL BE MONITORED CLOSELY AS REPLACE THEM ALL PER THE AD SCHEDULE.		1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
2006061900253	20060619	00253	EU  	2006	6	19	CA060116004      	1	20060112	G	5347	B530042	SEAT TRACK      			SAAB  	SF340 	340B        	7860101	EU  										BS 297-375	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING THE 4K2Y BRIDGE CHECK VISIT, THE AISLE LT SIDE SEAT TRACK BL 18.3 WAS FOUND TO HAVE AREAS OF CORROSION FORWARD OF	 FRAME STA 375 BEYOND ALLOWABLE LIMITS IAW SRM.  THE AISLE LT SIDE SEAT TRACK BL 18.3 WILL BE REPLACED WITH A NEW SEAT T	RACK SECTION P/N B53004-2 AT FRAME STA 297-375 AND REPAIR BEAM P/N B53004-3 IAW THE COMPANY APPROPIATE EO.				2	L	7	2 	4T			RT	A52EU   					 
2006061900254	20060619	00254	EU  	2006	6	19	CA060116005      	1	20060103	G	2121	TVT10728H3	COOLING FAN     			AMD   	FALC90	FALCON900B  	2730171	EU  											SEIZED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			3067 								WHILE ON THE GROUND WITH THE APU RUNNING, SMOKE WAS OBSERVED IN THE CABIN.  THE CREW IMMEDIATELY SHUT DOWN THE APU.  THE	 TURBO COOLING FAN WAS FOUND SEIZED.					2	L	7	3 	4F			RT	        					 
2006061900080	20060619	00080	EA  	2006	6	19	CA060116006      	2	20060111	G	8520	74968	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				698  							THE CRANKSHAFT A/C WAS INSPECTED DUE TO A FAILURE OF A CRANKSHAFT ON ANOTHER AIRCRAFT IN THE FLEET (INTERNAL CORROSION).	  UPON REMOVAL OF THE FRONT CRANK PLUG AND CLEANING OF THE CRANKSHAFT, IT DISCOVERED THAT URETHABOND COATING WAS BLISTER	ING.  URETHABOND REMOVED AND CORROSION WAS FOUND WITHIN FIRST INCH OF CRANK.  ENGINE WAS A FACTORY EXCHANGE OVERHAUL (21	 APR 2002) AND THE CRANK HAD BEEN RE-WORKED.  THE CRANKSHAFT WAS AT MAX ID THEREFORE PITTING FROM CORROSION COULD NOT BE	 COMPLETLY REMOVED.  CRANK WAS INSPECTED BY AN APPROVED AMO(NDT) AS PER LYC SB 505B AND NO FAILING INDICATION WERE FOUND	.  CRANK WAS MARKED PID AND DID NOT REQURIE ANY INTERNAL INSPECTIONS UNTIL 2000-HRS.	1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006061900255	20060619	00255	CE  	2006	6	19	CA060116007      	1	20060115	G	5340	0512128	BRACKET         	CESSNA      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	BS 65.33	BROKEN          	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			3815 								UPON APPROACH TO LAND ON LAKE, FLAPS 10 SELECTED.  A/C IMMEDIATELY BEGAN TO ROLL TO LT, RETURNED FLAPS TO ZERO, A/C RETU	RNED TO LVL FLT.  TRIED TO DEPLOY FLAPS AGAIN (SLOWLY) AND OBSERVED RT FLAP DEPLOYED NORMALLY,  LT FLAP DID NOT MOVE, A/	C THEN RETURNED TO WHERE A FLAPLESS LANDING WAS CARRIED OUT WITH NO FURTHER PROBLEMS.  ONCE ON GROUND PILOT SELECTED FLA	PS 10 AND NOTED WHILE RT FLAP DEPLOYED IMMEDIATELY, LT FLAP SLOWLY FELL TO POSITION.  ONCE IN HANGAR AND OPENED UP FOR I	NSPECT IT WAS DISCOVERED THAT FLAP PULLEY BRACKET (LT) AT STA 65.33 DETACHED/TORN FROM BULKHEAD ASSY THUS CAUSING PULLEY	 TO NO LONGER BE ATTACHED TO AIRFRAME CAUSING FLAP TO MALFUNCTION.  PILOT CONFIRMED FLAPS FUNCTIONING NORMALLY FOR T/O.	1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006061900256	20060619	00256	SW  	2006	6	19	CA060116008      	1	20060113	G	5302	205032814103	PANEL           			BELL  	412   	412EP       	1182205	SW  										TAILBOOM	MISMANUFACTURED 	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											MFG WAS ADVISED BY A SUPPLIER THAT PANELS WERE PROCESSED UNDER A DIFFERENT CURE CYCLE THAN THE ONE PRESCRIBED BY THE MFG	 PROCESS SPECIFICATION.					1	G	7	2 	4U				H4SW    					 
2006061900257	20060619	00257	SW  	2006	6	19	CA060116009      	1	20060113	G	5302		PANEL           			BELL  	412   	412EP       	1182205	SW  										TAILBOOM	MISMANUFACTURED 	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											MFG WAS ADVISED BY A SUPPLIER THAT PANELS WERE PROCESSED UNDER A DIFFERENT CURE CYCLE THAN THE ONE PRESCRIBED BY THE MFG	 PROCESS SPECIFICATION.					1	G	7	2 	4U				H4SW    					 
2006061900278	20060619	00278	NM  	2006	6	19	CA060117001      	1	20060117	G	7931		ENGINE          			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  					NR 1	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											ECAM MSG ENG 1 LOW OIL PRESS ON APPROACH/AGAIN ON GRD DROPPED TO 13 PSI ENG SHUTDOWN.  TSM 79-00-00 PG 1, FOUND OVER 2 G	AL OF OIL IN AGB-OIL DRAINED AND CKD SUPPLY FILTER/SCAVENGE FILTER AND MAG PLUGS.   ALL OK, CK AGB SCAVENGE LINE, CLEAR,	 CK OIL TANK STRAINER, CLEAR.  GRD RUN AT T/O POWER AND LEAK CK OK.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2006062100076	20060621	00076	NE  	2006	6	21	CA060117002      	2	20060117	G	7240		DUCT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					14TH STG	FAILED          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											L14TH DUCT MSG ON DESCENT.  ACTIONED CHECKLIST AND SHUTDOWN ENGINE.  CHANGED DETECTOR ELEMENT A59WK.  OP TEST CARRIED OU	T IAW AMM SERV.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062100077	20060621	00077	CE  	2006	6	21	CA060117003      	1	20060113	G	3710	7297088	GEAR            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	VACUUM PUMP	SEIZED          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			858  	858  							VACUUM PUMP DRIVE SHAFT SEIZED AND SHEARED OFF 2 GEAR TEETH.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062100079	20060621	00079	CE  	2006	6	21	CA060117005      	1	20060114	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	BROKEN          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											DURING CRUISE AT 19,000 FT ALTITUDE, CABIN DIFF OF 5.8 PSI, THE INNER PANE OF THE CO-PILOT'S WINDSHIELD SHATTERED.  THE 	CREW LANDED THE AIRCRAFT SAFELY AT IT'S DESTINATION.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062100081	20060621	00081	NM  	2006	6	21	CA060118001      	1	20060116	G	3040	KCD4N	RELAY           			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											WHEN WINDSCREEN HEAT SELECTED TO WARM UP ON THE GROUND, SMOKE AND SPARKS CAME FROM RT FWD CORNER OF OVERHEAD PANEL. WIND	SCREEN HEAT RELAY 3041-K6 FOUND BURNED, RELAY BASE ALSO FOUND DAMAGED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062100082	20060621	00082	NE  	2006	6	21	CA060118002      	2	20060116	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1	MALFUNCTIONED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) HELI-SKING: AC DROPPED SKIERS AT TOP, HAD LIFTED OFF MOUNTAIN TO GO TO SKIER PICK UP PAD.  AC WAS ON A DESCENDING,	 SLIDE SLIPPING,  PILOT CARRIED OUT A SCAN OF INDICATORS, NOTICE NR AT 99 PERCENT, DESCENDING TO 98 PERCENT, WAS EXPECTI	NG A 101 PERCENT FOR HIM TO BEEP DWN TO 100 PERCENT. ENG OUT LIGHT NR1 ENG CAME ON AS WELL AS OTHER LIGHTS. NG, ITT WERE	 DECREASING ON NR 1 ENG. CREEPED NR BACK UP TO 100 PERCENT. ALSO CONFIRMED THAT THROTTLE WAS FULL OPEN. LEVEL OUT AC, IS	OLATED DEAD PWR SEC AND RETURNED TO HANGAR. NORMAL SHUTDOWN ON NR 2 PWR SEC. MAINT BOTH PWR SEC WERE STARTED UP ON GROUN	D, BOTH PWR SEC STARTED NML, OPS CHECK APPEARED TO BE NML. AC GROUNDED TO TROUBLESHOOT THE DEFECT. (TC NR 20060118002)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062100083	20060621	00083	NE  	2006	6	21	CA060118003      	2	20060117	G	7414	1050765	CLAMP           	CONT        	BL6006163   	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO COIL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				190  		C019710E					ENGINE MAGNETO COIL CLAMP FAILED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062100141	20060621	00141	NM  	2006	6	21	CA060119003      	1	20060117	G	3233	65C3575816	ACTUATOR        			BOEING	727   	727231      	1384079	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					UPLOCK	LEAKING         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, NLG FAILED TO EXTEND NORMALLY. SUSPECT POSSIBLE FREEZING IN UPLOCK MECHANISM AND/OR BUNGEE LINK. MANU	AL EXTENSION USED, NLG EXTENDED AND LOCKED. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION BY MAINTENANCE SUSPECTED A	CTUATOR BYPASSING INTERNALLY. ACTUATOR REPLACED.  (TC NR 20060119003)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006062100143	20060621	00143	NM  	2006	6	21	CA060119004      	1	20060117	G	3233	69141001	ACTUATOR        			BOEING	727   	727231      	1384079	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					MLG	FROZEN          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, NLG FAILED TO EXTEND NORMALLY. SUSPECT POSSIBLE FREEZING IN UPLOCK MECHANISM AND/OR BUNGEE LINK. MANU	AL EXTENSION USED. NLG EXTENDED AND LOCKED. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION BY MAINTENANCE SUSPECTED B	UNGEE ACTUATOR FROZEN. BUNGEE LINK REPLACED.  (TC NR 20060119004)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006062100145	20060621	00145	NM  	2006	6	21	CA060119005      	1	20060119	G	3297		WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	DAMAGED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) LANDING GEAR FAILED TO RETRACT: 3X RED AND 3X GREEN ON (UP) SELECTION. ON ARRIVAL THE ENGINEERS HAVE FOUND A FAULT	 WITH NWCENT UNREASONABLY FAR.  OPERATOR IS REPLACING THE WOW 2 HARNESS P/N 47151-5. (TC NR 20060119005)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006062100147	20060621	00147	EA  	2006	6	21	CA060120001      	1	20060118	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			27950								(CAN) FO WINDSHIELD OUTER PLY CRACKED IN FLIGHT.  REMOVED AND REPLACED WINDSHIELD.   WINDSHIELD IS PRE AD 2001-35-R1 (BA	 SB 601R56-04). (TC NR 20060120001)					2	L	7	2 	4F			RT	A21EA   					 
2006062100148	20060621	00148	SW  	2006	6	21	CA060120002      	1	20060117	G	6220	206011111003	BEARING RACE    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					M/R TRUNNION	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A SCHEDULED 1200 HR M/R CORROSION INSPECTION THE INNER RACE OF THE M/R TRUNNION BEARING WAS FOUND TO BE SEVERLY	 CORRODED TO THE POINT THAT THE INNER RACE WAS CRACKED. THIS BEARING RACE IS THERMALLY PRESS FIT AND THE TIGHT TOLLERANC	E, SEVERE CORROSION AND FLIGHT LOADS CAUSED THIS RACE TO CRACK (TC NR 20060120002)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006062100151	20060621	00151	NM  	2006	6	21	CA060120003      	1	20060119	G	2910	69744131	CONNECTOR       	BOEING      		BOEING	737   	7378Q8      	13844BX	NM  										SHUTOFF VALVE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			18156	18156							(CAN) RT ENGINE HYDRAULIC SHUTOFF VALVE FOUND LEAKING. FAULT TRACED TO CRACKED CONNECTOR - IPC REF 29-11-81-01, ITEM 50.	 CONNECTOR REPLACED. (TC NR 20060120003)					2	L	7	2 	4F			RT	A16WE   					 
2006062100153	20060621	00153	EA  	2006	6	21	CA060122001      	1	20060119	G	3310	2LA0069137	LIGHT           			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CONTAMINATED    	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CO-PILOT'S FLOOD LIGHT BELOW I-STRAP AREA WAS CONTAMINATED BY WATER, WHICH SHORTED THE FLOOD LIGHT AND MELTED. (TC	 NR 20060122001)					2	L	7	2 	4F			RT	A21EA   					 
2006062100154	20060621	00154	NM  	2006	6	21	CA060123001      	1	20060117	G	3233	AE7128852	FLEX LINE       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	NLG LOCK ACT	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			5895 								(CAN) CREW FOUND A PUDDLE OF THE HYDRAULIC FLUID ON THE GROUND AROUND OF THE NLG STRUT AFTER THE AIRCRAFT WAS PARKED. NL	G WHEEL WELL WAS WET CONDITION. RESULT OF THE INSPECTION, FOUND WIRE BRAID BROKEN AND FLUID LEAKAGE ON THE FLEXIBLE HOSE	 CONNECTED TO THE NLG LOCK ACTUATOR (UP) SIDE. HYDRAULIC FLUID QTY OF THE NR 2 SYSTEM WAS DOWN TO 35 PERCENT.  THE BROKE	N HOSE WAS REPLACED.  BOTH NOSE WHEEL ASSEMBLIES WERE REPLACED. NR 2 HYD FLUID LEVEL WAS ADJUSTED (REFILL).  LEAKAGE AND	 OPERATION CHECK NR 2 HYD SYSTEM (FLT CONTROL, STEERING)  OPERATION CHECK AND AIR BLEED NR 2 HYD SYSTEM WITH GHPU. (TC N	R 20060123001)	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE	 
2006062100155	20060621	00155	WP  	2006	6	21	CA060123002      	1	20060118	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FLT CONTROLS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			621  								(CAN) SERVO REMOVED FROM SERVICE BECAUSE OF A HYDRAULIC FLUID LEAK.  SERVO WAS INSTALLED AT THE FACTORY. (TC NR 20060123	002)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062100157	20060621	00157	GL  	2006	6	21	CA060123003      	2	20060121	G	7250	6898663	TURBINE WHEEL   			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	DAMAGED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			54   								(CAN) PILOT HEARD LOUD SQUEALING NOISE FOLLOWED BY VIBRATION WHILE IN CRUISE FLIGHT WITH PASSENGERS. ELECTED TO LAND IMM	EDIATELY. NORMAL LANDING AWAY FROM BASE CARRIED OUT. INSPECTION FOUND DAMAGE TO ENGINE TURBINE SECTION, SUSPECT 3RD STAG	E TURBINE WHEEL PROBLEM. ENGINE REMOVED AND REPLACED. TURBINE WILL BE SENT FOR INSPECTION. (TC NR 20060123003)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006062300031	20060623	00031	EA  	2006	6	23	CA060123004      	1	20060120	G	5630	C3FS5152	WINDOW          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PAX DOOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A TRAINING FLIGHT, AC CAME BACK TO DEPARTURE, WHERE ON THE VISUAL INSPECTION OF EXTERIOR OF FUSELAGE IT WAS 	NOTICED THAT RT AFT DOOR WAS MISSING EXTERIOR PART OF WINDOW (PLEXIGLASS) INCLUDING WEATHER STRIP AND THE FILLER STRIP. 	INTERIOR PART OF THE WINDOW (SCRATCH PANE) REMAINED IN PLACE. SURROUNDING AREA ON DOOR AND ALL AFT STRUCTURES THAT COULD	 HAVE BEEN IN CONTACT WITH THE WINDOWS TRAJECTORY WAS INSPECTED AND NO DAMMAGE WAS FOUND. AT THE TIME OF THIS REPORT, WI	NDOW, WEATHER AND FILLER STRIPS WERE ORDERED AND AWAITING PARTS.  OPERATOR HAS INITIATED A ONE-TIME FLEET INSPECTION ON 	COMPANY CAMPAIGN NOTICE 451-56-30-004. (TC NR 20060123004)	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006062300046	20060623	00046	GL  	2006	6	23	CA060123005      	1	20060110	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                     			TX	TAXI/GRND HDL  	1			CA			1725 								(CAN) PILOT REPORTED THAT THE REEL MECHANISM IN THE LT SHOULDER HARNESS ASSEMBLY ON THE RT SEAT WAS DEFECTIVE AND WAS NO	T ALLOWING THE BELT TO RETRACT.  AFTER REMOVAL, THE BELT WAS FINALLY 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 R	EEL WAS NO LONGER LOCKING. BELT ASSY. WAS REPLACED WITH NEW UNIT (TC NR 20060123005)			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006062300047	20060623	00047	CE  	2006	6	23	CA060123006      	1	20060119	G	2897	D3899926FJ4	PIN             			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CONNECTOR	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			1996 								(CAN) WHILE DE-FUELING AC FOR ROUTINE MAINT, IT WAS DISCOVERED THAT LT WING WOULD NOT DE-FUEL. MAINT FOUND THAT STBY FUE	L PUMP WAS NOT WORKING. TROUBLESHOOTING FOUND CONNECTOR PLUG P221 UNDER CENTER PEDESTAL HAD A BURNED PIN AND CONNECTOR. 	 PLUG AND CONNECTION BOTH SHOWED SIGNS OF OVERHEATING RESULTING FROM A SHORT CIRCUIT.  C/B PROTECTING THIS SYS NEVER TRI	PPED.  IT IS A 15 AMP C/B.  INVESTIGATION REVEALED EICAS INDICATION FOR STBY PUMP WAS (ON), INDICATING PUMP WAS WORKING 	WHEN IT WAS NOT. CONNECTOR PLUG WAS REPLACED AND FUNCTION CHECKS CARRIED OUT, RETURNED TO SERVICE.  DISCUSSION WITH MFG 	FSR IS ON GOING TO DETERMINE HOW THIS COULD HAPPEN. (TC NR 20060123006)	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062300049	20060623	00049	CE  	2006	6	23	CA060124001      	1	20060121	G	3233	1158100283	PINION GEAR     	BEECH       		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ACTUATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				937  		ALG5856					(CAN) THE GEAR ACTUATOR WAS REMOVED FROM THE AIRCRAFT FOR A RELUBE AND END PLAY CHECK IAW AD72-10-04R2 PART B AND C.  WH	EN IT WAS CLEANED UP THE MECHANIC NOTICED THAT SEVERAL OF THE TEETH ON THE PINION GEAR WERE BROKEN OFF.  THERE WAS NO OB	VIOUS REASON FOR FAILURE OF THE TEETH.  THIS WAS THE FIRST INSPECITON SINCE THE ACTUATOR WAS INSTALLED AFTER OVERHAUL.  	THE ACTUATOR ALSO FAILED THE END PLAY CHECK BY .003 THOUSANDS OF AN INCH. (TC NR 20060124001)			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006070500021	20060705	00021	SW  	2006	7	5	CA060124002      	1	20060120	G	2720	315372LR	RUDDER PEDAL    			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7559 								(CAN) DURING THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE AIRCRAFT RUDDER PEDALS WERE SENT FOR NDT I	NSPECTION WHERE IT WAS DISCOVERED THAT BOTH LT AND RT REAR RUDDER PEDALS WERE CRACKED.  THESE PEDALS ARE AN OLDER STYLE 	PEDAL AND ARE NO LONGER AVAILABLE FROM MFG.  (TC NR 20060124002)				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006062300056	20060623	00056	EU  	2006	6	23	CA060124003      	1	20060119	G	6710	ASNA00190961	SPHERICAL STOP  			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					COLLECTIVE	CORRODED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			3341 								(CAN) ON MONDAY 16 JANUARY 2006, PILOT REPORTED COLLECTIVE WAS ROUGH AT HIGH POWER SETTING. HE WAS UNABLE TO REPLICATE. 	(TC NR 20060124003)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2006062300061	20060623	00061	SO  	2006	6	23	CA060124004      	1	20060124	G	2720	6342008	BELLCRANK       			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	RUDDER CABLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17250	17250							(CAN) CRACKS ON THE LT RUDDER CABLE ATTACHING BELLCRANK FOR MORE INFORMATION INCLUDING PICTURES CONTACT SUBMITTER. (TC N	R 20060124004)					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006062300062	20060623	00062	NM  	2006	6	23	CA060124005      	1	20060118	G	7160		ARM             	ROTAX       		AMBLP 	A150  	A150        	3850110	NM  	ROTAX 	912   	ROTAX912F3  	 	EU  					AIRBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1490 								(CAN) ENGINE RECIEVED FOR OVERHAUL WITH AIRBOX INSTALLED. THE CARB DRIP TRAYS ARE CONNECTED TO THE AIRBOX BY A SUPPORT A	RM WITH TWO SCREWS HOLDING THE TRAYS ONTO THE SUPPORT ARM. THE DRIP TRAY SUPPORT ARM WAS FOUND CRACKED AT THE HOLES FOR 	THE SCREWS. (TC  20060124005)				1	B	7	2 	3O	3	O	0	SOOOO2SE	E00051EN				 
2006062300063	20060623	00063	NE  	2006	6	23	CA060124006      	2	20060118	G	7321	8063489	FUEL CONTROL    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1 ENGINE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			17872	3225 				807342			(CAN) NR 1 ENGINE FAILED TO START WITH IGNITION OPERATING NORMALLY.   5 ATTEMPTS WERE MADE BY THE FLIGHT CREW.  GROUND P	ERSONNEL NOTED EXTREME AMOUNT OF FLAMES COMING FROM THE JETPIPE AND ADVISED FLIGHT CREW.  FUEL CONTROL SN WYG85082 REPLA	CED, ENGINE GROUND RUN, STARTS NORMAL. GROUND CHECKED SERVICEABLE.  FDR DOWNLOAD SHOWED 2300 LBS OF FUEL FLOW ON START. 	NORMAL FUEL FLOW ON START EQUALS APPROX. 400 LBS. AFFECTED MFC IS BEING SENT FOR INVESTIGATION AND CORRECTIVE ACTION AS 	APPLICABLE.  (TC NR 20060124006)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062300064	20060623	00064	NM  	2006	6	23	CA060125001      	1	20060119	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	INOPERATIVE     	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			2764 								(CAN) AFTER TAKEOFF AND LANDING GEAR SELECTED UP, ALL GREEN AND RED UNLOCK LIGHTS REMAINED ON. AIRCRAFT RETURNED TO AIRP	ORT.    MAINT: PSEU PRESENT FAULTS NG WOW 2, NWCENT LOGGED. LANDING GEAR RETRACTION TEST CONFIRMED FAULT. HARNESS RESIST	ANCE CHECK CONFIRMED OPEN CIRCUIT. REPLACED WOW2/NWCENT HARNESS ASSY THEN LDG AND NW STEERING TESTED OK. (TC NR 20060125	001)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006062300065	20060623	00065	CE  	2006	6	23	CA060125002      	1	20060120	G	3110	07601316	COLLAR          			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	INSTRUMENT PANEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1299 								(CAN) DURING INSPECTION THE PILOT CONTROL COLUMN WAS NOTICED TO HAVE MORE MOVEMENT OFF-AXIS THAN THE CO-PILOT CONTROL PA	NEL.  THE PILOT'S CONTROL COLUMN SUPPORT & LOCK COLLAR WAS FOUND TO BE CRACKED LONGITUDINALLY AND WAS REPLACED NEW. (TC#	 20060125002)				1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2006062300067	20060623	00067	CE  	2006	6	23	CA060125003      	1	20060119	G	2710	2660001114	CONTROL CABLE   			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AILERONS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING NORMAL INSPECTION IT WAS FOUND THAT ONE OF THE AILERON WING LOOP CABLES WAS WEARING INTO THE SIDE OF THE LI	GHTNING HOLE OF THE FIRST WING RIB ON THE LT WING.  THE CABLE WAS DAMAGED AS WELL.  THE AIRCRAFT WAS GROUNDED UNTIL THE 	CABLE WAS REPLACED, THE DAMAGE TO THE LIGHTNING HOLE WAS DRESSED OUT AND THE RUBBER SEAL/GUIDE JUST IB OF THE WING RIB (	ON THE FUSELAGE) WAS REPLACED.  THE OTHER CARAVANS IN OUR FLEET WERE INSPECTED IN THAT AREA, NO OTHER DEFECTS WERE FOUND	. (TC NR 20060125003)		1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006062600129	20060626	00129	CE  	2006	6	26	CA060125004      	1	20060124	G	5350	50910276BSC	CAM             			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  		BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			22980	22980							HEARD A BANG DURING APPROACH, FOUND RT UPPER FWD COWL INNER PORTION HAD LIFTED FROM NORM POSITION.  FOUND CAM BOLT FAILE	D THAT PROVIDES TENSION TO LWR COWL ASSY.  OVER CTR COWL FASTENERS ON THESE A/C (4) INSTILL CONSIDERABLE FORCE AND HAVE 	A HISTORY ON ALL SIMILAR INSTALLATIONS WITH VARIOUS FAILURE MODES.  AS A RESULT, INSTALLED A BACKUP SYS OF PROVIDING HAR	DPOINTS TO ALLOW .032 LOCKWIRE TO BE INSTALLED BETWEEN TWO COWL HALVES, SHOULD ANY OF CAM POINTS FAIL.  LOCKWIRE ON INBD	 POINTS ALSO FAILED BUT OUTER POINTS HELD THRU CONCLUSION OF FLT.  COWL SUSTAINED SOME DAMAGE REQUIRING REPLACEMENT.  NO	W LOOKING AT DEVELOPING AN STC TO REMOVE ORIG CAM SYS ENTIRELY AND GOING WITH AN OVERLAP ARRANGEMENT AND SEVERAL CAMLOCK	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006062300136	20060623	00136	EA  	2006	6	23	CA060125005      	2	20060119	G	7414	10382585	POINTS          	BENDIX      		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			160  								(CAN) WHEN PERFORMING GROUND RUNUP,CHECKING MAGS ON RT ENG,  ENG WOULD QUIT WHEN RUNNING ON LT MAG ONLY.  TROUBLESHOOTIN	G REVEAL THAT LT POINTS WERE WORN SO MUCH THAT THEY WERE NOT OPENNING.  POINTS WERE REPLACED AND ENGINE RAN NORMAL AGAIN	. THIS HAS BEEN RECURRING, INTERMITTENT PROBLEM, WHERE YOU CANNOT COUNT ON HOW LONG THE POINTS WILL LAST.  PLASTIC NYLON	 ARM THAT RIDES ON THE CAM, WEARS PREMATURELY UNTIL ITS WORN SO MUCH THAT THE POINTS NO LONGER OPEN AND THEN IT QUITS FI	RING.  SAME PROBLEM WITH THE DUAL MAGNETO.   ALSO IT IS A DIFFICULT AREA TO GET AT TO SEE THE PONTS, USUALLY IT'S ON A 5	00 HOUR INSPECTION ITEM.  (TC NR 20060125005)	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062300173	20060623	00173	EA  	2006	6	23	CA060125006      	2	20060113	G	7322		SHAFT SEAL      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL PUMP	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				4185 		A75755					(CAN) WHILE DOING A GROUND RUN TO VERIFY THE COMPASS SYSTEM, TECH NOTICED UNCOMMANDED ACCELERATION AND DECELERATION OF T	HE RT ENGINE.  VISUAL INSPECTION IDENTIFIED BLUE DYE WASHOUT FROM THE FUEL PUMP TO FUEL CONTROL UNIT SEAL AREA AND CONFI	RMED A FAULT. THE FUEL CONTROL UNIT AND FUEL PUMP ASSEMBLY WERE REMOVED AND REPLACED WITH SERVICEABLE UNITS.   (TC NR 20	060125006)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006062300176	20060623	00176		2006	6	23	CA060125007      	4	20060125	G	3100		UNKNOWN         			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					UNKNOWN	MULTIPLE FAIL   	W				D				RETURN TO BLOCK         				G			MULTIPLE FAILURE          			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI OUT (TWICE) EICAS MESSAGES A/T FAIL, A/P FAIL, AFCS FAIL, MACH TRIM FAIL, SHAKER, ANTICIPATED, ADS 2 FAIL,	 TAT NR 2 FAIL,ADS FAIL, WINDSHEAR FAIL, AOA LIMIT FAIL, ADS PROBE NR 1 FAIL, ADS PROBE NR 2 FAIL, ADS PROBE NR 3 FAIL, 	ADS PROBE NR 4 FAIL, STALL PROTECTION FAIL, YD FAIL, ECT.  ACTION: ADS PROBES, ADS SYSTEM, TEST CARRIED OUT IAW AMM 34-1	3-01-06 SYSTEM CHECKS SERVICEABLE. STILL UNDER INVESTIGATION WITH FLEET MANAGEMENT AND MFG ENGINEERING.  (TC NR 20060125	007)		2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2006062300177	20060623	00177	SO  	2006	6	23	CA060125008      	1	20060124	G	5540	6342008	BAR             			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17249	17249							(CAN) PILOTS SIDE LT RUDDER BAR, CRACK FOUND ON COLLER BETWEEN ACCUATING ARM (FOR RUDDER CABLE) AND RUDDER BAR.  2 ADDIT	IONAL CRACKS WERE FOUND ADJACENT TO THE INITAL CRACK. (TC NR 20060125008)					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006062300178	20060623	00178	CE  	2006	6	23	CA060126001      	1	20060125	G	5520	115610010325	TORQUE TUBE     	BEECH       	115610010341	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1850 							(CAN) DURING THE 100 HR INSPECTION THE TAIL CONE WAS REMOVED TO INSPECT THE TORQUE TUBES IAW INSPECTION PACKAGE.  THE LT	 TORQUE TUBE WAS FOUND CRACKED AROUND HALF THE TUBE BRACE.  IT HAD BEEN 100 HRS SINCE THE LAST INSPECTION. THE PN OF THE	 BRACKET IS 115-610018-1 (TC NR 20060126001)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006072400089	20060724	00089	NE  	2006	7	24	CA060126002      	2	20060118	G	7200	CT78A	ENGINE          								GE    	CT7TP 	CT7TP*      	30030	NE  					NR 2	MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			686  								NR 2 ENGINE CHIP LIGHT WAS EXPERIENCED ON OB LEG TO THE FPSO.  THE AIRCRAFT WAS TURNED AROUND FOR DEPARTURE POINT.  THER	E WAS A SECOND INDICATION OF OIL BYPASS, HIGHER TGT AND LOWER OIL PRESSURE.  ENGINE WAS SHUTDOWN BY THE FLIGHT CREW.  TH	E AIRCRAFT RETURNED TO BASE ON SINGLE ENGINE WITHOUT FURTHER INCIDENT.  UPON ARRIVAL BACK TO BASE THE ENGINE WAS INVESTI	GATED AND FOUND TO HAVE METAL CONTAMINATION ON THE CHIP PLUG AND SUMP SCREENS.  THE ENG WAS REPLACED AND FORWARDED TO TH	E MFG FOR A FURTHER INVESTIGATION.							4	T			E8NE				 
2006062300180	20060623	00180		2006	6	23	CA060126005      	4	20060123	G	2330	50401100003	VIDEO DISPLAY   			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 11B	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON JANUARY 23, 2006 A/C WAS IN CRUISE WHEN SMOKE WAS OBSERVED COMING FROM SEAT 11B VDU. THE IFE SYSTEM WAS DEACTIV	ATED. MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFAC	TURER AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE. (TC	 NR 20060126005)			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062300181	20060623	00181	WP  	2006	6	23	CA060126006      	1	20060126	G	5343	5484911503	ATTACH FITTING  	DOUG        		DOUG  	DC6   	DC6A        	3021706	WP  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			42266								(CAN) DURING ANNUAL INSPECTION, AD 89-11-07 WAS BEING ACCOMPLISHED. THE LT IB MLG ATTACH FITTING WAS FOUND TO BE CRACKED	 BETWEEN THE 4TH AND 5TH FASTENER HOLES ON THE OB VERTICAL LEG. THERE WERE 2 CRACKS NOTED. THE LENGTH OF THE CRACK RUNNI	NG BETWEEN THE 2 FASTENER HOLES IS APPROXIMATELY .7500 INCH.  THERE WAS A SECOND CRACK NOTED RUNNING IN AN OUTWARD DIREC	TION AND IS APPROXIMATELY .2500 INCH IN LENGTH. THE FITTING IS BEING REPLACED WITH A SERVICEABLE FITTING. (TC NR 2006012	6006)		2	L	7	4 	4R	3	R		6A3     	ATC14	6	C	P871	 
2006062300183	20060623	00183	GL  	2006	6	23	CA060126007      	3	20060120	G	6111	T10282N	BLADE           	HARTZL      	HCB3TN5     	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2390 		BVA7387			BVA7387		(CAN) DISCOVERED WARPED TRAILING EDGE OF PROPELLER BY MAINTENANCE.  UNIT HAD BEEN OVERHAULED FEB 2003 THEN RETURNED FOR 	THIN TRAILING EDGE APRIL 2003.  REPAIRED BY SAME FACILITY.  TRAILING EDGE WAS SIGNIFICANTLY THINNER THAN SIMILAR IN FLEE	T.  REMOVED PROPELLER FROM SERVICE. (TC NR 20060126007)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2006062300184	20060623	00184	CE  	2006	6	23	CA060126008      	1	20060124	G	5540	MS289135	BEARING         	BEECH       	1306300001  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						207					(CAN) DURING A GENERAL WALKAROUND THE RUDDER WAS MOVED BY HAND. NOTICING THAT THE RUDDER SEEMED TO MOVE UP AND DOWN AND 	APPEARED TO RUB AGAINST THE TAIL CONE. RUDDER ATTATCHMENT INSPECTED. INVESTIGATION REVEALED THAT ALL THREE BEARINGS HAVI	NG SOME PLAY. THE LOWER BEARING SEEMED TO CAUSE THE RUDDER TO DROP. THIS INTURN WORE THE CLEVIS BRACKETS. REPLACED ALL T	HREE BEARINGS AND BOTH CLEVIS BRACKETS. RUDDER REINSTALLED AND TRAVEL CHECKED OK. AIRCRAFT RETURNED TO SERVICE. (TC NR 2	0060126008)		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006062300187	20060623	00187	NM  	2006	6	23	CA060127001      	1	20060127	G	5410	85410617005	DOOR            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT NACELLE	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) ON ARRIVAL TO BASE, THE DOOR FOR THE REFUEL PANEL WAS FOUND TO HAVE SEPARATED FROM THE NACELLE. THE HINGES, HINGE 	ATTACHMENT BOLTS AND SMALL FRAGMENTS OF THE COMPOSITE PANEL REMAINED ATTACHED. (TC NR 20060127001)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062300203	20060623	00203		2006	6	23	CA060127002      	4	20060123	G	2562	ELT10	ELT             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CABIN	INTERMITTENT    	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA				50   							(CAN) ELT FAILED THE ACTIVATION TEST DURING THE ROUTINE INSPECTION.  THE UNIT HAD THE BATTERY REPLACED AND RECERTIFIED 2	1 DAYS EARLIER.  AVIONICS SHOP FOUND THE PROBLEM TO BE A INTERMITTENT ON/OFF SWITCH. (TC NR 20060127002)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006062300204	20060623	00204	CE  	2006	6	23	CA060127003      	1	20060119	G	7333	903800097	INDICATOR       			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	FUEL FLOW	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) FUEL FLOW INDICATIONS WENT INTERMITTENT THEN FAILED IN FLIGHT.  FOUND TRANSMITTER TO HAVE FAILED INTERNALLY.  TIME	 ON UNIT APROX.5000 HRS. (TC NR 20060127003)					1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2006062300205	20060623	00205	CE  	2006	6	23	CA060127004      	1	20060126	G	5100	10038900161	SWITCH          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUEL DRAIN	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLOAT SWITCH FAILED INTERNALLY CAUSING THE EPA CAN TO DRAIN OVERBOARD ON SHUTDOWN. (TC NR 20060127004)						1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006062300206	20060623	00206	EU  	2006	6	23	CA060127005      	2	20060124	G	7260	DART5342	ENGINE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 1	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) ON DESCENT INTO AIRPORT, THE NR 1 ENGINE FAILED. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. (TC NR 20060127005)						2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2006071100116	20060711	00116	SW  	2006	7	11	CA060127006      	1	20060127	G	3210	71461	LANDING GEAR    			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			796  								(CAN) 2 SMALL CRACKS UNDER UPPER RADIUS OF LANDING GEAR.						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006062300208	20060623	00208	EU  	2006	6	23	CA060127007      	1	20060127	G	3097	330A63622309	WIRE HARNESS    			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					DE ICE SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			101  								(CAN) A/C RETURNED FROM AN OFFSHORE TRIP, THE MAINTENANCE STAFF WERE CARRING OUT A ROUTINE TURN AROUND CHECK AND FOUND T	HE M/R DEICE HARNESS BROKEN AT THE CONNECTOR PLUG. MAINTENANCE DEPT REPLACED THE HARNESS AND THE A/C RETURNED TO THE FLY	ING SCHEDULE. (TC NR 20060127007)				2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2006062300210	20060623	00210	NE  	2006	6	23	CA060129001      	2	20060125	G	7261	PW535A	ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  						LOW PRESSURE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVER	TED FOR AN UNSCHEDULED LANDING. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 2006	0129001)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006062300212	20060623	00212	NE  	2006	6	23	CA060129002      	2	20060115	G	7322	50099820	PUMP            			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL BOOST	FAULTY          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE LOST POWER AND WAS SHUTDOWN INFLIGHT.  SUBSEQUENT INVESTIGATION DETERMINED THE HYDROMECH	ANICAL FUEL CONTROL TO BE FAULTY.  FUEL CONTROL AND FUEL PUMP WERE REPLACED. (TC NR 20060129002)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006062600065	20060626	00065	NE  	2006	6	26	CA060129004      	2	20060123	G	7200	PW545A	ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	545   	PW545A      	 	NE  						DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	A	J	FLUID LOSS                	FLAME/FIRE                	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW OBSERVED ENGINE TEMPERATURE AND FUEL FLOW SPLIT. THE FLIGHT DIVERTED TO POINT OF DEPARTURE 	AND THE ENGINE WAS SHUT DOWN DURING DESCENT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE ENGINE INNER BYPASS DUCTING C	ONSISTENT WITH AN INTERNAL ENGINE FIRE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 	(TC NR 20060129004)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006062600076	20060626	00076	EA  	2006	6	26	CA060129005      	2	20060120	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  						FIRE            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A	R	J	FLAME/FIRE                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER AND FLAMES EMINATING FROM THE EXHAUST.	  THE ENGINE WAS SHUT DOWN IN FLIGHT.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DE	TERMINED. (TC NR 20060129005)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062600077	20060626	00077	NE  	2006	6	26	CA060129006      	2	20060118	G	7200		ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								DC0262			(CAN) THE ENGINE FLAMED OUT DURING GROUND HANDLING OPERATIONS.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT C	AUSE ONCE ESTABLISHED. (TC NR 20060129006)					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006062600078	20060626	00078		2006	6	26	CA060129007      	4	20060112	G	6122	3037685	GOVERNOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					OVERSPEED	FAULTY          	W				A				UNSCHED LANDING         				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			1599 	1    							(CAN) DURING CRUISE THE PROPELLER SPEED DECREASED. AN UNSCHEDULED LANDING WAS CARRIED OUT WHICH RESULTED IN A PROPELLER 	STRIKE.  SUBSEQUENT INSPECTION REVEALED A FAULTY PROPELLER OVERSPEED GOVERNOR.  IAW WILL INVESTIGATE THE EVENT AND ADVIS	E OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129007)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006062600079	20060626	00079	NE  	2006	6	26	CA060129008      	2	20060110	G	7321		FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	FAULTY          	W				A				UNSCHED LANDING         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE ENGINE LOST POWER FOLLOWED BY (ENGINE OUT) AND (LOW ROTOR SPEED) WARNING ANNUNCIATIONS. A SINGL	E-ENGINE UNSCHEDULED LANDING WAS CARRIED OUT.  SUBESQUENT INSPECTION REVEALLED A FAULTY AUTOMATIC FUEL CONTROL UNIT.  MF	G WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129008)				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2006062600081	20060626	00081	NE  	2006	6	26	CA060129010      	2	20060111	G	7200		ENGINE          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			CA								PR0565			(CAN) DURING FLIGHT TEST OPERATIONS (PERFORMING ENGINE RELIGHT) ENGINE DID NOT RELIGHT.  A DEADSTICK LANDING WAS ACCOMPL	ISHED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129010)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006062600082	20060626	00082	NE  	2006	6	26	CA060129011      	2	20060111	G	7200		ENGINE          			PROPJT	200   	200A        	0140304	NM  	PWA   	306   	PW306B      	 	NE  						SHUTDOWN        	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			CA						CC0045					(CAN) ON ROLL OUT FOLLOWING LANDING, THE PILOT REPORTED AN UNCOMMANDED ENGINE SHUT DOWN.  THE ENGINE BLEED VALVES AND BL	EED VALVE SOLENOID WERE SUBSEQUENTLY REPLACED. (TC NR 20060129011)					1	L	7	1 	3O	4	F		3A18    	E35NE				 
2006062600083	20060626	00083	CE  	2006	6	26	CA060129012      	1	20060102	G	7931	PT6A6D	ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						LOW PRESSURE    	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLL, THE ENGINE LOW PRESSURE WARNING ANNUNCIATED AND THE TAKE-OFF WAS ABORTED.  MFG WILL MONITOR 	INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129012)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006062600084	20060626	00084	EA  	2006	6	26	CA060129013      	2	20060102	G	7230		COMPRESSOR      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA								81119			(CAN) DURING DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION, ACCOMPANIED BY NOISE AND FLAMES EMANATING F	ROM THE EXHAUST.  THE ENGINE WAS SHUT DOWN IN FLIGHT, AN EMERGENCY DECLARED AND THE AIRCRAFT DIVERTED TO POINT OF DEPART	URE.  SUBSEQUENT INSPECTION REVEALED COMPRESSOR SECTION DAMAGE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL AD	VISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129013)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006062600086	20060626	00086	NM  	2006	6	26	CA060129014      	1	20060104	G	7900		ENGINE          		PW308C      	AMD   	FALC50	FALCON2000  	2730170	NM  	PWA   	306   	PW306B      	 	NE  						ODOR            	W				O				OTHER                   				B	O	O	SMOKE/FUMES/ODORS/SPARKS  	OTHER                     	OTHER                     	NR	NOT REPORTED   	1			CA								CF0049			(CAN) THE ENGINE WAS REPORTED TO EXHIBIT OIL SMELL IN CABIN AIR ACCOMPANIED BY HIGH OIL CONSUMPTION.  MFG WILL INVESTIGA	TE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129014)					2	K	7	2 	4F	4	F	RT	A50NM   	E35NE				 
2006062600088	20060626	00088	EU  	2006	6	26	CA060129015      	1	20060103	G	3610	31B576201	LINE            			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305B      	52128	NE  					PNEUMATIC SYS	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) FOLLOWING TAKEOFF, THE ENGINE FIRE WARNING ANNUNCIATED AND THE ENGINE WAS REPORTED TO BE (TRAILING SMOKE).  THE EN	GINE WAS SHUTDOWN IN FLIGHT, AN EMERGENCY DECLARED AND THE FLIGHT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION	 REVEALED NO EVIDENSE OF FLUID LOSS OR FIRE. A BLEED VALVE PNEUMATIC TUBE WAS FOUND FRACTURED. (TC NR 20060129015)				2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2006070300050	20060703	00050	NE  	2006	7	3	CA060129019      	2	20060102	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J	A		WARNING INDICATION        	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			CA											DURING START, AN ENGINE FADEC WARNING LIGHT ANNUNCIATED ACCOMPANIED BY FUEL AND FLAME EMANATING FROM THE ENGINE EXHAUST.	  THE START WAS ABORTED.  PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006070300051	20060703	00051	NE  	2006	7	3	CA060129020      	2	20060110	G	7321		FUEL CONTROL    			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					ENGINE	FAULTED         	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											DURING TAXI, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUT DOWN.  SUBSEQUENT INSPECTION RE	VEALED A FAULTY FUEL CONTROL UNIT.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006070300052	20060703	00052	NE  	2006	7	3	CA060129021      	2	20060121	G	7200		ENGINE          			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  						POWER LOSS      	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								AV0032			DURING CRUISE, ENGINE EXPERIENCED AN UNCOMMANED POWER REDUCTION.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  PWC WILL INVESTIG	ATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006070300053	20060703	00053	WP  	2006	7	3	CA060130001      	1	20060116	G	6321	E02400373500S	SPRING          	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ROTOR BRAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			92   			10913					DURING THE FIRST 100 HR INSPECTION CARRIED OUT ON THE AIRCRAFT, IT WAS NOTICED THAT THE ABOVE SPRING WAS BROKEN.  IT APP	EARS TO HAVE BROKEN AT THE UPPER ATTACHMENT POINT WHERE IT ATTACHES TO THE LOWER ROTOR BRAKE CALIPER ARM.  THE SPRING WA	S REPLACED WITH NEW.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006070300054	20060703	00054	CE  	2006	7	3	CA060130002      	1	20060125	G	5610		WINDSCREEN      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											WHILE IN CRUISE FLIGHT AT FL230, THE LT WINDSHIELD INNER PANE SHATTERED.  THE WINDSHIELD ANTI-ICE HAD BEEN SELECTED AT N	ORMAL SINCE DEPARTURE AND THE OAT WAS 38C.  THE CREW CONTACTED ATC TO DECLARE AN EMERGENCY AND REQUESTED RETURN TO AIR	PORT.  THE CREW THEN COMPLETED THE CRACKED OR SHATTERED WINDSHIELD CHECKLIST.  AS A PRECAUTION, THE OXYGEN MASKS WERE DO	NNED BY THE CREW MEMBERS AND PASSENGERS.  THE CAPTAIN FLEW THE APPROACH AND THE CO-PILOT FLEW THE DESCENT TO VISUAL AND 	LANDED SAFELY ON RWY 06.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006070300055	20060703	00055	NE  	2006	7	3	CA060130003      	2	20060116	G	7250	3053094CL9	SHROUD          			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	HOT SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1245 								ROUTINE BOROSCOPE INSPECTION OF HOT SECTION COMPONENTS REVEALED THAT TWO CT SEGMENTS HAD DROPPED OUT OF PLACE AND CONTAC	TED CT WHEEL.  THE SEGMENT RETAINING RING P/N 3020139 WAS FOUND OUT OF PLACE AND THE CT BLADES HAD WORN BEYOND LIMITS DU	E TO HEAVY TIP RUB.  THE WHEEL WAS REBLADED AND SEGMENTS REPLACED WITH P/N 3035673CL12 AND RETAINING RING P/N 3110741-02	, SB1627 AND SB1628 WERE EMBODIED.			1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2006070300056	20060703	00056	NE  	2006	7	3	CA060130004      	2	20060116	G	7250	3053094CL14	SHROUD          			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	HOT SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1666 								ROUTINE BOROSCOPE INSPECTION OF HSI COMPONENTS FOUND TWO SEGMENTS HAD DROPPED OUT OF POSITION.  POWER SECTION REMOVED AN	D CT COMPONENTS INSPECTED.  CT BLADES FOUND TO HAVE CONTACTED SEGMENT ENDS AND RETAINING RING P/N 3020159 FOUND OUT OF P	LACE.  SEGMENTS REPLACED WITH NEW P/N 3053094CL16 AND NEW RETAINING RING P/N 3020159 AND ALTERNATE SEGMENTS AND RING NOT	 AVAILABLE IN THE REQUIRED CLASS.  ENGINE REASSEMBLED.  SB1627 EMBODIED.			1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2006070300057	20060703	00057	CE  	2006	7	3	CA060130005      	1	20060124	G	5344		HINGE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	CABIN DOOR	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			598  								CABIN DOOR SIDE OF HINGE WAS REPLACED ON MARCH 15 2005 AT 5248.4 TTAF AND 4829 CYCLES.  DOOR SIDE OF HINGE FAILED JAN 23	 2006 AT 5846.8 TTAF AND 5480 CYCLES DOOR AND HINGE AREA WAS INSPECTED AND NO ADDITIONAL DAMAGE WAS NOTED CHERRYMAX RIVE	TS WHICH WERE INSTALLED WERE FOUND TO BE INCORRECT SIZE.  RECTIFICATION WAS TO REPLACE CHERRYMAX RIVETS WITH SOLID RIVET	S.			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2006070300058	20060703	00058	EA  	2006	7	3	CA060131001      	1	20060124	G	2497		WIRE HARNESS    			CNDAIR	CL600 	CL6002C10   	1390015	EA  											DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6607 								DURING T/S OF INOP LAV LIGHTS, FOUND 6 WIRES BELOW FLOOR, RT SIDE AFT FWD SERVICE DOOR DAMAGED, BURNED.  SMALLER HARNESS	 IS ROUTED UNDER LARGER HARNESS.  TWO BUNDLES WERE NOT SECURED AND THIS ALLOWED 2 HARNESSES TO RUB UNTIL CENTER CONDUCTO	RS EXPOSED AND A POWER AND GROUND MADE CONTACT RESULTING IN BLACK RESIDUE ON THE HARNESSES.  WIRING WAS REPLACED AND HAR	NESS SECURED TO ELIMINATE THE FOULING.  FOLLOWING WIRES ARE DAMAGED, OUTER JACKET DAMAGE WIRE NO ATA SYSTEM FBF7941-22 2	8-40-00, REFUEL/DEFUEL PANEL FBG6885-18 33-21-00, RT CEILING LT DIM/BRT FBG6884-18 33-21-00, RT CEILING LT DIM CONTROL C	ORE EXPOSED WIRE NO ATA SYSTEM FBF6420-22 33-24-00, FASTENER SEAT BELT SIGN FBH6770-22 33-22-00, PSU TEST FBH6771-22 33-	2	L	7	2 	4F			RT	A21EA   					 
2006070300059	20060703	00059	EU  	2006	7	3	CA060131002      	1	20060127	G	2160	5829C00	CONTROLLER      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN TEMP	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				810  							PILOT SELECTED ENVIRONMENTAL SYSTEMS TO AUTO PRIOR TO FLIGHT AND RECEIVED A CAUTION LIGHT ON PANEL THAT THE SYSTEM WAS N	OT FUNCTIONING.  THE SYSTEM WAS CYCLED ON AND OFF THEN AN INCREASE IN POWER WAS APPLIED AND THE CAUTION LIGHT EXTINGUISH	ED INDICATING NORMAL. FURTHER FLIGHTS THAT DAY WERE UNEVENTFUL. MAINTENANCE TROUBLESHOOTING VIA THE MANUAL SWITCH FROM F	ULL COLD THEN FULL HOT RESULTED IN A STUCK IN HOT VALVE.  THE TEMP VALVE WAS REPLACED AND SYSTEM FUNCTIONED FINE.  AIRCR	AFT TTSN 4650HRS,CYC 3286, THE ORIGINAL VALVE WAS REPLACED AT 3837 HRS 2662 CYC.  THE ONE REPORTED FAILED AT 810 HRS AND	 622 CYC.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006070300096	20060703	00096	CE  	2006	7	3	CA060131003      	1	20060120	G	2823	S160315865	CABLE           			CESSNA	337   	337C        	2075712	CE  	CONT  	O360  	IO360C      	17025	SO  					FUEL SELECTOR	BENT            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											AIRCRAFT WAS IN CRUISE FLT WHEN THE PILOT ATTEMPTED TO CHANGE LT FUEL SELECTOR FOR FORWARD ENGINE TO A DIFFERENT TANK.  	WHEN SELECTED THE KNOB STOPPED AT THE 1/2 WAY POINT CAUSING FUEL FLOW AND ENGINE POWER TO DECREASE.  THE PILOT SHUT DOWN	 THE ENGINE AND CONTINUED TO BASE WITHOUT FURTHER INCIDENT.  UPON MAINTENANCE INSPECTION, THE SELECTOR CABLE WAS FOUND K	INKED.  THE SELECTOR MECHANISM AND SELECTOR KNOB MECHANISM WERE BOTH FOUND TO MOVE FREELY.  NO OTHER DISCREPENCIES FOUND	.  NEW CABLE BEING INSTALLED.		1	H	7	2 	3O	3	O		A6CE    	E1CE				 
2006070500027	20060705	00027	SW  	2006	7	5	CA060131004      	1	20060127	G	6730	AN8345D	TEE FITTING     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SERVO ACTUATOR	CRACKED         	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						3153					WHILE IN CRUISE FLIGHT, THE PILOT FELT FEEDBACK SHOCK IN THE CYCLIC CONTROL.  THE PILOT ISOLATED HYDRAULICS AND MADE AN 	UNSCHEDULED LANDING.  MAINTENANCE CREW PERFORMED AN INSPECTION OF THE HYDRAULIC FLIGHT CONTROL SYSTEM.  A TEE FITTING TH	E LEFT HAND SERVO ACTUATOR WAS FOUND CRACKED AROUND HALF IT'S DIAMETER RESULTING IN A LEAK.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006070500030	20060705	00030	GL  	2006	7	5	CA060131005      	2	20060120	G	7250	23001967	TURBINE WHEEL   	ALLSN       	6898735     						ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			819  			CAT25545					TURBINE RECEIVED AT ETI FOR REPAIR.  NR 3 TURBINE WHEEL INSPECTED ON TEARDOWN.  NR 3 TURBINE WHEEL SENT TO NDT FOR FPI. 	 CRACKS WERE FOUND ON RIM.  LOG CARDS SHOW THAT NR 3 TURBINE WHEEL (S/N HX-84-131) HAS TTSN: 819.1 AND TCSN: 770.  NR 3 	TURBINE WHEEL LIFE IS TT: 4450 ^ TC: 6000.									3	U			E4CE				 
2006070500036	20060705	00036	CE  	2006	7	5	CA060201001      	1	20060201	G	5711	12212352	SPAR            			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3861 	3861 							A 100 HR INSPECTION WAS STARTED A CRACK WAS DISCOVERED AT THE RIGHT FRONT SPAROUT BOARD END WHERE IT ATTACHES TO THE SUB	 SPAR.  THE CRACK IS VERTICAL RUNNING APPROXIMATELY 1 1/2 TO TWO INCHES IN LENGTH.  THE CRACK STARTS AT THE TOP AND RUNS	 DOWN THROUGH A RIVET AND CONTINUES ON.				1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL	 
2006070500037	20060705	00037	GL  	2006	7	5	CA060201002      	3	20060201	G	6111		BEARING         	HARTZL      	HC83V202C   	GRUMAV	STC   	STCSCANTY30 	       	    						HARTZL	HC83V	HC83V202    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPON MPI INSPECTIONS, IT WAS NOTED THAT 2 A14B BEARINGS, 2 C838-6 CLAMPS, 1 C1404 HUB, AND 1 A1496-0 ARM WERE ALL CORROD	ED BEYOND LIMITS.  THROUGH DIMENSIONAL INSPECTIONS THE FOLLOWING PARTS WERE FOUND TO BE WORN BEYOND SERVICEABLE LIMITS, 	1 B806 CYLINDER AND ONE A871 MUSHROOM.				1	H	7	2 	3I				A734    		5	C	P14EA	 
2006070500038	20060705	00038	GL  	2006	7	5	CA060201003      	3	20060201	G	6111		CLAMP           	HARTZL      	HC83V202C   	GRUMAV	STC   	STCSCANTY30 	       	    						HARTZL	HC83V	HC83V202    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						D1629					UPON MPI INSPECTION IT WAS NOTED THAT 2 A14B BEARINGS, 3 C838-6 CLAMPS, 1 C1404 HUB, AND 2 A1496-0 ARMS WERE ALL CORRODE	D BEYOND LIMITS.  THROUGH DIMENSIONAL INSPECTIONS THE FOLLOWING PARTS WERE FOUND TO BE WORN BEYOND SERVICEABLE LIMITS,1 	B806 CYLINDER AND 1 A871 MUSHROOM.				1	H	7	2 	3I				A734    		5	C	P14EA	 
2006070500039	20060705	00039	CE  	2006	7	5	CA060201004      	1	20060129	G	5344	1154400311	HINGE BRACKET   			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											A 3/4 INCH CRACK WAS DISCOVERED WHEN MAINTENANCE WENT TO CHANGE A BUSHING.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006070500040	20060705	00040	CE  	2006	7	5	CA060202001      	1	20060131	G	5297		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	CARGO BAY	CHAFED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											A/C BROUGHT INTO HANGAR AFTER THE DAY OF FLYING.  WHILE IN THE HANGAR THE CARGO DOOR WARNING CAME ON.  INSPECTED THE DOO	R WARNING AND FOUND THE DOOR AJAR SWITCH STICKY AND THE LATCH HANDLE SWITCH CRACKED.  SWITCHES REPLACED ALL CHECKED OK. 	 THE REASON FOR THIS SDR IS THAT DURING THE INSPECTION OF THE CARGO DOOR ELECTRICAL SYSTEM FOUND THAT THE LOWER WIRING H	AS BEEN CHAFING ON THE DOOR. THIS COULD POSSIBLE CAUSE ERRONEOUS INDICATIONS IN THE FUTURE. SPIRAL WRAP WAS PLACED ON TH	E WIRING AND WIRING RESECURED TO TYWRAP POINTS.  WOULD SUGGEST THAT THIS WIRING BE SPIRAL WRAPPED TO PREVENT THIS FROM C	AUSING A FAULT IN THE FUTURE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006070500041	20060705	00041	NE  	2006	7	5	CA060202002      	2	20060201	G	7261		OIL SYSTEM      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 1 ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											AFTER DEPARTING, THE CREW OBSERVED LOSS OF OIL PRESSURE ON NR 1 ENGINE.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WIT	HOUT FURTHER INCIDENT.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006070500043	20060705	00043	NM  	2006	7	5	CA060202003      	1	20060129	G	2910		HYDRAULIC LINE  			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					THRUST REVERSER	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											HYDRAULIC LEAK DISCOVERED ON STOW LINE TO LT INBOARD THRUST REVERSER SYNC ACTUATOR ON NR 2 ENGINE, CAUSED FROM RUBBING O	N AN ANGLE EDGE SUPPORT.  LINE REMOVED AND FITTINGS CAPPED.  A FLEET CAMPAIGN IS NOW IN PROGRESS TO CHECK ALL SYNC ACTUA	TOR LINES FOR DAMAGE.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500111	20060705	00111	SO  	2006	7	5	CA060202004      	1	20060118	G	7120	8621202	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	LEFT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8436 								WHILE CARRYING OUT SCHEDULED 100 HOUR INSPECTION ON LEFT ENGINE A CRACK ON THE LT ENGINE MOUNT TOP OUTBOARD SECTION WAS 	NOTED.  MOUNT WAS REMOVED, REPAIRED AND REINSTALLED.					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006070500113	20060705	00113		2006	7	5	CA060202005      	4	20060201	G	2330		VIDEO DISPLAY   			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					SEAT 3C	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											A/C WAS IN CRUISE WHEN THE VDU AT SEAT 3C WENT BLANK FOLLOWED BY A SLIGHT ELECTRICAL SMELL. THE IFE SYSTEM WAS DEACTIVAT	ED.  MAINTENANCE PLACED THE VDU ON MEL.  THIS SDR WILL HAVE THE DEFECTIVE COMPONENT PART NUMBER AND SERIAL NUMBER UPDATE	D WHEN THAT INFORMATION IS AVAILABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006070500114	20060705	00114	SW  	2006	7	5	CA060202006      	1	20060201	G	5320	206031106079	ANGLE           			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11601								ANGLE FROM VERTICAL TUNNEL TO BOX BEAM CRACKED.						1	G	7	1 	3U				H2SW    					 
2006070500115	20060705	00115	NE  	2006	7	5	CA060203001      	2	20060201	G	7310	8280127119	FUEL LINE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT ENGINE	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											IT WAS DISCOVERED DURING OVERNIGHT ROUTINE MAINTENANCE THAT THE FUEL LINE IN THE LT ENGINE COMPARTMENT HAD BEEN IN CONTA	CT WITH A BRAIDED SHIELDED WIRE HARNESS CAUSING SEVERAL PIN HOLES WITHIN THE FUEL LINE CAUSING AN ATOMIZING EFFECT OF TH	E FUEL WITHIN THE ENGINE NACELLE.  FUEL LINE WAS REPLACED AND WIRE HARNESS RESECURED TO ENSURE TO CONTACT WITH FUEL LINE	.  AIRCRAFT GROUND RUN AND RELEASED INTO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070500083	20060705	00083	SO  	2006	7	5	CA060203003      	1	20060129	G	3297		WIRE HARNESS    	PIPER       	4550402     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	BROKEN          	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) WHEN LANDING GEAR WAS SELECTED ON APPROACH THE LT GEAR DOWN AND LOCKED LIGHT DID NOT COME ON.  CREW CHECKED THE BU	LB AND NOTIFIED AIR RADIO OF THE SITUATION. A FLY PAST WAS CARRIED OUT AND THE GEAR WAS CONFIRMED TO BE DOWN AND LOCKED.	 THE AIRCRAFT LANDED AND THE GEAR WAS INSPECTED FOR THE PROBLEM, A BROKEN WIRE WAS IDENTIFIED AND REPAIRED. (TC NR 20060	203003)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006060800386	20060608	00386	EA  	2006	6	8	CA060203004      	2	20060130	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RIGHT	FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA				2272 							DURING CRUISE FLIGHT, THE CREW HAD A SUDDEN LOSS OF POWER ON THE RIGHT HAND ENGINE.  THE ENGINE WAS FEATHERED AND THE AI	RCRAFT WAS DIVERTED TO THE NEAREST AIRPORT.  AFTER LANDING THE ENGINE WAS INSPECTED FOR ANY EXTERNAL DAMAGE OR OIL LEAKS	 NONE WERE FOUND.  OIL FILTER WAS REMOVED, METAL WAS FOUND SO FLIGHT WAS TERMINATED AND ENGINE ORDERED.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006060800387	20060608	00387	CE  	2006	6	8	CA060203005      	1	20060131	G	5544	AD200020	STOP            			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	RUDDER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											NO JAMMING OR EVIDENCE OF SEE ON EITHER RUDDER STOPS.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006060800388	20060608	00388	NM  	2006	6	8	CA060203006      	1	20060129	G	2760	82740061020	CLUTCH          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					RT SPOILER	UNKNOWN         	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			326  								FLIGHT CREW FOUND THEY COULD NOT OPERATE THE CONTROL WHEEL CCW DIRECTION AFTER ENGINE STARTING.  THE FLIGHT WAS CANCELLE	D.  MAINTENANCE FOUND THE MICROSWITCH ON THE RT SPOILER CLUTCH ASSY CONTACTING WITH THE BRACKET-UPPER MOUNTING.  THE CON	TACT WAS CAUSED BY THE IMPROPER INSTALLATION OF THE MICROSWITCH SCREWS.  BOMBARDIER AEROSPACE IS INVESTIGATING THIS EVEN	T.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006060800389	20060608	00389	CE  	2006	6	8	CA060203007      	1	20060202	G	2701	126011131	GUARD           			CESSNA	206   	T206H       	2073303	CE  										AILERON CABLE	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			14   								WHILE INSTALLING ALTERNATOR/WIRING UPGRADE, IT WAS NOTICED THAT THE STRAP COVER WAS LOOSE ON THE CABLE GUARD ON THE LEFT	 SIDE AILERON CONTROL QUADRANT.  SUBSEQUENT INSPECTION REVEALED THE RIGHT SIDE WAS ALSO LOOSE.  TOP AND BOTTOM SCREWS ON	 THE LEFT AND RIGHT SIDE WERE TOO SHORT DUE TO A WASHER BEING PLACED IN BETWEEN THE STRAP COVER AND THE AILERON CABLE GU	ARD FROM THE FACTORY.   INSUFFICIENT THREAD DEPTH INTO NUTPLATE, IE: 2 THREADS HOLDING ALL 4 FASTENERS = NOT IN SAFETY. 	 A CONDITION REPORT WAS SENT TO THE CESSNA FIELD REP TO INVESTIGATE QUALITY CONTROL ISSUES IN REGARDS TO THE POSSIBILITY	 OTHER NEW A/C AFFECTED.	1	H	7	1 	3O			RT	A4CE    					 
2006060800390	20060608	00390	CE  	2006	6	8	CA060205001      	1	20060202	G	2497	10936102247	WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	DC POWER	BURNED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											ON START, THE CREW ATTEMPTED TO START THE RIGHT ENGINE.  BUT NO LUCK STARTING THE ENGINE.  AIRCRAFT BROUGHT TO HANGAR AN	D MAINTENANCE DISPATCHED.  UPON ARRIVAL, MAINTENANCE ATTEMPTED TO START THIS ENGINE.  NO JOY.  THE STARTING ONLY HAD APP	ROX 300 HOURS REMAINING TIL OVERHAUL THEREFORE MAINTENANCE REPLACED THE STARTER THINKING THIS WOULD BE THE FAULT.  THE S	TARTER GENERATOR WAS NOT THE FAULT.  INSPECTION REVEALED THAT THE STARTER CABLE FEED THRU WAS BURNT UP ALONG WITH THE DC	 POWER PANEL.  THE STARTER LUG.  REPLACED THE FEED THRU CABLE AND THE POWER PANEL AND ENGINE START AND RUNS CARRIED OUT.	  NOW CHECKING SERVICEABLE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006060800391	20060608	00391	NM  	2006	6	8	CA060206001      	1	20060129	G	3297	471509	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG WOW	UNKNOWN         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											AN AIRCRAFT EXPERIENCED INTERMITTENT WOW CAUTION LIGHT DURING FLIGHT.  MAINTENANCE TELL US THAT THERE IS NO CURRENT FAUL	T TO BE FOUND IN THE PSEU NVM.  HOWEVER, THE NLG WOW 1 SENSOR SHOWS A HISTORY OF FAULTS IN RIGGING HISTORY.  WOW 1 SENSO	R HARNESS IN NLG REPLACED.  A/C RTS.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006060800392	20060608	00392	NM  	2006	6	8	CA060206004      	1	20060129	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG WOW	UNKNOWN         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											AN AIRCRAFT EXPERIENCED AN INTERMITTENT WOW CAUTION LIGHT DURING FLIGHT.  MAINTENACE PERSONNEL FOUND THAT THERE IS NO CU	RRENT FAULT TO BE FOUND IN THE PSEU NVM.  HOWEVER, THE LT GEAR WOW 2 SENSOR SHOWS A HISTORY OF FAULTS IN FAULT HISTORY. 	 WOW NR 2 HARNESS IN NLG REPLACED.  A/C RTS.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006060800393	20060608	00393	NM  	2006	6	8	CA060206007      	1	20060129	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG CENTERING	UNKNOWN         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											AN AIRCRAFT HAD TO RETURN TO FIELD BECAUSE OF FAILURE OF THE LANDING GEAR TO RETRACT.  UPON INVESTIGATION AND INTERROGAT	ION OF THE PSEU THE FAULT CODES WERE UNREASONABLE FAR -00.  NLG WOW 2/CENTERING HARNESS REPLACED.  A/C RTS.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006060800394	20060608	00394	NM  	2006	6	8	CA060206008      	1	20060201	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG	UNKNOWN         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											AN AIRCRAFT EXPERIENCED A WOW CAUTION LIGHT DURING FLIGHT.  MAINTENANCE FOUND PSEU INDICATED NR 2 WOW UNREASONABLE FAR, 	WITH TARGET PLACED IN FRONT OF SENSOR, THERE WAS NO CHANGE.  THE TECHNICIANS CHANGED THE NLG NR 2 WOW HARNESS PER AMM 32	-21-11-400-801, AND PSEU SHOWS NO FAULTS.  A/C RTS.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006060800395	20060608	00395	NM  	2006	6	8	CA060206009      	1	20060203	G	3230	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG DOOR	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											DURING DESCENT, THE NLG DID NOT EXTEND UNDER NORMAL EXTENSION, ALTERNATE RELEASE USED.  MAINTENANCE REPLACED THE NLG DOO	R SOLENOID SEQUENCE VALVE, CONDUCTED HYD BLEEDING AND GEAR SWINGS.  A/C RTS.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006070500175	20060705	00175	NM  	2006	7	5	CA060206010      	1	20060203	G	3260	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE GEAR FAILED TO RETRACT UPON GEAR UP SELECTION. MAINTENACE FOUND NWCENT OPEN ON THE PSEU. NLG WOW	 2/ CENTERING HARNESS REPLACED. A/C RTS. (TC NR 20060206010)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006070500177	20060705	00177	NM  	2006	7	5	CA060206012      	1	20060128	G	2740	106054554	BEARING RACE    			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ELEVATOR MAST	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) LOW FREQUENCY OSCILLATION FELT THROUGH AIRFRAME DURING CLIMB BETWEEN 240-270 KTS. NO CHANGE WITH AUTOPILOT ON OR O	FF.  ( NOTE: THIS WAS NOT VIBRATION ) HORIZ STAB PIVOT BEARINGS ON BOTH THE LT AND RT SIDE WERE REPLACED, BEARING HOUSIN	G WAS REPLACED ON LT SIDE . ELEVATOR INPUT BEARINGS ON ELEVATOR MAST WERE REPLACED BOTH LT AND RT SIDE.     FOLLOW UP AC	TION THERE HAS BEEN A HARD FAILURE FOUND. COMPONENTS HAVE BEEN REPLACED. THERE IS NO FOLLOW UP REQUIRED.   AC REMOVED FR	OM SERVICE FOR HORIZONTAL PIVOT BEARING REPLACEMENT.		2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006070500179	20060705	00179	CE  	2006	7	5	CA060207001      	1	20060130	G	3222	57411501	AXLE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9824 								(CAN) THE FORK, AXLE ASSY WAS SENT TO SHOP FOR BUSHING REPLACEMENT, INPECTION AND PAINTING. THEY FOUND THE AXLE BACK PLA	TE CRACKED. NEW AXLE FITTED.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2006070500180	20060705	00180	CE  	2006	7	5	CA060207002      	1	20060207	G	2720	504200337	SUPPORT BEAM    			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	RUDDER QUAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26469	26469							(CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THE	SE CRACKS WERE FOUND AT THE TOP BEND RADIUS AND AT SOME HOLES FOR NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 3 OTHER	 OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLACED AND CHECKED SERVICABLE (TC NR 20060207002)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2006070500181	20060705	00181	NM  	2006	7	5	CA060207003      	1	20060207	G	3231	46503105	TARGET          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG UPLOCK ASSY	MISSING         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			345  								(CAN) AFTER THE LANDING GEAR SELECTED TO UP DURING CLIMB, THE LT DOOR AMBER INDICATION REMAINED ON AS WELL AS THE LT MLG	 RED INDICATOR REMAINED ON.  CREW RETURNED TO BASE.  MAINTENANCE FOUND:  LT UP-LOCK SENSOR INDUCTANCE REPORTED TO BE OUT	 OF LIMITS. THE LOW INDUCTANCE FOR THE UP-LOCK SENSOR HAS BEEN TRACED TO A MISSING TARGET ON THE UP-LOCK. MLG UPLOCK ASS	Y TO BE REPLACED. (TCNR 20060207003)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006070500182	20060705	00182	GL  	2006	7	5	CA060207004      	3	20060205	G	6112	4E256010	BOOT            	HARTZL      		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	MISSING         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			344  			BUA27749					(CAN) WHILE ON A ROUTINE LOCAL TRAINING FLIGHT, THE PILOT EXPERIENCED SEVERE VIBRATION FROM THE ENGINE/PROPELLER. RETURN	ING TO THE AIRFIELD THE AIRCRAFT WAS LANDED SAFELY. INSPECTION REVEALED THAT ONE PROPELLER BLADE DE-ICER BOOT HAD DETACH	ED FROM THE BLADE AND WAS MISSING. THE MISSING BOOT HAD BEEN INSTALLED ON SEPT 9/2005 AND HAD ACCRUED 343.7 HRS TSN. (TC	 NR 20060207004)			1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2006070500183	20060705	00183	CE  	2006	7	5	CA060207005      	1	20060207	G	3222	0641124	AXLE            			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200*      	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4331 	4331 							(CAN) DURING A STRUCTURAL INSPECTION, A CRACK WAS FOUND IN RADIUS OF PART WHERE THE CYLINDER PORTION MEET THE BLOCK WHER	E THE BOLTS ARE. BOTH AXLES (QTY 2) WERE CRACKED. ONE WAS VERY EASY TO SEE. THE OTHER APPEARED UNDER LIQUID PENETRANT. P	ARTS HAVE BEEN REPLACED BY NEW PARTS.  DND HAVE A SPECIAL INSPECTION ON THAT PART FOR THE MFG OPERATED BY THE MILITARY. 	SOME WERE FOUND WITH CRACKED AXLES 3 YEARS AGO. (TC NR 20060207005)			1	H	7	1 	3O	3	O		5A5     	E269	5	N	P874	 
2006070500184	20060705	00184	EA  	2006	7	5	CA060208001      	1	20060130	G	7603	1603730007	THROTTLE CABLE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			11003								(CAN) THE LT ENGINE WOULD NOT GO BELOW 82 PERCENT WHEN THE THROTTLE WAS RETARDED TOWARD IDLE. THE LT ENGINE WAS SHUT DOW	N IAW QRH INSTRUCTION. TROUBLESHOOTING REVEALED THE CABLE ASSEMBLY FROM THE GEARBOX TO MFC BROKEN. CABLE WAS REPLACED IA	W AMM. (TC NR 20060208001)				2	L	7	2 	4F			RT	A21EA   					 
2006070500214	20060705	00214	EA  	2006	7	5	CA060208002      	1	20060119	G	2730	6224404101	CONTROL CABLE   			CNDAIR	CL600 	CL6002C10   	1390015	EA  										ELEVATOR	STUCK           	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			2991 								(CAN) DURING APPROACH ELEVATOR CONTROL STUCK MOMENTARILY. APPROX 5 LB CONTROL FORCE BROKE ELEVATOR CONTROL FREE. ELEVATO	R CONTROL OPERATED NORMALLY FOR APPROACH AND LANDING.  AUTO PILOT PITCH SERVO CONDITION AND CABLE TENSION, PERFORMING A 	SLIP CLUTCH CHECK OF THE PITCH SERVO MOUNT, PERFORM OPERATIONAL CHECK OF THE AUTOPILOT SYSTEM. ALSO COMPLETED LUBRICATIO	N OF THE ELEVATOR SERVO IAW REQUEST.  ALL CHECKS WERE GOOD AND LUBRICATION COMPLETED (TC NR 20060208002)			2	L	7	2 	4F			RT	A21EA   					 
2006070500240	20060705	00240	SO  	2006	7	5	CA060208003      	1	20060207	G	3221	67054003	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6857 								(CAN) PART OF THE INSPECTION PROGRAM INCLUDES LANDING GEAR SERVICING. THE GEAR TRUNNIONS ARE FITTED WITH GREASE HOLES AN	D/OR FITTINGS TO ALLOW QUICK AND EASY SERVICING DURING SCHEDULED INSPECTIONS. WHILE CARRYING OUT THIS SERVICING ON THE N	OSE GEAR TRUNNION GREASE WAS NOTED COMING OUT OF AN ODD LOCATION. PAINT WAS STRIPPED FROM THE LOWER KNUCKLE AND REVEALED	 CRACKS TOP AND BOTTOM.  A SERVICEABLE INSPECTED UNIT WAS INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060208003	)		1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006070500241	20060705	00241	EU  	2006	7	5	CA060208004      	1	20060208	G	2760	70282721801	MODULE          			EMB   	ERJ190	ERJ190100IGW	3260408	EU  										SPOILERS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) SPOILER FAULT CAUTION AT 33000. THE AIRCRAFT DID YAW AS A SPOILER PANEL EXTENDED AND RETRACTED. QRH PROCEDURES CAR	RIED OUT. SPOILERS CONFIRMED RETRACTED VISUALLY FROM CABIN. IB MULTIFUNCTION SPOILERS INDICATED A FAULT ON MFD FLIGHT CO	NTROL  PAGE FLT CTRL NO DISPATCH AFTER LANDING. ACTION: FLIGHT CONTROL MODULE REPLACED IAW AMM 27-03-02 (TC NR 200602080	04)			2	L	7	2 	4F			RT	A57NM   					 
2006070500242	20060705	00242	GL  	2006	7	5	CA060208006      	2	20060207	G	7230	23059598	SCROLL          	ALLSN       		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ANTI ICE BOSS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1480 		CAC33937					(CAN) ON INSPECTION THE ENGINEER WAS TAKING APART THE ANTI-ICE BODY 6856984 FOR INSPECTION AND FOUND A CRACK AROUND THE 	BOSS. (TC NR 20060208006)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006070500244	20060705	00244	WP  	2006	7	5	CA060208007      	1	20060207	G	6730	D2121	SERVO           			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				455  							(CAN) DURING AN INSPECTION HYDRAULIC LEAKS WAS FOUND AROUND THE FWD AND AFT SERVOS.THE RT FWD SERVO S/N 0251 AND THE AFT	 SERVO S/N 0667 WERE REMOVED AND NEWLY OVERHAULED ARE BEING INSTALLED. (TC NR 20060208007)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006070500246	20060705	00246	NM  	2006	7	5	CA060208009      	1	20060207	G	2910	NAS1611130	O-RING          			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	SWOLLEN         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA			7336 								(CAN) SHORTLY AFTER TAKEOFF, CREW NOTICED SYS (A) HYDR INDICATED ZERO QTY. CREW DECLARED AN EMERGENCY, ASKED FOR A RETUR	N TO AIRPORT. CREW REQUESTED A FUEL DUMP, THIS WAS APPROVED BY ATC. AFTER FUEL DUMPING WAS COMPLETED AC RETURNED AIRPORT	 FOR ARRIVALS ILS 29. AC LANDED SAFELY AND WAS TOWED TO RAMP. INSP WAS ACCOMPLISHED. CAUSE OF HYDR FAILURE WAS  FAILED O	-RING EXTRUDING FROM IB FLAP PWR UNIT HYDR MOTOR. MOTOR ASSY AND O-RING REPLACED, (A) SYSTEM FILTERS REMOVED, INSPECTED 	FOR METAL. FILTERS FOUND CLEAN. OB MOTOR WAS REMOVED, INSPECTED, FOUND SERVICEABLE.  IAW MM FILTERS TO BE REINSPECTED AF	TER 200 HOURS.  AC HYDR SYS SERVICED, AC WAS RETURNED TO SERVICE. (TC NR 20060208009)	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006070500285	20060705	00285	EA  	2006	7	5	CA060208011      	2	20060202	G	7321	25244392	FCU             			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	FLUCTUATES      	W				A				UNSCHED LANDING         				X	M	J	ENGINE FLAMEOUT           	OVER TEMP                 	WARNING INDICATION        	DE	DESCENT        	1			CA				3479 							(CAN) WHEN AC WAS ABOUT 10 MIN FROM LANDING, ON DESCENT, ENG POWER LEVERS WERE RETARDED FROM 38 LBS OF TORQUE. THE RT EN	GINE TQ AND T5 STARTED FLUCTUATING. RT POWER LEVER WAS BROUGHT BACK FURTHER BUT TQ AND T5 CONTINUED TO RISE. RT POWER LE	VER WAS PUT TO IDLE AND PROP LEVER TO FULL FINE IN AN ATTEMPT TO REDUCE TQ AND T5 HOWEVER BOTH PARAMETERS STILL INCREASE	D FURTHER TO 55 LBS OF TQ AND 900 DEGREES ON T5. ENG WAS SHUT DOWN AND THE AC LANDED WITHOUT INCIDENT. FCU WAS REPLACED,	 RIGGED AND ENGINE RUN-UPS COMPLETED. AC WAS FLOWN BACK TO BASE. RT POWER SECTION WAS REMOVED AND SENT FOR AN OVER TORQU	E INSPECTION, AND THE FCU SENT FOR REPAIR.   (TC NR 20060208011)	1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006071100151	20060711	00151	EA  	2006	7	11	CA060208015      	1	20060130	G	7120	73512562	MOUNT           			DHAV  	DHC6  	DHC6300     	2802606	EA  										ENGINE	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			631  								(CAN) THE PILOT REPORTED AFTER LANDING THE LT ENGINE WAS BROKEN. THE MAINTENANCE CREW REPLACED THE BROKEN TOP LT ENGINE 	MOUNT ALONG WITH THE VIBRATION ISOLATOR AND NEW GASKETS AND ATTACHMENT BOLTS. (TC NR 20060208015)					1	H	7	2 	3T			RT	A9EA    					 
2006071100152	20060711	00152	CE  	2006	7	11	CA060209001      	1	20060131	G	2910	CM3574D460B0	HOSE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HYD SYSTEM	BURST           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA			6000 								(CAN) LANDING THE CREW DEPLOYED THE THRUST REVERSERS AND GOT 6 LIGHTS FOLLOWED BY (HYD LOW LEVEL) AND (HYD LOW FLOW) LIG	HTS. MAINTENANCE FOUND ONE LINE P/N CM3574D460B000S ON THE LT SIDE HAD BURST. REPLACED LINE WITH NEW. INSPECTED BOTH PRE	SSURE FILTERS AND NO METAL WAS FOUND. THE HYDRAULIC RESERVOIR WAS SERVICED AND THE THRUST REVERSER AND SPEED BRAKES WERE	 FUNCTION CHECKED. STARTED RT ENGINE TO PERFORM FUNCTION CHECKS. INSPECTED HYDRAULIC FILTERS FOR METAL, NONE FOUND. AIRC	RAFT PLACED ON JACKS AND GEAR SWING COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060209001)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006071100153	20060711	00153	WP  	2006	7	11	CA060209002      	1	20060207	G	3222	MS288891	PRESSURE VALVE  			NAMER 	B25   	B25J        	6400710	WP  	WRIGHT	R2600 	R260035     	67050	EA  	HAMSTD	23E	23E50       	NE  	NLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			4534 								(CAN) AC NOSE WHEEL STEERING INDICATOR SHOWED A NON-CENTRED CONDITION OF NOSE WHEEL IMMEDIATELY AFTER TAKE-OFF.  AFTER S	EVERAL LOW FLYOVERS TO VISUALLY CHECK CONDITION,  EMERGENCY WAS DECLARED, AC WAS LANDED.  POST LANDING, NOSE OLEO WAS DI	SCOVERED TO HAVE BECOME FULLY DEFLATED (ALTHOUGH THERE WAS NO OIL LEAKAGE), WHICH PREVENTED  OLEO FROM FULLY EXTENDING, 	THUS NOT ALLOWING INTERNAL CENTERING DEVICE TO CENTER THE WHEEL.  SOURCE OF LEAK WAS DETERMINED TO BE A LEAKING HIGH PRE	SSURE INFLATION VALVE (SCHRADER).  WHILE VALVE IS CORRECT ONE, CALLED FOR IN PARTS MANUAL, STANDARD PRACTICE TO INSTALL 	MECHANICALLY CLOSED VALVES. THIS WAS DONE, OPERATION OF OLEO CENTRING DEVICE WAS CONFIRMED. (TC NR 20060209002)	2	M	7	2 	4R	4	R		AL2     	PAGE42	6	C	P603	 
2006071100154	20060711	00154		2006	7	11	CA060209003      	4	20060202	G	6122		GOVERNOR        			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	PROPELLER	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			2295 	477  				356706			(CAN) ENGINE OVERSPEED ON A TOUCH AND GO LANDING AT AIRPORT, ON TAKEOFF. ENGINE WAS REPORTED ROUGH ON THE RETURN FLIGHT.	  THE INSTRUCTOR AND THE OWNER ONBOARD DECIDED TO DECLARE AN EMERGENCY AND LAND BACK WHERE THE AIRCRAFT IS BASED AT THIS	 TIME.  MAINTENANCE HAS DISCOVERED THAT THE SPARK PLUGS WHERE FOULED AND IN POOR SHAPE THE PROP GOVENOR WAS REMOVED FOUN	D BITS OF A RUBBER SEAL OR O-RING MATERIAL. GOVERNOR WAS SENT OUT FOR TESTING AND RECERTIFICATION. THIS WORK WAS ACCOMPL	ISHED ON FEB 8 2006. (TC NR 20060209003)		1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
2006071100155	20060711	00155	SW  	2006	7	11	CA060209004      	1	20060206	G	5524	214001920101	HORN            			BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			551  								(CAN) AFTER LANDING AND SHUTDOWN, DURING REGULAR INSPECTION, A CRACK WAS FOUND IN THE ELEVATOR HORN ASSY. PART WAS REMOV	ED AND REPLACED BEFORE FURTHER FLIGHT. (UNDER CODES F1 WAS USED HOWEVER FLIGHT CONTROLS WERE NOT AFFECTED, AS  PILOT DID	 NOT NOTICE ANY CHANGE IN FLIGHT CARACTERISTICS. THE ELEVATOR WAS STILL ABLE TO FUNCTION NORMALY WITH THE CRACK. (TC NR 	B20060209004)			2	G	7	1 	4U	4	U		H6SW    	E4NE				 
2006071100156	20060711	00156	EU  	2006	7	11	CA060209005      	1	20060207	G	2435	23079009	STARTER GEN     			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				1132 							(CAN) RT GENERATOR FAILER INDICATION ON APPROACH. CREW LANDED A/C WITH NO MORE PROBLEMS.  STARTER/GENERATOR REPLACED. ST	ARTER/GEN 67.9 HOURS REMAINING BEFORE OVERHAUL DUE. BRUSH INSPECTED TO BE 20 PERCENT  REMAINING. (TC NR 20060209005)					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2006071100157	20060711	00157	CE  	2006	7	11	CA060209006      	1	20060208	G	5312	0411951	BULKHEAD        			CESSNA	150   	150         	2071802	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100*      	GL  	MLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ANNUAL INSPECTION, AM AME NOTICED THE MLG STRUT BULKHEAD UNDER THE CABIN FLOOR HAD SMALL CRACKS. UPON FU	RTHER INSPECTION WITH THE FLOORS REMOVED IT WAS FOUND THE ENTIRE MLG ATTACHMENT BULKHEAD/BOX STRUCTURE WAS NEAR FAILURE.	 MANY COMPONENTS MAKE UP THE ENTIRE BOX STRUCTURE AND MANY OF THEM WERE CRACKED OR FAILED. ALL THE DAMAGED AND CRACKED C	OMPONENTS WERE REPLACED WITH NEW PARTS AND REASSEMBLED.  THE PN OF THE 2 BULKHEADS ARE 0411951-5 AND -6. (TC NR 20060209	006)		1	H	7	1 	3O	3	O	NT	3A19    	E252	5	N	P918	 
2006071100158	20060711	00158	EA  	2006	7	11	CA060210001      	1	20060209	G	5740	C6WM102727	FITTING         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			32840								(CAN) UPON INSPECTION OF WING FRONT SPAR ADAPTER FITTINGS IAW REO 6-57-30-013, CRACKS WERE FOUND ON THE LT AND RT WING F	RONT SPAR ADAPTER FITTINGS AS FOLLOWS; LT WING, BETWEEN WING STATION 35.15 AND 47.5, ONE CRACK BETWEEN 5TH AND 6TH RIVET	. LT WING, BETWEEN WING STATION 47.5 AND 60.0, ONE CRACK BETWEEN THE 7TH AND 8TH RIVET. RT WING BETWEEN WING STATION 35.	15 AND 47.5, ONE CRACK BETWEEN 4TH AND 5TH RIVET. AIRCRAFT ADVISED. (TC NR 20060210001)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006071000103	20060710	00103	NM  	2006	7	10	CA060210002      	1	20060209	G	3297		GROUND WIRE     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG SELECTOR	LOOSE           	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											PILOT REPORTED THAT THE LANDING GEAR DID NOT EXTEND ON SELECTION.  AN ALTERNATE GEAR EXTENSION SELECTION WAS CARRIED OUT	 AND THE AIRCRAFT LANDED WITH OUT INCIDENT.  THE PSEU HISTORY AND PRESENT FAULT WERE AS FOLLOWS: "DIN 01A FAULT"(DISCRET	E INPUT EXTEND COMMAND) THE PROBLEM WAS TRACED TO A LOOSE GROUND "GS9" CONNECTED TO THE  LANDING GEAR CONTROL AND INDICA	TION PANEL CONNECTOR P55  PIN "P".  REF: WDM 32-61-00  SHT 7 OF 12 PAGE 1.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006071100164	20060711	00164	EU  	2006	7	11	CA060210003      	1	20060131	G	3010	FAL1007	HOSE            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					RT SLAT	COLLAPSED       	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			111  	111  							(CAN) DURING APPROACH THE FLIGHT CREW NOTICED THAT THE RT OB SLAT WAS NOT SHEDDING ICE WITH THE WING ANTI-ICE ACTIVATED.	 UPON INSPECTION THE RT OB SLAT FLEX HOSE WAS FOUND TO BE SLIGHTLY COLAPSED INTERNALLY.  ANTI-ICE SYSTEM WAS ACTIVATED 4	4 TIMES.  (TC NR 20060210003)				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2006071100193	20060711	00193	EU  	2006	7	11	CA060210004      	1	20060126	G	2822	P94B12208	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					LT FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOOST PUMP JUST STOPPED WORKING. REMOVED AND INSTALLED OVERHAUL PUMP SAME P/N AND ALL IS OK. (TC NR 20060210004)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006071100194	20060711	00194	WP  	2006	7	11	CA060210006      	1	20060202	G	2822	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			882  								(CAN) PILOT RECORDED A DEFECT THAT THE PUMP WAS MAKING A GRINDING NOISE.  PUMP ASSEMBLY WAS REPLACED.  NO FURTHER DEFECT	S NOTED. (TC NR 20060210006)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006080800101	20060808	00101	NE  	2006	8	8	CA060210007      	2	20060203	G	7200		ENGINE          			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TP 	CT79B       	30030	NE  					NR 2	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			42   								(CAN) AFTER TAKE-OFF, ENGINE NR 2 CHIP LIGHT STARTED TO FLICKER.  AC WAS TURNED AROUND TOWARDS PLACE OF DEPARTURE. EMERG	ENCY CHECKLIST WAS FOLLOWED, ENG NR 2 WAS BROUGHT BACK TO IDLE.  DURING A LONG FINAL ON DESCENT, ENGINE WAS BROUGHT BACK	 ON LINE FOR LANDING.   AC LANDED WITHOUT FURTHER INCIDENT, RETURNED TO HANGAR FOR INSP. AFTER INVESTIGATION,  TECH REPS	 WERE CONTACTED, RECOMMENDED A GROUND RUN AS OUTLINED IN MM. THIS GROUND RUN WAS CARRIED OUT, THERE WAS NO CHIP LIGHT BU	T UPON FURTHER INVESTIGATION SOME METAL CONTAMINATION WAS FOUND ON THE CHIP PLUG, IT WAS UPON THE ADVICE OF THE MANUFACT	URER TO REPLACE THE ENGINE. THE ENGINE WAS REPLACED AND THE A/C WAS RETURNED TO SERVICE.	2	G	7	2 	4U	4	T		R00024BO	E8NE				 
2006071100195	20060711	00195	CE  	2006	7	11	CA060210008      	1	20060209	G	7110		LATCH           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT COWL	LOOSE           	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			9741 								(CAN) RT ENGINE COWLING UNLATCHED IN FLIGHT (CALLED IN PRIORITY LANDING). RT ENGINE COWLING INSPECTED, FOUND FORWARD LAT	CH WAS LOOSE. RT ENGINE COWLING SECURED. RETRAINING CARRIED OUT WITH FLIGHT CREW AND TECHNICIANS ON PROPER COWLING LATCH	ING PROCEDURES.  (TC NR 20060210008)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006071100196	20060711	00196	NM  	2006	7	11	CA060210009      	1	20060210	G	5312	85310109	ANGLE           			DHAV  	DHC8  	DHC8102     	2809003	NM  										BULKHEAD	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35538								(CAN) DURING A C-CHECK HEAVY CORROSION WAS FOUND ON THE FRONT PRESSURE BLK STA 120.0 ON THE LOWER AFT CAP ANGLE P/N 8531	0109 AND ON THE FORWARD CAP ANGLE P/N 85310108. THE DAMAGE WAS SUBMITTED TO MFG WHO ISSUE A SPECIFIC REPAIR TO BE CARRIE	D OUT. (TC NR 20060210009)				2	H	7	2 	4T			RT	A13NM   					 
2006071100197	20060711	00197		2006	7	11	CA060211001      	4	20060210	G	6113		PLATE           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	PROPELLER	DAMAGED         	W				O				OTHER                   				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA			89   								(CAN) SHEARED RIVETS ON BACKPLATE FACE. (TC NR 20060211001)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006071100198	20060711	00198	EA  	2006	7	11	CA060211002      	1	20060207	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) THE COPILOT SIDEWINDOW CRACKED IN DESCENT.  WINDOW REPLACED, AIRCRAFT RELEASED TO SERVICE.  (TC NR 20060211002)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071100201	20060711	00201	NM  	2006	7	11	CA060213001      	1	20060212	G	7921	800600M03005	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 NACELLE	OVERHEATED      	W				A				UNSCHED LANDING         				M			OVER TEMP                 			CR	CRUISE         	1			CA											(CAN) ABOUT TEN MINUTES AFTER TAKEOFF NR 2 ENGINE OIL TEMPERATURE STARTED RISING, CREW WENT THROUGH CHECKLIST CLOSED BYP	ASS DOORS, TEMPERATURE WAS ABOVE 107 DEGREES FOR ABOUT 20 MINUTES AND ABOVE 115 DEGREES FOR ABOUT 10 MINUTES. TEMPERATUR	E PEAKED AT 122 DEGREES THEN IT STARTED COOLING AGAIN ON OUR DESCENT BACK TO BASE.  BY THE TIME THE CREW LANDED, THE TEM	PERATURE WAS NORMAL AT 94 DEGREES. OIL COOLER DOOR ACTUATOR WAS DETERMINED TO BE THE CAUSE. THE OIL COOLER DOOR ACTUATOR	 REPLACED. (TC NR 20060213001)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006071900032	20060719	00032	SW  	2006	7	19	CA060213002      	1	20060212	G	2140	ES721822	AIR DUCT        	AIRCOM      		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					CABIN HEATER	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE, AN AME NOTICED THAT HE COULD NOT MOVE THE HEATER AIR OUTLET.  ON CLOSER INVESTIGATION, HE FOUN	D THE OUTLET MELTED.  NO OTHER DAMAGE WAS NOTED. (TC NR 20060213002)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006071900033	20060719	00033	NM  	2006	7	19	CA060213003      	1	20060210	G	2751	18157014	TRANSMITTER     			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					IB TE FLAP	FAILED          	W				L				ABORTED APPROACH        				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA			7591 								(CAN) AIRCRAFT EXPERIENCED A FLAP ASYMMETRY ON APPROACH. CREW DECLARED AN EMERGENCY AND ELECTRICLY DROVE THRU FLAPS TO L	ANDING CONFIGURATION. AIRCRAFT LANDED SAFELY AND WAS TAXIED TO THE HANGER. HANGER MAINTENANCE CONFIRMED THE LT IB FLAP T	RANSMITTER AS THE CAUSE. LT IB FLAP TRANSMITER REPLACED AND ENTIRE FLAP SYSTEM CHECKED FOR RIGGING IAW THE MM. NO FURTHE	R FAULTS FOUND. SUBMITTER WILL UP-DATE THIS SDR AS MORE INFORMATION COMES IN FROM FLIGHT CREW. (TC NR 20060213003)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006071900034	20060719	00034	EA  	2006	7	19	CA060213004      	1	20060210	G	2910	MM67075294009	LINE            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	GE    	CF34  	CF348C1     		NE  					NR 2 HYD SYS	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) TOTAL LOSS OF NR 2 HYDRAULIC FLUID, FROM A RUPTURE ON THE PRESSURE MANIFOLD LINE P/N MM670-75294-009. NR 2 HYDRAUL	IC LINES P/N MM670-75294-009, MM670-75294-005 AND SUPPORT CLAMPS P/N MM670-75800-041, MM670-75800-029 ALL REPLACED. ENGI	NE DRIVEN PUMP FAILED AND REPLACED. IT IS SUSPECTED THE CAVITATIONS CAUSED BY THE FAILURE OF THE ENGINE DRIVEN PUMP CAUS	ED EXCESSIVE BUFFETING IN THE HYDRAULIC LINES. THE BUFFETING OF THESE LINES CAUSED DAMAGE TO THE CLAMPS AND RESULTED IN 	THE HYDRAULIC LINE CHAFING THROUGH UNTIL TOTAL LOSS OF HYDRAULIC FLUID OCCURED. (TC NR 20060213004)		2	H	7	2 	4R	4	F	RT	A14EA   	EOOO63EN				 
2006071900036	20060719	00036	NE  	2006	7	19	CA060213006      	2	20060209	G	7510	577957	MANIFOLD        			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, THE NR 2 FIRE WARNING CAME ON THROUGH CLIMB, POWER LEVER REDUCED WITH SUBSEQUENT WARNING EXTINGUI	SHING AND AIRCRAFT RETURNED.  INSPECTION CARRIED OUT AND FOUND THE NR 2, 13TH STAGE FUEL HEAT DUCT RUPTURED AT BOTH ENDS	. THE DUCT WAS THEN REPLACED.  (TC NR 20060213006)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006071900037	20060719	00037	SW  	2006	7	19	CA060213008      	1	20060210	G	5302	206033004051	SKIN            	BELL        		BELL  	206   	206L        	1181522	SW  										TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AORP00728					(CAN) DURING A 100 HOUR INSPECTION THE ENGINEER DISCOVERED 2 CRACKS EMINATING FROM 2 RIVETS ON THE THE TAIL ROTOR GEARBO	X ATTACH SUPPORT.  THE CRACKS GO OUT TO THE EDGE OF THE SKIN.  THE RIVETS WERE ALSO FOUND TO BE SMOKING OR LOOSE. (TC NR	 20060213008)				1	G	7	1 	3U				H2SW    					 
2006071900038	20060719	00038	CE  	2006	7	19	CA060214001      	1	20060213	G	2133	NN5040	TUBE            		10357626    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					OUTFLOW VALVE	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING UNSCHEDULED MAINT FOR AN UNRELATED MAINTENANCE ISSUE, THE POLYFLOW LINE PROVIDING ATMOSPHERIC REFERENCE PRE	SSURE TO THE RT OUTFLOW VALVE WAS FOUND MELTED AND OPEN TO CABIN PRESSURE. THE POLYFLOW LINE WAS TOO LONG AND WAS POSITI	ONED IN SUCH A WAY AS TO REST AGAINST THE EMERGENCY PRESSURIZATION LINE P/N: 6515201-3. THE HEAT FROM THE EMERGENCY PRES	SURIZATION LINE CAUSED NYLON TUBING TO MELT.  NEW TUBING OF THE CORRECT LENGTH WAS INSTALLED AND ROUTED CLEAR OF THE EME	RGENCY PRESSURIZATION LINE. AIRCRAFT WAS RETURNED TO SERVICE.  AC SERVICES HAS INITIATED CAMPAIGN 851-21-30-031TO INSPEC	T THE REST OF OUR FLEET FOR CORRECT INSTALLLATION OF THE POLYFLOW LINE. (TC NR 20060214001)	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006071900039	20060719	00039	EU  	2006	7	19	CA060214002      	1	20060214	G	7830	28850009	LOCK            			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					THRUST REVERSER	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THRUST REVERSER NR 4 UNLOCKED. SHUTDOWN NR4 V/S ON OVERWEIGHT LANDING 500FT/MIN LANDING WT 233000 KG.   SEE FMR M1	243972. ACTION:411T/S 78-31-00-810-970 CARRIED OUT NO FAULT FOUND.  SUSPECT PRIMARY LOCK P/N 2885000-9 LOCATED AT IB UPP	ER SIDE. 4 LOCK PLUGS ARE LOCATED IN THE OB PARTS BOX. (TC NR 20060214002)				2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2006071900040	20060719	00040	EU  	2006	7	19	CA060214003      	1	20060207	G	2710	LN93614C46R210	CONTROL CABLE   			CASA  	C212  	C212CC      	2410204	EU  	GARRTT	TPE331	TPE33110R   	0517	WP  	HARTZL	HCB4M	HCB4M       	GL  	AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18632								(CAN) DURING ROUTINE MAINTAENANCE INSPECTION, SEVERAL WIRES FOUND BROKEN ON RT AILERON CONTROL CABLE AS IT PASSES AROUND	 CABLE PULLEY AT FRAME 4. PULLEY FOUND SEIZED TO BOLT. CABLE, PULLEY AND BOLTS REPLACED. (TC NR 20060214003)					2	H	7	2 	4T	4	T		A43EU   	E4WE	6	C	P56GL	 
2006071900065	20060719	00065	NM  	2006	7	19	CA060214004      	1	20060214	G	3244	314381	TIRE            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					NOSE GEAR ASSY	DEFLATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN MAINTENANCE ARRIVED AT THE GATE FOR THE DAY'S FIRST DEPARTURE, IT WAS NOTICED THAT THE LT NOSE TIRE WAS FLAT.	 UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE RT NOSE TIRE WAS ALSO FLAT. BOTH NOSE ASSEMBLIES REPLACED AND AIR	CRAFT RETURNED TO SERVICE.  (TC NR 20060214004)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006071900066	20060719	00066	SO  	2006	7	19	CA060214005      	1	20060213	G	2121	C180559A1	BLOWER          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN AIR	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			1598 	447  							(CAN) DURING CRUISE FLIGHT, WITH NO PASSENGERS ON BOARD, THE CREW NOTICED AN ELECTRICAL BURNING SMELL IN THE AIRCRAFT AN	D SMOKE IN THE CABIN. THE AIRCRAFT WAS DIVERTED TO THE NEAREST SUITABLE AIRPORT AND LANDED. UPON INVESTIGATION MAINTENAN	CE PERSONNEL DISCOVERED THAT THE SMELL AND SMOKE WAS COMING FROM THE CABIN BLOWER. THE CABIN BLOWER WAS DISABLED AND DEF	ERRED AND A GROUND RUN WAS COMPLETED WITH NO FURTHER SMOKE OR BURNING SMELL NOTED. THE AIRCRAFT WAS THEN RETURNED TO SER	VICE. ONCE THE AIRCRAFT RETURNED TO A MAINTENANCE BASE THE BLOWER WAS REMOVED AND SENT OUT FOR REPAIR AND A COMPONENT ST	RIP REPORT. (TC NR 20060214005)	1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006071900067	20060719	00067	GL  	2006	7	19	CA060214006      	2	20060210	G	7260	6820588	WASHER          	ALLSN       		AEROSP	AS355 	AS355*      	       	EU  	ALLSN 	250C  	250C20R1    	03013	GL  					GEARBOX	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						CAG40968					(CAN) AS ENG NR 2 WAS INCREASED, EXCEEDANCE ON INSTR PANEL, M/R READING HIGH ON TRIPLE TACH, NO INDICATION OF N2 SPEED O	N TACH INDICATOR. FOUND N2 GOV GEAR FREEWHEELING, DISENGAGED FROM INTERNAL GB N2 DRV SYS.   TEARDOWN OF GB REVEALED BRG 	RETAINING WASHER WAS MISSING, N2 PWR TRAIN IDLER GEAR ASSY.  WASHER RETAINS BRG ON IDLER GEAR SUPT SHAFT. KEY WASHER RET	AINED BRG ON IDLER SUPT SHAFT, UNTIL BRG INNER RACE WORE EDGE OF KEY WASHER ALLOWING BRG TO SLIDE AXIALLY, DISENGAGE N2 	TACH DRV GEARTRAIN. WITH N2 TACH DRV GEARTRAIN DISENGAGED FROM N2 DRV, ENG COULD OVERSPEED.  WEAR ON ID OF N2 PWR TRAIN 	IDLER BRG, PORTION OF KEY WASHER, IDLER GEAR. PREVIOUS CHIP LIGHTS REPORTED ARE RESULT OF WEAR. (TC NR 20060214006)	1	G	7	2 	3U	3	U		H11EU   	E4CE				 
2006071900068	20060719	00068	NM  	2006	7	19	CA060214007      	1	20060210	G	2730	BACB10ET06	BEARING         			BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					ELEVATOR	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			52087								(CAN) REPORTED THAT ELEVATOR FELT HEAVY FOR BOTH CAPT AND F/O. AILERON NORMAL.  TROUBLESHOOTING SHOWED THAT THE ROLLER B	EARING THAT RIDES IN THE ELEVATOR INPUT CAM WAS SEIZED, CAUSING HIGHER THAN NORMAL FORCE REQUIED TO MOVE FLIGHT CONTROL 	OUT OF (DETENT).  BEARING REPLACED AND SYSTEM CHECKED IAW AMM 27-31-17 P216, OPS FOUND NORMAL.   AFTER BEARING REPLACEME	NT, NO FURTHER DEFECTS NOTED. (TC NR 20060214007)			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2006071900069	20060719	00069	CE  	2006	7	19	CA060215001      	1	20060213	G	3411	AERROQUIP206	HOSE            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					PITOT SYS	CRACKED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			1873 								(CAN) DURING A SCHEDULED PITOT/STATIC CHECK, THE AVIONICS TECHNICIAN DISCOVERED A LEAK ON THE LT PITOT CIRCUIT.  AFTER F	URTHER TROUBLESHOOTING, THE TECHNICIAN DISCOVERED A HOSE THAT WAS CRACKED (MIL-H-5593-4).  THE HOSE WAS REPLACED AND THE	 SYSTEM WAS SERVICEABLE. (TC NR 20060215001)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006071900070	20060719	00070	GL  	2006	7	19	CA060215002      	2	20060213	G	7261	6870032N	FILTER          								ALLSN 	250C  	250C20      	03013	GL  					OIL SYSTEM	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ENGINE OIL FILTER, VENDOR NR IS 05228-759280-101.  THERE WAS A PROBLEM WITH ONE OF THE SEAMS IN ONE OF THE ELEMENT	S NOT BEING SEALED.  ALL OF THE PTI FILTERS IN STOCK WERE INSPECTED AND FOUND THE SAME DEFECT IN EACH FILTER.  THE FILTE	RS WERE PURCHASED AND THE VENDOR HAS BEEN NOTIFIED OF THIS DEFECT AND ALL THE FILTERS HAVE BEEN PLACED IN QUARANTINE STO	RES PENDING RETURN TO THE VENDOR. (TC NR 20060215002)								3	U			E4CE				 
2006071900071	20060719	00071	EA  	2006	7	19	CA060215003      	2	20060210	G	7260	3027977	CARRIER ASSY    								PWA   	PT6   	PT6A6       	52043	EA  					RGB	DISPLACED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2998 	16   							(CAN) OPERATOR COMPLAINED OF NOISE FROM THE REDUCTION GEARBOX, EXCESSIVE PROPELLER LOOSENESS AND METAL ON THE RGB CHIP D	ETECTOR. UPON GEARBOX DISMANTLE AND EXAMINATION OF THE 2ND STAGE CARRIER (PN 3027977), THE SLEEVE USED TO REPAIR THE NR 	5 BEARING JOURNAL WAS FOUND TO HAVE SHIFTED OFF OF THE JOURNAL (REFER TO FIGURES 1 AND 2).  NO SECONDARY DAMAGE TO THE R	EDUCTION GEARBOX ASSEMBLY WAS NOTED.   THE SLEEVE REPAIR IS PERMITTED ON 2ND STAGE CARRIER PN 3027977 FOR OTHER ENGINE M	ODELS, AND THIS PART NR IS ELIGIBLE FOR USE ON THE ENGINE, HOWEVER SLEEVE REPAIR IS PROHIBITED IAW MM 3034543 FOR THE EN	GINE APPLICATION.  (TC NR 20060215003)						3	T			E4EA				 
2006071900072	20060719	00072	EA  	2006	7	19	CA060216001      	1	20060215	G	2435	03600923	BEARING         	BFGOODRICH  		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18997	1231 		Y20071R					(CAN) ORIG SNAG (STARTER SWITCH DOES NOT AUTO DELATCH) DRIVE END BEARING FAILURE (03-6009-23)  STARTER GENERATOR HAS BEE	N MODIFIED TO -008 (S/B -8-24-81)   (TC NR 20060216001)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006071900073	20060719	00073	EU  	2006	7	19	CA060216002      	1	20060124	G	6321	AHA1121	CALIPER         			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR BRAKE	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PISTON DOES NOT RETRACT INTO CALIPER HOUSING AFTER BRAKING CAUSING ROTOR BRAKE PAD TO REMAIN IN CONTACT WITH BRAKE	 DISC.  (TC NR 20060216002)					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006061600128	20060616	00128	CE  	2006	6	16	CA060216003      	1	20060215	G	5711		FRAME           			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16976								UPON BEGINNING A PHASE 3 INSPECTION, A TECHNICIAN DISCOVERED A SMALL CRACK ON THE RIGHT FORWARD LOWER SPAR HINGE CAP.  T	HE CRACK WAS OUT FROM THE FOURTH FASTENER FORWARD TOWARD THE HINGE EDGE.  A SMALL AREA OF PAINT HAD BEEN FLAKED AWAY IN 	THIS AREA.  MORE PAINT WAS REMOVED IN THIS AREA IN AID TO FURTHER INVESTIGATE THE DISCREPANCY.  IT WAS CLEARLY VISIBLE T	O SEE WITHOUT ANY NDT INSPECTION METHODS REQUIRED.  THE AIRCRAFT WAS REMOVED FROM SERVICE.  IT WAS NOTED THE PREVIOUS ED	DY CURRENT INSPECTION (AS REQUIRED IAW THE RAYTHEON SIRM) WAS CONDUCTED IN THIS AREA IN JANUARY 2005, 754.8 HOURS AGO.		1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
2006060600225	20060606	00225	NM  	2006	6	6	CA060216004      	1	20060216	G	2140	RBGB161	BLOCK           			BOEING	737   	7378Q8      	13844BX	NM  										TERMINAL BLOCK	OVERHEATED      	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			IN	INSP/MAINT     	1			CA			18445	18445							REPLACING AFT WATER DRAIN MAST DUE TO INOPERATIVE HEATER.  GROUND TERMINAL BLOCK GD11996 WAS FOUND DAMAGED WITH SIGNS OF	 OVERHEATING.  WIRES DISCONNECTED AND CAPPED, AND EFFECTED CIRCUIT BREAKERS PULLED TO ISOLATE TERMINAL BLOCK UNTIL REPLA	CEMENT PART AVAILABLE.				2	L	7	2 	4F			RT	A16WE   					 
2006061900175	20060619	00175	NE  	2006	6	19	CA060216005      	2	20060215	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			547  					4374			(CAN) DURING A 100 HR INSPECTION THE IGNITORS WERE REMOVED AND IT WAS FOUND THAT THE CERAMIC SURROUNDING CENTER ELECTROD	E WAS LOOSE.  BOTH IGNITORS WERE CHAMPIONS.  ENGINE VIB CHECK WAS CARRIED OUT AND FOUND WITHIN LIMITS. LT IGNITOR S/N 04	020731 AND RT S/N 03124329. (TC NR 20060216005)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006060700248	20060607	00248	NM  	2006	6	7	CA060216006      	1	20060216	G	2822	3823002	PUMP            			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 2 FUEL TANK	UNKNOWN         	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA											ON CLIMB, NR 2 RT AFT FUEL BOOST PUMP CB RELEASED FOLLOWED BY NR 2 LT AFT CB RELEASING APPROX 3 MIN LATER, NR 2 RT FWD C	B RELEASED AND NR 2 LT FWD BOOST PUMP LOW PRESS LIGHT ILLUMINATED INTERMITTENTLY.  A/C RETURNED TO DEPARTURE.  MX INSPEC	TED ALL EFFECTED PUMPS, CONNECTORS, BREAKERS AND SWITCHES, NO FAULTS FOUND.  BREAKERS WERE RESET, PUMPS WERE RUN FOR AN 	HOUR.  DURING THIS TIME PUMPS WERE SELECTED OFF AND ON NUMEROUS TIMES.  A/C RETURNED TO SERV & OPERATED WITH NO INCIDENT	.  MX REINSPECTED ALL OF ABOVE ALONG WITH CHECKING NR 2 TANK FOR FUEL CONTAMINATION.  NOTHING FOUND.  DUE TO UNUSUAL CIR	CUMSTANCES MAINT HAS DECIDED TO REPLACE THREE EFFECTED BOOST PUMPS, BREAKERS AND SWITCHES.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006060800197	20060608	00197	CE  	2006	6	8	CA060217001      	1	20060214	G	3150	70H10A	DIODE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	FAILED          	W				O				OTHER                   				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						BB24					CREW REPORTS THAT MULTIPLE SYSTEMS AND ANNUNCIATORS UNSERVICEABLE.  MAINTENANCE PERSONAL DISPATCHED AND FOUND THAT NR 1 	DUAL FED ELECTRICAL BUS HAD FAILED BOTH MAIN FEED DIODES (P/N 70H10A).  DIODES REPLACED AND FUNCTION CHECKED SERVICEABLE	.  COMPANY HAS NOW IMPLEMENTED A MONTHLY REPETITIVE CHECK OF THE BUS SYSTEM DUE TO THE DORMANT FAILURE RISK OF THESE DIO	DES.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060800397	20060608	00397	CE  	2006	6	8	CA060217002      	1	20060207	G	3233	79990022A	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF.  MAINTEANCE DID MULTIPLE GEAR SWINGS BUT COULD NOT DUPLICATE THE PROB	LEM.  THE ACTUATOR WAS REMOVED AND PUT IN A TEST STAND WHERE IT FINALLY FAILED STAYING IN THE LOCKED POSITION.  A OVERHA	ULED ACTUATOR WAS INSTALLED AND THERE HAS BEEN NO MORE PROBLEMS REPORTED.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006060700251	20060607	00251		2006	6	7	CA060217003      	4	20060213	G	2562	PS400010	ELT             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					CABIN	ACTIVATED       	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			CA			194  								ELT ACTIVATED IN FLIGHT.  ELT REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006060800199	20060608	00199	CE  	2006	6	8	CA060218001      	1	20060214	G	3230	571302	MOTOR           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	BURNED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFTER TAKEOFF, AIRCRAFTS LANDING GEAR WOULD NOT RETRACT.  CREW CONTACTED MX AND CREW AND MX DECIDED TO LEAVE THE LANDING	 GEAR DOWN AND CONTINUE THE 30 MINUTE FLIGHT TO THE MAIN BASE.  ALL INDICATIONS SHOWED THAT THE LANDING GEAR WAS DOWN AN	D LOCKED.  THE AIRCRAFT LANDED AND DEPLANED THE PASSENGERS AND RETURNED TO THE HANGAR.  WHEN MAINTENANCE TROUBLESHOT THE	 LANDING GEAR SYSTEM THE FAULT WAS FOUND WITH THE MOTOR.  MOTOR WAS REPLACED AND GEAR SWINGS CARRIED OUT SATISFACTORY.  	THE PCB WAS ALSO REPLACED DUE TO THE TIME DELAY BUT THIS HAD NOTHING TO DO WITH THIS FAULT.  AIRCRAFT THEN RETURNED TO S	ERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006060800201	20060608	00201	CE  	2006	6	8	CA060219001      	1	20060117	G	5520	1158100714	SEAL            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					TORQUE SHAFT	CUT             	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											RUBBER SEAL DETERIORATED ALLOWING METAL SPRING TO CUT A LARGE GROOVE IN THE TORQUE SHAFT.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006060800283	20060608	00283	EU  	2006	6	8	CA060220001      	1	20060214	G	3897	E0266QF20EO261	WIRE HARNESS    			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2*    	 	GL  					TOILET	BURNED          	W				K				NONE                    				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			CA											AIRCRAFT ARRIVED AT STATION WITH A DEFECT LOG REPORT OF THE FORWARD LAVATORY NOT FLUSHING.  TROUBLESHOOTING FOUND THAT 4	 WIRES BETWEEN THE FLUSH MOTOR AND THE TIMER UNIT WERE BROKEN.  IT WAS NOTED THAT MINOR ARCH/BURNING OF THE WIRES HAD OC	CURRED.  ALL 4 WIRES AND PINS WERE REPLACED AND SYSTEM WAS TESTED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006061200354	20060612	00354	NM  	2006	6	12	CA060220002      	1	20060216	G	5330	737200C	SKIN            			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			71011								DURING THE PREFLIGHT INSPECTION 2 CRACKS WERE OBSERVED IN THE FUSELAGE SKIN.  BOTH DEFECTS WERE APPROXIMATELY 2 INCHES I	N LENGTH.  THE LOCATION IS ESTIMATED TO BE BS 750 STR 19/20.  THE AIRCRAFT IS CURRENTLY OUT OF SERVICE FOR REPAIR.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006061300004	20060613	00004		2006	6	13	CA060220003      	1	20060216	G	4900	MDL15R2001	SCREEN          	BOMBDR      																APU INLET	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			CA											A COMPRESSOR INLET SCREEN MODIFICATION, AWI RECEIVED INFORMATION FROM STANDARD AERO LATE ON FEB 16,2006 THAT THREE OR FO	UR OF THE SCREENS HAD RUPTURED IN SERVICE AND THERE WAS A POSSIBILITY THAT FOD TO THE ENGINE HAD OCCURRED.  THE PARTS WE	RE SHIPPED TO AWI AND RECEIVED FEB. 17, 2006, THERE ARE SOME SCREENS THAT HAVE BEEN PERFORATED.  BUT, THE INLET SCREENS 	DO NOT APPEAR TO HAVE BEEN IN SERVICE.  THE RUBBER AROUND THE INLET SCREENS IS NOT BURNED FROM ENGINE HEAT AND THE SCREE	NS ARE NOT BLACKENED.  AEROSPACE WELDING TAKES THIS MATTER VERY SERIOUSLY AND A MATERIAL REVIEW BOARD MEETING HAS BEEN C	ALLED FOR MONDAY AFTERNOON FEB 20,2006 TO REVIEW AND RESOLVE THIS MATTER AS SOON AS POSSIBLE.														 
2006061300005	20060613	00005	GL  	2006	6	13	CA060220004      	1	20060208	G	2730	C2TP199	HINGE PIN       			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					STABILIZER	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19966								DURING A ROUTINE 100 HOUR INSPECTION, ALL FOUR ELEVATOR HINGE PINS WERE FOUND TO BE HOMEMADE.  AIRCRAFT WAS RECENTLY IMP	ORTED FROM VENEZULA.					1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006061900191	20060619	00191	WP  	2006	6	19	CA060220005      	1	20060215	G	6220	369H120351G	LINK            		369D21200503	HUGHES	369   	369D        	4470706	WP  										M/R HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2156 			022222520					(CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTICED A CRACK ON ONE OF THE EARS OF THE LEAD LAG LINK OF THE MAIN ROTO	R HUB ASSEMBLY.  CRACK PROPAGATED FROM THE BUSHING OUTWARD. (TC NR 20060220005)					1	G	7	1 	3U				H3WE    					 
2006061300006	20060613	00006	GL  	2006	6	13	CA060221001      	1	20060208	G	5711	C2W927A	SPAR            	DHAV        	DHC2L20     	DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21602			579					DURING MAINTENANCE (WING REMOVAL) FRONT SPAR WEB FOUND CRACKED AT ROOT FITTING.  ONCE DOUBLER WAS REMOVED, THE CRACK WAS	 FOUND TO HAVE BEEN STOP DRILLED.					1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006061300008	20060613	00008	GL  	2006	6	13	CA060221002      	1	20060208	G	5720	C2FS537A	CHANNEL         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  						WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			19966								FOUND CHANNEL ASSEMBLY WAS MADE FROM APPROXIMATELY .125 STEEL.  CHECKED WITH VIKING AND WAS INFORMED THAT CHANNEL IS .08	0 ALUMINUM.  AIRCRAFT WAS RECENTLY IMPORTED FROM VENEZULA.					1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006061300010	20060613	00010	NE  	2006	6	13	CA060221003      	2	20060220	G	7320	8061532	HMU             			AIRBUS	A321  	A321211     	3930370	EU  	GE    	CFM56 	CFM56*      	13802	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											AFTER T/O YOW EN ROUTE YVR ENG 2 COMPRESSOR VANE MSG SEVERAL TIMES DURING FLIGHT.  CREW ELECTED TO DIVERT TO YUL.  ACFT 	ROUTED TO BASE FOR INVEST.  HMU REPLACED AS PER T/S.					2	L	7	2 	4F	4	F	RT	A28NM   	E2GL				 
2006061300011	20060613	00011	GL  	2006	6	13	CA060221004      	1	20060208	G	2730	C2CF619A	ROD             			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19966								FOUND ELEVATOR ROD ASSEMBLY RUSTY AD HOLES RUSTED THROUGH TUBE AND WHEN ROD END WAS REMOVED SEVERAL TEASPOONS OF RUSTED 	METAL FLAKES CAME OUT OF THE TUBE, FOUND DURING AN EXTENSIVE 100 HOUR INSPECTION.					1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006061300012	20060613	00012	SW  	2006	6	13	CA060221006      	1	20060211	G	5410	2762019111	PANEL           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24794								WHILE UN-COWLING, RT ENGINE MAINTEANCE FOUND A PIECE OF STAINLESS STEEL IN THE LOWER SECTION OF COWL.  INVESTIGATION REV	EALED A HOLE IN THE LT SIDE OF ASPIRATOR ASSEMBLY ABOVE THE OIL COOLER.  THE ASPIRATOR WAS REPLACED AND AIRCRAFT SINCE R	ETURNED TO SERVICE.  THE MOST PROBABLE CAUSE WOULD BE FATIGUE CRACKING LEADING TO THE PIECE FALLING INTO THE LOWER COWLI	NG.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2006061900207	20060619	00207	EU  	2006	6	19	CA060221007      	1	20060204	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FLT CONTROLS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5759 	1753 							(CAN) ON GROUND RUN: WHEN HYDRAULIC TEST PUSH BUTTON DEPRESSED AND ACCUMULATORS EMPTY, THE CYCLIC WOULD MOVE HARD TO THE	 LEFT.  SWITCHED LT SERVO AND RT SERVO.  THIS PROBLEM MOVED WITH SERVO TO THE RT SIDE.  INSTALLED A NEW OVERHAUL SERVO O	N THE RT SIDE WHICH CLEARED UP OUR PROBLEM.  AC HYDRAULIC SYSTEM NOW OPERATES IAW TYPE.  (TC NR 20060221007)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006061300040	20060613	00040		2006	6	13	CA060221008      	3	20060209	G	6111	W69EK763	BLADE           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					PROPELLER	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1851 			AE7827					DURING PRE-FLIGHT INSPECTION, THE PILOT INSTRUCTOR DISCOVERED A POSSIBLE CRACK ON THE PROPELLER.  CLOSER INSPECTION REVE	ALED AN APPROXIMATELY 4" CRACK ON NR 2 BLADE OF PROPELLER.  THE CRACK IS DEVELOPED LONGITUDINAL ON BLADE FROM TIP TO HUB	.  NO IMPACT MARK OR OTHER DAMAGE TO PROPELLER OBSERVED.  PROPELLER REMOVED FROM SERVICE.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006061300162	20060613	00162	SW  	2006	6	13	CA060221009      	1	20060213	G	7603	C8102419	CONTROL CABLE   			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	POWER LEVER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CREW ATTEMPTED TO START THE ENGINE ON 4TH LEG OF THE DAY.  ENGINE ACCELERATED TO 30 PERCENT AND TEMPERATURE INCREASED.  	ENGINE WAS SHUT DOWN.  MAINTENANCE DISCOVERED THE POWER LEVER CABLE HAD SEVERED IN THE PEDASTAL AND THE ENGINE WAS STUCK	 IN FULL REVERSE.  (REVERSE IS SELECTED ON SHUTDOWN TO PUT THE PROPS ON THE START LOCKS).  THE CABLE WAS REPLACED WITH A	 SERVICEABLE PART AND THE ENGINE PERFORMED NORMALLY.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2006061300164	20060613	00164	GL  	2006	6	13	CA060221010      	1	20060216	G	2410	2224121400	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ALTERNATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			550  					806495			DURING ROUTINE INSPECTION, A SMALL CRACK WAS DISCOVERED ON THE ALTERNATOR BRACKET.  FURTHER INSPECTION REVEALED THAT THE	 TOP NUT TCM P/N 2443 WHICH IS USED TO MOUNT THE BRACKET TO THE ENGINE WAS STRIPPED.  THE NUT ATTACHES TO ONE OF THE ENG	INE THRU STUDS AT THE FORWARD MAIN BEARING.  LUCKILY THE STUD WAS NOT DAMAGED AND A NEW BRACKET AND NUT WERE INSTALLED A	ND TQ`D.  IT WAS ALSO NOTED THAT ALT BRACKET MOUNTING HOLES ARE LARGER THAN THE STUDS AND BOLT USED TO SECURE THE BRACKE	T TO ENG.  THESE WERE TAUGHT AT FIRST TO BE ELONGATED BUT THE NEW BRACKET SUPPLIED BY THE MANUFACTURE REVEALED THEY WERE	 MANUFACTURED THIS WAY.  A REQUEST WAS SENT TO THE MANUFACTURE FOR EXPLANATION.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006061300166	20060613	00166	NM  	2006	6	13	CA060221011      	1	20060220	G	2710	85711570102	BRACKET         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AILERON	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			35314	35314							DURING CRUISE FLIGHT, CREW REPORTED AILERON CONTROL SEEMED STIFF.  AFTER NORMAL LANDING MAINTENANCE INSPECTION FOUND RT 	AILERON SUPPORT BRACKET FOR AILERON INPUT QUADRANT CRACKED.  CAUSING OUTBOARD AILERON QUADRANT TO RUB ON BRACKET.  THIS 	AIRCRAFT IS PRE MOD 8/2160.  DEHAVILLAND SB 8-57-27 REFERS TO THIS BRACKET CRACKING.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300167	20060613	00167	EA  	2006	6	13	CA060221012      	2	20060220	G	8520	18810	CAMSHAFT        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2396 							SPALLING ON CAM AND LIFTERS.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006061300168	20060613	00168	SW  	2006	6	13	CA060222001      	1	20060217	G	2820	206061677001	LINE            			BELL  	206   	206B        	1181511	SW  										FUEL SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ON REINSTALLATION OF FUEL LINES IN FUEL VALVE COMPARTMENT TUBE ASSY WAS TORQUED AND FERRULE WAS FOUND TO BE CRACKED.  TU	BE ASSY WAS SUSPECTED TO BE CRACKED ON REMOVAL BUT NO LEAKS DETECTED.  LINE REMOVED FROM SERVICE.  RECOMMEND BETTER VISU	AL INSPECTION OF ALUMINUM LINES AND PROPER TORQUE PROCEDURES.				1	G	7	1 	3U				H2SW    					 
2006061400039	20060614	00039	NE  	2006	6	14	CA060222002      	3	20060222	G	6114	72429	BOLT            	HAMSTD      		CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	PROP BARREL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				656  							ON RE-ASSEMBLY OF A 43E60-583 PROPELLER, THE TORQUE SEQUENCE OF THE BARREL BOLTS WAS BEING ACCOMPLISHED AS PER CANADAIR 	MAINTENANCE MANUAL SUPPLEMENT 61-10-51. WHEN TORQING ONE OF THE BARREL BOLTS P/N 72429, THE HEAD SHEARED OFF OF THE BOLT	 SHANK JUST AS MAXIMUM TORQUE WAS BEING REACHED.  IT WAS OBSERVED THAT THE WEIGHT INSERT IN THE MIDDLE OF THE BOLT WAS C	ORRODED AND COULD BE THE CAUSE OF THE HEAD SHEARING.			2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2006061300190	20060613	00190	CE  	2006	6	13	CA060223001      	1	20060223	G	2510	051421518	SEAT BACK       			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	COCKPIT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3880 								WHILE PERFORMING NORMAL MAINTENANCE IT WAS NOTED THAT THE PILOTS SEAT BACK WAS TILTED MORE ON THE LEFT THAN THE RIGHT.  	THE SEAT WAS REMOVED AND THE MATERIAL WAS REMOVED FROM THE SEAT BACK WHICH REVEALED A CRACKED SEAT BACK FRAME AT THE PIO	NT WERE THE ALUMINUM SEAT MOUNT CASTING ENDS IN THE SQUARE ALUMINUM TUBING WHICH FORMS THE SEAT BACK.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2006061300294	20060613	00294	CE  	2006	6	13	CA060223002      	1	20060222	G	3245	302039402	TUBE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TIRE	SPLIT           	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											A NORMAL LAND UP UNTIL, SENSED WHAT FELT LIKE DRAGGING BRAKE ON RT M/G.  ONCE SAFELY STOPPED, AND ENG`S SHUT DOWN, CREW 	EXITED A/C, DISCOVERED RT O/B WHEEL ASSY FLAT TIRE.  RETURNED TO A/C TO FIND TWO OTHER TIRES FLATTENED.  THESE WERE BOTH	 RT AND LT INBDS TIRES. PLANE RETURNED TO BASE.  ONCE THE WHEEL ASSEMBLIES WERE TAKEN APART FOR TIRE/TUBE REPLACEMENT, D	ISCOVERED INNER TUBES HAD SPLIT IN A RADIAL DIRECTION ACROSS TUBE.  THE FOLLOWING MORNING, MX FOUND 4TH MAIN WHEEL, THE 	ONE NOT PREVIOUSLY REPLACED,  ALSO LOST IT'S AIR OVERNIGHT.  A SIMILAR SPLIT WAS FOUND IN INNER TUBE.  ALL 4 WHEELS WERE	 NEW JUDGING FROM CONDITION.  A/C FLEW DURATION OF FLT IN EXTREME COLD CONDITIONS (-40'C) AT FL 230.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061300295	20060613	00295	CE  	2006	6	13	CA060223003      	1	20060220	G	2731	26612159	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TRIM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ELEVATOR TRIM SCREW JACK FAILED ON INSTALLATION.						1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2006061400002	20060614	00002	CE  	2006	6	14	CA060223004      	1	20060220	G	2730	26612159	JACKSCREW       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TRIM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ELEVATOR TRIM SCREW JACK (RT) FAILED ON INSTALLATION.						1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2006061400004	20060614	00004	CE  	2006	6	14	CA060223005      	1	20060223	G	5230	26012031	SPRING          			CESSNA	208   	208B        	2073701	CE  										DOOR LATCH	WEAK            	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			5337 								AIRCRAFT DEPARTED AND AFTER TAKEOFF, ATC INFORMED THE PILOT THAT THE AFT POD CARGO DOOR WAS OPEN.  THE AIRCRAFT RETURNED	 AND THE PILOT IN COMMAND INSPECTED THE DOOR, HINGES AND AND THE POD AND FOUND NO DAMAGE.  THE AIRCRAFT DEPARTED AND MAI	NTENANCE INSPECTED THE DOOR AND FOUND THE DOOR SERVICEABLE.  FOUND THE AFT LATCH SPRING WEAK AND REPLACED SPRING AS A PR	ECAUTION.			1	H	7	1 	3T				A37CE   					 
2006061400006	20060614	00006	NM  	2006	6	14	CA060224001      	1	20060216	G	5730	85720062010	SKIN            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT WING LE	DEPARTED        	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			28716								DURING TAKEOFF THE AIRCRAFT LOST THE RT INBOARD LEADING ASSY 611AR UPON ROTATION.  THE LEADING EDGE SECTION REPORTEDLY B	LEW OFF, AND OVER THE TOP OF THE WING AND CAME DOWN WITHIN THE AIRPORT BOUNDARY AREA TOWARDS THE END OF THE RUNWAY.  THE	 AIRCRAFT WAS ABLE TO PERFORM A CIRCUIT AND LANDED SAFELY.  ENGINEERING INSPECTED THE AIRCRAFT AND REPORTED THAT THE UPP	ER LEADING EDGE ATTACHMENT SCREWS WERE STILL IN PLACE AFTER LANDING, BUT ONLY TWO OF THE 26 LOWER ATTACHMENT SCREWS WERE	 IN PLACE.  ONE SCREW WAS LOCATED TOWARDS THE INBOARD SIDE AND ONE AT THE OUTBOARD SIDE.  THE OTHER 24 ATTACHMENT SCREWS	 WERE MISSING.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400010	20060614	00010	SW  	2006	6	14	CA060224002      	1	20060217	G	6700		CYCLIC CONTROL  			BELL  	427   	427         	1182207	SW  										COCKPIT	OBSTRUCTED      	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											CYCLIC STICK FWD MOVEMENT RESTRICTED BY T/R PEDAL STOP MECHANISM CABLE.  T/R PEDAL STOP MECHANISM CABLE BRACKET 427-001-	296-103 FOUND MISLOCATED.					1	G	7	1 	3U				R00001RC					 
2006061400012	20060614	00012	GL  	2006	6	14	CA060224003      	2	20060222	G	7321	84250077	FUEL CONTROL    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			CA				597  				CAE895012			ON A TWO MINUTE COOL DOWN AFTER ONE HOUR FLIGHT, THE ENGINE STARTED TO SURGE, THE PILOT SHUTDOWN THE ENGINE AND AFTER A 	MOMENT TRIED A RESTART BUT IT WOULD NOT LIGHT-OFF.  THE ENGINEER FOUND NO FUEL WOULD COME OUT OF FCU.  FCU WAS REPLACED.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006061400014	20060614	00014	CE  	2006	6	14	CA060224004      	1	20060222	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											WHILE IN CRUISE FLT AT FL 270, APPROXIMATELY 250 MILES INTO THE MIDDAY FLT, FLIGHT CREW REPORTED HEARING A MILDLY LOUD B	ANG WITHIN THE CABIN.  THEY THEN NOTICE SMALL SHARDS OF GLASS FALLING ONTO THE LAP OF THE FIRST OFFICER.  THE INNER PANE	 OF THE RIGHT WINDSHIELD HAD SHATTERED.  THE CREW INITIATED THE STANDARD PROCEDURE FOR A CRACKED WINDSHIELD IAW THE POH 	BY REDUCING THEIR CRUISE SPEED, DESCENDED TO 14000 FEET AND REDUCE CABIN DIFFERENTIAL TO 4.0 PSI.  THE FIRST OFFICER DON	ED HIS GOGGLES AND THEY RETURNED  SAFELY.  THE WINDSHIELD WAS REPLACED AND THE AIRCRAFT WILL BE RETURNED TO SERVICE UPON	 COMPLETING THE CURE TIME FOR THE SEALANT.  NOTE THAT THE OAT AT THE TIME OF THE FLIGHT AT 270 WAS -47'C.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061900232	20060619	00232	NE  	2006	6	19	CA060224005      	2	20060207	G	7200		ENGINE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4272			IN(CAN) AIR OPERATOR:   MODULE 3: CENTRIFUGAL COMP. INDUCER PN 0292251370 S/N 1260FT LIFE LIMIT 14000CYC ACTUAL 14711CYC	. CENTRIFUGAL COMP. IMPELLER PN 2292252980 S/N 1019FB LIFE LIMIT 14000CYC ACTUAL 14711CYC. REF: MM NR 29201931, CHAP 05-	10-03 PAGE 9 (OCT 2003).  MODULE 4: FREE TURBINE DISK PN 2292802500 S/N ADB4234YC LIFE LIMIT 10000CYC ACTUAL 10727CYC. R	EF: MM NR 29201931, CHAP 05-10-03 PAGE 10 (DEC 1996).  (TC NR 20060224005).			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006061400019	20060614	00019	EA  	2006	6	14	CA060224006      	2	20060215	G	7414	LW15416	ADAPTER         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					RT MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING 25 HOUR INSPECTION, OIL WAS DRAINED FROM ENGINE AND FOUND BEARING CAGE BALL RETAINER MADE OF PLASTIC (KIND OF) ON	 ENGINE OIL SCREEN.  REMOVED BOTH MAGNETO DRIVE ADAPTER ASSEMBLY AND FOUND THE PROBLEM ON THE RT ADAPTER (BALL RETAINERS	 MISSING).  REPLACED THE PART P/N LW15416.				1	G	7	1 	3O	3	O	O	4H12    	E286				 
2006061400073	20060614	00073		2006	6	14	CA060224007      	4	20060216	G	2562		SWITCH          	POINTER     		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ELT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						408804					WHEN THE PILOT ACTIVATE THE ELT REMOTE SWITCH IN THE CABIN, THE ELT FAIL TO ACTIVATE.  REPLACED ELT.						1	G	7	1 	3O	3	O		H10WE   	E274				 
2006061400075	20060614	00075	CE  	2006	6	14	CA060224008      	1	20060224	G	2710	MS21251B5S	TURNBUCKLE      	CESSNA      		CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					CONTROL CABLES	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5899 								DURING A SCHEDULED PHASE 5 INSPECTION ON CESSNA 650 C-FIMO, THE TECHNICIAN DISCOVERED THAT THE LT AND RT AILERON OUTBOAR	D AFT CABLE CHAFED THROUGH THE LOKCLAD AND THE TURNBUCKLE WAS DAMAGED.					2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2006061400076	20060614	00076	CE  	2006	6	14	CA060224009      	1	20060224	G	2510	051402133	SEAT            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11104								WHILE DOING 100HR INSPECTION ON AIRCRAFT AME WAS DOING THE SEAT RAIL INSPECTION NOTICED PILOTS SEAT WAS LOOSE WHEN HE MO	VED IT BACK. ON FURTHER INSPECTION OF THE SEAT IT WAS DISCOVERED THAT ONE OF THE ATTACHMENT LEGS USED TO ATTACH THE SEAT	 TO THE PEDESTAL WAS CRACKED AND ONE OF THE LEGS WAS BROKEN.  SEAT WAS REMOVED AND NEW PARTS ORDERED.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061400077	20060614	00077	CE  	2006	6	14	CA060224010      	1	20060222	G	7540	42302200	SWIVEL          	LEAR        		LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					PYLON DUCT	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1467 								ENGINE PYLON DUCT OVERHEAT CAS MESSAGE LIGHT ILLUMINATED 25 MINUTES INTO FLIGHT.  AIRCRAFT RETURNED TO BASE.  ENGINE GRO	UND RAN AND FOUND THAT LIGHT EXTINGUISHES WITH POWER BELOW 50%.  PYLON DUCT REPLACED.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006061400079	20060614	00079	CE  	2006	6	14	CA060224011      	1	20060223	G	3350	65181097	BATTERY PACK    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					EMERGENCY LIGHT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A PHASE INSPECTION, EMERGENCY LIGHT OPERATIONAL CHECK, THE LIGHTS FAILED TO TURN ON.  FURTHER INVESTIGATION REVEA	LED THAT THE EMERGENCY LIGHT POWER SUPPLY WAS DAMAGED.  ALL BATTERIES CELLS WERE CORRODED AND THE BATTERY BOX MELTED.  T	HE BATTERY PACK 2 AMP FUSE CHECKED SERVICEABLE.  BATTERY PACK WAS REPLACED.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006061400094	20060614	00094	NM  	2006	6	14	CA060227001      	1	20060226	G	3240	21599	BRAKE ASSY      			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT MLG	LEAKING         	W				O				OTHER                   				K	A		FLUID LOSS                	FLAME/FIRE                		LD	LANDING        	1			CA											BRAKES ON RT MLG CAUGHT FIRE DURING LANDING AND CAUSED A 'FLASH FIRE'.  FIRE WAS CAUSED BY FLUID LEAKING FROM BRAKE UNIT	 AND COMING INTO CONTACT WITH HOT BRAKING SURFACE.  AN OFF-DUTY PILOT WITNESSED INCIDENT FROM PAX CABIN AND REPORTED FIR	E WAS A 'FLASH BALL' THAT EXTINGUISHED ALMOST IMMEDIATELY.  A/CS FWD MOTION AND PROP WASH BLEW SMOKE AND FLAMES AFT. BO	TH TIRES BLEW, FIRE DEPART WERE ON SCENE APPROX 3 MINS AFTER INCIDENT AND COOLED GEAR DOWN, INITIALLY WITH A MIST AND TH	EN WITH A SPRAY AND THEN A FAN WAS USED TO FURTHER REDUCE TEMP. TEMP READING TAKEN APPROX 23 MINS AFTER INCIDENT SHOWED 	350 DEGREES F.  A TEMP READING TAKEN A FURTHER 10 MINS LATER SHOWED 240 DEGREES F.  A VISUAL INSPECTION OF LWR END OF DR	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400095	20060614	00095	SW  	2006	6	14	CA060227002      	1	20060223	G	5320	206032319023	STIFFENER       			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FUSELAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											AFTER REMOVAL OF AFT FUSELAGE FAIRING FOR REPAIR.  VISUAL INSPECTION AND CLEANING OF AFT FUSELAGE A STIFFENER FOUND CRAC	KED.  STIFFENER REPLACED NEW.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006061400096	20060614	00096	NE  	2006	6	14	CA060227003      	2	20060221	G	7200	PW121	ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA								PCE121280			DURING DESCENT AN OPERATOR EXPERIENCED AN INCIDENT IN SEVERE TURBULENCE WHERE BOTH PROPELLERS/ENGINES WERE OVERSPEED.  T	HE NR 1 ENGINE HAD THE TORQUE SHAFT BREAK AND THE POWER TURBINE BLADES SEPARATE.  BOTH PROPELLERS/ENGINES TO BE REPLACED	.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400097	20060614	00097	NE  	2006	6	14	CA060227004      	2	20060122	G	7200		TURBINE BLADES  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								19352			THE PILOT REPORTED A LOSS OF ENGINE POWER AND ATTEMPTED A FORCED LANDING.  THE AIRCRAFT CRASHED DURING THE ATTEMPT.  PRE	LIMINARY INVESTIGATION HAS REVEALED TURBINE BLADE DISTRESS.  P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT 	CAUSE ONCE ESTABLISHED.				1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2006061400098	20060614	00098		2006	6	14	CA060227005      	1	20060224	G	7120	6898806	SUPPORT         								ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			8132 	1314 							ON REMOVAL OF TURBINE SECTION FROM ENGINE ASSY ONE OF THE FWD SUPPORT STUTS WAS FOUND TO BE CRACKED.  TURBINE ASSY SENT 	FOR REPAIR.  RECOMMEND BETTER VISUAL INSPECTIONS ON SCHEDUELED INSPECTIONS AND POSSIBLY VIBRATION CHECKS.										3	U			E1GL				 
2006061400173	20060614	00173	NE  	2006	6	14	CA060227006      	2	20060130	G	7321	41380102	FUEL CONTROL    			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WOULD NOT RESPOND TO THROTTLE LEVER INPUT.  THE PILO	T ACTIVATED THE FUEL CONTROL MANUAL OVER-RIDE AND ACCOMPLISHED AN UNSCHEDULED LANDING.  GROUND INSPECTION COULD NOT DUPL	ICATE THE INCIDENT.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.				1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2006061400207	20060614	00207	NE  	2006	6	14	CA060227007      	2	20060111	G	7321		FUEL CONTROL    			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								PR0565			DURING AIRCRAFT FLIGHT TESTING, THE ENGINE DID NOT RE-LIGHT FOLLOWING A COMMANDED INFLIGHT SHUT DOWN FOR RE-LIGHT TEST P	URPOSES.  A DEAD STICK LANDING WAS ACCOMPLISHED.  THE FUEL CONTROL UNIT AND FLOW DIVIDER VALVE WERE SUBSEQUENTLY REPLACE	D.  P&WC WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006061400209	20060614	00209	NE  	2006	6	14	CA060227008      	2	20060129	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								EB0011			IN CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY AN UNCOMMANDED INCREASE IN PROP SPEED.  	THE ENGINE WAS SHUT DOWN IN FLIGHT.  GROUND INSPECTION WAS UNABLE TO DUPLICATE THE PROBLEM.  THE ENGINE FUEL CONTROL UNI	T, FUEL PUMP, FADEC, ELECTRICAL HARNESS AND TORQUE SENSOR WERE SUBSEQUENTLY REPLACED.  P&WC WILL MONITOR INVESTIGATION O	F THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006061400211	20060614	00211	EU  	2006	6	14	CA060227009      	1	20060203	G	7930		WARNING LIGHT   			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE OIL SYS	ILLUMINATED     	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA								EB0078			DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT GROUND 	TESTING WAS UNABLE TO DUPLICATE THE EVENT.  THE OIL PRESSURE TRANSMITTER AND LOW OIL PRESSURE SWITCH WERE REPLACED AND T	HE AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006061400212	20060614	00212	NE  	2006	6	14	CA060227010      	2	20060204	G	7230		COMPRESSOR      			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					ENGINE	SEIZED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PR0508			THE ENGINE ACCESSORY GEARBOX CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT AND AN UNSCHEDULED LANDING WAS CARRIED OUT.  SU	BSEQUENT INSPECTION REVEALED SEIZURE OF THE COMPRESSOR SECTION.  P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF R	OOT CAUSE ONCE ESTABLISHED.				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2006061400214	20060614	00214	EU  	2006	6	14	CA060227011      	1	20060225	G	3230	19071100403	RELEASE ACTUATOR			EMB   	ERJ170	ERJ170100LR 	       	EU  	GE    	CF34  	CF348E5A1   	30015	NE  					MLG DOWNLOCK	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											LEFT MAIN GEAR DID NOT RETRACT AFTER TAKEOFF.  NO GEAR PIN ON MAIN WERE FOUND ON ARRIVAL, PARK BRAKE REMAINED ON AFTER B	RAKE HANDLE RELEASED.  LT MLG DOWNLOCK RELEASE ACTUATOR REPLACED IAW AMM 32-31-05-000-801-A AND 32-31-05-400-801-A.  GEA	R SWING CARRIED OUT AS PER AMM 32-33-00-710-801-A.  ALL FUNCTIONS NORMAL.				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2006061400215	20060614	00215	NE  	2006	6	14	CA060227012      	2	20060201	G	7210		PACKING         			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  					RGB OIL SYS	CUT             	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED 	A CUT O-RING PACKING AT THE PROPELLER CONTROL UNIT ADAPTER INTERFACE TRANSFER TUBE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006061400217	20060614	00217	EU  	2006	6	14	CA060227013      	1	20060210	G	7810		EXHAUST DUCT    			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											DURING FLIGHT, A LOUD WHISTLING NOISE WAS REPORTED BY THE CREW.  SUBSEQUENT INSPECTION REVEALED THE ENGINE-MOUNTED AIRFR	AME EXHAUST DUCT HAD FRACTURED AND LIBERATED WITH RESULTANT DAMAGE TO THE MAIN ROTOR AND VERTICAL FIN.  P&WC WILL MONITO	R THE INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2006061400218	20060614	00218	NE  	2006	6	14	CA060227014      	2	20060210	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								71397			THE ENGINE FLAMED OUT DURING TAXI.  SUBSEQUENT INVESTIGATION COULD NOT DUPLICATE THE PROBLEM.  THE ENGINE FUEL FILTER WA	S REPLACED, THE AIRFRAME RIGGING CHECKED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006061400220	20060614	00220	SO  	2006	6	14	CA060227015      	1	20060223	G	5740		MOUNT           			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O320  	O320A2B     	41508	EA  	MCAULY	1A175	1A175GM     	GL  	AFT FLAP PULLEY	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											FLAP PULLEY MOUNT INSTALLED IN AFT FUSELAGE CABIN AS PER STC SA578AL AT UNKNOWN TIME, FAILED IN FLIGHT.  MOUNT WAS WELDE	D TO FUSELAGE BRACE TUBE 5/8".035 WALL.  TUBING FATIGUED AROUND WELD AND PULLEY MOUNT SHIFTED CAUSING MISALIGNMENT OF PU	LLEY TO CABLE.  THIS CAUSED THE PULLEY TO SUBSEQUENTLY FAIL ON CLIMB AND A LOSS OF "DOWN" FLAP CONTROL.  THE TUBING AROU	ND THE WELD APPEARED WORKED DOWN TO .025" BY UNKNOWN PERSON WHO INSTALLED IT.  AIRCRAFT LANDED WITHOUT INCIDENT.			1	H	7	1 	3O	3	O		A780    	E274	5	N	P857	 
2006061400221	20060614	00221	EA  	2006	6	14	CA060227016      	2	20060206	G	7200		ENGINE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  						POWER LOSS      	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA								50413			DURING DESCENT, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER.  A SINGLE-ENGINE LANDING WAS ACCOMPLISHE	D.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006061400222	20060614	00222	NE  	2006	6	14	CA060227017      	2	20060215	G	7321	81850011	FUEL CONTROL    			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											DURING DESCENT, THE ENGINE WAS FOUND TO NOT RESPOND TO THROTTLE LEVER INPUT AND WAS SHUT DOWN IN FLIGHT.  THE ENGINE FUE	L CONTROL UNIT AND FLOW DIVIDER VALVE WERE SUBSEQUENTLY REPLACED.					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2006061400224	20060614	00224	EA  	2006	6	14	CA060227018      	2	20060213	G	7261		ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A28      	 	EA  					OIL SYS	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								50036			DURING CLIMB, THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER AND INCREASE IN TURBINE TEMPER	ATURE.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  GROUND INSPECTION REVEALED 	AN ENGINE OIL LEAK.  THE ENGINE HAD BEEN OVERHAULED 100 HOURS PRIOR TO THE EVENT, WHERE IT WAS CONVERTED UNDER STC TO A 	PT6A-34 CONFIGURATION.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2006061400225	20060614	00225	NE  	2006	6	14	CA060227019      	2	20060219	G	7200		ENGINE          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  						MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA								PR0117			ON APPROACH, THE ENGINE WAS FOUND NOT TO RESPOND THE THROTTLE LEVER INPUT.  THE PILOT ENGAGED THE FUEL CONTROL MANUAL OV	ER-RIDE AND REGAINED AUTHORITY OVER THE ENGINE.  P&WC WILL MONITOR THE INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF 	ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006061500003	20060615	00003	NE  	2006	6	15	CA060227020      	2	20060213	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15*       	52060	NE  						POWER LOSS      	W				E				ENGINE SHUTDOWN         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	DE	DESCENT        	1			CA											ON DESCENT, THE ENGINE WAS REPORTED TO EMIT A GRINDING NOISE ACCOMPANIED BY AN UNCOMMANDED POWER LOSS.  THE ENGINE WAS S	HUT DOWN IN FLIGHT AND A SINGLE-ENGINE LANDING ACCOMPLISHED AT POINT OF DESTINATION.  GROUND INSPECTION REVEALED INTERNA	L ENGINE DAMAGE.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	L	7	2 	4F	4	T		A22CE   	E1NE				 
2006061500004	20060615	00004	NE  	2006	6	15	CA060227021      	2	20060221	G	7261		LINE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					REDUCTION GBOX	FRACTURED       	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											DURING FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED FOLLOWED BY AN UNCOMMANDED ROLL BACK IN ENGINE POWER.  TH	E ENGINE WAS SECURED IN FLIGHT AND A SUCCESSFUL FORCED LANDING ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED A FRACTURED	 PRESSURE OIL TRANSFER TUBE ELBOW.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETE	RMINED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006061500008	20060615	00008	NE  	2006	6	15	CA060227022      	2	20060220	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											THE ENGINE EXPERIENCED AN UNCOMMANDED IN-FLIGHT SHUT DOWN AFTER TAKEOFF.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE E	NGINE EXHAUST.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006061500010	20060615	00010	CE  	2006	6	15	CA060227023      	1	20060224	G	3230	M710501	MOTOR           			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	NLG	UNSERVICEABLE   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			LD	LANDING        	1			CA			5160 								NOSE GEAR FAILED TO EXTEND CORRECTLY AS INDICATED BY GEAR IN TRANSIT.  GEAR EXTENDED MANUALLY AND LANDED WITHOUT INCIDEN	T.  CAUSE UNDER INVESTIGATION AT THIS TIME.					1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2006061500011	20060615	00011	CE  	2006	6	15	CA060227024      	1	20060116	G	7120	509800891	MOUNT           			BEECH 	100   	A100A       	       	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	DETACHED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPPER INBOARD ENGINE MOUNT FITTING RT NACELLE UNDER SKIN FOUND DETACHED.  SUBSEQUENT INSPECTION OF OTHER FITTINGS ON SAM	E AIRCRAFT (THERE ARE 4) FOUND ALL WITH ATTACHING FASTENER DEFECTS SUCH AS LOOSE OR SHEARED.  AREA IS ALMOST UN-INSPECTA	BLE.  SUGGEST BOROSCOPE INSPECTION OR REMOVING A PORTION OF NACELLE SKIN IF ENGINE MOUNT MOVEMENT IS DETECTED IN FITTING	 AREA.			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006061500012	20060615	00012	EA  	2006	6	15	CA060228001      	1	20060215	G	5610	6003303025	WINDSHIELD      			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  						CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											WHILE CRUISING THE LT WINDSHIELD OUTER PLY CRACKED.  THE AIRCRAFT CONTINUE INTO WHERE A NEW WINDSHIELD WAS INSTALLED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061500014	20060615	00014	CE  	2006	6	15	CA060228002      	1	20060224	G	3000	5918411	DIODE           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ANTI-ICE SYSTEM	FAILED          	W				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA			2577 								DURING PREDEPARTURE CHECK, THE LT ANTI-ICE VALVE FAILED TO OPEN.  DURING TROUBLESHOOTING OF THE SYSTEM FOUND THE DIODE D	25 HAD HIGH RESISTANCE PREVENTING THE ANTI-ICE SHUTOFF VALVE TO GET A GROUND WHEN REQUIRED.  NEW DIODE WAS INSTALLED AND	 SYSTEM FUNCTIONED CHECK NORMAL.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006061500016	20060615	00016	EU  	2006	6	15	CA060228003      	1	20060226	G	2750	9028A000201	PICKUP          			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											AIRCRAFT LANDED WITH FULL SLATS AND NO FLAPS.  UNABLE TO EXTEND FLAPS ON LANDING.  SYSTEM TORQUE LIMITERS AND SCREW JACK	S LIMITER INSPECTED AND NO FAULT FOUND.  DURING TROUBLESHOOTING, THE LT AND RT POWER PICK UP UNITS WERE FOUND CONTAMINAT	ED WITH SKYDROL AND READOUTS NOT MEETING THE MM LIMITS.  BOTH UNITS REPLACED AND SYSTEM TESTED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006061500017	20060615	00017	NM  	2006	6	15	CA060228004      	1	20060226	G	3230	846802	PSEU            			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											SELECTING LANDING GEAR DOWN, STATUS MSG 'LDG GEAR MONITOR' CAME ON AND REMAINED ON, DURING LANDING, TAXI, AND PARKING.  	PSEU CARD FAILED ILLUM.  PSEU REPLACED PER AMM 32-09-04 PB 401.  PSEU BITE TEST OKAY.  MESSAGES CLEARED.  OKAY TO PROCEE	D.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2006061500019	20060615	00019	CE  	2006	6	15	CA060228005      	1	20060220	G	2731	26612159	JACKSCREW       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TRIM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THE LT ELEVATOR TRIM JACK WAS REMOVED AND DISASSEMBLED FOR INSPECTION AFTER THE RT TRIM JACK FAILED ON INSTALLATION.  TH	E LT TRIM JACK WAS FOUND TO CONTAIN NO GREASE.  THE JACK WAS INSPECTED, LUBRICATED IAW AMM 27-30-02, 9A, REASSEMBLED, TE	STED AND RETURNED TO SERVICE.				1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2006061500144	20060615	00144		2006	6	15	CA060228006      	4	20060222	G	3418	9754421421	VANE            	ROSEMOUNT   		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AOA TRANSMITTER	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1573 		0288					DURING A ROUTINE PHASE 5 INSPECTION , THE LT AOA VANE HEATER WAS FOUND TO BE INOPERATIVE.  ASSY REPLACED WITH SERVICEABL	E UNIT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006061500188	20060615	00188	EU  	2006	6	15	CA060228007      	1	20060119	G	2160	9599020135	CONTROL VALVE   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN TEMP	INTERMITTENT    	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				1608 		0048					TEMPERATURE CONTROL VALVE FOUND TO INTERMITTENTLY STICK AT HOT POSITION CAUSING A DUCT TEMPERATURE WARNING.  VALVE REPLA	CED WITH SERVICEABLE ASSY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006061500189	20060615	00189	NM  	2006	6	15	CA060228008      	1	20060227	G	2910	65C265101024	LINE            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											FLUID LEAK ON RT GEAR "UP" HYDRAULIC RETURN LINE NOTICED DURING OVERNIGHT CHECK.  LINE WAS CHAFED THROUGH DUE TO RUBBING	 ON A BRACKET.  LINE REPLACED,GEAR SWING CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE.     TT-37255:17 TC-22887.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061500191	20060615	00191	CE  	2006	6	15	CA060228009      	1	20060222	G	2731	2661259	JACKSCREW       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ELEVATOR TRIM	FAILED          	W				K				NONE                    				W		O	INADEQUATE Q C            		OTHER                     	IN	INSP/MAINT     	1			CA			8    								AS A PRECAUTION FOLLOWING THE FAILURE ON INSTALLATION OF A SIMILAR TRIM JACK ON A DIFFERENT AIRCRAFT, BOTH ELEVATOR TRIM	 JACKS ON FSKS WERE REMOVED AND DISASSEMBLED TO INSPECT FOR CORRECT LUBRICATION.  THE LT TRIM JACK (S/N CA0009) WAS FOUN	D TO BE CORRECTLY LUBRICATED.  THE RT TRIM JACK (S/N CA0008) WAS FOUND TO BE DEVOID OF GREASE.  BOTH JACKS WERE CLEANED,	 INSPECTED, REPACKED WITH GREASE IAW AMM 27-30-02 9A.  REASSEMBLED, FUNCTION TESTED, AND RETURNED TO SERVICE.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006061500195	20060615	00195	CE  	2006	6	15	CA060228013      	1	20060220	G	3340	TTGCTA201TWB	SWITCH          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	EXTERIOR LIGHTS	SEIZED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											UPON APPROACH TO LAND, PILOT TURNED ON LANDING LIGHT AND OBSERVED A SMALL AMOUNT OF SMOKE COMING FROM THE SWITCH AND WAS	 UNABLE TO TURN THE SWITCH OFF DUE TO IT SEIZING IN THE 'ON' POSITION.  TURNED OFF THE AIRCRAFT MASTER SWITCH INSTEAD AN	D LANDED SAFELY.  THE SWITCH WAS REPLACED.  THE REMOVED SWITCH LOOKED NORMAL ON THE OUTSIDE BUT THE WHITE PORTION WAS SL	IGHTLY BLACKENED.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061500197	20060615	00197	CE  	2006	6	15	CA060228014      	1	20060206	G	5700		WING            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	BOTH	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											DURING INSPECTION, FOUND INBD EDGES OF BOTH LT AND RT FLAP ASSEMBLIES WERE TOUCHING FUSELAGE IN FULL UP POSITION.  MX DE	PART COMPLETED INSPECTIONS OF FOLLOWING AREAS FLAP ATTACHMENT, FLAP RIGGING, FLAP STRUCTURE FOR BENDING OR WARPING, STRU	CTURE OF WINGS FOR BENDING OR WARPING.  NOTHING WAS FOUND.  13 MONTHS PREVIOUS, WINGS WERE REMOVED TO FACILITATE INSPECT	IONS FOR CORROSION AND STRUCTURAL DAMAGE.  WHEN WINGS WERE REINSTALLED ATTACHING HARDWARE REPLACED WITH NEW.  REAR ATTAC	H POINTS OF WINGS ARE ADJUSTABLE TO SET WING AT PROPER ANGLE.  WINGS WERE ADJUSTED OUT AND A TEST FLT WAS COMPLETED.  AL	L OTHER CARAVANS IN FLEET WERE INSPECTED, NO FAULTS FOUND.  CESSNA WAS ALSO MADE AWARE OF THE SITUATION.	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006061500198	20060615	00198	CE  	2006	6	15	CA060228015      	1	20060119	G	7120	9998000060463	MOUNT           			BEECH 	99    	99AFACH     	       	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35093								DURING A SCHEDULED DETAILED NR 3 INSPECTION, OBSERVED THE RT ENGINE MOUNT ASSY HAD SEPARATED APPROX 1/4 OF AN INCH FROM 	RT NACELLE.  LIFTING OF ENG WITH CRANE CONFIRMED MOVEMENT.  VISUAL INSPECTION REVEALED 2 OF THE 4 UPPER INBD BOTTOM ENGI	NE MOUNT CASTING RIVITS SHEARED. THIS AREA IS DIFFICULT TO INSPECT.  REMOVAL OF THE INBD AND OUTBD NACELLE SKINS IS THE 	ONLY WAY TO GAIN ACCESS TO THE UPPER CASTINGS FOR INSPECTION WHICH WERE FOUND WITH SIGNS OF RIVET FAILURE.  THE RT ENGIN	E, PROPELLER, COWLINGS, AND FUSELAGE SUFFERED SUDDEN STOPPAGE DAMAGE BY A DEER STRIKE 125 HOURS PRIOR TO THESE OBSERVATI	ONS WHICH MAY HAVE ATTRIBUTED IN THIS FAILURE. REPAIRS C/O BY R.D.C.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006061500200	20060615	00200	NE  	2006	6	15	CA060228016      	2	20060222	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA								127025			ON DESCENT, THE ENGINE FLAMED OUT AND THE PROPELLER FEATHERED.  A RE-LIGHT ATTEMPT WAS UNSUCCESSFUL.  P&WC WILL INVESTIG	ATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006061500201	20060615	00201	CE  	2006	6	15	CA060228017      	1	20060227	G	7931		OIL SYSTEM      		PW306C      	CESSNA	680   	680CE       	2076811	CE  	PWA   	306   	PW306B      	 	NE  					ENGINE	LOW             	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA								CG0023			FOLLOWING TAKEOFF ENGINE OIL PRESSURE DECREASED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  THE AIRCAFT DIVERTED FOR AN UNS	CHEDULED LANDING.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
2006061500204	20060615	00204	NE  	2006	6	15	CA060228018      	2	20060206	G	7314	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			628  								PILOT WAS ATTEMPTING TO START THE AIRCRAFT AND THE AUX PUMP LIGHT ILLUMINATED AND THE CB POPPED.  IT WAS RESET AND AGAIN	 THE CB POPPED.  THE PUMP WAS REPLACED AND NO FURTHER DEFECT WAS NOTED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600038	20060616	00038	NE  	2006	6	16	CA060228019      	2	20060220	G	7314	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			128  								DURING START UP PILOT COULD NOT PRIME THE AIRCRAFT.  FURTHER INVESTIGATION FOUND PUMP FAILED.  PUMP REPLACED AND NO FURT	HER DEFECTS NOTED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600040	20060616	00040		2006	6	16	CA060228021      	4	20060210	G	2562	PS400010	ELT             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CABIN	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				93   							DURING AN ANNUAL ELT RECERTIFICATION A FUNCTION CHECK OF THE G SWITCH WAS CARRIED OUT.  IT WAS NOTED TO SET OFF PRIOR TO	 ITS REQUIRED SETTING (FAULTY G SWITCH).  ELT HAS BEEN SENT BACK TO POINTER FOR REPAIR.					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061600043	20060616	00043	NM  	2006	6	16	CA060301002      	1	20060227	G	3240	26124121A	CARRIER ASSY    			BOEING	767   	7673Y0      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					NR 4 BRAKE	BURNED          	W				O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											GND CREW REPORTED BRAKE FIRE ON RT MAIN GEAR AFTER SHUTDOWN.  FIRE EXTINGUISHED.  FOUND NR 4 BRAKE PISTONS WORN THROUGH 	STATORS AND INTO THE ROTORS.  AXLE INSPECTED AS PER AMM 05-51-15-212-001 AND 05-51-14 PB201.  AXLE OK.  BRAKE REPLACED A	S PER JC 6-232A.  WHEEL ASSY.  REPLACED AS PER JC 6-232B.  FURTHER INFO WILL FOLLOW WITH WHEEL/BRAKE SHOP REPORT.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2006061600044	20060616	00044		2006	6	16	CA060301003      	4	20060301	G	2562	PS400010	ELT             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CABIN	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				657  							DURING ANNUAL RECERTIFICATION, FOUND G SWITCH WEAK.  ELT SENT BACK TO OVERHAUL FACILITY.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061600045	20060616	00045		2006	6	16	CA060301004      	4	20060301	G	2562	PS400010	ELT             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CABIN	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				92   							DURING ANNUAL RECERTIFICATION, FOUND G SWITCH WEAK.  ELT SENT BACK TO OVERHAUL FACILITY.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061600047	20060616	00047	EA  	2006	6	16	CA060301005      	1	20060228	G	5410	60L12AA	COWL LATCH      			DHAV  	DHC2  	DHC2MK3     	2800107	EA  										NACELLE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											INSPECTION PERSONNEL AT VIKING AIR HAVE DISCOVERED A REOCCURENCE OF SUBSTANDARD COWL LATCHES; THIS ISSUE WAS PREVIOUSLY 	RAISED, AND ADDRESSED THROUGH 2 SERVICE BULLETINS, TB/7 (FOR THE TURBO BEAVER) AND 6/34 (FOR THE TWIN OTTER).					1	H	7	1 	3T				A806    					 
2006061600048	20060616	00048	EA  	2006	6	16	CA060301006      	1	20060228	G	5410	60L12AA	COWL LATCH      			DHAV  	DHC6  	DHC6        	2802606	EA  										NACELLE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											INSPECTION PERSONNEL AT VIKING AIR HAVE DISCOVERED A REOCCURRENCE OF SUBSTANDARD COWL LATCHES; THIS ISSUE WAS PREVIOUSLY	 RAISED, AND ADDRESSED THROUGH 2 SERVICE BULLETINS - TB/7 (FOR THE TURBO BEAVER) AND 6/34 (FOR THE TWIN OTTER).					1	H	7	2 	3T			RT	A9EA    					 
2006061600049	20060616	00049	CE  	2006	6	16	CA060301007      	1	20060224	G	3230	K10004	NUT PLATE       	BEECH       	1018200351  	BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4M       	GL  	MLG	DAMAGED         	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA			1700 			PAC16505					AIRCRAFT WAS ON APPROACH.  POSITIVE NOSE GEAR DOWN LOCK WAS NOT INDICATING USING THE NORMAL SYSTEM.  EMERGENCY GEAR DOWN	 WAS REQUIRED TO HAVE POSITIVE DOWN AND LOCK INDICATION.  NOSE LANDING GEAR INSPECTION WAS CARRIED OUT OF THE GREEN LIGH	T INDICATOR SWITCHES ON THE ACTUATOR AND DRAG BRACE.  THE SWITCH STOP WAS BACKED OFF INTO THE ANCHOR NUT.  STOP WAS RERI	GGED AND SECURED.  LANDING GEAR SWING CARRIED OUT AS PER B300 MM AND CHECKED SERVICEABLE.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006061600109	20060616	00109	NM  	2006	6	16	CA060302001      	1	20060227	G	2121		BEARING         	SUNDSTRANDAI		BOEING	767   	767300      	1385204	NM  	GE    	CF6   	CF680C2B7   	 	NE  					COOLING FAN	DAMAGED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				8132 		3490					FORWARD EQUIPMENT COOLING FAN BEARINGS APPEARED TO BE DAMAGED AND THE FAN SHOWS SIGNS OF RUBBING ON THE CASE.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006061900046	20060619	00046	EA  	2006	6	19	CA060302002      	1	20060223	G	2810	215640011	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 1	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1253 								WHILE COMPLETING THE A 500 HR INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS 	DETERMINED THAT THE LEAK WAS IN THE RIGHT FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECK	ED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND R	EPLACED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061900047	20060619	00047	EA  	2006	6	19	CA060302003      	1	20060223	G	2810	21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 2	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1253 								WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERING FUEL IT WAS DE	TERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CH	ECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061900048	20060619	00048	EA  	2006	6	19	CA060302004      	1	20060223	G	2810	215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 3	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1253 								WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERING FUEL IT WAS DE	TERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CH	ECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AN	D REPLACED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061900049	20060619	00049	EA  	2006	6	19	CA060302005      	1	20060223	G	2810	215640026	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 5	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1253 								WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS D	ETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND C	HECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED A	ND REPLACED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061900050	20060619	00050	EA  	2006	6	19	CA060302006      	1	20060223	G	2810	21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 6	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1253 								WHILE COMPLETING THE A 500 HR INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERING FUEL IT WAS D	ETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND C	HECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED A	ND REPLACED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061900051	20060619	00051	EA  	2006	6	19	CA060302007      	1	20060223	G	2810	215640751	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 8	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1253 								WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS D	ETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND C	HECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED A	ND REPLACED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061600146	20060616	00146	EA  	2006	6	16	CA060302008      	1	20060223	G	2810	CL215640751	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  		LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1342 								WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS D	ETERMINED THAT THE LEAK WAS IN THE RIGHT FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKE	D FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND RE	PLACED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061600147	20060616	00147	WP  	2006	6	16	CA060302009      	1	20060220	G	2913		SEAL            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYDRAULIC PUMP	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1664 			0763					INPUT SEALS FOUND TO BE LEAKING DURING INSPECTION.  PUMP WAS REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600148	20060616	00148	WP  	2006	6	16	CA060302010      	1	20060220	G	6730		SEAL            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1664 								LOWER PISTON SEAL WAS FOUND LEAKING.  SERVO WAS REPLACED WITH A SERVICEABLE UNIT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600149	20060616	00149	WP  	2006	6	16	CA060302011      	1	20060220	G	6730	VARIOUS	SEAL            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					SERVO	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1664 			1976					UPPER PISTON SEAL LEAKING.  NEW SEAL AND O-RING INSTALLED.  NO FURTHER DEFECTS FOUND.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061900252	20060619	00252	GL  	2006	6	19	CA060302012      	2	20060118	G	7297		WIRE HARNESS    			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					LT ENGINE	MISINSTALLED    	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											AIRCRAFT ON A TEST FLIGHT AND DURING AN RPM DECAY TEST, THE LT ENGINE POWER LEVER WAS REDUCED BELOW 1400 HP.  THE RPM TH	EN STARTED TO DECAY BELOW PRESCRIBED LIMITS.  DUE TO THIS, THE CREW ELECTED TO SHUT DOWN THE ENGINE.  THE PROBLEM ONLY O	CCURRED BELOW 1400 HP.  THE CREW CARRIED OUT SEVERAL RESTARTS, WHICH DID NOT RESOLVE THE OCCURRENCE AND ELECTED TO LAND 	WITH THE ENGINE SHUT DOWN.  TROUBLE SHOOTING IDENTIFIED AN INCORRECT WIRING CONFIGURATION, WHICH WAS CORRECTED.			2	L	7	2 	4R	4	T		6A6     	E282				 
2006061900081	20060619	00081	EA  	2006	6	19	CA060302013      	1	20060226	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			6762 								COPILOT SIDE WINDOW BROKEN.  SIDE WINDOW CHECKED, FOUND MIDDLE PLY DAMAGED.  RT SIDE WINDOW ACC AMM TASK 56-12-01-000-80	1 CHANGED.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006061900089	20060619	00089	EA  	2006	6	19	CA060302014      	1	20060228	G	2133	GG670980041	OUTFLOW VALVE   			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					CABIN PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											UNABLE TO PRESSURIZE CABIN IN FLIGHT.  AIRCRAFT RETURNEDTO FIELD OF ORIGIN.  GROUND VALVE REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006061900091	20060619	00091	WP  	2006	6	19	CA060303001      	1	20060301	G	2822	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			541  								DURING START UP THE AUX FUEL PUMP C/B POPPED.  FUEL PUMP WAS REPLACED AND NO FURTHER DEFECTS WERE NOTED.  HAVE AUDITED T	HE FUEL PUMP ISSUE.  HAVE HAD SEVERAL PUMPS IN THE LAST YEAR FAIL.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061900093	20060619	00093	CE  	2006	6	19	CA060303002      	1	20060201	G	5711	18144L	SPAR            			BEECH 	18    	3TM         	1151046	CE  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8290 								CENTER SECTION FUSELAGE REAR WING CARRY-THRU SPAR CRACKED 3/4" FROM TOP OF SPAR RUNNING DOWNWARD AT EDGE OF REINFORCEMEN	T INSIDE FUSELAGE AT REAR LT FLOAT FITTING STATION NR 199.5 BULKHEAD NR 8.					1	L	7	2 	3R	3	R		A765    	5E1	5	C	P736	 
2006061900096	20060619	00096		2006	6	19	CA060303003      	4	20060221	G	3497		CONNECTOR       	COLLINS     	6227384001  	CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF34*       	 	NE  					ANTENNA	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1325 	1325 		1WGNF					WHILE TROUBLESHOOTING A DEFERRAL FOR AN ADF SIGNIFICANT CORROSION AND A BROKEN PIN WAS DISCOVERED ON THE BELLY MOUNTED A	DF ANTENNA CONNECTOR.  THE ASSOCIATED CONNECTOR WAS ALSO CORRODED AND CONTAINED THE BROKEN PIN.  IT IS ASSUMED MOISTURE 	FROM THE AIRCRAFT INTERIOR FOUND ITS WAY INTO THE CONNECTOR AND POOLED CAUSING THE CORROSION.  THE ANTENNA SEALS AERODYN	AMIC AND PRESSURE WERE IN A SERVICABLE STATE.  MAINTENANCE REPLACED THE ADF ANTENNNA, CONNNECTOR PLUG AND PINS AND RETUR	NED THE AIRCRAFT TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061900098	20060619	00098	CE  	2006	6	19	CA060303005      	1	20060116	G	2821	305262401	FILTER          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RT FUEL SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1148 								RT ENGINE FUEL FILTER CONTAMINATED WITH LINT FROM LARGE (12" X 30") TOWEL WHICH WAS FOUND IN THE RT INTEGRAL WING TANK. 	 THE TOWEL WAS "INSTALLED" BY CESSNA AIRCRAFT FACTORY WHEN THE AIRCRAFT WAS BUILT.  THE TOWEL WAS OUTBOARD OF THE BOOST 	AND EJECTOR PUMPS AND DID NOT AFFECT THE OPERATION OF ENGINE OR PUMPS.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006061900099	20060619	00099	CE  	2006	6	19	CA060303006      	1	20060116	G	2710	556555038CR	CONTROL CABLE   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					AILERON	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1148 								RT AILERON CONTROL YOKE CROSSOVER CABLE BROKEN STRANDS.  THIS WAS FOUND ON PHASE 5 INSPECTION AND IS A COMMON FINDING AT	 1200 HOURS OF USE.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006061900100	20060619	00100	CE  	2006	6	19	CA060303007      	1	20060116	G	2710	656512037CR	CONTROL CABLE   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1148 								LT AILERON CONTROL YOKE CROSSOVER CABLE BROKEN STRANDS.  THIS WAS FOUND AT PHASE 5 INSPECTION AND IS A COMMON FINDING AT	 1200 HOURS.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006061900101	20060619	00101	CE  	2006	6	19	CA060303008      	1	20060116	G	5220	651126619	SEAL            	CESSNA      		CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ESCAPE HATCH	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1148 								ESCAPE HATCH SEAL MIGRATING UNDER CABIN PRESSURE TO THE EXTERIOR OF THE AIRCRAFT.  DUE TO POOR BONDING TO THE HATCH STRU	CTURE.  REPLACED SEAL AND PRESSURIZED AIRCRAFT, SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006061900102	20060619	00102	CE  	2006	6	19	CA060303009      	1	20060116	G	3244	0316138	TIRE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					NLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			678  								NOSE WHEEL TIRE, TREAD IS STARTING TO SEPARATE FROM TIRE.						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006061900279	20060619	00279	SW  	2006	6	19	CA060303010      	1	20060303	G	3240		HOSE            			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	BRAKE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			303  								WHILE PERFORMING A GEAR SWING DURING THE ANNUAL INSPECTION, IT WAS DISCOVERED THAT THE MLG BRAKE HOSES WERE ROUTED SO TH	AT THEY WERE RUBBING DIRECTLY ON THE TREAD PORTION OF THE TIRES.  THE STRAIGHT BULKHEAD FITTINGS P/N AN832-4D (4 OF) WER	E REPLACED WITH 45 DEGREE BULKHEAD FITTINGS AND BRAKE HOSES WERE CHECKED FOR CLEARANCE ON A SUBSEQUENT GEAR SWING WITH N	O RUBBING NOTED.  BRAKE SYSTEM WAS BLED.  THE OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED.			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2006062100068	20060621	00068	CE  	2006	6	21	CA060303011      	1	20060204	G	2160	7547512	BYPASS VALVE    	HAMSTD      	73838426    	CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ACM	FAILED          	W				O				OTHER                   				M	P		OVER TEMP                 	NO WARNING INDICATION     		CR	CRUISE         	1			CA			1189 			200303012					BYPASS VALVE INTERMITTENTLY STICKING IN OPEN (HOT) POSITION, UNABLE TO CONTROL CABIN AIR TEMPERATURE IN AUTO OR MANUAL S	ELECTION.  REPLACED VALVE, GROUND CHECK OF VALVE OPERATION SATISFACTORY.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006062100069	20060621	00069	CE  	2006	6	21	CA060303012      	1	20060210	G	2916	S53FC	GAUGE           	CESSNA      	651710021   	CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RESERVOIR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1204 								BRAKE HYDRAULIC RESERVOIR UPPER AND LOWER SIGHT GAGES UNSERVICEABLE, SIGHT GAGE FLOATS ABSORBED SKYDROL BRAKE FLUID AND 	WOULD NOT FLOAT, MAKING IT IMPOSSIBLE FOR THE (PILOT) TO DETERMINE THE BRAKE FLUID LEVEL.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006062100070	20060621	00070	CE  	2006	6	21	CA060303013      	1	20060211	G	2752	0523921	ROLLER          	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	TE FLAP	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											12 HOURS AFTER THE AIRCRAFT CAME BACK FROM A PAINT JOB, A FLIGHT INSTRUCTOR HEARD A BANG AS THEY WERE RETRACTING THE FLA	PS AFTER LANDING.  AFTER TAXIING BACK TO THE HANGAR, AND UPON SUBSEQUENT INSPECTION, OUR FLIGHT INSTRUCTOR REPORTED THE 	LT IB AFT FLAP ROLLER MISSING.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062100071	20060621	00071	CE  	2006	6	21	CA060303014      	1	20060131	G	2720		STOP FITTING    			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	RUDDER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											SDA AL-2000-04 CF-2000-20R2 SEB 01-1 COMPLETED, NO EVIDENCE OF JAMMING OR RUBBING ON EITHER RUDDER STOPS.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006062100075	20060621	00075	EA  	2006	6	21	CA060303019      	1	20060303	G	2810	CL21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT NR 6	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1342 								WHILE UNDERGOING IT'S 12 MTH INSPECTION FUEL WAS FOUND DRIPPING FROM THE RT WING TIP.  ALL 8 FUEL CELLS FROM THE RT WING	 WERE REMOVED FOR LEAK CHECK.  6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  DEFECTIVE CELLS WILL BE RE	PLACED.				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006062200071	20060622	00071	EA  	2006	6	22	CA060303020      	1	20060303	G	2810	CL215640026	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					RT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1342 								WHILE UNDERGOING IT'S 12 MTH INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  ALL 8 FUEL CELLS FROM THE RIGH	T WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  DEFECTIVE CELLS WILL 	BE REPLACED.				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
2006062100133	20060621	00133	EA  	2006	6	21	CA060303021      	1	20060303	G	2810	CL215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT NR 3	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1342 								(CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP.  ALL 8 FUEL CELLS FROM THE RT 	WING WERE REMOVED FOR LEAK CHECK.  6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE	 REPLACED. (TC NR 20060303021)				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006062100134	20060621	00134	EA  	2006	6	21	CA060303022      	1	20060303	G	2810	CL21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT NR 2	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1342 								(CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP.  ALL 8 FUEL CELLS FROM THE RT 	WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE 	REPLACED. (TC NR 20060303022)				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006062100135	20060621	00135	EA  	2006	6	21	CA060303023      	1	20060303	G	2810	CL215640011	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT NR 1	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1342 								(CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP. ALL 8 FUEL CELLS FROM THE RT W	ING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE R	EPLACED. (TC NR 20060303023)				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006062100139	20060621	00139	WP  	2006	6	21	CA060306004      	1	20060228	G	2740	T40032	TRIM SWITCH     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  TRIM SWITCH INTERMITTENT.   REPLACED SWITCH.  (TC NR 20060306004)						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062100140	20060621	00140	EU  	2006	6	21	CA060306005      	1	20060106	G	6720	350A33105803	CONTROL LEVER   			SNIAS 	350   	AS350*      	       	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  CONTROL TUBE WORN IN ATTACH POINT OF CONTROL LEVER.   REPLACED LEVER.  (TC NRV 20060306005)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062300034	20060623	00034	EA  	2006	6	23	CA060306006      	2	20060306	G	7250	311532101	TURBINE BLADES  								PWA   	PT6T  	PT6T3       	52045	EA  					POWER SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14821	3641 							(CAN) POWER SECTION WAS RECEIVED FROM THE OPERATOR FOR REPAIR DUE TO HIGH VIBRATION LEVELS.  INSPECTION REVEALED THAT TH	E COMPRESSOR TURBINE BLADES HAD SUFFERED EXTENSIVE DAMAGE. 12 CT BLADES WERE FOUND DAMAGED TO VARYING DEGREES OF THE BLA	DE SURFACE MISSING. ANOTHER 12 BLADES EXHIBITED FATIGUE CRACKING EMANATING FROM THE TRAILING EDGE OF THE BLADE.  (TC NR 	20060306006)								4	U			E22EA				 
2006062300160	20060623	00160	EA  	2006	6	23	CA060306007      	2	20060110	G	7414	4347	MAGNETO         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1793 							(CAN)  AIRCRAFT HARD TO START AND 125 DROOP.  REPLACED LT MAGNETO.  (TC NR 20060306007)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2006062300163	20060623	00163	EA  	2006	6	23	CA060306008      	2	20060112	G	7322	252434710	FUEL CONTROL    			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			500  			73707					(CAN) CANNOT UNJUST IDLE MIXTURE.  REPLACED FUEL CONTROL.  (TC NR 20060306008)						1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2006062300169	20060623	00169	SW  	2006	6	23	CA060306013      	1	20060113	G	8011	31B21064	STARTER         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				61   							(CAN)  STARTER NOT OPERATING.  REPLACED STARTER.  (TC NR 20060306013)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2006062300225	20060623	00225		2006	6	23	CA060306017      	4	20060303	G	2565	4A40302	SLIDE           			EMB   	ERJ170	ERJ170100LR 	       	EU  	GE    	CF34  	CF348E5A1   	30015	NE  					L1 DOOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			792  								(CAN) IAW FLEET ENGINEEERING REQUEST VERIFY  L-1, R-1, L-2 AND R-2 SLIDE FOR ANY EXTRA LACING AROUND THE SLIDE PACK OPEN	ING PIN. CONTACT MOC FOR INSTRUCTIONS AND PHOTOS OF PROPER INSTALLATION . REPORT FINDING FOR EACH DOOR AND CORRECTIVE AC	TION IF REQUIRE.  L1 DOOR SLIDE ASSEMBLY REPLACED IAW AMM,NEW SLIDE ASSY INSTALLED IAW AMM. (TC NR 20060306017)				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2006062300228	20060623	00228	CE  	2006	6	23	CA060306018      	1	20060303	G	3710	AA216CWOHE	PUMP            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	AIR PUMP	FAILED          	W				A				UNSCHED LANDING         				L			NO TEST                   			CR	CRUISE         	1			CA				144  							(CAN) AIR PUMP WAS INSTALLED IN AIRCRAFT AND FAILED AFTER 144 HOURS. (TC NR 20060306018)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2006062300229	20060623	00229	CE  	2006	6	23	CA060306019      	1	20060304	G	3710	AA216CWOHE	PUMP            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	AIR PUMP	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				1    							(CAN) AIR PUMP WAS INSTALLED IN AIRCRAFT AND FAILED AFTER 0.7 HOURS, FAILED DURING THE RUN UP. (TC NR 20060306019)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2006062600056	20060626	00056	EU  	2006	6	26	CA060306020      	1	20060304	G	2750	MS24178D1	RELAY           			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB4T	HCB4TN5     	GL  	TE FLAPS	INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APROACH FLAPS WERE SELECTED TO THE NR 2 POSITION AND DID NOT RESPOND . SYSTEM TROUBLESHOOTING FOUND THE RELAY T	O BE NOT FUNCTIONING . RELAY WAS REPLACED WITH A SERVICABLE UNIT AND FLAPS TESTED NORMAL (TC NR 20060306020)					2	H	7	2 	4T	4	T	RT	A16EU   	E2WE	6	C	P40EA	 
2006070300002	20060703	00002		2006	7	3	CA060307001      	4	20060304	G	3460	6224717004	CONTROL PANEL   			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					COCKPIT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											ON CLIMB-OUT YVR, NO A/T, NO CMD BARS, NO A/P L AND C. NO L NAV, (ACFT RETURNED TO YVR).  REPLACED MCP PER AMM 22-11-02 	PB 201.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006062600057	20060626	00057		2006	6	26	CA060307002      	4	20060305	G	3444	9733033111	PROXIMITY SWITCH			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			5497 								(CAN) DURING CRUISE, THE (AIR/GROUND) LIGHT ON THE CAWS PANEL ILLUMINATED. UPON TOUCHDOWN, THE LIGHT WENT OUT.  INVESTIG	ATION REVEALED A FAULTY LT GROUND PROXIMITY SWITCH. THE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR	 20060307002)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062600058	20060626	00058		2006	6	26	CA060307003      	4	20060125	G	2216	11538011119	ACCUMULATOR     	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE ABOVE P/N FAILED SENT FOR REPAIR THEN FAILED AGAIN WITH IN 5.3 HRS. SERVICEABLE ACTUATOR INSTALLED WITH NO MOR	E PROBLEMS. (TC NR 20060307003)					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006062600059	20060626	00059	NE  	2006	6	26	CA060307004      	2	20060303	G	7210	MS949034	BOLT            	PWA         	PT6A65AR    						PWA   	PT6   	PT6A65AR    	52043	NE  					GEARBOX	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20   	20   		PCEPS97533					(CAN) THE POWER SECTION OF ENGINE S/N PCE-PS 97533 WAS REMOVED DUE TO SEIZED CONDITION. THE REASON FOR REMOVAL AS DESCRI	BED BY THE OPERATOR WAS FAILURE ON START-UP. THE POWER SECTION ROTATION HUNG ON LIGHT UP, RELEASED AND HUNG UP AGAIN.  S	TART ABORTED.  POWER SECTION BINDS UP DURING MANUAL ROTATION. (TC NR 20060307004)									4	T			E4EA				 
2006062600060	20060626	00060	CE  	2006	6	26	CA060307005      	1	20060106	G	3230	1280811	MOTOR           			CESSNA	210   	210         	2073402	CE  										MLG	ERRATIC         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			721  								(CAN) GEAR MOTOR CHANGED DUE TO ERATIC GEAR OPERATION.  GEAR MOTOR WAS SPRAYING SOLDER.  PRESSURE SWITCH ADJUSTED TO SPE	C FOR GEAR OPEARTION.  (TC NR 20060307005)					1	H	7	1 	3O			RT	3A21    					 
2006062600061	20060626	00061	GL  	2006	6	26	CA060307006      	1	20060303	G	2720	C2CF177A	MOUNT           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RUDDER PEDALS	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) UPON LANDING, PILOT NOTICED THAT RUDDER PEDALS FELT LOOSE.  HAD NO PROBLEM WITH TAXING AND ON THE WATER. AC WAS RE	MOVED FROM SERVICE, INSP CARRIED OUT. CABLES WERE FOUND TO BE LOOSE. BELLY PNLS WHERE REMOVED, RUDDER BAR ASSY WAS INSPE	CTED. IT WAS NOTICED THAT RUDDER TUBES ON LT SIDE WERE RUBBING TOGETHER. UPON FURTHER VISUAL INSP IT WAS NOTICED THAT MO	UNT ASSY P/N C2CF177A WAS PULLED AWAY FROM ITS SUPPORT TUBE. WELD THAT SECURES IT TO TUBE HAD FAILED WHICH CAUSED STRESS	 ON OTHER SUPPORT TUBE, CAUSED MOUNT ASSY TO CRACK, COME AWAY FROM TUBE WHICH IN TURN CAUSED SLACK IN CABLES. RUDDER BAR	 WAS REMOVED FROM AC, PICTURES TAKEN, BAR WAS SENT FOR REPAIRS AS NO SPARE ASSY WAS AVAILABLE. (TC NR 20060307006)	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006062600062	20060626	00062	EU  	2006	6	26	CA060307007      	1	20060302	G	7500	26361090018	BLEED AIR SYS   			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					NR 2	INOPERATIVE     	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN)  DISPATCHED WITH BLEED NR 2 OFF IAW MEL.  LT WING LEAK IN CRUISE EMERGENCY DESCENT COMPLETED.  REMOVED ACCESS PANE	LS FOR  ZONE 521 BLEED DUCT FROM THE ENG NR 1 PYLON TO THE FUSELAGE. REMOVED ACCESS DOORS TO AIR CONDITIONING UNITS (191	+192). REMOVED BELLY FAIRINGS FOR ACCESS TO BLEED DUCT FWD OF THE AIR CONDITIONING UNITS. (TC NR 20060307007)				2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2006062600066	20060626	00066	NE  	2006	6	26	CA060307008      	2	20060306	G	7230		VANE            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					3RD STAGE VSV	CHAFED          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) NR 1 ENG STALL, ENG 1 SHUTDOWN AND LANDED.  BORESCOPE CARRIED OUT IAW AMM 72-00-00-200-003 AND 72-31-00-290-001 FO	UND 3 RD STAGE VSV  VANES RUBBING ON IB END MAKEING A GROOVE WITH DISPLACED METAL AT BOTH ENDS OF VANE TRAVEL. (TC NR 20	060307008)				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2006070300006	20060703	00006	EA  	2006	7	3	CA060307009      	2	20060306	G	7414	10357479	SHAFT           	BENDIX      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			790  	663  		L2294432E					DURING A 500 HR MAG INSPECTION, FOUND SHAFT FOR THE ROTATING MAGNET WORN BEYOND LIMITS.  BELIEVE SOMEONE HAD TRIED TO CH	ANGE THE COUPLING AND THEN COULD NOT PULL COUPLING OFF THE SHAFT.  THE NUT WAS REINSTALLED, TIGHTEN AND NEW COTTER PIN I	NSTALLED, BUT FAILED TO TORQUE THE NUT.  THIS IN TURN DID NOT LOAD THE SPACER PROPERLY WHICH THEN WORN THE SHAFT PREMATU	RELY.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062600067	20060626	00067	EA  	2006	6	26	CA060307010      	2	20060306	G	7414	10357426	DISTRIBUTOR BLK 	BENDIX      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				755  		F189908E					(CAN) DURING A 500 HR INSPECTION FOUND DISTRIBUTOR BLOCK BUSHING WORN. THIS CAUSED THE GEAR TO WOBBLE.  WHEN THE GEAR WO	BBLED THE ELECTRODE MADE CONTACT WITH THE BLOCK TERMINALS.  THIS CAUSED THE GEAR TO STRIP AND ELECTRODE TO BREAK. BUSHIN	G POSSIBLY DID NOT HAVE ENOUGH LUBRICATION. (TC NR20060307010)				1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062600068	20060626	00068	NE  	2006	6	26	CA060307011      	2	20060306	G	7414	10357586	DISTRIBUTOR GEAR	BENDIX      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				810  		L26962SE					(CAN) REMOVED DUE TO ROUGH RUNNING ENGINE.  ONCE THE MAGNETO WAS INSPECTED FOUND DISTRIBUTOR GEAR TEETH WERE STIPPED. DU	E TO POSSIBLE BACKFIRE ON ENGINE. (TC NR 20060307011)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062600069	20060626	00069		2006	6	26	CA060309001      	4	20060208	G	2210	9960013	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					AUTOPILOT	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, THE FLIGHT CREW REPORTED THEY HAD LOST THE AUTOPILOT, MACH TRIM AND THE STAB TRIM.  NR 1 STAB TRIM S	WITCH WAS NOTICED TO BE STICKY AND HARD TO DISENGAGE. THE CREW WAS ADVISED THAT IT WAS PROBABLY THE NR 1 (CAPT'S) DISENG	AGE SW (P/N 996-0013) AT FAULT AND CAUSING BOTH CHANNELS TO DISENGAGE AND THAT THE SWITCH NEEDED TO BE REPLACED. THE CRE	W CONTINUED ON IN A SLIGHTLY NOSE UP ATTITUDE AND THE AUTOPILOT UNSERVICEABLE. THE AIRCRAFT LANDED WITHOUT FURTHER INCID	ENT AND THE SWITCH (P/N 996-0013) HAS BEEN REPLACED (TC NR 20060309001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062600070	20060626	00070	EA  	2006	6	26	CA060309002      	2	20060225	G	7322		FUEL CONTROL    			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  		UNSERVICEABLE   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN)  ON TAKEOFF, THE STATIC RPM WAS ABOUT 2200RPM. AFTER TAKE-OFF AT AN ESTIMATED 300-400FT AGL THE ENGINE FAIRLY ABRU	PTLY DROPPED IN RPM AND THE AIRCRAFT BEGAN TO DESCEND. THE ENGINE WAS RUNNING ROUGH AND SOUNDED WEAK  BUT STILL RUNNING 	AT 2000 RPM.  PILOT THOUGHT (NOT SURE)HE PULLED ON CARB HEAT AND THEN TRIED TO WORK THE THROTTLE A BIT WITH NO SATISFACT	ORY RESPONSE. BY THE TIME THE AIRCRAFT WAS TAXIED TO THE HANGAR THE THROTTLE RESPONSE HAD RETURNED TO NORMAL.  (TC NR 20	060309002)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062600071	20060626	00071	NE  	2006	6	26	CA060309003      	2	20060219	G	7250		TURBINE BLADES  			BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ENGINE	FAILED          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								709421			(CAN) ON START UP THE CREW WAS UNABLE TO SUCCESSFULLY START THE NR 2 ENGINE.  LARGE PIECES OF TURBINE BLADES WERE DISCOV	ERED LAYING IN THE TAILPIPE AREA. THE ENGINE WAS REPLACED AND  A/C RETURNED TO SERVICE. (TC NR 20060309003)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006062600072	20060626	00072	NM  	2006	6	26	CA060309004      	1	20060308	G	5330	65C32362	SKIN            			BOEING	737   	737490      	1384715	NM  										BS 871-883	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUSELAGE SKIN CHAFFING BS 871 TO 883 AT STR 1-2 L REPAIRED IAW EA 5330-02065 (TC NR 20060309004).						2	L	7	2 	4F			RT	A16WE   					 
2006062600073	20060626	00073	CE  	2006	6	26	CA060309005      	1	20060307	G	5520	1016100197	RIVET           	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	TORQUE TUBE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3143 								(CAN) PHASE INSPECTION REVEALED SLIGHT MOVEMENT BETWEEN THE TORQUE TUBE AND THE ACTUATING ARM. THE ASSEMBLY IS SECURED B	Y 8 CHERRY LOCK RIVETS THAT WERE BEGINNING TO WORK, ALLOWING SUBTLE PLAY IN THE ASSEMBLED JOINT. TORQUE TUBE ASSEMBLY DE	TERMINED TO BE NON-REPAIRABLE AND WILL BE REPLACED. (TC NR 20060309005)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2006062600074	20060626	00074	CE  	2006	6	26	CA060309007      	1	20060308	G	7331	99103386	TRANSDUCER      			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	CONNECTOR	FLUCTUATES      	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			10376	10376							(CAN) DURING CRUISE FLIGHT FUEL FLOW INDICATOR STATED FLUCUATING FROM 80 LBS - 350 LBS/HR.  A/C RETURNED TO BASE AND UPO	N INSPECTION BY MAINT.  IT WAS DISCOVERED THAT THE CANNON PLUG ATTACHED TO THE FUEL FLOW TRANSDUCER WAS DIRTY.  CONNECTI	ON WAS CLEANED, A/C GROUND RUN SERVICEABLE AND RETURNED TO SERVICE.  (MFG OF THE FUEL FLOW INDICATION IS: RIGAN DATA SYS	TEMS) (TC NR 20060309007)			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006062600075	20060626	00075	CE  	2006	6	26	CA060310001      	1	20060302	G	2810	4572	FUEL CAP        			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT	LOOSE           	W				J	A			DUMP FUEL               	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			8331 								(CAN) DURING TAKEOFF ROLL AND ATC NOTICED FUEL COMING OUT OF THE LT TIP TANK.  ATC CONTACTED THE CREW ABOUT THE SITUATIO	N. THE CREW ELECTED TO DUMP FUEL FROM THE RT TIP TANK DUE TO FUEL IMBALANCE AND LAND THE AIRCRAFT WITH NO FURTHER INCIDE	NT.  THE FUEL CAP WAS FOUND BY AIRPORT MAINTENANCE CREW ON THE RUNWAY.  MAINTENANCE EXAMINED THE FUEL CAP AND NOTICED TH	E LOCKING MECHANISM HAD EXCESSIVE PLAY AND THE LOCKING TAB COULD EASILY BE TRIGGERED UNLOCK.  TECHNICIAN ALSO VERIFIED T	HE RT FUEL CAP AND NOTICED IT WAS ALSO DEFECTIVE.  BOTH CAPS WERE REPLACED. (TC NR 20060310001)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006062600090	20060626	00090	WP  	2006	6	26	CA060310002      	1	20060227	G	8011	BC3151002	STARTER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2887 	1028 							(CAN) STARTER WOULD NOT TURN OVER ENGINE.  TROUBLESHOOTING REVEALED A STARTER PROBLEM.  STARTER WAS REPLACED, AND NO FUR	THER DEFECTS WERE NOTED. (TC NR 20060310002)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006070300007	20060703	00007		2006	7	3	CA060310005      	4	20060308	G	2562	MN1300	BATTERY         	ACK         																ELT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						043775					AT ANNUAL CERTIFICATION OF ELT, THE BATTERIES REMOVED FROM CASE FOR INSPECTION.  FOUND ONE BATTERY LEAKING CAUSING CORRO	SION ON THE BATTERY CONTACT AT BOTTOM OF CASE.  BATTERY CASE AND BATTERIES REPLACED ABD UNIT TESTED SATISFACTORY.																		 
2006070300008	20060703	00008	NE  	2006	7	3	CA060310006      	1	20060310	G	6321	S6125203480	FLANGE          			SKRSKY	S61   	S61A        	814210C	NE  										ROTOR BRAKE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ATTEMPTED TO REPLACE A PART DAMAGED BEYOND REPAIR.  A PART WAS LOCATED AND ACQUIRED TO REPLACE DAMAGED UNIT.  PART WAS D	ELIVERED TO US FOR REVIEW.  SUPPLIER SUBMITTED VARIOUS CERTIFICATION DOCUMENTS TO VALIDATE PART.  PART JOURNAL IS UNDERS	IZE AND IN NEED OF A CHROME REPAIR PER THE MANUAL.  THE ONLY DOCUMENT THAT WAS NOT SUPPLIED WAS AN 8130-03 ATTESTING THA	T SIKORSKY HAD ACCEPTED THE MANUFACTURED PART AS AIRWORTHY.  ATTEMPTED TO CONTACT VENDOR ABOUT NEED OF THIS DOCUMENT, AN	D IT IS AT THIS TIME THAT IT WAS DISCOVERED THAT PART WAS AN OVERRUN PART.  TOLD VENDOR WE COULD NOT USE THE UNIT AND WO	ULD RETURN IT	2	G	7	2 	4U				H2EA    					 
2006070500032	20060705	00032	CE  	2006	7	5	CA060310007      	1	20060309	G	7830	LJ78352005	ISOLATION VALVE 			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					THRUST REVERSER	FAULTY          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			55   								(CAN) ON TAKEOFF THE LT ENGINE INDICATION SHOWS AN AMBER (REV), WHICH MEANS THE LT THRUST REVERSER IS ARMED WHEN THE AIR	CRAFT IS AIRBORNE AND/OR THE THRUST REVERSER IS ARMED WITH THE POWER LEVER ABOVE IDLE POSITION. THE CREW RETURNED. THE S	YSTEM WAS TROUBLESHOT TO A DEFECTIVE PRESSURE SWITCH ON THE LT THRUST REVERSER ISOLATION VALVE.  AN ISOLATION VALVE ON O	RDER. (TC NR 20060310007)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006070500033	20060705	00033	CE  	2006	7	5	CA060310008      	1	20060308	G	5270		SWITCH          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					PAX DOOR	MISRIGGED       	W				B				EMER. DESCENT           				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING THRU FL400 THE CAS MESSAGE (ENTRY DOOR) ILLUMINATED, THERE WAS NO PRESSURIZATION PROBLEM AND NO WHI	STLING SOUND. THE AIRCRAFT RETURNED WHERE AN AIRCRAFT MAINTENANCE ENGINEER INSPECTED THE DOOR AND CHECKED THE DOOR WARNI	NG SWITCHES FOR PROPER RIGGING. DOOR SWITCHES WERE S-115, AND S-117 THRU S-121 WERE RE-RIGGED. SYSTEM WAS FUNCTION CHECK	ED AND THE AIRCRAFT RETURNED HOME. (TC# 20060310008)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006070500042	20060705	00042	CE  	2006	7	5	CA060313001      	1	20060310	G	4910	70820262	SEAL            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					APU	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			956  								(CAN) AFTER EXPERIENCING DC POWER DIFFICULTIES OVER SEVERAL TIMES, FURTHER INSPECTION REVEALED WATER STAINS ON TOP OF TH	E LT AFT POWER DISTRIBUTION PANEL (PDP).  AFTER REMOVING THE PDP COVERS, WHITE POWDER ALUMINUM LIKE CORROSION WAS FOUND 	INSIDE THE COVERS.  INTERNAL PCB HAD 2 LARGE CORROSION SPOTS OVER SEVERAL CONTACTS.  FOUND DIRECTLY ON TOP OF THE LT AFT	 PDP WAS A MATING FLANGE FOR APU COOLING.  THIS FLANGE WAS LEAKING WATER FROM RAIN AND FREQUENT AIRCRAFT WASHING.  THE S	EALING WAS FOUND TOO THIN ALL OVER THE FLANGE AND SEALING WAS COMPLETELY MISSING WHERE THE 4 RETAINING BOLTS WERE DUE TO	 FLIGHT VIBRATIONS OVER TIME. (TC NR 20060313001)	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006070500044	20060705	00044	EA  	2006	7	5	CA060313002      	1	20060308	G	5514	C6FSM182031	BUSHING         			DHAV  	DHC6  	DHC6        	2802606	EA  										ADAPTOR	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) THE RAISED BUSHING AREA OF THE ADAPTOR ARE NOT MACHINED AT THE CORRECT ANGLE. BOTH MACHINED SURFACES ARE ANGLED AF	T, THIS CAUSES THE HORIZONTAL AND VERTICAL STABILZERS TO SIT OFF SET ON AN ANGLE AND NOT DOWN FLUSH.  MARKING ON THE ADA	PTOR ALONG WITH THE PN ARE NR 451443, W/O 0928, AUG 11/99 AND FIRST ARTICAL. PLEASE REFER TO S/B 6/454 AND 6/516 FOR MOR	E DETAILS. (TC NR 20060313002)			1	H	7	2 	3T			RT	A9EA    					 
2006070500045	20060705	00045	EU  	2006	7	5	CA060313003      	1	20060309	G	6410	10531980	BLADES          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	INOPERATIVE     	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AFTER FLIGHT, PILOT REPORTED THAT THE T/R PEDALS WERE STIFF.  PEDAL TENSION WAS CHECKED WITH THE AIRCRAFT RUNNING 	AND IN FLIGHT AND MEASURED AT 30 LBS TENSION. THE T/R BLADES WERE REPLACED BY SERVICEABLE UNITS AND PROBLEM DISAPPEARED,	 TENSION ON PEDALS RETURNED TO NORMAL AT 14 LBS. THE A/C WAS RETURNED TO SERVICE. (TC NR 20060313003)				1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006070300009	20060703	00009	SW  	2006	7	3	CA060313004      	1	20060308	G	2910	2781032776	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											HYD FLUID LEAKING FROM LEFT ENGINE COMPARTMENT.  PRESSURE LINE FROM HYD PUMP TO FIREWALL FOUND CHAFED AND LEAKING.  LINE	 WAS CHAFED ON A UNION FITTING ON THE OIL TANK IN A "OUT OF VIEW" AREA.  LINE REPLACED, GEAR SWINGS CARRIED OUT, HYD RES	EVOIR TOPPED UP AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006070300017	20060703	00017	EU  	2006	7	3	CA060313005      	1	20060309	G	2435	23032027	STARTER GEN     			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ENGINE	NOISY           	W				E				ENGINE SHUTDOWN         				E	H		VIBRATION/BUFFET          	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			CA											VIBRATION ON START TO 60 PERCENT, AND STRANGE NOISE FROM THE ENGINE, FOUND BROKEN STARTER.						1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2006070300026	20060703	00026	WP  	2006	7	3	CA060313006      	1	20060310	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				132  							SERVO FOUND LEAKING FROM TOP AND BOTTOM OF CYLINDER BARREL.  SERVO REMOVED AND REPLACED WITH A SERVICEABLE UNIT.  THE AT	TACHED PHOTOS SHOW THE SERVO AREAS THAT HAVE BEEN LEAKING.  THE BULK OF THE OIL HAS BEEN CLEANED OFF THE SERVO, BUT IT C	AN STILL BE SEEN WHERE THE LEAKS WERE COMING FROM.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006070300027	20060703	00027	WP  	2006	7	3	CA060313007      	1	20060310	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				132  							SERVO WAS FOUND LEAKING FROM TOP AND BOTTOM OF CYLINDER BARREL.  SERVO WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006070300028	20060703	00028	NE  	2006	7	3	CA060313008      	1	20060307	G	2913	7665009808102	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					HYDRAULIC SYS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											PUMP FAILURE.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006070300029	20060703	00029	NM  	2006	7	3	CA060313009      	1	20060312	G	4920	170101106A	APU             			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					APU BAY	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			28094								AFTER A FLIGHT FROM A HOLIDAY RESORT, THE AIRCRAFT HAD LANDED AT HOME BASE AND WAS TAXIING TO THE GATE.  AN APU START WA	S ATTEMPTED BUT THE UNIT WOULD NOT START.  ON INSPECTION, THE APU APPEARS TO HAVE HAD AN INTERNAL FAILURE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070300030	20060703	00030	CE  	2006	7	3	CA060313010      	1	20060307	G	2435	M230881320	BRUSHES         	LUCAS       		CESSNA	441   	441         	2076020	CE  										STARTER GEN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			90   	90   		996					SCHEDULED MX CHECK OF BRUSHES, OPERATOR FOUND 1 BRUSH HAMMERPLATE BROKEN OFF DURING INSPECTION OF BRUSHES.  RETURNED UNI	T TO OVERHAUL AMO FOR REPAIRS.  UNIT HAS ONLY 90 HOURS TSO.  AMO FOUND ALL BRUSHES CHIPPED AT T/E AND WORN FROM OSCILLAT	ION MOTION IN BRUSH HOLDERS.  ANOTHER BRUSH HAD A BROKEN HAMMERPLATE.  ARMATURE COMMUTATOR HAS ONE BAR PROTRUDING ABOVE 	TURNED DIA BY .003" IND RUNOUT.  MAX ALLOWED IS .0002".  ARMATURE HAD BEEN REWOUND AT OVERHAUL, SO HAS ONLY 90 HOURS ON 	IT.  STEEL HUB OF COMMUTATOR IS DARKENED, CONSISTENT WITH HIGH HEAT.  TO REPAIR, ARMATURE WAS REPLACED WITH REWOUND ONE,	 AND OEM REGULAR BRUSHES INSTALLED.  REMOVED ARMATURE AND BRUSHES ARE QUARANTINED.  WRITER IS CONCERNED THAT HIGHER INTE	1	L	7	2 	3T			RT	A28CE   					 
2006070300031	20060703	00031	SW  	2006	7	3	CA060313011      	1	20060202	G	6710	212001181001	COLLECTIVE STICK			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COCKPIT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3214 								THE AME WAS MANIPULATING THE COLLECTIVE STICK TO EXPOSE GREASE FITTINGS ON THE SWASHPLATE DURING A ROUTINE SERVICING OPE	RATION.  WHEN THE COLLECTIVE STICK WAS PULLED UP, STICK ASSY DETAIL P/N 212-001-181-001 BROKE AND SEPARATED AT THE SLOT 	WHERE THE NR 2 THROTTLE STOP PIN IS LOCATED, BETWEEN THE TWO THROTTLE GRIPS.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006070300032	20060703	00032	EU  	2006	7	3	CA060314001      	1	20060309	G	5230	A5247015100200	COVER           			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					CARGO DOOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											THE AIRCRAFT ARRIVED FROM FLIGHT WITH ONE OF THE FORWARD CARGO DOOR ACCESS PANEL LATCH COVER MISSING.  DURING INVESTIGAT	ION FOUND THE PANEL ATTACHMENT AREAS HAD ELONGATED, WHICH ALLOWED THE ATTACHMENT SCREWS TO PASS THROUGH THE ACCESS PANEL	.  NEW PANEL ASSY WAS INSTALLED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006070300033	20060703	00033		2006	7	3	CA060314002      	4	20060202	G	2350	GMA340	CIRCUIT BOARD   	GARMIN INTL 		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					AUDIO PANEL	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1468 			96266004					THREE GARMIN AUDIO PANELS GMA 340 HAD TO BE SENT BACK TO GARMIN FOR REPAIRS DUE TO A SHORT CIRCUIT OCCURRING WHEN PLUGGI	NG IN HEADSETS WITH THE MASTER SWITCH ON.  FIRST WAS ON JANUARY 17, 2006, LAST TWO OCCURRED ON SAME DAY FEB 2, 2006.  OP	ERATING AIRCRAFT FOR A LITTLE MORE THAN TWO YEARS, SUSPECTED FIRST FAILURE MAY HAVE BEEN AN ISOLATED EVENT DUE TO FACT T	HAT REPLACEMENT OF UNIT, WITH A LOANER, FROM ATLANTIC AVIONICS, WORKED JUST FINE.  DIAMOND ISSUED SB DAC1-23-01 REV 0 TI	TLED DA20 C1 -  GMA 340 ISOLATION DIODES ISSUED 08 DECEMBER 2004.  NOT PROVIDED A COPY OF BULLETIN UNTIL AFTER FAILURES.		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006070300034	20060703	00034	NM  	2006	7	3	CA060314003      	1	20060312	G	5100		UNKNOWN         			BOEING	737   	737*        	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  						MULTIPLE FAIL   	W				A				UNSCHED LANDING         				S	B	H	AFFECT SYSTEMS            	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	CL	CLIMB          	1			CA											WHILE CLIMBING THROUGH 15000 FT, THE FOLLOWING WAS ENCOUNTERED: CABIN EMERGENCY LIGHTS FLASHING. THRUST REVERSER ISOLATI	ON VALVE OPEN ILLUMINATED.  NOSE GEAR UNSAFE INDICATION (GEAR RETRACTED).  DFDR ILLUMINATED.  CARGO OVERHEAT/DETECTION F	AULT.  APU FAILED TO START WHEN SELECTED.  CAPTAIN HSI COMPUTER FLAG.  CSD LOW OIL PRESSURE ILLUMINATED.  ON SHORT FINAL	, THE MAIN GEAR GREEN LIGHTS TURNED RED.  OVERHEAD MASTER CAUTION WOULD NOT EXTINGUISH.  AFTER TOUCH DOWN, THE FOLLOWING	 WAS FURTHER EXPERIENCED, NR 1 ENGINE THRUST REVERSER WOULD NOT OPERATE.  MAIN GEAR ILLUMINATED GREEN AND THEN BLACK.  V	ERY FAINT GEAR CONFIGURATION HORN SOUNDED FOR 30 SECONDS.  A FAINT ELECTRICAL SMELL WAS OBSERVED.  F/O STATED THAT IT WA	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006070300035	20060703	00035	CE  	2006	7	3	CA060314004      	1	20060313	G	3297	16001260	CIRCUIT BREAKER 			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											LANDING GEAR FAILED TO EXTEND WHEN SELECTED.  POWERPACK C/B OPEN.						1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
2006070300036	20060703	00036	EU  	2006	7	3	CA060315001      	1	20060314	G	6300	332A67145620	BRACKET         			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					M/R DEICE SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			186  								DURING A ROUTINE DAILY INSPECTION, TWO MAIN ROTOR DEICE BRACKET WERE FOUND TO HAVE CRACKS IN THE SAME AREA. THESE BRACKE	TS WERE REPLACED AND THE A/C RETURNED TO SERVICE.					2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2006070300044	20060703	00044	NE  	2006	7	3	CA060315002      	2	20060314	G	7261	3037223	CARBON SEAL     			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA				291  				120986			IN CRUISE, AT FL200, OBSERVED SHORT INTERMITTENT ILLUMINATION OF OIL PRESS WARN LIGHT OF NR 2 ENG.  IND OF SLIGHT OIL PR	ESS FLUCTUATIONS OF CORRESPONDING GAUGE COUPLED WITH HIGHER OPERATING OIL TEMP ON NR 2 ENG.  CREW DECIDED TO DIVERT A/C 	TO BASE WHERE NORM APPROACH AND LANDING.  INVESTIGATION REVEALED SLIGHTLY LWR THAN NORM OIL LEVEL NR 2 ENG.  OIL LEVEL A	DJUSTED TO MM LEVELS AND FOLLOWING SATIS ENG GROUND RUNS A/C RETURNED TO SERVICE.  FOLLOWING DAY OF OPERATION, INVESTIGA	TIONS WERE UNDERTAKEN TO ENSURE OIL CONSUMPTION NOT COMPROMISED AND DURING INVESTIGATIONS IT WAS REVEALED SEALING FACE O	F BREATHER SYS CARBON SEAL DAMAGED WHICH COMPROMISED EFFICIENCY ON BREATHER SYSTEMS OP RESULTING IN INCREASED OIL CONSUM	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006070500077	20060705	00077	EU  	2006	7	5	CA060315003      	1	20060209	G	5610	350A25902500	WINDSHIELD      			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			926  	926  							(CAN) DURING INSPECTION BEFORE FLIGHT THE PILOT FOUND A CRACK IN THE CENTER WINDSHIED. CRACK WAS IN THE LOWER RT CORNER 	AND WAS 4 INCHES LONG. CRACK WAS STOP DRILLED AND TAPED IAW ECC INSTRUCTION NR 8598.  CENTER WINDOW WAS REPLACED AT ECC.	 (TC NR 20060315003)				1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2006070300045	20060703	00045	EA  	2006	7	3	CA060315004      	1	20060309	G	2434	A700AP	RELAY           			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	REVERSE CURRENT	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA				603  							A/C SHUT DOWN AFTER FLT, CREW REPORTED NR 2 GENERATOR WARNING LIGHT DID NOT ILLUMINATE.  A/C WAS RUN FOR TROUBLESHOOTING	, DURING WHICH TIME GEN FUNCTIONED INTERMITTENTLY.  WHEN ENGINES WERE SHUT DOWN, SMOKE BEGAN TO EMANATE FROM THE ELECTRI	CAL BAY IN THE CABIN CEILING.  ALL ELECT PWR WAS REMOVED FROM AIRCRAFT AND SMOKING STOPPED.  INVESTIGATION REVEALED THAT	 NR 2 REVERSE CURRENT RELAY HAD FAILED INTERNALLY AND WAS HEAVILY HEAT DAMAGED.  LARGE ELECTRICAL LEADS ATTACHED TO IT S	HOWED SIGNS OF OVERHEATING AS WELL.  ALL DAMAGED WIRING WAS REPLACED, AS WELL AS THE RT REVERSE CURRENT RELAY AND THE RT	 VOLTAGE REGULATOR.  AIRCRAFT WAS RETURNED TO SERVICE.	1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006070300046	20060703	00046		2006	7	3	CA060315005      	4	20060312	G	2330	RDAV2133	MONITOR         			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					COCKPIT	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				227  							ELECTRICAL BURNING SMELL FROM MONITOR.  MONITOR SWITCHED 'OFF'.  SMELL DISSIPATED.  MONITOR ELECTRICALLY DISCONNECTED.						2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2006070300047	20060703	00047	CE  	2006	7	3	CA060315006      	1	20060314	G	2823	1183890051	SHUTOFF VALVE   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	FUEL SYSTEM	UNKNOWN         	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											DURING PRE FLIGHT INSPECTION, FUEL PRESSURE ANNUNCIATOR EXTINGUISHED WHILE THE FIRE WALL SHUTOFF VALVE T HANDLE WAS PULL	ED.  THIS INDICATED THAT THE VALVE WAS STILL OPEN.  DURING THE MX T/S IT WAS FOUND THAT VALVE POSITION INDICATOR ARM WAS	 CONTACTING THE FUEL FILTER BRACKET AND PREVENTING THE VALVE FROM CLOSING.  REWORK OF THE BRACKET GAVE ENOUGH CLEARANCE 	FOR THE VALVE TO OPERATE NORMALLY. THE RIGHT HAND SIDE WAS CHECKED AND THE VALVE WAS FROM A DIFFERENT MANUFACTURER AND H	AD A MUCH SMALLER INDICATOR ARM. THIS WOULD NOT INTERFERE WITH THE BRACKET. THE MANUFACTURES PART NUMBERS ARE:  LEFT - Z	MV13 (CIRCLE SEAL CONTROLS) RIGHT - AV24B1351BR.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006070300048	20060703	00048	SW  	2006	7	3	CA060315007      	1	20060302	G	5347	204072921009	YOKE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					CARGO TRACK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CRACKS ORIGINATING IN ATTACHMENT BOLT HOLES.						1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006070300095	20060703	00095	CE  	2006	7	3	CA060316001      	1	20060309	G	7160	BAS2452502	CLAMP           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					RT INTAKE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2743 								DURING INSPECTION, RT ENGINE COWLING WAS OPENED AND TECHNICIAN FOUND PARTS OF RUBBER HOSE INSIDE COWLING.  FURTHER INVES	TIGATION LEAD TO OPENING OF THE RT LOWER ACCESS PANEL WHERE THE CLAMP FOR THE RT LOW PRESSURE BLEED AIR TO THE MIXING VA	LVE DUCT WAS FOUND BROKEN AND PARTS OF THE RUBBER DUCT.  CLAMPS WERE FOUND NOT LOCKWIRED.  IT IS FELT THAT THE CLAMP FAI	LED LEADING TO THE FAILURE OF THE DUCT ASSEMBLY.  THE CREW HAD NO INDICATION OF DUCT FAILURE.  DUCT ASSEMBLY AND BOTH CL	AMPS WERE REPLACED AND THE LT LOW PRESSURE DUCT TO MIXING VALVE WAS INSPECTED AND FOUND TO BE LOCKWIRED AND SECURED.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006070500092	20060705	00092	CE  	2006	7	5	CA060316002      	1	20060227	G	2421		TERMINAL        			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	3D32C	B3D32C407   	GL  	ALTERNATOR	BROKEN          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											PILOT REPORTED TOTAL LOSS OF ELECTRICAL POWER.  FOUND A BROKEN TERMINAL ON ALTERNATOR OUTPUT WIRE.  DURING THE GROUND RU	N, FOLLOWING REPAIR, ENGINE STARTED NORMALLY FROM THE BATTERY WITHOUT CHARGING FIRST, AND CHARGING SYSTEM FUNCTIONED NOR	MALLY.				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	EXPP5C	 
2006070500095	20060705	00095	GL  	2006	7	5	CA060316003      	2	20060314	G	7314	6896822	PUMP            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				2435 							AFTER COMPLETION OF 300 HR ENGINE INSPECTION ENGINE WAS BEING GND RUN AND LEAK CHECKED.  FUEL WAS NOTICED IN ENGINE COMP	ARTMENT AFTER INVESTIGATING DRAIN LINE WAS REMOVED FROM OVERBOARD DRAIN FOR FUEL PUMP AND EXCESSIVE LEAK WAS DETECTED.  	PUMP REMOVED AND REPLACED WITH SERVICEABLE UNIT.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006070500098	20060705	00098	CE  	2006	7	5	CA060316004      	1	20060306	G	5720	12212055	FITTING         			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520M    	17040	SO  					LT WING	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13764								DURING WING REMOVAL FOR PAINT, LT LOWER WING STRUT FITTING WAS FOUND TO HAVE A GOUGE OF APPROXIMATELY 1/8" FROM STRUT FA	IRING SCREW.					1	H	7	1 	3O	3	O		A16CE   	E8CE				 
2006070500104	20060705	00104	NM  	2006	7	5	CA060316005      	1	20060302	G	2460	50086003	CIRCUIT BREAKER 			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ELECTRICAL SYS	FAILED          	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA											CREW REPORTED ON DEPARTURE/CLIMB-OUT, ALL FUEL TANK NR 1 AND NR 2 BOOST PUMP CB'S POPPED.  EXTENSIVE VISUAL INSPECTION O	F PUMPS, WIRING CONNECTORS, ELECTRICAL HARNESSES AND SPLICES CARRIED OUT.  THE FOLLOWING COMPONENTS REPLACED: NR 2 GENER	ATOR HARNESS FROM FIRE WALL DISCONNECT TO GENERATOR REPLACED DUE TO HIGH RESISTANCE.  NR 1 GENERATOR CB (GCB) REPLACED D	UE TO 47V DROP ACROSS T2-L2.  NR 2 GENERATOR CN (GCB) REPLACED, SUSPECT FAULT.  NR 1 GENERATOR CONTROL PANEL PRECAUTIONA	RY REPLACEMENT.  ALL CB'S RESET, SYSTEM FUNCTION TESTED SERVICEABLE.  NO FURTHER REPORTS.  THIS AIRCRAFT WAS IN STORAGE 	FOR PREVIOUS 18 MONTHS PRIOR TO RE-ENTERING SERVICE. THE DEFECTS APPEAR TO BE RELATED TO THIS STORAGE PERIOD.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006070500105	20060705	00105	NM  	2006	7	5	CA060316006      	1	20060221	G	2822	91248075	RELAY           			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA											ALL 4 FUEL BOOST PUMP CIRCUIT BREAKERS POPPED IN FUEL TANK NR 2.  RECTIFICATION: 1 RELAY 109 ESS NR 2 BUS REPLACED.   MA	INTENANCE DETERMINED L1 AND L2 TERMINALS SHORTED TOGETHER CAUSING INTERNAL DAMAGE.  LEFT AFT BOOST PUMP RELAY REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006070500106	20060705	00106	SW  	2006	7	5	CA060316007      	1	20060314	G	2910	7U7467	MANIFOLD        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYDRAULIC SYS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			12155								DURING PILOT TRAINING AIRCRAFT COMPLETED A HYDRAULICS OFF LANDING.  HYDRAULIC SWITCH WAS THEN TURNED BACK ON AND THE FOR	E AND AFT MOVEMENTS CAME BACK HOWEVER THE LATERAL MOVEMENTS DID NOT COME BACK TO NORMAL HYDRAULIC ON.  AIRCRAFT WAS THEN	 SHUT DOWN AND HYDRAULIC SOLENOID/MANIFOLD WAS CHANGED.  SUSPECT OBSTRUCTION IN THE LATERAL SECTIONS OF THE MANIFOLD.  A	IRCRAFT HAS SINCE RETURNED TO SERVICE AFTER ASSEMBLY WAS CHANGED.  DELAY IN REPORTING WSDR WAS DUE TO THE SYSTEM NOT GIV	ING ME FULL ACCESS TILL THE NEXT DAY.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006070500107	20060705	00107	EA  	2006	7	5	CA060316008      	3	20060315	G	6111	W69EK763	BLADE           			DIAMON	DA20  	DA20C1      	2990001	GL  						SNSNCH	W69EK	W69EK63     	EA  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20   	20   							CRACK FOUND ON TRAILING EDGE OF PROPELLER TIP.						1	L	7	1 	3O			NT	TA4CH   		5	N	TA4CH	 
2006070500108	20060705	00108	SO  	2006	7	5	CA060316009      	2	20060301	G	8530		EXHAUST VALVE   			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	ENGINE	STICKS          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			1271 	1271 							EXHAUST VALVE STICKY.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006070500109	20060705	00109	SO  	2006	7	5	CA060316010      	1	20060316	G	8011		GEAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	STARTER BENDIX	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1027 							THE STARTER BENDIX GEAR WAS BROKEN IN 3 THREE PLACES.  THE STARTER HOLD DOWN BOLTS WERE EITHER BROKEN OR STRETCHED.  SIN	CE THE STARTER AND ALT HAVE A SUPPORTING BRACE BETWEEN THEM, VERY STRONGLY SUSPECT THAT THE STARTER WAS ENGAGED WHILE TH	E ENGINE WAS RUNNING.  THE STARTER SW WAS CHECKED FOR DEFECTS BUT NONE FOUND.				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006070500110	20060705	00110	WP  	2006	7	5	CA060316011      	1	20060219	G	8011	72566	RING GEAR       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER	CHIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			664  								TEETH FOUND MISSING DURING INSPECTION.  SERVICEABLE SUPPORT ASSEMBLY INSTALLED.  SUSPECT PROBLEM WITH THE STARTER/RING G	EAR ENGAGEMENT.  A CHIPPED TOOTH WAS ALSO FOUND ON THE STARTER.  STARTER P/N BC315-100-4 WAS ALSO REPLACED AT THE SAME T	IME.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006070500084	20060705	00084	CE  	2006	7	5	CA060317001      	1	20060314	G	3233	99810057652	ACTUATOR        	BEECH       		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						890273					(CAN) ON DEPARTURE, A LOUD BANG WAS HEARD AFTER GEAR WAS SELECTED UP, LANDING GEAR (IN TRANSIT) LIGHT REMAINED ON. GEAR 	WAS CYCLED, NO FURTHER NOISES WERE HEARD, (IN TRANSIT) LIGHT REMAINED ON. PASSENGER SEATED IN REAR ADVISED PILOT, RT MLG	 WAS NOT RETRACTING. PILOT SELECTED GEARDOWN AND OBSERVED THAT ALL 3 GREEN, GEAR DOWN AND LOCKED LIGHTS WERE ILLUMINATED	. AC WAS FLOWN WITH GEAR DOWN AND LANDED WITHOUT INCIDENT. AC WAS JACKED UP, A GEAR SWING CARRIED OUT, NOTED THAT DRIVE 	TO RT MLG ACTUATOR WAS ROTATING, ACTUATOR WOULD NOT EXTEND OR RETRACT, REPLACED, AC RETURNED TO SERVICE. WHEN ACTUATOR W	AS TESTED DRIVE WAS ROTATED AND THERE WAS SLIGHT RESISTANCE FELT, PINION DID NOT ENGAGE SCREW HSG.	1	L	7	2 	3T	3	T		A14CE   	E4EA	6	C	P15EA	 
2006091300288	20060913	00288	CE  	2006	9	13	CA060317002      	1	20060310	G	3397	2B1PECC532000	CONNECTOR       			LEAR  	35    	36A         	5170603	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					GLARESHIELD	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			15303								(CAN) AIRCRAFT DEPARTED APPROXIMATELY 30 MINUTES AFTER DEPARTURE SMOKE WAS NOTED UNDER GLARESHIELD AND EMERGENCY LANDING	 EXECUTED. MAINTENANCE PERSONNEL FOUND SOURCE OF SMOKE TO BE GLARESHIELD FLOODLIGHT. MAINTENANCE DE-ACTIVATED FLOODLIGHT	ING BY PULLING/COLLARING CIRCUIT BREAKER AND DEFERRING FLOODLIGHT IAW MEL. AIRCRAFT RETURNED TO HOME. FURTHER TROUBLESHO	OTING REVEALED COAX CONNECTOR/COAX WAS SHORTED WHERE IT ATTACHES TO GLARESHIELD FLORESCENT LAMP ASSEMBLY.  (TC NR 200603	17002)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006070500093	20060705	00093		2006	7	5	CA060317003      	1	20060317	G	3210	CRS8517319	BUSHING         																	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 16 NEW BUSHINGS RECEIVED, P/N CRS85-173-19 ALL FAILED NDT REQUIREMENT PRIOR TO INSTALL DUE TO CRACK IN THE BORE AR	EA.   (TC NR 20060317003)																		 
2006070500094	20060705	00094	GL  	2006	7	5	CA060317004      	1	20060316	G	3246	C2UT473	TORQUE TUBE     			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	WATER RUDDER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TAXING FLOAT EQUIPED AIRCRAFT, PILOT HAD COMPLETE FAILURE OF WATER RUDDER STEERING SYSTEM.  UPON INSPECTION 	IT WAS FOUND THAT THE TORQUE TUBE HAD CRACKED, SPLITTING INTO TWO PIECES.  FURTHER VISUAL INSPECTION FOUND THAT THE TORQ	UE TUBE WAS SEVERLY CORRODED INSIDE.  THIS CORROSION WAS MOST LIKELY CAUSED FROM WATER COLLECTING INSIDE THE TUBE DUE TO	 LACK OF DRAINAGE BECAUSE OF THE TILLER BAR WHICH IS ATTACHED HORIZONTALLY AT THE BASE OF THE VERTICAL TORQUE TUBE. (TC 	NR 20060317004)		1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006062600022	20060626	00022	SW  	2006	6	26	CA060317007      	1	20060213	G	5520	214001920101	HORN            	BELL        		BELL  	214   	214B1       	1182105	SW  										ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1468 			RE225					CRACK FOUND ON ELEVATOR HORN ASSY ON REGULAR INSPECTION.  REMOVED FROM SERVICE AND REPLACED WITH NEW ASSEMBLY.  PART HAS	 A RETIREMENT LIFE OF 2500 HOURS.					2	G	7	1 	4U				H6SW    					 
2006062600023	20060626	00023	EA  	2006	6	26	CA060317008      	2	20060315	G	7314	3034794	PUMP            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1037 							VISUAL INSPECTION CARRIED OUT IAW SERVICEABILITY CHECK. PRE-DISPATCH CHECK NOTICED FUEL UNDER THE RT ENGINE.  INSPECT FU	EL FILTER AND DRAINS WITH THE BOOST PUMP ON AND NO LEAKAGE WAS FOUND.  REMOVED FUEL PUMP DRAIN HOSE AND A LARGE AMOUNT O	F FUEL WAS EXPELLED FROM THE FUEL PUMP DRAIN.  THE FUEL PUMP/FUEL CONTROL ASSEMBLY WAS REMOVED FROM SERVICE DUE TO SUSPE	CTED INTERNAL BEARING WASHOUT DUE TO SEAL FAILURE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006062600024	20060626	00024	CE  	2006	6	26	CA060317009      	1	20060317	G	2435		BEARING         	LEARSIEGLER 		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				493  		16110					VISUAL INSPECTION CARRIED OUT IAW OPERATION FOUR.  NOTICED METAL DUST ON BACK OF THE ACCESSORY GEARBOX AND FOUND IT TO B	E MAGNETIC.  REMOVED STARTER GENERATOR AND FOUND THE QUILL SHAFT BEARING HAD FAILED.  UNIT WAS REMOVED FROM SERVICE.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006062600025	20060626	00025	CE  	2006	6	26	CA060317010      	1	20060311	G	3233	50820285	ACTUATOR        	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A64      		EA  					NLG	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA				1912 							NOSE LANDING GEAR ACTUATOR SEIZED AND OVER-LOADED MLG MOTOR BREAKER.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062600034	20060626	00034	CE  	2006	6	26	CA060317011      	1	20060314	G	2910		HYDRAULIC SYSTEM			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  		LEAKING         	W				K				NONE                    				K	S		FLUID LOSS                	AFFECT SYSTEMS            		IN	INSP/MAINT     	1			CA			14914								ON INVESTIGATING A HYDRAULIC LEAK IN THE NR 1 GEAR WELL AREA, CRACKS WERE NOTED IN THE CHANNELS P/N 101-120025-57 AND P/	N 101-120025-55 AS WELL AS THE ANGLE'S P/N 101-120025-67 AND 101-120025-68.  THE A/C HAD A HYDRAULIC GEAR INSTALLED IN 1	988 (REPLACING THE MECHANICAL GEAR ACTUATORS), AND AT THAT TIME HAD 2403.9 HOURS ON THE AIRFRAME.  THE NR 2 GEAR WELL WA	S INSPECTED FOR SIMILAR DAMAGE AND NONE WAS NOTED.  THE AFFECTED PARTS WERE REPLACED GEAR SWINGS ACCOMPLISHED AND THE A/	C RETURNED TO SERVICE.		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006070500097	20060705	00097	EU  	2006	7	5	CA060317012      	1	20060311	G	2797		WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			11782								(CAN) FLAPS FAILED TO EXTEND ON LANDING. FLAPS WORKED INTERMITTENTLY IN THE HANGER. VARIOUS FAULTS CODES WERE NOTED BUT 	THEY WERE NOT CONSISTENT AFTER RESETTING THE SYSTEM. UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE WIRES TO THE P029 	PLUG TO THE FCWU HAD FAILED INSULATION ABOUT A INCH BACK FROM THE PLUG UNDERNEATH THE FIRST CLAMP.  DAMAGED SECTION OF T	HE WIRING WAS REMOVED AND THE PLUG REPLACED. FLAPS WERE RESET ETC. AND OP'S CHECKED NORMAL. THIS PLUG AND WIRING WERE IN	STALLED AS PART OF SB 27008 WHICH WAS INCORPORATED ON THE A/C AT 26 AFTT AND 12 TC. (TC NR 20060317012)		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006070500099	20060705	00099	EA  	2006	7	5	CA060318001      	1	20060315	G	4950	WE38007703	APU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  											ODOR            	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA			3891 								(CAN) CREW REPORTED SMOKE AFT LAV WARNING MSG ABORTED T/O AND EVACUATED PAX THROUGH MAIN DOOR ON RUNWAY. REPORTED SMELL 	ONLY, NO VISIBLE SMOKE. SOURCE OF SMOKE SMELL BELIEVED TO BE APU BLEEDS. APU WAS REPLACED IAW AMM. (TC NR 20060318001)					2	L	7	2 	4F			RT	A21EA   					 
2006070500100	20060705	00100	EA  	2006	7	5	CA060318002      	1	20060312	G	3234	601R7520617	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			2507 								(CAN) A GEAR DISAGREE MESSAGE ON EICAS ALONG WITH MASTER WARNING AFTER GEAR DOWN SELECTION.  ON INVESTIGATION, IT WAS NO	TED NLG DID NOT SHOW DOWN AND LOCKED.  DOING A FLY BY, CONTROL TOWER WAS ABLE TO VERIFY THE NLG WAS NOT DOWN.   CREW PRO	CEEDED WITH QRH PROCEDURES AND ACTIVATED MANUAL RELEASE HANDLE WITHOUT OBTAINING THE DESIRED RESULT.  THE MLG HANDLE WAS	 THEN CYCLED AND ONLY THEN DID THE GEAR INDICATE DOWN AND LOCKED.  AN EMERGENCY WAS DECLARED. THE AIRCRAFT LANDED WITHOU	T FURTHER EVENT. MAINTENANCE REPLACED THE NLG SELECTOR VALVE AND UPLOCK ACTUATOR.  ALL SUBSEQUENT CHECKS IAW AMM.  AIRCR	AFT WAS RELEASED BACK TO SERVICE.  NLG UPLOCK ACTUATOR P/N 1660-103, S/N NGL10329/99 TSN 15283.42 (TC NR20060318002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006070500101	20060705	00101	EA  	2006	7	5	CA060319001      	1	20060319	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		CL	CLIMB          	1			CA											(CAN) APROX 19 MIN AFTER TAKEOFF, AIRCRAFT REPORTED SMOKE, SPARKS AND FIRE IN THE COCKPIT, COMING FROM THE PILOTS WINDSH	IELD. WINDSHIELD HEAT WAS IMMEDIATELY SWITCHED OFF AND FIRE/SPARKS EXTINGUISHED.  AIRCRAFT RETURNED TO BLOCKS.  INITIAL 	VERBAL REPORT FROM MAINTENANCE CONTROL INDICATES THAT THE PILOT WINDSHIELD HEAT TERMINAL BLOCK IS BURNED, THERE IS SOME 	SOOT ON THE COCKPIT CELING PANEL AND A SMALL PORTION(TC NR  20060319001)			2	L	7	2 	4F			RT	A21EA   					 
2006062700002	20060627	00002	GL  	2006	6	27	CA060320001      	3	20060316	G	6110	311466001	SEAL            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	DAMAGED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			1    					PCE25397			IN CRUISE 16,000 FT, NOTICED OIL LEAK ON TOP RT FWD ENG COWL. LEAK PROGRESSIVELY GOT WORSE, PILOTS ELECTED TO RETURN TO 	BASE. EVEN THOUGH ENG OIL TEMP AND PRESS NORM, PILOTS SHUTDOWN RT ENG.  CREW DECLARED EMERG.  BECAUSE QTY OF OIL LOST, P	ROP SHAFT SEAL SHOULD BE LOOKED AT.  RT PROP SEAL HAD BEEN REPLACED 2 DAYS EARLIER DUE TO OIL LEAKAGE IN NOSE CASE AREA.	 MX FOUND FAULTY PROP SEAL WAS WRONG P/N.  BY TIME OF DISCOVERY OUR P & W FSR WAS ON SITE, WENT BACK TO OUR STORES AND P	ULLED THE REMAINING SEAL IN STOCK STAMPED 3114661-01, AND IT TO WAS WRONG PART INSIDE, (3114660-01).  WITNESSED BY FSR. 	 SEALS CAME FROM CPWA, PACKAGED ON 02/2000.  BECAUSE OF LOSS OF OIL/AIR PRESSURE IN THE RGB, OIL WAS ALLOWED TO MIGRATE 	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006091300289	20060913	00289	CE  	2006	9	13	CA060320002      	1	20060315	G	2750	6627503000019	TRANSDUCER      			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					TE FLAP CONTROL	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			68   								(CAN) ON THE FLIGHT WITH A SCHEDULED REFUELING STOP. WHILE IN CRUISE APPROXIMATIVELY 1.5 HOURS AFTER DEPARTURE, THE AMBE	R CAS MESSAGE (FLAP FAIL) ILLUMINATED. THE CREW WAS UNABLE TO RESET THE SYSTEM AND MADE A FLAP LESS LANDING, INSTEAD OF 	WHERE AUTHORIZED SERVICE FACILITY WAS ABLE TO CONNECT THE DIAGNOSTIC COMPUTER TO THE AIRCRAFT. THE FAULT HAD ALREADY RES	ET ITSELF AND THE GROUND CREW WAS UNABLE TO DUPLICATE THE PROBLEM. THE AIRCRAFT WAS RETURNED TO SERVICE. ON THE FLIGHT T	HE AMBER CAS MESSAGE (FLAP FAIL) ILLUMINATED AND THE AIRCRAFT MADE A FLAPLESS LANDING. A TEAM OF TECHNICIANS FROM SERVIC	E CENTER WAS DISPATCHED TO THE AIRCRAFT WHERE TROUBLESHOOTING WAS PERFORMED. THE TECHNICIANS WERE UNABLE TO DUPLICATE TH	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062300017	20060623	00017	CE  	2006	6	23	CA060320003      	1	20060309	G	5520	1156100153	SUPPORT BRACKET 	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  CRACK FOUND ON IB SUPPORT BRACKET WHILE CARRYING OUT REPETITVE INSPECTION MSB 2145.  TORQUE TUBE REPLACED WITH NE	W.  (TC NR 20060320003)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006062300018	20060623	00018	WP  	2006	6	23	CA060320004      	1	20060320	G	1100	369A81433	DATA PLATE      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL TANK	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GLUE ON DATA TAG DETERIORATED DUE TO CONTACT WITH FUEL AND WAS LOCATED AT BOTTOM OF FUEL TANK (TC NR 20060320004)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006070500102	20060705	00102	NM  	2006	7	5	CA060320005      	1	20060320	G	3231	CL12068161	SOCKET          			BOMBDR	DHC8  	DHC8402     	1390042	NM  										MLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK, FUNCTIONAL CHECK ON TASK CARD 3230/15 (OPERATIONAL CHECK OF LANDING GEAR DOOR SEQUENCE CONTROL CIR	CUIT) DOES NOT WORK. AFTER INVESTIGATION, RELAY (3260-K9) SOCKET FOUND BROKEN AND PINS OLDER SOCKET UNGLUED. WIRE WERE F	OUND HANGING LOOSE WITH A HI RISK OF CONTACT WITH STRUCTURE. POSSIBILITY OF (WOW) CIRCUIT FAILURE AND THE MOST IMPORTANT	, IMPOSSIBILITY OF GEARS EXTENSION IN ALTERNATED RELEASE IN CASE OF EMERGENCY EXTENSION. (TC NR 20060320005)			2	H	7	2 	4T			RT	A13NM   					 
2006070500103	20060705	00103		2006	7	5	CA060320006      	2	20060310	G	7321	21195761011	ECU             			BOMBDR	BD700 	BD7001A10   	1390006	GL  										ENGINE	INOPERATIVE     	W				O				OTHER                   				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CL	CLIMB          	1			CA											(CAN) THE PROBLEM OCCURED ON THE 11/03/2006. DUE TO INTERNET CAPACITY TO DISPLAY THE RIGHT DATE, THE DATE OF MARCH 10 WA	S WRITTEN IN THE (OCCURENCE DATE) ABOVE DUE TO INTERNET INCAPACITY TO DISPLAY CERTAIN DATE.  FLIGHT CREW NOTICED A LT EN	GINE ROLL BACK AT CLIMB. PROBLEM OCCURED TWICE BEFORE ENGINE FLAMED OUT. ENGINE AUTO RESTARTED. WAS FINE FOR THE REST OF	 THE FLIGHT.  AMBER FADEC FAIL CAS POSTED.  AFTER LANDING LT T/R WOULD NOT STOW.  3-13-06 REPLACED LT ENGINE FADEC ECU A	 AND RT ENGINE FADEC ECU B REMOVED AS A PRECAUTIONARY MEASURE. GROUND RUNS OPS CHECKS GOOD.		2	L	7	2 	4F			RT	T00003NY					 
2006070500122	20060705	00122	EA  	2006	7	5	CA060320008      	1	20060315	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) EN ROUTE DISCOVERED 2 CRACKS IN LT SIDE WINDOW, DIVERTED.  LT SIDE WINDOW REPLACED AND TESTED IAW AMM PROCEDURE.  	AIRCRAFT RETURNED TO SERVICE. (TC NR 20060320008)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071100120	20060711	00120	EU  	2006	7	11	CA060321001      	2	20060316	G	7310		FUEL FILTER     			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DEPARTING, THE CREW OBSERVED A FUEL FILTER INDICATION ON NR 2 ENGINE. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RE	TURNED TO THE COMPANY RAMP. MAINTENANCE REPLACED THE FILTER AND AFTER SATISFACTORY GROUND RUN THE AIRCRAFT WAS RETURNED 	TO SERVICE. (TC NR 20060321001)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2006070500200	20060705	00200	NM  	2006	7	5	CA060321002      	1	20060317	G	3240	214747	BRAKE           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  						FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON LANDING ( MONCTON ) WITH THE ANTI-SKID SYSTEM OPERATING UNDER MEL 32-2 (ANTI-SKID SYSTEM INOP), THE AC LANDED	 ON A BARE RUNWAY AND BLEW 3 MAIN WHEEL TIRES AND BADLY SCUFFED THE FOURTH.  ALL FOUR MAIN TIRES REPLACED. AIRCRAFT FERR	IED. UPON FURTHER INVESTIGATION,THE NOSE GEAR SAFETY SENSOR AND E11 CIRCUIT CARD WERE REPLACED.  FURTHER INVESTIGATION O	N-GOING. TIMES: 37418:14   CYCLES: 22960  (TC NR 20060321002)			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500201	20060705	00201	NM  	2006	7	5	CA060321003      	1	20060321	G	5243	6556235159	DOOR            			BOEING	727   	727247      	138408F	NM  										HYD BAY	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			68406								(CAN) AIRCRAFT WAS LEAVING ON-ROUTE. SHORTLY AFTER TAKEOFF AT APPROX. 12000 FT. THE CREW NOTICED A VIBRATION. ALL INDICA	TIONS WERE NORMAL AND THE AIRCRAFT CONTINUED. AFTER TAXIING TO THE RAMP THE MAINTENANCE PERSON NOTICED THAT THE HYDRAULI	C SERVICING BAY DOOR WAS MISSING. AN INVESTIGATION WAS PERFORMED AND IT WAS FOUND THAT THE MAINTENANCE PERSON HAD NOT CL	OSED THE DOOR PROPERLY. NOT ALL LATCHES HAD NOT BEEN CLOSED PROPERLY. SERVICEABLE DOOR AND HINGE WAS INSTALLED AND THE A	IRCRAFT WAS INSPECTED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060321003)		2	L	7	3 	4F				A3WE    					 
2006070500202	20060705	00202	WP  	2006	7	5	CA060321004      	2	20060317	G	7397	C8102414	CABLE           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  		BROKEN          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT CREW REPORTED THAT DURING START THE RPM WAS UNCONTROLLABLE AND INITIATED A MANUAL SHUT DOWN. MAINTENANCE DI	SCOVERED THE POWER LEVER BROKEN APPROX. 4 INCHES FROM THE END JUST SHORT OF THE QUICK DISCONNECT FITTING.  DUE TO THE FA	CT THAT THE TELE-FLEX CABLE IS LOCATED INSIDE A (SHEATH) THE DEFECT IS NOT DETECTABLE UNTIL THE CABLE BREAKS. IT APPEARS	 AS THOUGH THE CABLE HAS BEEN CONTACTING THE INNER PORTION OF THE SHEATH FOR SOME TIME AND THE FACT THAT THE PILOTS PULL	 THE POWER LEVER INTO REVERSE EVERY SHUT DOWN CAUSED SOME WORK HARDENING OF THE MATERIAL WHICH ULTIMATELY CAUSED IT TO F	AIL. (TC NR 20060321004)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2006070500203	20060705	00203	EA  	2006	7	5	CA060321005      	1	20060321	G	2810	CL21564001	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1220 								(CAN) WHILE UNDERGOING A SCHEDULED INSPECTION FUEL WAS FOUND DRIPPING FROM THE LT WING. ALL 8 FUEL TANKS WERE REMOVED FO	R LEAK CHECK. THIS AND SEVERAL OTHER CELLS WERE FOUND LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC 	NR 20060321005)				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006070500118	20060705	00118	EA  	2006	7	5	CA060321006      	1	20060321	G	2820	CL215640026	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 2	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1222 								WHILE UNDERGOING A SCHEDULED INSPECTION FUEL WAS FOUND DRIPPING FROM THE LEFT WING.  ALL 8 FUEL TANKS WERE REMOVED FOR L	EAK CHECK.  THIS AND SEVERAL OTHER CELLS WERE FOUND LEAKING INCLUDING THIS ONE.  DEFECTIVE CELLS WILL BE REPLACED.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006070500119	20060705	00119	EA  	2006	7	5	CA060321007      	1	20060321	G	2820	CL215640022	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 6	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1222 								DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LEFT WING WAS LEAKING FUEL.  ALL 8 FUEL CELLS WERE REMOVED FOR LE	AK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE.  LEAKING CELLS WILL BE REPLACED.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006070500204	20060705	00204	EA  	2006	7	5	CA060321008      	1	20060321	G	2810	CL21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1222 								(CAN) DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LT WING WAS LEAKING FUEL.  ALL 8 FUEL CELLS WERE REMOVED FO	 LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. (TC NR 20060321008)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006070500208	20060705	00208	EA  	2006	7	5	CA060321009      	1	20060321	G	2810	CL21564075	FUEL CELL       			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1222 								(CAN) DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LEFT HAND WING WAS LEAKING FUEL. ALL 8 FUEL CELLS WERE REMO	VED FOR LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. (TC NR 20060321	009)				2	H	7	2 	4R	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006070500220	20060705	00220	GL  	2006	7	5	CA060321011      	1	20060130	G	5344	C2FS3282A	STRUT           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	DOOR POST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29083								(CAN) ULTRASONIC INSPECTION REVEALED THAT THE RT DOOR POST STRUT HAD FAILED THE INSPECTION CRITERIA.  NEW DOOR POST STRU	TS INSTALLED. (TC NR 20060321011)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006070500137	20060705	00137	GL  	2006	7	5	CA060321012      	1	20060303	G	5311	C2FS3203A	TUBE            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	BIRD CAGE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				4497 							DIAGONAL BIRD CAGE TUBE FOUND TO BE BELOW LIMITS DURING ULTRASONIC INSPECTION.						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006070500138	20060705	00138	EA  	2006	7	5	CA060321013      	1	20060203	G	5342	C3FS4727	HINGE BRACKET   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					HORIZ STAB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23509								BOTH THE FORWARD HORIZONTAL STABILIZER ATTACH HINGE BRACKETS (C3FS472-7 RT AND C3FS473-7 LT) WERE FOUND TO BE BUSHED BEY	OND SERVICEABLE LIMITS.  VIKING AIR HAD GIVEN A MAXIMUM OD OVERSIZE BUSHING OF .500.  DURING INSPECTION THE BUSHINGS WER	E MEASURED AT .650 + BOTH BRACKETS WERE REPLACED WITH NEW PARTS.				1	H	7	1 	3R	3	R		A815    	5E2				 
2006070500146	20060705	00146	EA  	2006	7	5	CA060321014      	1	20060201	G	5700	C3FS145	BAR             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					WING	CORRODED        	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			23509								DURING A VISUAL INSPECTION OF THE OTTER TIE BAR ASSEMBLY A LARGE COLLECTION OF DEAD FLY CARCASSES WERE FOUND CRAMMED INT	O THE "U" CHANNEL SECTION OF THE TIE BAR.  ON FURTHER INVESTIGATION WITH THE BUG BIOMASS IT BECAME EVIDENT THAT THE BAR 	HAD STARTED TO EXFOLIATE.  THE TIE BAR ASSEMBLY WAS REPLACED.  A CONTRIBUTING FACTOR TO THE FAILURE MAY HAVE BEEN THE FA	CT THAT THE INSPECTION HOLES THAT WERE INCORPORATED TO INSPECT THE TIE BAR HAD NEVER BEEN ADEQUATELY RESEALED AFTER THE 	LAST INSPECTION.		1	H	7	1 	3R	3	R		A815    	5E2				 
2006070500154	20060705	00154	EA  	2006	7	5	CA060321016      	1	20060103	G	5312	C3FS3413	BULKHEAD        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23509								THE FOLLOWING FLOOR SUPPORTING STRUCTURE WAS FOUND TO BE UNSERVICEABLE IN THE CABIN AREA PN NR C3FS34-13 BULKHEAD LOWER 	STATION 133.33, C3FS13-27 BULKHEAD LOWER STATION 153.77, C3FS51-27 BULKHEAD LOWER STATION 174.2, C3FS58-15 BULKHEAD LOWE	R STATION 194.00 REPEATED HEAVY LOADS TO THE FLOOR AREA OVER 23'000 HRS HAD DAMAGED OR WEAKENED THE STRUCTURAL INTEGRITY	 OF THE FLOORBEAM ATTACH POINTS.  ALL OF THE TOP BULKHEAD FLANGES WERE DAMAGED AT THE INTERSECTION OF THE FLOORBEAMS REF	 #C3FS351-2.  THIS DEFECT IS ESPECIALLY IMPORTANT SINCE THE REAR CABIN SEAT/SEAT BELT RESTRAINT IS INDIRECTLY ATTACHED T	O THE FLOOR BULKHEADS.	1	H	7	1 	3R	3	R		A815    	5E2				 
2006070500158	20060705	00158	EA  	2006	7	5	CA060321017      	1	20060209	G	2730	C3CF1267	HOUSING         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	ELEV QUADRANT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23509								THE ELEVATOR QUADRANT BEARING HOUSING WAS WORN BEYOND LIMITS AT THE BEARING ATTACH POINTS, REF NRB538.						1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2006070500159	20060705	00159	EA  	2006	7	5	CA060322001      	1	20060209	G	2720	C3CF1277	HOUSING         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	RUDDER QUADRANT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23509								THE RUDDER QUADRANT BEARING HOUSING WAS WORN BEYOND LIMITS AT THE BEARING ATTACH POINTS/PIVOT POINT.						1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2006070500164	20060705	00164	EA  	2006	7	5	CA060322002      	1	20060209	G	2750	C3CF1073	FITTING         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	T/E FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23509								BOTH INBOARD FLAP(C3CF104-5) TUBE END ASSEMBLIES (LT AND RT WINGS) C3CF107-3 WERE REPLACED DUE TO WEAR AND LOOSE ATTACH 	FASTENERS.  FAILURE OF THE PLUG END ON THE FLAP CONTROL TUBE COULD LEAD TO AN ASYMMETRIC FLAP CONDITION.					1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2006062700083	20060627	00083	NE  	2006	6	27	CA060322003      	2	20060314	G	7240	6003T07G01	COMBUSTION CASE 			SKRSKY	S61   	S61L        	8142102	NE  	GE    	CT58  	CT581401    	30011	NE  					ENGINE	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				3356 				295269			(CAN) THE PILOT NOTICED A GRADUALLY INCREASING ENGINE OIL PRESSURE, AND T5, ALONG WITH DECREASING OIL PRESSURE.  AFTER S	HUTDOWN, THE ENGINE WAS INSPECTED, AND A CRACK FOUND IN THE LOWER COMBUSTION CASE HALF.  THE ENGINE WAS REMOVED FOR CASE	 REPLACEMENT AND TEST CELL RUN TO DETERMINE IF ALL INDICATIONS WERE A RESULT OF AIR LOSS THROUGH THE CASE CRACK. (TC NR 	20060322003)			2	G	7	2 	4U	4	U		1H15    	1E3				 
2006070500170	20060705	00170	EU  	2006	7	5	CA060322004      	1	20060320	G	3020	5302412140	DEICE SYSTEM    	PILATS      	571101207   	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	INLET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4720 								DURING MAINTENANCE OPERATION NOTICED EXHAUST SOOT TRAIL FROM INNER EDGE OF DEICE LIP ASSY.  REMOVAL OF DEICER LIP ASSY F	ROM COWL REVEALED A CRACK ON INNER PART OF LIP DEICE ON INLET SIDE.  DEICE LIP ASSY REPLACED WITH NEW.  P/N; OF CRACKED 	DEICE LIP ASSY IS 530.24.12.140.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006071100136	20060711	00136	CE  	2006	7	11	CA060322006      	1	20060316	G	2910	991242322	VALVE           			CESSNA	525   	525         	2076601	CE  										HYD SYSTEM	STUCK           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3247 								LANDING GEAR DID NOT COME UP ON CLIMB.  PILOT FOUND COMPLETE FAILURE OF ALL HYDRAULIC SYSTEM.  ON TROUBLESHOOTING, FOUND	 SOLENOID LANDING VALVE SCREEN STUCK ON VALVE SEAT CAUSING COMPLETE BYPASS OF THE HYDRAULIC FLUID.  THIS VALVE WAS PLANN	ED TO BE REPLACED AT NEXT VISIT IAW SB 525-24-10.				1	L	7	2 	4F			RT	A1WI    					 
2006071100159	20060711	00159	EA  	2006	7	11	CA060322007      	1	20060321	G	2797	MS3476L2241S	CONNECTOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ELEVATOR HEAT	BURNED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			34538	34538							(CAN) DURING CLIMB POSITION LT CIRCUIT BREAKER POPPED. MAINTENANCE TROUBLE SHOOTING FOUND REAR PRESSURE BULKHEAD (STA 70	8.45) PLUG CONNECTOR (9811-J9) TO HAVE SEVERAL BURNED PINS. ELEVATOR HORN HEAT , LOGO LIGHTS AND AFT POSITION LTS ARE AL	L CONNECTED THRU THIS CONNECTOR PLUG. ELEVATOR HORN HEAT, POSITION LIGHTS , AND LOGO LIGHTS HAD REPORTED PREVIOUS INTERM	ITTANT FAULTS. CONNECTOR REPLACED AND TESTED SERVICEABLE. (TC NR 20060322007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006071100160	20060711	00160	WP  	2006	7	11	CA060322008      	1	20060320	G	8011	BC3151002	STARTER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				456  							(CAN) AIRCRAFT FAILED TO START. STARTER WAS REMOVED AND A OVERHAULED UNIT WAS INSTALLED AND NO FURTHER DEFECTS WERE NOTE	D. STARTER JUST COME OUT OF A REPAIR, 20.5 HRS EARLIER FOR INTERMITTENT/ERRATIC OPERATION. (TC NR 20060322008)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062600001	20060626	00001	WP  	2006	6	26	CA060322009      	1	20060308	G	6322	369D25623	BELT            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					BLOWER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			421  								(CAN) DURING A 100 HOUR INSPECTION THE BLOWER BELT WAS NOTED AS HAVING SEVERAL TEETH MISSING. BELT IS IDENTIFED WITH THE	 PN IN WHITE MARKER. BELT TENSION WAS VERIFIED AFTER INSTALLATION AND NO DEFECTS WERE NOTED DURING THE NEXT 3-100 HOUR I	NSPECTIONS. NO VIBRATIONS OR NOISE WERE NOTED. (TC NR 20060322009)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006071000104	20060710	00104	NE  	2006	7	10	CA060322010      	2	20060315	G	7321	324485318	FUEL CONTROL    			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ENGINE	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			26983	1106 							DURING CRUISE PILOT REPORTED ENGINE PARAMETERS WANDERING.  NH +-0.4% NL +- 0.2%, RPM +- 2 .  MAINTENANCE INSPECTION FOUN	D POWER LEVERS ARMS LOOSE (LOW TORQUE/STILL COTTER PINNED ARMS RETIGHTEN AT ALL PIVOT POINTS AND RE-COTTER PINNED.  AIRC	RAFT RETURNED TO SERVICE FUEL CONTROL UNIT HAD BEEN INSTALLED FOR 1106 HR/1331 CY.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006071100161	20060711	00161	EA  	2006	7	11	CA060323001      	2	20060131	G	7414	1068291013	HOUSING         	BENDIX      		RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				671  		B101195					(CAN) DURING SCHEDULED MAINTENANCE, AN OIL LEAK WAS NOTED AT THE RT ENGINE MAGNETO GASKET. THE MAGNETO WAS REMOVED TO RE	PLACE A DEFECTIVE GASKET. UPON CLOSER INSPECTION A SMALL CRACK WAS FOUND ALONG THE MAGNETO MOUNTING FLANGE. OIL WAS SEEP	ING THROUGH THE CRACK. THE CRACK WAS HIDDEN BY THE MAGNETO RETAINING CLAMP, NUT AND LOCK WASHER.  (TC NR 20060323001)				1	L	7	2 	3O	3	O		A12SW   	E14EA	5	C	P33EA	 
2006071000105	20060710	00105	NE  	2006	7	10	CA060323002      	2	20060311	G	8530	1830	CYLINDER        			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	NR 13	CRACKED         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA				422  				CP356035			THE EXHAUST EAR OF NR 13 CYLINDER DEVELOPED A CRACK WHICH AFFECTED THE VALVE CLEARANCE OF THE EXHAUST VALVE, RESULTING I	N A ROUGH RUNNING ENGINE.   CYLINDER ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603	 
2006062300002	20060623	00002	EU  	2006	6	23	CA060323003      	1	20060224	G	2930	MS2771923	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COLLECTIVE	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											THE PILOT WAS CARRYING OUT HIS/HER PRE FLIGHT HYDRAULIC TEST "FAILED", HORN WAS UNABLE TO SOUND DUE TO FAULTY SWITCH.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062600091	20060626	00091	CE  	2006	6	26	CA060323004      	1	20060323	G	7120		MOUNT           			HELIO 	H250  	H250        	4300302	CE  										ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FWD FUSELAGE TUBING MOUNTING BOSSES FOR THE ENGINE MOUNT, AND THE L/H MAIN GEAR REAR ATTACH FITTING FOUND CRACKED DURING	 INSPECTION.  THE AREAS CRACKED WERE THE WELD JOINTS OF ALL 4 FWD FITTINGS AND THE INNER WELD JOINT ON THE LANDING GEAR 	FITTING.  ALL WELDS APPEAR TO BE FACTORY WELDS.  CAUSE OF FAILURE BELIEVED TO BE THAT WELD JOINTS WERE NOT PROPERLY NORM	ALIZED FROM FACTORY CAUSING BRITTLE REGIONS WITHIN THE WELDED AREA ITSELF.			1	H	7	1 	3O				1A8     					 
2006071000106	20060710	00106	GL  	2006	7	10	CA060324001      	2	20060316	G	7200		ENGINE          			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	E	J	FLUID LOSS                	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA											DURING CLIMB-OUT, ENGINE BEGAN TO VIBRATE AND COMPRESSOR STALL.  OIL PRESSURE WENT TO ZERO.  PILOT PERFORMED SHUTDOWN AN	D RETURNED TO AIRPORT.  POST FLIGHT INSPECTION OF ENGINE REVEALED METAL ON CHIP COLLECTORS AND THE SPOOLS DID NOT TURN F	REELY (BEARING NOISE).  THE MANUFACTURER WILL PROVIDE A TEARDOWN REPORT SOON.				1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006071000107	20060710	00107	NM  	2006	7	10	CA060324002      	1	20060322	G	2897	W1134360118	WIRE HARNESS    			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL PUMP	DAMAGED         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			3010 								A/C HAS NR 2 AFT FUEL PUMP LOW PRESSURE LIGHT ILLUMINATE ON TAXI.  A/C RETURNED TO GATE AND IT WAS DISCOVERED THAT ASSOC	IATED CIRCUIT BREAKER WAS TRIPPED.  FURTHER INVESTIGATION REVEALED WIRE W1134-3601-18 HAD SHORTED TO GROUND.  MOC CONSUL	TED WITH BOEING ENGINEERING AND THE WIRE WAS TEMPORARILY REPAIRED IAW THE BOEING STANDARD WIRING PRACTICES MANUAL WITH A	 10 DAY CONSTRAINT.  THE WIRE IS TO BE PERMANENTLY REPAIRED THIS WEEKEND.  THIS DEFECT HAS ALSO BEEN SUBMITTED TO THE BO	EING FSE AS THIS IS AN IN SERVICE ISSUE.		2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006062600093	20060626	00093	NE  	2006	6	26	CA060324003      	2	20060324	G	7310	0301007710	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUEL SYS	BROKEN          	W				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA											A/C WOULD NOT START, FOUND LINE WAS BROKEN.  IF THE CONDITIONS WERE RIGHT A FIRE MAY HAVE OCCURRED ON START UP.  TURBOME	CA HAS REPLACEMENT LINE WITH AN INCREASED DIAMETER AND WALL THICKNESS.  THE SB STATES, IN ORDER TO MINIMIZE THE POSSIBIL	ITY OF THE PIPE RUPTURE DUE TO DISTORTION SB 292 73 0339 UPDATE 1.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062600094	20060626	00094	NE  	2006	6	26	CA060324004      	2	20060324	G	7310	0301007720	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					INJECTOR	BROKEN          	W				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA											THE PILOT WAS TRYING TO START THE ENGINE, IT WOULD NOT START.  UPON INSPECTION OF THE STARTING PROBLEM IT WAS FOUND THE 	THIS LINE WAS BROKEN.  TURBO MECA HAVE A REPLACEMENT LINE WITH AN INCREASED DIAMETER AND WALL THICKNESS.  THE SB IS RECO	MMENDED/OPTIONAL. SB292 73 0339 UPDATE 1.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062600096	20060626	00096	EU  	2006	6	26	CA060326001      	1	20060325	G	6720	704A34130184	CONTROL CABLE   			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											PILOT REPORTED T/R PEDALS FELT STICKY.  CABLE WAS INVESTIGATED AND FOUND STIFF AND ROUGH.  CABLE WAS CHANGED PROBLEM WAS	 SOLVED.  INSIDE CABLE MOISTURE AND CORROSION WERE FOUND.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006071000108	20060710	00108	NM  	2006	7	10	CA060327002      	1	20060323	G	2780	745583	SHAFT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											AFTER LANDING, THE PILOT WAS UNABLE TO RETRACT THE FLAPS. UPON INVESTIGATION BY MAINTENANCE, THE FLAP SECONDARY DRIVE CA	BLE WAS FOUND SIEZED (THE INNER CABLE HAD BROKEN STRANDS WHICH JAMMED THE CABLE).  THE SECONDARY DRIVE CABLE WAS REPLACE	D AND THE AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062600097	20060626	00097	EU  	2006	6	26	CA060327003      	1	20060324	G	3411		LINE            			SOCATA	TBM   	TBM700      	8682000	EU  										PITOT/STATIC SY	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING BIANNUAL ALTIMETER SYSTEM TEST AND INSPECTION PILOTS ALTIMETER AND VSI RESPONDED ERRATICALLY TO INCREASING/DECREA	SING PRESSURE.  WATER DROPLETS WERE FOUND IS PILOTS STATIC SYSTEM BETWEEN NR 1 LEFT STATIC VENT AND Y CONNECTION TO RIGH	T VENT.				1	L	7	1 	3T			RT	A60EU   					 
2006071100165	20060711	00165	CE  	2006	7	11	CA060327004      	1	20060321	G	3220	07436051	TORQUE LINK     			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3826 								(CAN) NOSE GEAR UPPER TORQUE LINK WAS FOUND CRACKED INSIDE UPPER CORNER ON THE LT SIDE.  FORGING NR 0543034-497, 2014 KA	E-2A  (TC NR20060327004)					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P880	 
2006071900023	20060719	00023	CE  	2006	7	19	CA060327005      	1	20060324	G	3244	650C063	TIRE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG	CUT             	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			103  								(CAN) LT MAIN TIRE POSSIBLE SIDEWALL PUNCTURE DURING LANDING ROLLOUT. NO OTHER DISCREPANCIES NOTED OTHER THAN DAMAGED SI	DEWALL. NO DAMAGE TO AIRCRAFT OR OTHER COMPONENTS NOTED. (TC NR 20060327005)					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
2006071900024	20060719	00024	NE  	2006	7	19	CA060328001      	2	20060320	G	7322	0319878030	FCU             			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			2891 	68   				34096			(CAN) DURING ROUTINE DAILY INSPECTION AFTER A FLIGHT, FUEL LEAK NOTICED AT THE MAIN FUEL OUTLET FITTING (NIPPLE) ON THE 	FCU. SUSPECT O-RING P/N 9794099203 DEFECTIVE. (TC NR 20060328001)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2006071900025	20060719	00025	SO  	2006	7	19	CA060328002      	1	20060326	G	5514	1101411073004	CHANNEL         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPLETION OF A 6C INSP, MAINT FOUND A CRACK IN THE FWD LT HORIZONTAL STABILIZER MACHINED CHANNEL. THIS PAR	TICULAR INSP WAS COMPLETED DUE TO AD 83-03-03R6 REQUESTING AN INITIAL INSP AND MODIFICATION OF ATTACHMENT AREA. INITIAL 	REQUIREMENTS WERE PREVIOUSLY COMPLETED BY A PREVIOUS OPERATOR.  A REPEAT INSP IS NOW CALLED UP DURING 6C INSP AS REQUIRE	D BY AD.  CRACK WAS FOUND IN NEW MODEL OF MACHINED CHANNEL PART NR 110-4A-1411-07-16 THAT WAS PREVIOUSLY REPLACED. A VIS	UAL INSP OF ALL SURROUNDING AREA WAS COMPLETED AND AN EDDY CURRENT INSPECTION OF REMAINING FITTING WAS COMPLETED AND NO 	OTHER DISCREPANCY WAS FOUND.  CHANNEL WILL BE REPLACED AND AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20060328002)	1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006071900026	20060719	00026	EU  	2006	7	19	CA060328004      	1	20060327	G	3260	C245890002	UPLOCK SWITCH   			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DEPARTING, THE CREW OBSERVED AN UNSAFE(RED) WARNING ON NR 2 MAIN LANDING GEAR AFTER RETRACTION WAS SELECTED. THE C	REW RETURNED TO POINT OF DEPARTURE AND AND CARRIED OUT A NORMAL CONFIGURATION LANDING. MAINTENANCE DETERMINED THAT THE U	NSAFE CONDITION INDICATION WAS FALSE DUE TO A FAILED UPLOCK BOX. THE NR 2 MAIN GEAR UPLOCK BOX WAS REPLACED, TESTED SERV	ICEABLE AND AIRCRAFT RETURNED TO SERVICE.(TC NR 20060328004)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006071900027	20060719	00027	SO  	2006	7	19	CA060328005      	1	20060321	G	7920	PH481101	SEAL            	CHAMPION    		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	OIL FILTER	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48   								(CAN) INTERNAL SEAL BETWEEN CARTRIDGE AND BASE PLATE COLLAPSED INTO CENTER OF FILTER.   (TC NR 20060328005)						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006071900028	20060719	00028	EU  	2006	7	19	CA060328006      	1	20060323	G	5610	1379377C406	WINDOW          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT THE COPILOT WINDOW CRACKED, NO SOUND WAS HEARD. THE CAPTAIN IMMEDIATELY INITIATED DESCENT TO A SAFER	 LEVEL AND CONTINUED TO LAND.  THE WINDOW WAS FOUND TO BE CRACKED ON THE EXTERNAL LAYER WITH NO OBVIOUS INITIATING POINT	 AND REMOVED FROM THE AIRCRAFT.   (TC NR 20060328006)				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2006071900029	20060719	00029	NM  	2006	7	19	CA060328007      	1	20060328	G	3350	D71701100	BATTERY PACK    			BOEING	737   	737824      	13844BZ	NM  										EMERGENCY LIGHT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) PERFORMING EMERGENCY LIGHT AT L1,R1 AND R2 DOORS LIGHTS FAILED TO ILLUMINATE AT TEST THIS IS PART OF SERVICE CHECK	  BATTERY PACK REPLACED (TC NR 20060328007)					2	L	7	2 	4F			RT	A16WE   					 
2006062600100	20060626	00100	NE  	2006	6	26	CA060328008      	2	20060327	G	7314	D7431	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			599  								AS PILOT WAS READY FOR TAKEOFF, THE AUX PUMP LIGHT ILLUMINATED AND THE BREAKER POPPED.  PILOT LANDED AND NOTIFIED MAINTE	NANCE.  REPLACED THE PUMP ASSY.  THE PUMP ASSY ALSO HAS A WELDON PUMP P/N B8187-B S/N 105188.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062600102	20060626	00102	CE  	2006	6	26	CA060329001      	1	20060321	G	3230		MOTOR           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											AFTER TAKEOFF, EN ROUTE TO DESTINATION, GEAR WARNING LIGHT CAME ON.  PILOT TRIED EXTENDING THE GEAR AND NO EXTENSION WAS	 NOTED.  AIRCRAFT RETURNED TO BASE AND GEAR WAS EXTENDED USING MANUAL EXTENSION.  AIRCRAFT PUT ON LOCKS.  GEAR MOTOR CIR	CUIT BREAKER WAS FOUND POPPED AND ACCUMULATOR WAS FOUND TO BE LOW IN PRESSURE.  CIRCUIT BREAKER WAS RESET AND ACCUMULATO	R CHARGED TO PROPER PRESSURE.  GEAR SWUNG SEVERAL TIMES WITH NO ABNORMAL RESULTS.  AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006071900030	20060719	00030	NE  	2006	7	19	CA060329002      	2	20060327	G	8530		CYLINDER HEAD   			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E	B	R	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      	CL	CLIMB          	1			CA				136  				2593			(CAN) PILOT REPORTED JUST AFTER T/O, HEARD A POP AND THE ENGINE LOST A BIT OF POWER WITH SLIGHT VIBRATION. JUST AFTER TH	IS HE COULD SMELL A BIT OF BURNED OIL SMELL. AIRCRAFT RETURNED TO POINT OF DEPARTURE. INSPECTION INTO PROBLEM FOUND THAT	 NR 7 CYLINDER HAD SEPARATED BETWEEN HEAD AND BARREL. CYLINDER HAD 136.2 HRS SINCE OVERHAUL. ULTRASONIC INSPECTION OF CY	LINDER IAW A/D 78-08-07 WAS CARRIED OUT AT OVERHAUL. CYLINDER ASSEMBLY WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE	 (TC NR 20060329002)		1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006071900042	20060719	00042	CE  	2006	7	19	CA060330001      	1	20060329	G	3233	12802091	PIN             	CESSNA      		CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	NLG ACTUATOR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			8274 			2459					(CAN) NO GEAR DOWN INDICATION UNTILL RECYCLED SEVERAL TIMES. INSPECTION REVEALED CRACKED DOWNLOCK PIN (REF SEB 95-20)AND	 WORN ACTUATOR BEARING END PIN HOLE. (TC NR 20060330001)					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2006062600108	20060626	00108		2006	6	26	CA060330002      	1	20060330	G	2824	AVZ4B11198	VALVE           																	FUEL SYSTEM	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											ELECTRIC MOTOR SECTION OF PUMP ASSY WAS FOUND DURING INSPECTION TO MISSING A "C" CLIP AND PLUG.  REPLACED WITH SERVICABL	E UNIT.																		 
2006072000320	20060720	00320	NM  	2006	7	20	CA060330003      	1	20060330	G	6330	500N3139	MOUNT           			DOUG  	600N  	600N        	3027377	NM  										GEARBOX	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACKS WERE FOUND IN THE MOUNT IS SIMILAR LOCATION ON 2 COMPANY AIRCRAFT. (TC NR 20060330003)						1	G	7	1 	3U			NC	H3WE    					 
2006071900054	20060719	00054	CE  	2006	7	19	CA060330004      	1	20060326	G	2751	7013348931	INDICATOR       			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					TE FLAPS	FAILED          	W				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA				1333 							(CAN) ON APPROACH, CREW NOTICED THAT AFTER FLAP WAS SELECTED LT FLAP INDICATION MOVED NORMALLY WHERE RT FLAP INDICATION 	REMAINS AT ZERO DEGREES POSITION. CREW DID NOT FEEL ANY FLAP ASSYMETRY. AC DID NOT REGISTER A FLAP ASSYMETRY, DID NOT PR	OVIDE A FLAP FAIL CAS MESSAGE. CREW NOTED THIS AS AN INDICATION PROBLEM ONLY. MAINT TROUBLESHOT SYS AND CONFIRMED IT TO 	BE AN INDICATION PROBLEM ONLY, REASON WHY AC DID NOT PROVIDE A FLAP FAIL CAS MESSAGE. FURTHER TROUBLESHOOTING DISCOVER I	NDICATION PROBLEM TO BE CAUSED BY RT DATA ACQUISITION UNIT, PORTION OF FLAP POSITION ON CHANNEL (B) HAD FAILED  AT ZERO 	DEGREES POSITION.  A REPAIRED DAU WAS INSTALLED AND AC WAS RETURNED TO SERVICE. (TC NR 20060330004)	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006071900055	20060719	00055	EA  	2006	7	19	CA060330005      	1	20060330	G	7120	C6WM151928	MOUNT           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								18503587			(CAN) ENGINE MOUNT PLATE INCORRECTLY MANUFACTURED. THE HOLE FOR THE ENGINE MOUNT BOLT (MS21250-06042) IS NOT DRILLED AT 	THE CORRECT ANGLE. THE HOLE FROM THE MOUNT PLATE TO THE FITTING, ENGINE MOUNT P/N C6WM 1517-28 DOES NOT LINE UP.  MARKIN	GS ON THE PLATE ARE, P/N C6WM 1519-28, W/O14947/1 AND AUG 12/04.  (TC NR 20060330005)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006071900056	20060719	00056	EA  	2006	7	19	CA060330006      	1	20060330	G	2810	2156400	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1318 								(CAN) DURING INSPECTION FOR A FUEL LEAK OF THE RT WING. ALL CELLS WERE REMOVED FOR LEAK CHECK. CELLS  NR 1,2,4,6 AND 7 W	ERE FOUND LEAKING. CELLS WILL BE REPLACED. (TC NR 20060330006)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006071900057	20060719	00057	NM  	2006	7	19	CA060330007      	1	20060330	G	2997	SM601BA20A1	CONTACTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD CIRCUIT BRKR	STUCK           	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF THE PILOTS WERE COMPLETING THE AFTER TAKE-OFF CHECKS AND THEY NOTICED THAT THE NR 2 HYDRAULIC STAND	BY POWER UNIT WAS INDICATING PRESSURE EVEN WITH THE SPU SELECTED OFF. THE PILOTS ELECTED TO RETURN TO BASE FOR FURTHER I	NVESTIGATION. THE MAINTENACE STAFF FOUND THAT THE HYDRAULIC REMOTE CIRCUIT BREAKER CONTACTOR WAS STUCK IN THE ON POSITIO	N. CONTACTOR WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060330007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062600109	20060626	00109	WP  	2006	6	26	CA060331001      	1	20060330	G	6510	C0411	BEARING         	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					T/ROTOR DRIVE	SPUN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			198  			0678					DURING INSPECTION IT WAS NOTED THAT THE T/R D/S ASSY BEARING HAD SPUN.  THE INNER RACE ROTATED ON SHAFT ROTATED 1/4 TURN	 AND WITNESSED BY TORQUE SEAL.  DRIVESHAFT REPLACED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006071900058	20060719	00058	NE  	2006	7	19	CA060331002      	2	20060329	G	7313	0301007720	INJECTOR        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA								10205			(CAN) UPON LANDING AT A MOUNTAIN TOP (6000 FT) ASL. PILOT UNABLE TO COMPLETE ENGINE START. AFTER ARRIVAL OF AME IS HAS B	EEN DISCOVERED THAT RT FUEL INJECTOR PIPE WAS CRACKED AROUND ENTIRE CIRCUMFERENCE AT THE FLARE END.  PIPE SUBSEQUENTLY R	EPLACED WITH SERVICEABLE.  A/C RETURNED TO SERVICE.  (TC NR 20060331002)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062600111	20060626	00111		2006	6	26	CA060331003      	4	20060331	G	2562		G SWITCH        	POINTER     	PS400010    	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ELT	WEAK            	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						409070					ELT WAS BEING RECERTIFIED AND TESTED IN-HOUSE.  THE G SWITCH WAS FOUND WEAK.  ELT WAS RETURNED TO POINTER FOR FURTHER RE	PAIR.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006071900059	20060719	00059		2006	7	19	CA060331004      	2	20060331	G	7261	CH481101	OIL FILTER      																	ENGINE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UPON RECEIPT OF NEW OIL FILTER, THREADS WERE FOUND TO BE GALLED. (TC NR 20060331004)																			 
2006062600112	20060626	00112	SW  	2006	6	26	CA060331005      	1	20060327	G	3246		SADDLE          			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					SKID TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CRACK WAS FOUND ON SKID TUBE AT FORWARD CROSSTUBE MOUNTING SADDLE.  THERE WAS NO REPORT OF A HARD LANDING WITH THIS AIRC	RAFT AT THIS TIME.  TIMES FOR THESE SKID TUBES WERE NOT AVAILABLE.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006062600113	20060626	00113	CE  	2006	6	26	CA060402001      	1	20060327	G	5532	11564000098	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					VERTICLE STAB TE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TRAILING EDGE SKIN, RT SIDE CRACKED APPROX 1 INCH AT MAIN SPAR STATION.  CRACK STARTS AT ONE JO BOLT FASTENER LOCATION A	ND GOES DOWN TO EDGE OF SKIN.  MOST OF THE CRACK WAS HIDDEN BY THE LOWER RIGHT STABILIZER ATTACH/FAIRING ANGLE P/N 97-44	0025-14.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006071900060	20060719	00060	EA  	2006	7	19	CA060403001      	1	20060328	G	5610	NP13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENROUTE THE OUTER PLY PILOT WINDSHIELD SHATTERED AND IMPAIRED CAPT'S VIEW . A/C DIVERTED  WINDSHIELD REPLACED, AIR	CRAFT DECLARED SERVICEABLE. (TC NR 20060403001)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006062600114	20060626	00114	SW  	2006	6	26	CA060403002      	1	20060330	G	6210	STC	WIRE STRIKE     			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  						DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			539  								DURING COOL DOWN AT IDLE RPM CYCLIC CONTROL STICK WAS MOVED FORWARD AND MAIN ROTOR BLADE (QTY 2) CONTACTED THE UPPER CUT	TER OF THE WIRE STIKE PROTECTION SYSTEM.					1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2006071900061	20060719	00061	EA  	2006	7	19	CA060403003      	1	20060219	G	2133	1036322	OUTFLOW VALVE   			CNDAIR	CL604 	CL604       	1900301	EA  										CABIN PRESSURE	FAILED          	W				O				OTHER                   				G			MULTIPLE FAILURE          			CL	CLIMB          	1			CA											(CAN) ON A FLIGHT DURING CLIMB OUT AT FL 110 AND CLEARED FOR FL150 A (CABIN ALT) EICAS MESSAGE POSTED. THE CREW OBSERVED	 THAT CABIN ALTITUDE WAS CLIMBING IN AN UNUSUAL HIGH RATE. WHEN CABIN ALTITUDE REACHED 10000 FEET CREW DECIDED TO CONTRO	L IN MANUAL MODE. NO RESPONSED WAS NOTED. NOW GOR A MASTER WARNING DUE TO CABIN ALTITUDE HIGHER THAN 10000 FEET AND O2 M	ASKS DROPPED AND CREW PUT THEIR OWN MASKS ON. CREW DECIDED TO LEVEL OFF AT 15000 FEET AND FERRY FLOWN THE AIRCRAFT AT LO	W LEVEL. ALSO OUTFLOW VALVE P/N 103664-2 WAS REPLACED AS BOTH VALVES FAILED THE TO PASS THE AMM TESTING. (TC NR 20060403	003)	2	L	7	2 	4F			RT	A21EA   					 
2006071900062	20060719	00062	EA  	2006	7	19	CA060403004      	1	20060305	G	2820	601R626765	SHROUD          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COLLECTOR BOX	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A POST HEAVY CHECK INSPECTION IT WAS DISCOVERED THAT A FUEL LEAK COMING OFF THE FUSELAGE DRAINS AT STATION 	559.00 AND 574.00. AFTER INVESTIGATION, IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE FUEL COLLECTOR BOX SHRO	UD (P/N 601R62676-5). A BRACKET INSIDE THE COLLECTOR BOX IS BROKEN AND CHAFED ON THE LT ENGINE FEED LINE. THE AIRCRAFT I	S CURRENTLY DOWN AND AWAITING PARTS (TC NR 20060403004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071900063	20060719	00063	NE  	2006	7	19	CA060403005      	2	20060302	G	7200		ENGINE          								PWA   	PT6   	PT6A67R     	52043	NE  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								106004			(CAN) IN FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND  THE ENGINE WAS SHUTDOWN.  SUBSEQUENT INSPECTION RE	VEALED METALIC DEBRIS IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE EXTABLISHED. (TC 	NR 20060403005)									4	T			E26NE				 
2006071900064	20060719	00064	NE  	2006	7	19	CA060403006      	2	20060305	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) INFLIGHT THE ENGINE EMITTED A LOUD NOISE, INTERTURBINE TEMPERATURE INCREASED AND THE ENGINE FLAMED OUT.  A DEAD-ST	ICK LANDING WAS CARRIED OUT RESULTING IN SIGNIFICANT AIRCRAFT DAMAGE.  MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONC	E ESTABLISHED. (TC NR 20060403006)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006061300250	20060613	00250	NE  	2006	6	13	CA060403007      	2	20060220	G	7314		PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					FUEL SYS	UNSERVICEABLE   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											ON DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN.  THE FUEL CONTROL UNIT AND FUEL PUMP WERE SUBSEQUENTLY REPLA	CED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060600226	20060606	00226	NE  	2006	6	6	CA060403008      	2	20060112	G	7314		SPLINE          			BEECH 	45    	T34C        	1152015	CE  	PWA   	PT6   	PT6A25      	52043	NE  					FUEL PUMP	WORN            	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION WHICH RESULTED IN THE AIRCRAFT CRASHING.  INVESTIGATION DETERMINED	 THE FUEL PUMP SPLINE TO BE SUFFICIENTLY WORN TO RESULT IN THE LOSS OF ENGINE FUEL FLOW.					1	L	7	1 	3T	3	T		A26CE   	E4EA				 
2006060700252	20060607	00252	NE  	2006	6	7	CA060403009      	2	20060309	G	7200		ENGINE          	PWC         	PT6A114A    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	POWER LOSS      	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						PC0624					DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED LOSS OF POWER.  THE AIRCRAFT CRASHED ON ATTEMPTING TO RETURN TO POIN	T OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006060700253	20060607	00253	GL  	2006	6	7	CA060403010      	2	20060326	G	7230		TUBE            	RROYCE      	6896024CP   	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	BROKEN          	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			C	E	R	F.O.D.                    	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	TO	TAKEOFF        	1			CA											PILOT HEARD A BIG "BANG" FROM ENGINE AND LOST POWER.  THE PILOT LANDED IN THE BUSH WITHOUT DAMAGING THE A/C.  AFTER THE 	INSPECTION OF THE COMPRESSOR BY THE MECHANIC, FOUND THE COMPRESSOR IN BAD SHAPE, CONFIRMED FOD WAS IN TO THE COMPRESSOR.	  MECHANIC CHECKED AND FOUND SOME LITTLE METAL PIECES IN THE INTAKE BEHIND THE INLET SCREEN, FINALLY FOUND THE INJECTOR 	TUBE BROKEN ON THE WELDING POINT.			1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006060700254	20060607	00254	NE  	2006	6	7	CA060403011      	2	20060305	G	7200		ENGINE          	PWC         	PT6A114A    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	POWER LOSS      	W				A				UNSCHED LANDING         				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		NR	NOT REPORTED   	1			CA						PC0717					THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY AN UNCOMMANDED INFLIGHT SHUTDOWN.  THE AIRCRAFT DEPARTED THE RUNWAY ON LANDI	NG RESULTING IN SIGNIFICANT AIRFRAME DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMI	NED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006060700255	20060607	00255	EA  	2006	6	7	CA060403012      	2	20060310	G	7532		BLEED VALVE     	PWC         	310082903   	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					COMPRESSOR	FAULTY          	W				E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CA											DURING APPROACH, THE ENGINE EMITTED AN UNUSUAL NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUT DO	WN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FAULTY COMPRESSOR BLEED VALVE.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006060700256	20060607	00256	NE  	2006	6	7	CA060403013      	2	20060315	G	7200		ENGINE          	PWC         	PT6A42      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					ENGINE	POWER LOSS      	W				A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA						94570					(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT DOWN.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC	 WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060700257	20060607	00257	GL  	2006	6	7	CA060403014      	3	20060316	G	6110		SEAL            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	LEAKING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA											DURING FLIGHT, AN ENGINE OIL LEAK WAS OBSERVED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A 	LEAKING PROPELLER SHAFT SEAL AND A LOOSE BETA VALVE RETAINING NUT.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006060700258	20060607	00258	NE  	2006	6	7	CA060403015      	2	20060316	G	7320		FUEL SYS        	PWC         	PT6A42      	BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					ENGINE	FLUCTUATES      	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			DE	DESCENT        	1			CA						94383					DURING INITIAL DESCENT, ENGINE FUEL FLOW WAS OBSERVED TO FLUCTUATE.  THROTTLE INPUT RESULTED IN EXCESSIVE INTERTURBINE T	EMPERATURE INCREASE AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVIS	E OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006061900179	20060619	00179	NE  	2006	6	19	CA060403016      	2	20060323	G	7200		ENGINE          			GULSTM	200   	200         	4500308	NM  	PWA   	306   	PW306B      	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								CC0095			(CAN) DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUTDOWN	 IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE EXHAUST.  MFG WILL INVESTIGATE THE EVENT AND ADVI	SE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060403016)				2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2006060700259	20060607	00259	NE  	2006	6	7	CA060403017      	2	20060321	G	7200		ENGINE          	PWC         	PW123D      	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE	POWER LOSS      	W				A				UNSCHED LANDING         				E	J	X	VIBRATION/BUFFET          	WARNING INDICATION        	ENGINE FLAMEOUT           	CR	CRUISE         	1			CA						AT0009					DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY A LOW ENGINE OIL PRESSURE INDICATION AND AN UNCOMMANDED ENGIN	E SHUT DOWN.  SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION AND A SEIZED COMPRESSOR.  P&WC WILL MONITOR INVESTIGATI	ON OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060700260	20060607	00260	EU  	2006	6	7	CA060403018      	1	20060329	G	7931		OIL SYSTEM      	PWC         	PW127E      	AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						127187					DURING CLIMB, ENGINE OIL PRESSURE WAS OBSERVED TO FLUCTUATE FOLLOWED BY A LOSS OF OIL PRESSURE.  THE ENGINE WAS SHUT DOW	N IN FLIGHT.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006060800222	20060608	00222	EA  	2006	6	8	CA060403019      	2	20060429	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  						FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS ON THE EN	GINE CHIP DETECTOR.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006060800285	20060608	00285	EA  	2006	6	8	CA060403020      	1	20060402	G	2910	MS21907D6	ELBOW           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYSTEM	SPLIT           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											45 DEGREE UNIVERSAL ELBOW FITTING FOUND SPLIT WITH HYDRAULIC FLUID LEAKAGE ON THE NR 2 HYDRAULIC SYSTEM, IPC 29-11-00, F	IG 20, VIEW K, ITEM NR 45.  FITTING REPLACED WITH THE SYSTEM CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061200343	20060612	00343	EA  	2006	6	12	CA060403021      	1	20060403	G	3246	AJ78241	TUBE            			DHAV  	DHC3  	DHC3        	2800202	EA  										MLG	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AFT LT STRUT TUBE CRACKED PN AJ78-24-1.						1	H	7	1 	3R				A815    					 
2006061200345	20060612	00345	EA  	2006	6	12	CA060403022      	1	20060403	G	3246	J78221	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  										MLG	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											AFT LT STRUT CLEVIS CRACKED.						1	H	7	1 	3R				A815    					 
2006061200346	20060612	00346	EA  	2006	6	12	CA060403023      	1	20060403	G	3246	AJ78211	CLEVIS          			DHAV  	DHC3  	DHC3        	2800202	EA  										MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											AFT RT SPREADER CLEVIS CRACKED.						1	H	7	1 	3R				A815    					 
2006061200348	20060612	00348	EA  	2006	6	12	CA060403024      	1	20060403	G	3246	J781112	PLATE           			DHAV  	DHC3  	DHC3        	2800202	EA  										FLOAT	CORRODED        	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											SEVERE CORROSION ON FWD AND AFT FLOAT BUILD-UP ESPECIALLY LOWER SURFACES OF P/N J78-11, J78-12.						1	H	7	1 	3R				A815    					 
2006061200349	20060612	00349	EA  	2006	6	12	CA060403025      	1	20060403	G	3246	J7819	CLEVIS          			DHAV  	DHC3  	DHC3        	2800202	EA  											DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											J78-19 CLEVIS, RT AND LT FRONT STRUT LOWER.  HOLE IN FITTING FILLED WITH ROD, HOLE MOVED AND LIKELY IN A NON-COMPLIANT M	ANNER DURING MFG.					1	H	7	1 	3R				A815    					 
2006062600115	20060626	00115	WP  	2006	6	26	CA060403026      	1	20060403	G	2910	D4523	B-NUT           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			398  								HYDRAULIC FLUID LEAKING FROM FITTING.  BACKUP NUT ON FITTING FOUND UNDER TORQUED.  FACTORY TORQUE SEAL AND PAL NUT WERE 	FOUND UNDISTURBED.  BACKUP NUT RETORQUED AND NO FURTHER DEFECTS FOUND.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062600117	20060626	00117	NE  	2006	6	26	CA060403028      	2	20060401	G	7314	7436024	FUEL CONTROL    			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA								666126			AT CRUISE ALTITUDE(FL350), THE NR 2 ENGINE WAS SURGING AND DROPPING POWER. ENGINE ANTI ICE AND FUEL HEAT CHECK C/W, NO C	HANGE, ENGINE FAILURE- SHUTDOWN CHECK LIST C/W, NR 2 ENGINE SHUTDOWN INFLIGHT.  MAINTENANCE INSPECTED AIRCRAFT IAW PW MM	 72-00-00 PAGE 531.  ENGINE FUEL PUMP/FCU PACKAGE REPLACED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006061200350	20060612	00350	EA  	2006	6	12	CA060403029      	1	20060403	G	5210	C3FS24950	DOOR            			DHAV  	DHC3  	DHC3        	2800202	EA  										FUSELAGE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											THE LT STRUT, FUSELAGE DOOR WAS CORRODED THROUGH.  SURFACE RUST PITTING WAS NOTICED, AND A PUNCH WAS DRIVEN THROUGH THE 	TUBE WITH MINIMAL EFFORT SEVERAL TIMES.  RT STRUT EXHIBITED SEVERE PITTING ALSO, AND WAS ALSO REMOVED FOR REPLACEMENT.  	LOGBOOKS INDICATED THAT THE STRUTS WERE INSPECTED AUG 20, 2001 IAW S/B 3/29 BY AMO 78-92.				1	H	7	1 	3R				A815    					 
2006061200351	20060612	00351	CE  	2006	6	12	CA060404001      	1	20060403	G	3411	MILH55934	HOSE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT PITOT/STATIC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1975 								DURING A SCHEDULED INSPECTION, THE AVIONICS TECHNICIAN VISUALLY DISCOVERED SEVERAL HOSES CRACKED IN THE RT PITOT/STATIC 	CIRCUIT.  HOSES WERE FOUND CRACKED AND LEAKING ON THE LT PITOT/STATIC CIRCUIT APPROXIMATELY 1 MONTH AGO.  THESE PARTICUL	AR HOSES WERE INSTALLED FOR RVSM CONVERSION.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006061200352	20060612	00352	EU  	2006	6	12	CA060404002      	1	20060329	G	2800	L95F50603	DISK            			AIRBUS	A321  	A321211     	3930370	EU  										CENTER TANK	RUPTURED        	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											FUEL AUTO TRANSFER FAULT ECAM IN CLIMB.  SELECTED MAN AS PER ECAM.  REALIZED NR 1 TANK WAS FEEDING BOTH ENG AND UNBALANC	E INCREASED.  UNABLE TO GET FUEL FROM CENTER OR RIGHT TANK.  RETURNED TO YYZ.   RECTIFICATION: TSM TASK 28-12-00-810-801	 CARRIED OUT.  OVERPRESSURE PROTECTOR DISK 96QM RUPTURED.  REMOVED TASK 28-12-41-000-003 AND INSTALLED TASK 28-12-41-400	-003 MM TASK 28-25-00-869-001 FUEL TRANSFER AND PANEL LEAK CHECK CARRIED OUT SERVICEABLE.			2	L	7	2 	4F			RT	A28NM   					 
2006061300045	20060613	00045		2006	6	13	CA060404003      	4	20060329	G	2330	845438421	VIDEO DISPLAY   			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					CABIN	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											4H VIDEO MACHINE GOT REALLY HOT AND SMELLED BURNED AT THE END OF FLIGHT.  THICK WHITE SMOKE CAME FROM PTV.  FOUND PTV OP	ERATION SERV.  FOUND SEAT PWR SUPPLY U/S AND ODOR OF SMOKE.  DEACTIVATED BY PULLING AND COLLERING C/B.					2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2006061300170	20060613	00170	NM  	2006	6	13	CA060404004      	1	20060314	G	3240	2445901	DISC            	BFGOODRICH  		DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	RT MLG BRAKE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				435  		0279					DURING BRAKE ASSY OVERHAUL THE TECHNICIAN DISCOVERED THE ROTATING DISC WAS BADLY DAMAGED.  AFTER FURTHER INVESTIGATION, 	IT WAS FOUND THAT THE KEYWAYS ON THE WHEEL ASSEMBLY WERE MISALIGNED ON THE BRAKE DISC DURING INSTALLATION.  THE BRAKE AS	SY WAS INSPECTED DURING OVERHAUL WITH NO DAMAGE FOUND ON IT.  THE WHEEL ASSY WAS ALSO REPLACED AND SENT FOR NDT ALSO WIT	H NO DAMAGE FOUND ON IT.  THE ONLY ITEM THAT WAS REPLACED ON THE WHEEL ASSY WERE THE KEYWAYS P/N 170-209-2.  THE ROTATIN	G DISC P/N 244-590-1 WAS REPLACED AND AIRCRAFT FOUND SERVICEABLE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006062600118	20060626	00118	SO  	2006	6	26	CA060404005      	1	20060403	G	2497		WIRE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DC REGULATOR	BROKEN          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											IN CRUISE, PILOT NOTICED THAT THE RIGHT GENERATOR ANNUNCIATOR WAS ON AND THERE WAS NO INDICATION ON THE RIGHT AMMETER.  	THE GENERATOR WOULD NOT COME ONLINE AND THE GENERATOR WAS SWITCHED OFF.  THERE WAS NO FURTHER EVENTS AND THE AIRCRAFT LA	NDED WITHOUT INCIDENT.  AFTER EXTENSIVE TROUBLESHOOTING, A BROKEN WIRE WAS DISCOVERED OFF THE RIGHT OVERLOAD SENSOR.  TH	E WIRE WAS REPAIRED AND SYSTEM TESTED SERVICEABLE.			1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2006061300171	20060613	00171	EA  	2006	6	13	CA060404006      	1	20060323	G	5551	600230681	BUSHING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HORIZONTAL STAB	WORN            	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			24789	24789							ON DEPARTURE (200 KTS GEAR UP FLAPS 0), A LOW FREQUENCY VIBRATION WAS FELT THROUGH THE AIRCRAFT, BOTH FLIGHT DECK AND CA	BIN.  VIBRATION WAS NOTICEABLE ENOUGH TO SHAKE SEATS SIDE TO SIDE, ENGINE FAN VIBRATION 0.2 AND 0.5, SMOOTH AIR FLIGHT C	ONDITIONS.  CHECKED COMPLETE AIRCRAFT AND FOUND ALL FOUR HORIZONTAL STABILIZER BUSHINGS (WHICH HOLD STAB ON) SLIGHTLY WO	RN.  BUSHING REPLACED AS PER SB 601R-55-007 PARTS A & B ONLY.  OVERSIZE BUSHINGS NOT REQUIRED IAW SB, STANDARD BUSHINGS 	INSTALLED.  AIRCRAFT TEST FLOWN AND COULD NOT REPRODUCE DEFECT.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062600119	20060626	00119	EA  	2006	6	26	CA060405002      	2	20060405	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ENGINE OIL METAL CONTAMINATION WAS REPORTED AND ENGINE SENT TO APPROVED ENGINE FACULITY.											4	T			E4EA				 
2006061300172	20060613	00172	WP  	2006	6	13	CA060405003      	2	20060316	G	7261	B441172	ADAPTER         			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	OIL FILTER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											DURING AN INSPECTION OF THE "OIL FILTER ADAPTER", IT WAS FOUND CRACKED IN TWO PLACES.  A SMALL OIL LEAK WAS EVIDENT.  TH	E PART WAS REPLACED.					1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2006061300173	20060613	00173	EA  	2006	6	13	CA060405004      	1	20060331	G	2730	HST22DU522	FASTENER        	BOMBDR      		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ELEVATOR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22971			RJ7095					HI-LIGHT FASTENERS (P/N HST22DU5-22) THAT ATTACHES LINKS (P/N 601R24056-55) TO FITTINGS (P/N 601R24056-51 ON LT AND FITT	INGS P/N 601R24056-49 ON THE RT ELEVATOR), FOUND WITH SHEARED HEADS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061300174	20060613	00174	EU  	2006	6	13	CA060405005      	1	20060213	G	2822	FRH280002	CANISTER        			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					BOOST PUMP	BROKEN          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA											FOB 5100 KG WING CROSSFEED SELECTED ON AS PER ATB 376.  FUEL IS 2500KG IN EACH TANK.  NO FUEL IN OUTERS AND TRIM.  ON SH	ORT FINAL "L TANK LOW FUEL" ON ECAMLTANK INDICATED 1200 KG AND RIGHT TANK 3500 KG REF SNAG 4205167.  FOUND RT WING NR 1 	MAIN BOOST PUMP CANNISTER DELIVERY ELBOW BROKEN AT FLANGE CONNECTION TO FUEL FEED MANIFOLD.  NEW ELBOW INSTALLED WITH NE	W SEALS.  OPERATION CHECK OF FEED SYSTEM COMPLETED.  CHECKS SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006061300175	20060613	00175	EU  	2006	6	13	CA060405006      	1	20060404	G	3340	9728787158	LAMP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NAV LIGHTS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			200  			25288300					THE A/C WAS MODIFIED PER LSTC 0-LSA06-001/D, INSTALLATION OF LED NAV LAMPS.  LAMPS WERE INTSTALLED PER DRAWINGS ECA-12-T	M-05-197.  SINCE THIS INSTALLATION THREE NAV LAMP FAILURES HAVE OCCURRED, ONE TIME ON THE RIGHT LED AND TWICE ON THE TAI	L NAV LED.  THE CAUSE IS UNKNOWN AT THIS TIME, HOWEVER PILATUS A/C HAS BEEN NOTIFIED OF THIS PROBLEM.  AT THE FIELD LEVE	L, MOISTURE IS SUSPECTED TO BE ENTERING THE UNIT'S THROUGH THE GROMMET WHERE THE WIRING GOES INTO THE LIGHT ASSY.  NO CO	NCRETE EVIDENCE AT THIS TIME AND WILL WAIT FOR THE MANUFACTURER TO RESPOND ON A FIX FOR THIS PROBLEM.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062600123	20060626	00123	NE  	2006	6	26	CA060405008      	2	20060119	G	7314	3022375	SEAL            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FCU/FUEL PUMP	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											AIRCRAFT DEPARTED AND ON CLIMB THE PILOT REPORTED A LOW OIL PRESSURE INDICATION ON THE LEFT HAND ENGINE.  THE AIRCRAFT R	ETURNED TO BASE.  A TECHNICIAN WAS CALLED IN, AND FOUND THAT THE FCU/FUEL PUMP DRIVE SEAL HAD MIGRATED, AND WAS LEAKING.	  A NEW SEAL P/N:3022375 AND SEAL CARRIER P/N:3004085 WERE INSTALLED.  ENGINE GROUND RUNS COMPLETED SATISFACTORY, AIRCRA	FT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006061300176	20060613	00176	SO  	2006	6	13	CA060405009      	2	20060405	G	8500		ENGINE          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  		MAKING METAL    	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			2640 								OIL SCREEN BYPASS LIGHT CAME ON INFLIGHT.  SCREEN INSPECTION FOUND FERROUS AND NON-FERROUS METAL IN QUANTITY.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2006061300177	20060613	00177	EA  	2006	6	13	CA060405010      	1	20060403	G	3240	0860163002	ACCUMULATOR     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					BRAKE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			20623								ON TAXI-OUT CREW REPORTED HEARING A LOUD POP AND THE RAMP PERSONNEL NOTIFIED THE CREW OF A HYDRAULIC LEAK FROM THE NOSE 	AREA AND THE AIRCRAFT RETURNED TO THE GATE. UPON FURTHER INVESTIGATION MAINTENANCE FOUND THE AFT END CAP ON THE BRAKE S	YSTEM HYDRAULIC ACCUMULATOR HAD FAILED. WHEN THE END CAP FAILED, IT BLEW THROUGH THE PRESSURE BULKHEAD INTO THE AVIONIC	S BAY CAUSING DAMAGE TO PITOT AND HYD LINES, BRAKING CONTROL RODS, WIRING AND SURROUNDING STRUCTURE.  ROUTE CAUSE OF THE	 FAILURE WILL BE PROVIDED ONE THE STRIP REPORT IS AVAILABLE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061300178	20060613	00178	EA  	2006	6	13	CA060405011      	1	20060331	G	4990	1603662	OIL COOLER      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										APU	LEAKING         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA			2819 	1528 							SHORTLY AFTER TAKEOFF, THE CREW REPORTED SMOKE IN THE CABIN AND RETURNED TO FIELD.  UPON LANDING, THE CREW DISCHARGE THE	 APU FIRE BOTTLE.  AFTER FURTHER TROUBLESHOOTING, THE SITUATION WAS DUPLICATED AND IT WAS REPORTED THAT THE APU OIL COOL	ER WAS CLOGGED.  REMOVED AND REPLACED OIL COOLER OPS CHECK GOOD.				2	L	7	2 	4F			RT	A21EA   					 
2006061300191	20060613	00191	EA  	2006	6	13	CA060405012      	1	20060326	G	5610	NP13992113	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			923  								ON CLIMB, THE PILOT WINDSHIELD CRACKED.  A/C RETURNED TO BLOCK.  THIS WAS A POST SB WINDSIELD.  WINDSHIELD WAS REMOVED A	ND REPLACED IN ACCORDANCE WITH AMM.					2	L	7	2 	4F			RT	A21EA   					 
2006061300281	20060613	00281		2006	6	13	CA060406001      	4	20060329	G	2311		RELAY           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					UHF SYS	DEFECTIVE       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											RELAY IS USED TO POWER THE RADIO-NAVIGATION SYSTEM.  ON A TRAINING FLIGHT INSTRUMENT APPROACH, SMOKE WAS NOTICED UNDER T	HE INSTRUMENT PANEL. THE APPROACH WAS ABORTED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE PERSONNEL CARRIED O	UT A DETAILED INSPECTION OF ALL THE RADIOS, INSTRUMENTS AND WIRING AND NOTHING WAS DISCOVERED, HOWEVER, WHEN THE 'AVIONI	CS MASTER' SWITCH WHICH FEEDS THE RADIOS WAS SELECTED 'ON' THE RADIOS BECAME UNSTABLE.  THE AVIONICS MASTER SWITCH WAS S	ELECTED OFF AND THE AIRCRAFT WAS DISPATCHED TO THE NEAREST AVIONIC FACILITY.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006062600124	20060626	00124	CE  	2006	6	26	CA060406002      	1	20060403	G	5520		TORQUE TUBE     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12859								DURING AN INSPECTION OF THE ELEVATOR TORQUE TUBE, THE PRIMARY ELEVATOR TORQUE TUBE WAS FOUND CORRODED.  THE PART WAS REP	LACED.					1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2006062600006	20060626	00006	CE  	2006	6	26	CA060406003      	1	20060330	G	3000	9755501115	DUCT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	HEAT DUCT	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A ROUTINE INSPECTION OF THE CABIN HEATING DUCTS THE HOT AIR DUCT ASSEMBLY P/N 97-555011-15 ITEM NR 22 IN PICTURE 	NR 1 WAS FOUND DISCONNECTED AT THE AFT END.  2 DUCTS FURTHER FWD WERE FOUND CRACKED ALLOWING THEM TO MOVE FWD AND ALLOWI	NG THIS DUCT TO DISCONNECT FROM ITEM NR 23.   ONCE THE DUCT HAD DISCONNECTED THE CABIN HEAT WAS FLOWING INTO THE FLOOR A	ND ONTO THE DE-ICE PRESSURE TUBE P/N 50-970101-143 ITEM 81 IN PICTURE NR 2.  THE HEAT ALLOWED A 15 INCH SECTION OF THE D	E-ICE TUBE DEFORM AND COLLAPSE RESTRICTING THE AIRFLOW TO THE TAIL PART OF THE DE-ICE SYSTEM. IT IS UNCLEAR WHETHER OR N	OT THE TAIL DE-ICE SYSTEM WAS SERVICEABLE.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2006121100372	20061211	00372	NM  	2006	12	11	CA060406006      	1	20060406	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 1016 S17L	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) BS 1016 AND STR17L WEB TO FLOOR ATTACH ANGLE CRACKED AND REPAIRED IAW EA AND SRM. (TC NR 20060406006)						2	L	7	2 	4F				A16WE   					 
2006121100374	20061211	00374	NM  	2006	12	11	CA060406007      	1	20060406	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 807	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CORROSION FOUND ON FWD FLANGE OF FLOORBEAM AT BS 807 RBL 56 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060406007)						2	L	7	2 	4F				A16WE   					 
2006121100377	20061211	00377	NM  	2006	12	11	CA060406008      	1	20060406	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 937 S24L	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CORROSION FOUND ON STR 24L AT BS 937 AND REPAIRED IAW CUSTOMER EA (TC NR 20060406008)						2	L	7	2 	4F				A16WE   					 
2006061300282	20060613	00282	EA  	2006	6	13	CA060406009      	1	20060403	G	5751	C3WA121	ARM             			DHAV  	DHC3  	DHC3        	2800202	EA  										AILERON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						FW198					MASS BALANCE ARM EXHIBITED LOOSENESS, AND WAS MOVING IN EXCESS OF 1/2 INCH AT THE END WHEN MOVED WITH MINIMAL HAND PRESS	URE.  AILERON DISASSEMBLED, FASTENERS REPLACED AND RETURNED TO SAFE AND FIT CONDITION IAW TYPE DESIGN.					1	H	7	1 	3R				A815    					 
2006061300283	20060613	00283	EA  	2006	6	13	CA060407001      	1	20060401	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			3089 								RT WINDSHIELD CRACKED AT FL180.  FOLLOWED BY "R WSHLD HEAT" MSG.  WINDSHIELD REPLACED IAW AMM 56-11-01.  WINDHIELD WAS A	 POST SERVICE BULLETIN.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061300284	20060613	00284	EA  	2006	6	13	CA060407002      	1	20060330	G	2710		CONTROL CABLE   			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					AILERONS	FROZEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			7286 								RIGHT AILERON JAMMED IN DOWN POSITION AFTER FLIGHT.  DURING LANDING GROUND ROLL AFTER CROSSWIND LANDING, STUCK CONTROL W	HEEL TO RIGHT AFTER RT AILERON INPUT.  RIGHT AILERON IN DOWN-POSITION.  LT AND RT AILERON CABLE CIRCUIT AND PULLEYS CONT	AMINATED WITH DEICING FLUID.  CLEANING PERFORMED.  OPERATIONAL TEST OF AILERON CONTROL SYSTEM ACC AMM 27-11-00-710-801-A	01, AMM 27-11-00-710-802-A01 PERFORMED.  DOUBLE INSPECTION PERFORMED.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006121100379	20061211	00379	EA  	2006	12	11	CA060407004      	1	20060403	G	5753		SKIN            			DHAV  	DHC3  	DHC3        	2800202	EA  										TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKIN REPAIRS NOT MADE IAW TYPE DESIGN, AND REPLACED. LEADING EDGE CORRODED, REPAIR MADE IN THE PAST USING INCORREC	T (BOGUS) STIFFENER MATERIAL, AND UNPRIMED BY INSTALLER LEAVING A CORRODED MESS.  RETURNED TO CONFORMANCE WITH TYPE DESI	GN. (TC NR 20060407004)				1	H	7	1 	3R				A815    					 
2006061300286	20060613	00286	EA  	2006	6	13	CA060407005      	1	20060405	G	5280	CC6701057113	HINGE FITTING   			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF34*       	 	NE  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2279 								LHS MAIN LANDING GEAR (MLG) P/N CC670-10520-965, S/N 15042 AND RT MLG DOOR P/N CC670-10520-966, S/N (SAME AS RHS) WERE C	RACKED AT THE AFT HINGE FITTING P/N CC670-10571-13 (SEE PIX.1) AND AT FORWARD HINGE FITTING P/N CC670-10570-5 (SEE PIX.2	).  LOOSE FASTERNERS WERE ALSO FOUND ON THE INBOARD AND OUTBOARD SIDE OF THE DOORS.				2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006061300287	20060613	00287	NE  	2006	6	13	CA060407006      	2	20060403	G	7314	510767	PUMP            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			506  								DURING DE-INHIBITING INSPECTION, A FUEL LEAK WAS DETECTED AT THE REAR OF THE FUEL PUMP ASSEMBLY.						1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2006061300289	20060613	00289	CE  	2006	6	13	CA060407007      	1	20060331	G	7714	9848025	TACHOMETER      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA				2328 							PILOTS FELT ENGINE WAS NOT PRODUCING FULL POWER RETURNED TO BASE.  ENGINE INSPECTED BY AN APPROVED AVIATION COMPANY, ALL	 ENGINE PARAMETERS WERE NORMAL.  HOWEVER, THEY DISCOVERED THE TACHOMETER WAS 100 RPM LOW AT FULL POWER. REPLACED TACHOME	TER.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006121100380	20061211	00380	GL  	2006	12	11	CA060407008      	1	20060331	G	5414	GS29701378	ACCESS PANEL    			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					FUSELAGE	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1509 								(CAN) THE AIRPLANE LANDED AT IT`S DESTINATION WHEN CREW EXITED THE PLANE, THEY NOTICED THAT THE AFT RT BELLY ACCESS PANE	L WAS MISSING.  NOTHING WAS NOTICED BY CREW WHILE IN FLIGHT (VIBRATIONS). (TC NR 20060407008)					2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2006121300073	20061213	00073		2006	12	13	CA060410001      	4	20060404	G	3417	ADS86	ADC             			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE FLIGHT CREW HAD SNAGGED THE NEUTRAL FUEL TANK FULL INDICATION AS NOT SHOWING FULL WHEN THE TANK WAS ACTUALLY F	ULL.  IN CONJUNCTION WITH THIS DEFECT THEY ALSO REPORTED THAT THE L/VMO TEST WAS NOT FUNCTIONING.  BOTH THESE DEFECTS WE	RE ACTIONED AND DURING THE TESTING OF THE L/VMO SYSTEM WE WERE DIRECTED BY THE AMM TO CONDUCT THE ADC SELF TEST IAW MM 3	4-10-17 ADS-86 TEST.  THE TEST PROCEDURE REQUIRES THAT DURING THE TEST THAT THE (MACH TRIM FAIL) LIGHT ILLUMINATES.  WHE	N THE TEST WAS ATTEMPTED, THIS LIGHT DID NOT ILLUMINATE.  BOTH THE AIR CREW MANUAL AND THE MM INDICATED THAT THE LIGHT W	ILL ILLUMINATE DURING THIS TEST.    THE MACH TRIM SYSTEM WAS FULLY TESTED AND WAS FOUND TO BE FUNCTIONING NORMALLY.  THE	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006121200073	20061212	00073	EU  	2006	12	12	CA060410002      	1	20060402	G	2750	532A000004	LIMITER         			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211*      	54555	NE  					TE FLAPS	TRIPPED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			16350	16350							(CAN) AIRCRAFT ARRIVED WITH THE FLIGHT CONTROL FLAPS FAULT ECAM MESSAGE ON FINAL WHEN SELECTING FLAPS 2IN. UNABLE TO EXT	END FLAPS FROM THE 0 POSITION. DURING TROUBLE SHOOTING, FOUND THE LT FLAP TORQUE LIMITER TRIPPED. TORQUE LIMITER REPLACE	D AND SYSTEM CHECKED SERVICEABLE.  (TC NR 20060410002)				2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006061300292	20060613	00292	EU  	2006	6	13	CA060410003      	1	20060321	G	7110	F50B258707	DOOR            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					S DUCT	DAMAGED         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			7300 								DURING TAKEOFF, THE NR 2 ENGINE "FAIL" LIGHT ILLUMINATED.  THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO THE RAM	P.  MAINTENANCE WAS CONTACTED AND UPON INVESTIGATION IT WAS DISCOVERED THAT NR 2 ENGINE S DUCT DOOR AFT LATCH HAD NOT BE	EN COMPLETELY ENGAGED WITH THE HOOK.  BOTH THE FRONT AND REAR LATCHES WERE RE-ENGAGED AND THE DOOR WAS CHECKED FOR PROPE	R SECURITY.  THE CREW RESUMED THE FLIGHT AND A NORMAL TAKEOFF WAS CONDUCTED.			2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2006061400099	20060614	00099	NE  	2006	6	14	CA060410004      	2	20060409	G	7314	02532330003	PUMP            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					RT ENGINE	UNSERVICEABLE   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			3946 	3946 				PCE94220			ON TAKEOFF, THE CREWS ROTATED AND HAD RT ENGINE POWER ROLL BACK.  CREWS FEATHERED AND SHUT DOWN THE ENGINE AND TURNED AR	OUND AND LANDED.  MAINTENANCE FOUND FUEL LEAKING FROM RT ENGINE DRIVEN HIGH PRESSURE FUEL PUMP P/N 025323-300-03.  PUMP 	ASSY REPLACED AND GROUND RUN, FLIGHT TEST SERVICEABLE.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006121200074	20061212	00074	EU  	2006	12	12	CA060410005      	1	20060406	G	2750		LIMITER         			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211*      	54555	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AT BEGINNING OF APPROACH, WHEN SELECTING SLATS/FLAPS DOWN, THE FLIGHT CONTROL FLAPS FAULT ECAM CAME ON. UNABLE TO 	EXTEND FLAPS FROM 0 POSITION. (REPEAT SNAG) DURING INVESTIGATION, FOUND THE LT TORQUE LIMITER AND THE LT ROTARY ACTUATOR	 TRIPPED. RESET CARRIED OUT. FOUND THE ROTARY ACTUATOR OIL CONTAMINATED WITH WATER.  ALL GEARBOXES AND ROTARY ACTUATORS 	RE-SERVICED WITH NEW OIL AND FLAPS SYSTEM TESTED SERVICEABLE. CAMPAIGN WAS INITIATED TO REPLACE THE OIL IN ALL GEARBOXES	 AND ROTARY ACTUATORS OF THE A-330 FLEET.  (TC NR 20060410005)		2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006061400101	20060614	00101		2006	6	14	CA060410006      	1	20060406	G	3213		CYLINDER        	MESSIER     							PWA   	PW120 	PW126A      	 	NE  	HAMSTD	2D	2D30        	NE  	MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23394			DRG721589					AT DISASSEMBLY BY FIRST AIR MAINTENANCE SERVICES (EASA APPROVAL NR 145-7030) THE OUTER CYLINDER WAS FOUND TO HAVE SEVERE	 CORROSION, VIRTUALLY PERFORATED AND ASSESSED AS INELIGIBLE FOR RETURN TO SERVICE.  THE RECORDS INDICATE THE LANDING GEA	R ASSEMBLY WAS REMOVED FROM AIRCRAFT SE-LGX (WEST AIR SWEEDEN).									4	T			E2ONE	5	C	P206	 
2006121200077	20061212	00077	SW  	2006	12	12	CA060410008      	1	20060402	G	2700	212010123101	ROD END         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					UNKNOWN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22   								(CAN) DURING A SCHEDULED INSPECTION OF THE ROD ENDS, IT WAS NOTED THAT THE BEARING WAS SHOWNING EVIDENCE OF MOVEMENT. BE	ARING WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060410008)					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006061400103	20060614	00103	CE  	2006	6	14	CA060410009      	1	20060401	G	5320	10541000057	CHANNEL         			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					NLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DISCOVERED DURING INSPECTION.  NLG ACTUATOR ATTACH BRACKET WAS FOUND CRACKED FROM THE EDGE OF THE BRACKET, THROUGH A LIG	HTENING HOLE AND OUT THE OTHER SIDE.  THE AREA IS DIFFICULT TO INSPECT.  THIS IS THE SUPPORT CHANNEL THAT THE UPPER END 	OF THE NLG ACTUATOR ATTACHES TO.				1	L	7	2 	3O	3	O		A29CE   	E286				 
2006061400105	20060614	00105		2006	6	14	CA060411001      	4	20060404	G	6122	HCB3TN3C	PROPELLER       			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA				352  							ON THE TAKEOFF ROLL, THE RT PROPELLER RPM WOULD ONLY GO TO 83% AND NOT BEYOND.  THE AIRCRAFT RETURNED TO THE HANGAR WHER	E MAINTENANCE FOUND THE RT PROPELLER TO BE AT FAULT.  THE PROPELLER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVIC	E.  THE PROPELLER HAS BEEN SENT TO A REPAIR FACILITY FOR FURTHER INVESTIGATION.				1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006061400106	20060614	00106	SO  	2006	6	14	CA060411002      	1	20060410	G	3240		BRAKE           			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					LEFT	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											LEFT SIDE BRAKE FAILED ON LANDING CAUSING RIGHT MAIN TIRE TO BLOW OUT.  NO DAMAGE TO A/C.						1	L	7	2 	4T	4	T		A23SO   	E4EA				 
2006101900196	20061019	00196	NM  	2006	10	19	CA060412001      	1	20060411	G	5610	58935733	WINDOW          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT ON ROUTE THE CAPTAINS NR 4 WINDOW INNER LAYER SHATTERED.AIRCRAFT LANDED AND WINDOW CHANGED.  	  TIMES- 34660:35   CYCLES- 21649 (TCNR  20060412001)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006121200079	20061212	00079	GL  	2006	12	12	CA060412002      	2	20060411	G	7300	6793969	LINE            			LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  					ENGINE	MISSING         	W				E				ENGINE SHUTDOWN         				W	Y		INADEQUATE Q C            	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA											(CAN) NR 2 ENGINE HAD A HUNG RESTART WHILE ON A TRAINING FLIGHT, THE ENGINE WAS SHUTDOWN, SECURED AND THE (3) ENGINE PRO	CEDURES WHEN FOLLOWED ON THE FLIGHT AND LANDING TO THE MAINTENANCE BASE. THE PRIMER PRESSURE LINE WAS FOUND TO BE NOT IN	STALLED ON THIS ENGINE. THE PRIMER SYSTEM HAD BEEN PUT BACK INTO SERVICE AFTER THE ENGINE HAD BEEN AQUIRED FROM AN OPERA	TOR THAT HAD TAKEN THEM OUT OF SERVICE IAW SB. (TC NR 20060412002)			2	L	7	4 	4T	4	T		4A22    	E282				 
2006121300088	20061213	00088	NM  	2006	12	13	CA060412003      	1	20060411	G	5310	65225847	BRACKET         			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE CONTROLS	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE INVESTIGATING A STIFF THRUST REVERSER SNAG, MAINTENANCE DISCOVERED THE NR 3 ENGINE CONTROL QUADRANT BRACKET 	CRACKED. BRACKET WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060412003)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006061400108	20060614	00108	NE  	2006	6	14	CA060413001      	2	20060406	G	7250		TURBINE         			BOEING	767   	767300      	1385204	NM  	GE    	CF6   	CF680C2B7   	 	NE  					NR 1 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								704122			EGT EXCEEDANCE OF NR 1 ENG DURING CLIMB FOLLOWED BY VIBRATION AND ROLLBACK.  DAMAGE TO LP TURBINE WAS FOUND.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006061400112	20060614	00112	SO  	2006	6	14	CA060413002      	1	20060406	G	7603		FRICTION BRAKE  			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	THROTTLE	DAMAGED         	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											DURING TRANSITION TO DESCENT, NR 3 THROTTLE WOULD NOT RETARD FULLY.  THE CREW ELECTED TO CARRY OUT A PRECAUTIONARY SHUTD	OWN OF NR 3 ENGINE.  A NORMAL LANDING WAS COMPLETED.  MAINTENANCE WAS UNABLE TO DETECT A FAULT DURING POST FLIGHT ASSESS	MENT.				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2006061400113	20060614	00113	EA  	2006	6	14	CA060413003      	1	20060327	G	3320	BR9500106	BALLAST         			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF34*       	 	NE  					CABIN LIGHTS	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			2191 	2191 							EN ROUTE A PASSENGER NOTICED AN ELECTRICAL BURNING SMELL.  HE ALERTED THE F/A WHO ALERTED THE CAPTAIN.  CAPTAIN CONFIRME	D THE SMELL.  AIRCRAFT THEN DIVERTED.  AIRCRAFT LANDED UNEVENTFULLY WITH NO NEED FOR EMERGENCY SERVICES.  AIRCRAFT PROCE	EDED TO GATE.  IN SPITE OF CREW AND SOC ADVISING STOC THAT THIS WAS A POTENTIAL EMERGENCY, DEPLANEMENT OF PASSENGERS WAS	 DELAYED 45 MINUTES.  MAINTENANCE FOUND LIGHT BALLAST AT ROW 23 U/S.  BALLAST WAS REMOVED AND NEW BALLAST INSTALLED.  AI	RCRAFT WAS VENTED FOR AN EXTENDED PERIOD AND RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061400121	20060614	00121	GL  	2006	6	14	CA060413005      	2	20060412	G	7321	23070613	FUEL CONTROL    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1373 							ONE OF THE FUEL CONTROL BYPASS COVER SCREWS BROKE CAUSING FUEL TO LEAK INTO THE ENGINE BAY.  THIS IS TO BE INSPECTED EVE	RY 100 HOURS IAW ALLISON 250 C30 CEB A-73-3075R1 WHICH IT WAS.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006061400124	20060614	00124	SO  	2006	6	14	CA060413006      	1	20060413	G	8120	4038180047	SEAL            	GARRTT      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1546 		YHO36265					PRIOR TO A TRAINING FLIGHT THE PILOT NOTED THE LT ENGINE OIL LEVEL TO BE AT 9 QUARTS.  AFTER THE FLIGHT, OIL WAS FOUND O	N THE LT GEAR DOOR AND THE ENGINE WAS DOWN TO 6 QUARTS.  MAINTENANCE INSPECTED THE ENGINE AND FOUND OIL AT THE LOW POINT	 OF THE TURBOCHARGER AND BADLY OIL FOULED SPARK PLUGS.  THE TURBOCHARGER OIL SEAL HAD FAILED AND WAS ALLOWING OIL INTO T	HE COMPRESSOR SIDE OF THE TURBO.  THE OIL WAS THE BEING INDUCTED INTO THE CYLINDERS WITH A PORTION OF IT BEING BURNED AN	D A PORTION OF IT BEING EXHAUSTED.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006121300089	20061213	00089	NM  	2006	12	13	CA060413007      	1	20060413	G	5313	140N01062	STRINGER SPLICE 			BOEING	757   	757200      	1384950	NM  										BS 1180	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORRODED EXTERNAL STRAP ON RT SIDE OF FUSELAGE AT BS 1180 ALONG STRINGER 17. (TC NR 20060413007)						2	L	7	2 	4F			RT	A2NM    					 
2006121300090	20061213	00090	NM  	2006	12	13	CA060413008      	1	20060413	G	5350	148N73081	FAIRING         			BOEING	757   	757200      	1384950	NM  										HORIZONTAL STAB	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT HORZ STAB TO BODY SEAL FAIRING LOWER IB GUIDE CHAFED AT FORWARD END. (TC NR 20060413008)						2	L	7	2 	4F			RT	A2NM    					 
2006121300091	20061213	00091	NM  	2006	12	13	CA060413009      	1	20060413	G	5753		SPAR            			BOEING	757   	757200      	1384950	NM  										LT TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT OB MAIN FLAP AFT SPAR UPPER CHORD 44 INCHES OB OF MAIN FLAP IB EDGE. (TC NR 20060413009)						2	L	7	2 	4F			RT	A2NM    					 
2006101900197	20061019	00197	NM  	2006	10	19	CA060413010      	1	20060413	G	5754	114N40827	SKIN            			BOEING	757   	757200      	1384950	NM  										NR 7 SLAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EXFOLIATED CORROSION AT 2 ADJACENT LOCATIONS (TC NR  20060413010)						2	L	7	2 	4F			RT	A2NM    					 
2006061400175	20060614	00175	EA  	2006	6	14	CA060414001      	3	20060414	G	6114		HUB             			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1156 			AF4209					4 INCHES LONGITUDINAL CRACK FROM TIP TO HUB ON NR 2 BLADE.  PROPELLER REMOVED FROM SERVICE.  CRACK SIMILAR TO CRACK ON A	/C C-GGMV,					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006061400226	20060614	00226	EA  	2006	6	14	CA060414002      	3	20060414	G	6111		BLADE           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	NR 2	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1156 						AF4209		4 INCHES CRACK FROM TIP TO HUB ON NR 2 BLADE, SIMILAR TO THAT REPORTED WITH SDR #20060221008.  PROPELLER REMOVED FROM SE	RVICE.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006061400228	20060614	00228	EA  	2006	6	14	CA060417001      	2	20060414	G	8500		ENGINE          			BELL  	47    	47G4        	1181030	SW  	LYC   	O540  	VO540B1B3   	41532	EA  						SHUTDOWN        	W				R	A			AUTOROTATION            	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA				286  							HELICOPTER WAS FLYING ALONG AND ENGINE QUIT, SUCCESSFUL AUTOROTATION WAS ACCOMPLISHED.  UPON INVESTIGATION OF ENGINE, IT	 WAS FOUND THAT NONE OF THE VALVES WERE OPENING OR CLOSING AND THEREFORE SUGGESTS THAT CAM SHAFT IS NOT TURNING OR HAS B	ROKEN, ENGINE IS BEING SENT FOR TEARDOWN INSPECTION AT THIS TIME.				1	G	7	1 	3O	3	O		2H3     	E304				 
2006061400232	20060614	00232	CE  	2006	6	14	CA060418003      	1	20060407	G	3297		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											CREW REPORTED LEFT MAIN GEAR NOT INDICATING GREEN BUT WAS DOWN AND LOCKED.  MAINTENANCE FOUND WIRE IN WHEEL WELL AREA CH	AFFED TO ACTUATOR DOWNLOCK.  WIRE REPAIRED AND PROTECTED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006061400242	20060614	00242	EU  	2006	6	14	CA060418004      	2	20060417	G	7261	301350238	COVER           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					OIL INLET	SCORED          	W				K				NONE                    				K		O	FLUID LOSS                		OTHER                     	IN	INSP/MAINT     	1			CA											MAINTENANCE WAS CARRYING OUT A 7 DAY CHECK ON AIRCRAFT WHEN NOTICED SIGNS OF OIL LEAKING IN THE AFT SECTION OF THE NR 2 	ENGINE.  ON INVESTIGATION, THE OIL WAS FOUND TO BE LEAKING PAST THE OIL INLET COVER FOR THE NR 5 BEARING AREA.  THE COVE	R WAS FOUND TO HAVE SCORING ON THE INTERIOR SMALL RADIUS.  THE COVER WAS REPLACED WITH A SERVICEABLE UNIT.  THIS SAME IT	EM WAS REPLACED FOR A SIMILAR PROBLEM IN JULY 2005.			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061400243	20060614	00243	EA  	2006	6	14	CA060418005      	2	20060414	G	8520	LW13521	MAIN BEARING    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					CONNECTING ROD	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2154 	2154 							CONNECTING ROD BEARINGS ON NR 1 AND NR 4 RODS SIGNIFICANT SURFACE DELAMINATION.  BROKEN PIECES 1/2"L BY 1/8"W FOUND IN B	ETWEEN CONNECTING ROD BEARING AND CRANKSHAFT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006061400244	20060614	00244	EU  	2006	6	14	CA060418006      	1	20060413	G	3260	V0214	WARNING HORN    			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	MLG	OVERHEATED      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											ON TAKEOFF, THE FLIGHT FINE PITCH STOP WARNING HORN SOUNDED FOLLOWED BY AN ACRID SMELL. ON APPROACH THE SHOWING GEAR DOW	N AND LOCKED THE CREW OBSERVED AN UNDERCARRIAGE FLAG ON THE ASI AND ELECTED TO HAVE VISUAL CONFIRMATION FROM THE GROUND 	THAT THE GEAR APPEARED SAFE.  THE AIRCRAFT LANDED AT POINT OF DEPARTURE WITHOUT FURTHER INCIDENT.  MAINTENANCE FOUND THE	 FFPS HORN SEVERELY OVERHEATED THE HORN WAS REPLACED AND ALL RELATED SYSTEMS WERE CHECKED IN CONJUNCTION WITH NLG SWING.	  SMOOTH OVERWEIGHT LANDING CARRIED OUT.  AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2006061400245	20060614	00245	EU  	2006	6	14	CA060419001      	1	20060418	G	3411		PITOT HEAD      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  		OBSTRUCTED      	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											DURING TAKEOFF ROLL, THE CREW OBSERVED A 20 KT DIFFERENTIAL BETWEEN ASIS.  THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RET	URNED TO RAMP.  MAINTENANCE CLEARED DEBRIS FROM THE CAPT'S PITOT PROBE AND CONDUCTED A SYSTEM LEAK CHECK.  THE AIRCRAFT 	WAS RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006061400246	20060614	00246	NM  	2006	6	14	CA060419002      	1	20060417	G	5711	PA60601	SPAR            			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4634 								CRACK WAS NOTICED DURING AN ANNUAL INSPECTION WITH THE AID OF FLASHLIGHT AND MIRROR.  THE DEFECT AREA IS JUST AFT OF THE	 NR 2 ENGINE FIREWALL THROUGH AN INSPECTION PANEL LOCATED ON THE WING UPPER SURFACE.  MORE INFORMATION TO FOLLOW CONFIRM	ING THE CRACK(S) WITH HFEC NDT INSPECTION.  ALSO THE WING STATION NUMBER AND PART NUMBER WILL BE PROVIDED.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2006061500145	20060615	00145	EA  	2006	6	15	CA060419003      	2	20060407	G	7322	43564	SCREW           	PRECISION   		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	IDLE MIXTURE	LOOSE           	W				O				OTHER                   				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			CA			731  			DC45353					ON FINAL APPROACH TO LAND, THE ENGINE QUIT.  AIRCRAFT GLIDED TO A LANDING AND ROLLED CLEAR OF THE ACTIVE RUNWAY.  ENGINE	 WOULD NOT RESTART, PUSHED AIRCRAFT TO PARKING SPOT.  WHEN AME EXAMINED THE ENGINE FOUND THE IDLE MIXTURE CONTROL SCREW 	HAD WORKED LOOSE AND DEPARTED THE AIRCRAFT IN FLIGHT.  REPLACED MIXTURE SCREW AND ENGINE RAN FINE.  ALL MIXTURE SCREWS W	ILL BE LOCKWIRED FOR SAFETY FROM NOW ON.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061500157	20060615	00157	CE  	2006	6	15	CA060419004      	1	20060407	G	3260	BZ2RQ181A2	LIMIT SWITCH    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3T*      	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			16   								A NEW LANDING GEAR GEARBOX WAS INSTALLED IN THE AIRCRAFT.  SEVERAL DAYS LATER THE CREW WERE UNABLE TO SELECT THE GEAR UP	 AFTER TAKEOFF.  THE AIRCRAFT RETURNED AND LANDED NORMALLY.  THE UP LIMIT SWITCH WAS FOUND TO BE DAMAGED WHERE THE INTER	NAL CONTACTS WERE NOT MAKING AND NOT ALLOWING THE GEAR TO BE POWERED FOR A GEAR UP SELECTION.  IT IS NOT KNOWN WHEN THE 	SWITCH WAS DAMAGED AS IT WAS REPLACED AT THE TIME THE GEARBOX WAS REPLACED.  THE SWITCH IS IN AN AREA THAT IS DIFFICULT 	TO REACH THEREFORE MAKING THE RIGGING ALSO DIFFICULT.		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006061500158	20060615	00158	SO  	2006	6	15	CA060419005      	2	20060418	G	8530		CYLINDER HEAD   			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  					NR 1	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			588  	588  							LEAKAGE FOUND BETWEEN BARREL AND HEAD.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2006061900242	20060619	00242	EU  	2006	6	19	CA060419006      	1	20060418	G	7120	332A32323300	TIE BOLT        			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					ENGINE MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A/C RETURNED FROM AN OFFSHORE TRIP, MAINTENANCE PERSONNEL WERE CARRYING OUT THE TURN AROUND CHECKS AND FOUND THAT 	ONE OF THE 3 ENGINE TIE BOLTS WAS ONLY HELD IN PLACE BY THE LOCKING WIRE.  ONCE THE LOCK WIRE WAS CUT THE BOLT WAS PULLE	D OUT AND FOUND TO BE SHEARED IN THE THREADED AREA.  A/C WAS INSPECTED WITH NO OTHER PROBLEMS FOUND, TIE BOLT WAS ORDERE	D. (TC NR 20060419006)			2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2006062600008	20060626	00008	CE  	2006	6	26	CA060419007      	1	20060412	G	5210	504300377	BOLT            	BEECH       	504300377   	BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	PAX DOOR	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											WHILE CLIMBING THROUGH 10000 FT, A LOUD BANG WAS HEARD FOLLOWED BY A CONSTANT HISSING SOUND.  THE FLIGHT RETURNED UNEVEN	TFULLY AND MAINT FOUND THE UPPER FWD DRAW BOLT ROLLER HAD FAILED CAUSING THAT PORTION OF THE DOOR TO SHIFT SLIGHTLY.  BO	TH UPPER DRAW BOLT ROLLERS WERE REPLACED AND DOOR INSPECTED FOR FURTHER DAMAGE.  NONE WAS FOUND AND GROUND CHECKS WERE C	/O SERVICEABLE.			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006061500162	20060615	00162	GL  	2006	6	15	CA060420001      	1	20060410	G	2820	374475	CHECK VALVE     			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5316 								ON ROUTINE INSPECTION AFT FUEL CHECK VALVE FOUND CRACKED, P/N 525 GG 1/2D, 3-744-75.  MINOR COLOR TO SHOW THAT FUEL LEAK	ING.  NO LEAK INDICATION AT LAST INSPECTION 50.20 HOURS PREVIOUS.					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006061500165	20060615	00165	SW  	2006	6	15	CA060420002      	1	20060407	G	5302	206032308003	BULKHEAD        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHILE PERFORMING 100 HR INSPECTION OF THE ATTACHMENT HOLES FOR TAILBOOM FOUND A CRACK ORIGINATING FROM UPPER RIGHT HOLE.	  CRACK WAS 1 INCH IN LENGTH.  BULKHEAD WAS REPLACED.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006121300092	20061213	00092	NM  	2006	12	13	CA060421001      	1	20060420	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 947	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOORBEAM CAP AT BS 947 LBL 39 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421001)						2	L	7	2 	4F				A16WE   					 
2006121300093	20061213	00093	NM  	2006	12	13	CA060421002      	1	20060420	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 967	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOORBEAM CAP AT BS 967 LBL 18 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421002)						2	L	7	2 	4F				A16WE   					 
2006121300094	20061213	00094	NM  	2006	12	13	CA060421003      	1	20060420	G	5713		STRINGER        			BOEING	737   	737290C     	138448V	NM  										RT WING	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT WING FUEL TANK AT WBL 135.5 STR 2R CRACKED AND REPAIRED IAW EA.  (TC NR 20060421003)						2	L	7	2 	4F				A16WE   					 
2006121300095	20061213	00095	NM  	2006	12	13	CA060421004      	1	20060420	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 947 S18R	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STR 18R AT BS 947 CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421004)						2	L	7	2 	4F				A16WE   					 
2007012900313	20070129	00313	NM  	2007	1	29	CA060421005      	1	20060420	G	5330		SKIN            			BOEING	737   	737290C     	138448V	NM  										FUSELAGE	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) BS 867 AT STR 19R SKIN GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421005)						2	L	7	2 	4F				A16WE   					 
2007012900314	20070129	00314	NM  	2007	1	29	CA060421006      	1	20060420	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										FUSEAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOORBEAM AT BS 767 LBL 24.5 CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421006)						2	L	7	2 	4F				A16WE   					 
2007012900315	20070129	00315	NM  	2007	1	29	CA060421007      	1	20060420	G	5320		STRUCTURE       			BOEING	737   	737290C     	138448V	NM  										FUSELAGE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STR 26L BS 380 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421007)						2	L	7	2 	4F				A16WE   					 
2007012900316	20070129	00316	NM  	2007	1	29	CA060421008      	1	20060420	G	5534		ATTACH ANGLE    			BOEING	737   	737290C     	138448V	NM  										VERICAL STAB	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) VERTICAL STAB LT TRAILING EDGE AT RUDDER STATION 174, PANEL ATTACH ANGLE CORRODED AND REPAIRED IAW CUSTOMER EA (TC	 NR 20060421008)					2	L	7	2 	4F				A16WE   					 
2006121300100	20061213	00100	NM  	2006	12	13	CA060421009      	1	20060420	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 520 S26L	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STR 26L AT BS 520 CORREDED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421009)						2	L	7	2 	4F				A16WE   					 
2006121300101	20061213	00101	NM  	2006	12	13	CA060421010      	1	20060420	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 500B S16L	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STR 16L AT BS 500B+13 INCHES CRACKED AT FASTNER HOLE AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421010)						2	L	7	2 	4F				A16WE   					 
2006121300102	20061213	00102	NM  	2006	12	13	CA060421011      	1	20060420	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 500B-520	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STR 26R AT BS 500B TO BS 520 CORRODED AND REPAIRED IAW CUSTOMER EA.  (TC NR  20060421011)						2	L	7	2 	4F				A16WE   					 
2006121300103	20061213	00103	NM  	2006	12	13	CA060421012      	1	20060420	G	5730		SKIN            			BOEING	737   	737290C     	138448V	NM  										LWS 76	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LT WING UPPER SKIN, WBL 76.75 FROM AFT EDGE OF SKIN FWD FOR 9.5 INCH SKIN CHAFED AND REPAIRED IAW CUSTOMER EA. (TC	 NR 20060421012)					2	L	7	2 	4F				A16WE   					 
2006061500167	20060615	00167	EA  	2006	6	15	CA060421013      	1	20060417	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											THE LEFT COCKPIT WINDOW CRACKED DURING CRUISE AT FL330.  WINDOW REPLACED, AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061500168	20060615	00168	NE  	2006	6	15	CA060421014      	2	20060416	G	7532	4157T43P01	BLEED VALVE     			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					4TH STAGE	STICKING        	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											AT V1 ON TAKEOFF, SMOKE AFT LAV WARNING ILLUMINATED.  CONTINUED TAKEOFF, DECLARED EMERGENCY AND RETURNED TO ORD.  4TH ST	AGE SHUTOFF VALVE FOUND DEFECTIVE.  VALVE REPLACED AND OPS CHECK GOOD.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006061500170	20060615	00170	CE  	2006	6	15	CA060421015      	1	20060402	G	3397		WIRE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PAX LIGHT	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				M			OVER TEMP                 			CR	CRUISE         	1			CA											DURING CRUISE, PAX ADVISED CREW PAX TABLE LIGHT SWITCH WAS VERY HOT.  PILOT PULLED CB, OPENED CABIN SIDE PANEL AND DISCO	NNECTED SWITCH CONNECTORS.  AFTER INVESTIGATION, FOUND LIGHT CONTROL SWITCH P/N: 30600557 (CUSTOMER P/N: SP-45-33) WIRIN	G WAS CHAFING ON CUP HOLDER LOWER BRACKET.  ALSO FOUND CUP HOLDER LATCH WAS MELTED, CUP HOLDER DAMPER (ACTUATOR) SEALS W	ERE MELTED AND WAS LEAKING, CUP HOLDER SPRING BECAME ANNEALED CONDITION.  NO MORE SPRING ACTION AND THE SIDEWALL AC PLUG	 PLASTIC COVER WAS DEFORMED DUE TO HEAT.  NOTICE THAT WHEN A SIDEWALL AC PLUG RECEPTACLE WAS INSTALLED, THAT RECEPTACLE 	WOULD PUSH ON SWITCH WIRING AGAINST CUP HOLDER LOWER BRACKET AND ANY MOVEMENT OF CUP HOLDER WOULD DAMAGE THE WIRING.	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006061500175	20060615	00175	CE  	2006	6	15	CA060421016      	1	20060413	G	3411	AN62704D0300	HOSE            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					PITOT STATIC SYS	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											CREW REPORTED A +- 400FT SPLIT WITH ALTEMETERS.  FOUND PITOT/STATIC HOSE CRACKED.   NOTE: OUR LEARJET 35 FLEET OF AIRCRA	FT WERE RVSM CONVERTED WITH A LEARJET STC, THESE HOSES ARE PART OF THE CONVERSION AND FOUND THIS PROBLEM WITH OTHER LEAR	JET 35 RVSM CONVERTED AIRCRAFTS IN OUR FLEET.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2006061500177	20060615	00177	SO  	2006	6	15	CA060421017      	1	20060413	G	2410	4111810	ALTERNATOR      			PIPER 	PA28  	PA28R201T   	7102813	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	3D36C	B3D36C424   	GL  	ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				220  							THE ALTERNATOR HAS BEEN OVERHAULED AND FAILED.						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P58GL	 
2006071000023	20060710	00023	NM  	2006	7	10	CA060421018      	1	20060421	G	2720	591841	DIODE           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					AILERON/RUDDER	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			240  								FOUND RUDDER TRIM FAST MOTION RT SIDE WAS U/S.  FAULT CONFIRMED FOUND AILERON/RUDDER TRIM DIODE CR2 WIRE A, UN-CLIP.  PA	NEL TESTED IAW CMM 27-15-01-700-801.  AFTER FURTHER INVESTIGATION, FOUND CONNECTOR PINS P/N M39029/58-363 INSTALLED WERE	 WRONG TYPE AND REPLACED WITH PINS P/N M39029/1-101 IN REF TO CMM 27-15-01.  CR2 SPLICE, P/N 591842-1, REPLACED AND TEST	ED SERVICEABLE IAW CMM 27-15-01, AND SYS TESTED IAW AMM 27-13-16-000-801/-400-801.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006061900243	20060619	00243	EA  	2006	6	19	CA060421019      	2	20060323	G	8520	74968	CRANKSHAFT      			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				847  				L2651636A			(CAN) FWD INNER DIA CRANKSHAFT CORRODED BEYOND LIMITS IAW AWD 98-02-08. (TC NR 20060421019)						1	H	7	1 	3O	3	O		A21CE   	E286				 
2006061600086	20060616	00086	EA  	2006	6	16	CA060421020      	2	20060323	G	8520	74968	CRANKSHAFT      			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1500 				L2717736A			CORROSION FOUND UNDER PID AT FWD ID.						1	H	7	1 	3O	3	O		A21CE   	E286				 
2006061600087	20060616	00087	EA  	2006	6	16	CA060421021      	2	20060323	G	8520	74968	CRANKSHAFT      			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1300 				RL2805636A			CORROSION FOUND UNDER PID FWD ID.						1	H	7	1 	3O	3	O		A21CE   	E286				 
2006080300257	20060803	00257	NM  	2006	8	3	CA060421022      	1	20060413	G	3244	PNDR0231T	TIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			400  	53   							(CAN) FOUND DURING DAILY CHECK 1 MAIN WHEEL WITH TIRE BEAD WIRE MIGRATION. LOOKS LIKE LOCKING WIRE PROTRUDING FROM TIRE 	SIDE WALL. WHEEL ASSY HAS BEEN REMOVED. NO TIRE PRESSURE WAS LOST. INVESTIGATION SHOWN THAT THE MIGRATING BEADWIRE HAS D	AMAGED THE WHEEL HUB, THE DAMAGED WAS SO DEEP THAT WE HAD TO SCRAP THE AFT WHEEL.  DUNLOP IS AWARE OF THIS MIGRATING BEA	DWIRE ISSUE CONDITION AND HAS SEEN THIS WIRE COME OUT OF THE TIRE IN THE PAST (SIMILAR TO THIS CONDITION AND IT SEEMS TO	 BE AN INCREASING PROBLEM).		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006121300104	20061213	00104	NM  	2006	12	13	CA060421023      	1	20060421	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 350-366	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STR 28R, BS 350 TO BS 366 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421023)						2	L	7	2 	4F				A16WE   					 
2006121300105	20061213	00105	NM  	2006	12	13	CA060421024      	1	20060421	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 925 S25L	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFT CARGO PIT STR 25L AT BS 925 HAS A GOUGE AND REPAIRED IAW CUSTOMER EA (TC NR 20060421024)						2	L	7	2 	4F				A16WE   					 
2006121300106	20061213	00106	NM  	2006	12	13	CA060421025      	1	20060421	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 947 S26R	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STR 26R AT BS 947 GOUGED AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421025)						2	L	7	2 	4F				A16WE   					 
2006121300107	20061213	00107	NM  	2006	12	13	CA060421026      	1	20060421	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 727B	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFT CARGO PIT FLOORBEAM UPPER CHORD CORRODED AT BS 727B FROM LBL 25-45 AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060	421026)					2	L	7	2 	4F				A16WE   					 
2006121300108	20061213	00108	NM  	2006	12	13	CA060421027      	1	20060421	G	5330		SKIN            			BOEING	737   	737290C     	138448V	NM  										BS 326 S2R	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FUSELAGE SKIN GOUGED AT BS 326, 2 INCHES ABOVE STR 2R AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421027)						2	L	7	2 	4F				A16WE   					 
2006121300109	20061213	00109	NM  	2006	12	13	CA060421028      	1	20060421	G	5330		SKIN            			BOEING	737   	737290C     	138448V	NM  										BS 500 S25-26L	DENTED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SKIN HAS SMALL DENT BETWEEN STR 25L AND STR 26L AT BS500+13 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421028)						2	L	7	2 	4F				A16WE   					 
2006121300110	20061213	00110	NM  	2006	12	13	CA060421029      	1	20060421	G	5322		SHEAR TIE       			BOEING	737   	737290C     	138448V	NM  										BS 727A S22-23R	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SHEAR TIE CRACKED AT BS 727A BETWEEN STR 22R AND 23R AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421029)						2	L	7	2 	4F				A16WE   					 
2006121300115	20061213	00115	NM  	2006	12	13	CA060421030      	1	20060421	G	5532		SKIN            			BOEING	737   	737290C     	138448V	NM  										VERTICAL STAB	DENTED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SKIN HAS A DENT IN VERTICAL STAB RT SIDE 12 INCHES AFT OF UPPER END AND REPAIRED IAW CUSTOMER EA. (TC NR 200604210	30)					2	L	7	2 	4F				A16WE   					 
2006121300116	20061213	00116	NM  	2006	12	13	CA060421031      	1	20060421	G	5347		SEAT TRACK      			BOEING	737   	737290C     	138448V	NM  										BS 504-616	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CORROSION ON SEAT TRACK BEAM BS 504-616 LBL 26 REPAIRED IAW CUSTOMER EA. (TC NR 20060421031)						2	L	7	2 	4F				A16WE   					 
2006121300117	20061213	00117	NM  	2006	12	13	CA060421032      	1	20060421	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 520	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOORBEAM AT BS 520 LBL 45 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421032)						2	L	7	2 	4F				A16WE   					 
2006121300118	20061213	00118	NM  	2006	12	13	CA060421033      	1	20060421	G	5511		BUSHING         			BOEING	737   	737290C     	138448V	NM  										HORIZONTAL STAB	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT HORIZONTAL STABILIZER, FRONT AND REAR SPAR BUSHING CORRODED REPAIRED IAW CUSTOMER EA. (TC NR 20060421033)						2	L	7	2 	4F				A16WE   					 
2006121300119	20061213	00119	NM  	2006	12	13	CA060421034      	1	20060421	G	5511		BUSHING         			BOEING	737   	737290C     	138448V	NM  										HORIZONTAL STAB	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LT HORIZONTAL STABILIZER FRONT AND REAR SPAR BUSHINGS CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20060421034)						2	L	7	2 	4F				A16WE   					 
2006121300120	20061213	00120	NM  	2006	12	13	CA060421035      	1	20060421	G	5230		SUPPORT ANGLE   			BOEING	737   	737290C     	138448V	NM  										CARGO DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAIN CARGO DOOR NR1 LATCH SUPPORTING ANGLE CRACKED REPAIRED IAW CUSTOMER EA. (TC NR 20060421035)						2	L	7	2 	4F				A16WE   					 
2006121300121	20061213	00121	NM  	2006	12	13	CA060422000      	1	20060421	G	5551		ATTACH FITTING  			BOEING	737   	737290C     	138448V	NM  										HORIZONTAL STAB	NICKED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LT STABILIZER CENTER SECTION AFT UPPER SPAR, UPPER FWD ATTACH LUG FACE NICKED REPAIRED IAW CUSTOMER EA. (TC NR 200	60422000)					2	L	7	2 	4F				A16WE   					 
2006121300122	20061213	00122	NM  	2006	12	13	CA060422001      	1	20060421	G	5313		STRINGER        			BOEING	737   	737290C     	138448V	NM  										BS 947 S26R	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STR 26R AT BS 947 GOUGED REPAIRED IAW CUSTOMER EA. (TC NR 20060422001)						2	L	7	2 	4F				A16WE   					 
2006121300123	20061213	00123	NM  	2006	12	13	CA060422002      	1	20060421	G	5510		HINGE FITTING   			BOEING	737   	737290C     	138448V	NM  										HORIZONTAL STAB	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT HORIZONTAL STAB NR 1 ELEVATOR HINGE FITTING LOWER PORTION HAS A GOUGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422	002)					2	L	7	2 	4F				A16WE   					 
2006121300124	20061213	00124	NM  	2006	12	13	CA060422003      	1	20060421	G	5315		FLOORBEAM       			BOEING	737   	737290C     	138448V	NM  										BS 986	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOORBEAM AT BS 986, LBL 18 TO LBL 52 CORRODED REPAIRED IAW CUSTOMER EA. (TC NR 20060422003)						2	L	7	2 	4F				A16WE   					 
2006121300125	20061213	00125	NM  	2006	12	13	CA060422004      	1	20060421	G	5230		STRUCTURE       			BOEING	737   	737290C     	138448V	NM  										CARGO DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAIN CARGO DOOR BS492 CRACKED 6 INCHES BELOW HINGE AT FRAME LIGHTNING HOLE TO THE IB EDGE REPAIRED IAW CUSTOMER EA	. (TC NR 20060422004)					2	L	7	2 	4F				A16WE   					 
2006121300126	20061213	00126	NM  	2006	12	13	CA060422005      	1	20060421	G	5230		SKIN            			BOEING	737   	737290C     	138448V	NM  										CARGO DOOR	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAIN CARGO DOOR SKIN AT NR 6 HINGE ATTACH AREA BS 441.5 GOUGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422005)						2	L	7	2 	4F				A16WE   					 
2006121300127	20061213	00127	NM  	2006	12	13	CA060422006      	1	20060421	G	5230		SKIN            			BOEING	737   	737290C     	138448V	NM  										CARGO DOOR	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAIN CARGO DOOR SKIN AT NR 5 HINGE STA 418 GOUGED REPAIRED IAW CUSTOMER EA. (TC NR 20060422006)						2	L	7	2 	4F				A16WE   					 
2006101900198	20061019	00198	NM  	2006	10	19	CA060422007      	1	20060421	G	5230		SKIN            			BOEING	737   	737290C     	138448V	NM  										CARGO DOOR	GOUGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAIN CARGO DOOR SKIN AT NR 4 HINGE ATTACH AREA STN 492 GOUGED REPAIRED IAW CUSTONER EA (TC NR 20060422007)						2	L	7	2 	4F				A16WE   					 
2006101900199	20061019	00199	NM  	2006	10	19	CA060422008      	1	20060421	G	5230		SKIN            			BOEING	737   	737290C     	138448V	NM  										CARGO DOOR	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN CARGO DOOR SKIN AT NR 4 HINGE ATTACH AREA STA 406 GOUGED AND REPAIRED IAW CUSTOMER EA (TC NR 20060422008)						2	L	7	2 	4F				A16WE   					 
2006061600088	20060616	00088	CE  	2006	6	16	CA060422009      	1	20060421	G	3233	130909B40130909	LOCK NUT        	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG ACTUATOR	MISSING         	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA						F99820					DURING L/G EXT IN FLT, LT MAIN AND NOSE GEAR DOWN AND LOCKED IND PRESENT, WITH NO RT IND AND LOUD BANGING SOUND FROM RT 	SIDE OF A/C.  C/O FLY-BY TO VISUALLY VERIFY ALL THREE LANDING GEARS WERE DOWN.  A/C LANDED SAFELY, VERIFIED ALL 3 L/G WE	RE DOWN AND LOCKED BEFORE TAXING A/C OFF RUNWAY.  DURING INSPECTION ACT TQ TUBE TO ACT DRIVE BOLT FOUND MISSING.  TQ TUB	E END AND ACT DRIVE INSPECTED FOR DAMAGE/CRACKS WITH 10X MAGNIFYING GLASS.  NO DAMAGE EVIDENT.  INNER TQ TUBE SPACER REP	LACED DUE TO SOME SCORING OF INNER BORE.  A NEW DRIVE BOLT AND LOCK NUT WAS INSTALLED ON LT AND RT ACT.  LANDING GEAR SY	STEM INSPECTION/RIGGING C/O: GOOD IAW KA200 MM NR 101-590010-19B9 CHAPTER 32-30-00.  FIVE FAULT FREE GEAR SWINGS C/O.	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006061600090	20060616	00090	EA  	2006	6	16	CA060423001      	1	20060330	G	2710	272955	LINK ASSY       			CNDAIR	CL600 	CL6002C10   	1390015	EA  										AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4886 								RT AILERON OUTBOARD PCU OUTPUT LINK ASSEMBLY BROKEN.  WHILE PERFORMING 5000 HOURS INSPECTION FOR  THE FLUTTER DAMPENER M	AINTENANCE FOUND RT AILERON OUTBOARD PCU OUTPUT LINK ASSEMBLY BROKEN.					2	L	7	2 	4F			RT	A21EA   					 
2006061600092	20060616	00092		2006	6	16	CA060424001      	2	20060403	G	7321	414T70P02	FUEL CONTROL    			CNDAIR	CL600 	CL6002B19   	1900309	EA  										ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA			4836 								RT ENGINE N1, N2 AND FUEL FLOW FLUCTUATING CLIMBING FROM 10000 FT AND THEN CLIMBING FROM 10000 FT TO FL210 THE RT ENGINE	 N1, N2 AND FUEL FLOW WERE FLUCTUATING RAPIDLY.  THE FLIGHT DIVERTED AND LANDED WITHOUT INCIDENT.  THE CREW REPORTED THA	T FLUCTUATION CEASED WHEN THE THROTTLES WERE RETARDED FOR LANDING.  THE FUEL CONTROL WAS REPLACED IN ACCORDANCE WITH AMM	.			2	L	7	2 	4F			RT	A21EA   					 
2006061600097	20060616	00097	EA  	2006	6	16	CA060424002      	1	20060410	G	3246	AN676AC6300	FLY WIRE        			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540*      	41532	EA  					MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			269  								THE AIRCRAFT IS EQUIPPED WITH AEROCET 3450 AMPHIBIAN FLOATS.  AFTER A TWO-HOUR FLIGHT AND AT 3000 FT ALTITUDE ON APPROAC	H FOR LANDING, THE PILOT HEARD A LOUD NOISE.  NO TURBULENCE WAS NOTED AT THE TIME AND AN UNEVENTFUL LANDING WAS COMPLETE	D.  UPON GROUND INSPECTION THE FORWARD FLY WIRE (ASSEMBLY P/N: U613) WAS OBSERVED TO HAVE BROKEN APPROXIMATELY 3 1/2 INC	HES FROM THE LOWER END.  FLY WIRE WAS REPLACED, AREA INSPECTION CONDUCTED WITH NO FURTHER DISCREPANCIES AND THE AIRCRAFT	 WAS RETURNED TO SERVICE.  THE PART IN QUESTION HAS BEEN SENT FOR A FAULT ANALYSIS.  A CLOSE VISUAL INSPECTION INDICATED	 A POSSIBLE FLAW IN THE MATERIAL.	1	H	7	1 	3O	3	O		A7EA    	1E4				 
2006101800063	20061018	00063	EA  	2006	10	18	CA060424003      	1	20060424	G	2620	215T950262	FIRE BOTTLE     			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  		MALFUNCTIONED   	W				F				ACTIVATE FIRE EXT.      				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			427  								(CAN)  1936 :58 CYCLES : 1316 LARGAGES : 8888  ENGLISH: THE INDICATOR FOR NORMAL DISCHARGE OF THE HEATER EXTINGUISHER (Y	ELLOW DISC) DID NOT WORK AND THE BOTTLE DID NOT COMPLETELY EMPTY AFTER DISCHARGE WAS SELECTED.    (TC NR 20060424003)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006061600099	20060616	00099	WP  	2006	6	16	CA060424004      	1	20060331	G	7810		CLAMP           	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					EXHAUST SHIELD	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			203  			10913					DURING PREFLIGHT INSPECTION, TAIL PIPE EXHAUST HEAT SHIELD P/N D317-1 WAS FOUND BENT AFT.  FURTHER INVESTIGATION DETERMI	NED THAT THE FWD CLAMP FOR THE SHIELD HAD FAILED AND CAME OFF IN FLIGHT ALLOWING THE AIRFLOW TO CATCH THE SHIELD AND BEN	T IT AFT.  ROBINSON HELICOPTER HAS UPGRADED THE TWO CLAMPS WHICH SECURE THE SHIELD TO A LARGE CLAMP SIZE.  HEAT SHIELD A	ND CLAMPS REPLACED.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600101	20060616	00101	SW  	2006	6	16	CA060424005      	1	20060412	G	5311	21949	FRAME           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C1E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7559 								DURING THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE RIGHT SIDE OF THE FUSELAGE FRAME WAS FOUND CRACK	ED IN THE AREA WHERE THE RIGHT MAIN GEAR LEG RESTS AGAINST THE AIRFRAME.  THE CRACK WAS LONGITUDINAL AND WAS ABOUT 1 1/8	" LONG.				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006061600103	20060616	00103	SW  	2006	6	16	CA060424006      	1	20060424	G	5753	5428L	SPAR            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	LT WING TE FLAP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											2 HOLES FOR MOUNTING INBD FLAP HINGE BRACKET LWR ATTACH AND INBD BOLT FOR SHIM PLATE BOTH FOUND CRUDELY DRILLED AND VERY	 OVAL.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2006062600009	20060626	00009	NM  	2006	6	26	CA060424007      	1	20060422	G	2612		FIRE LOOP       	GARRTT      	GTCP85129   	BOEING	737   	737248C     	1384415	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU	FAULTY          	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											AFTER ARRIVAL AT DESTINATION AND DURING TAXI, A FIRE INDICATION WAS OBSERVED WHEN APU WAS STARTED.  FIRE DRILL CARRIED O	UT, EMERGENCY CREW FOUND NO EVIDENCE OF FIRE AND THE AIRCRAFT WAS TOWED TO GATE FOR PASSENGERS DEPLANE.  AIRCRAFT RELEAS	ED ON MEL, APU INOP.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006061600105	20060616	00105	NM  	2006	6	16	CA060424008      	1	20060421	G	6121	87620130101	SHAFT           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PROPELLER	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											FLIGHT CREW REPORTED EXCESS BACKLASH AND PROP SYNC DOES NOT SYNC.  PROP WANDERING + - 5 TO 7 RPM.  ENGINE SPRING STRUT A	SSEMBLY REPLACED.  AFTER DISASSEMBLY IN THE O/H SHOP, SHAFT P/N 87620130-101 WAS FOUND BROKEN AT POINT RIVET P/N MS20417	0AD3. THE SIZE OF THE RIVET HOLE LEAVES MINIMAL MATERIAL AROUND THE SHAFT, WHICH IS PRONE TO BREAKING UNDER VIBRATION.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061600107	20060616	00107	SW  	2006	6	16	CA060424009      	1	20060327	G	6700		YOKE            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WITH THE COLLECTIVE IN THE MID TO FULL DOWN POSITIONAND THE CYCLIC FULL FORWARDAND LEFT THE RT CONTROL YOKE CONTACTS T	HE WINDSCREENDEFROST HEATER PIPE.					1	G	7	1 	3U				H2SW    					 
2006061600129	20060616	00129	WP  	2006	6	16	CA060425001      	1	20060423	G	7697	VF741H11	RELAY           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL PUMP	STUCK           	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1482 								AFTER PRIMING THE ENGINE, IT WAS NOTED THAT THE AUX FUEL PUMP WOULD NOT SHUT OFF.  THE TROUBLE WAS TRACED TO THE CONTROL	 RELAY.  THE INTERNAL POINTS IN THE RELAY HAD STUCK TOGETHER AND WERE KEEPING THE CIRCUIT CLOSED.  THE RELAY WAS REPLACE	D, AND NO FURTHER DEFECTS WERE FOUND.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006061600151	20060616	00151	CE  	2006	6	16	CA060425002      	1	20060425	G	5712	05230821	RIB             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	RT WING	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7169 								RIGHT WING RIB AT STN 40.125 AFT UPPER FLANGE CRACKED ALONG BEND RADIUS.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006061600154	20060616	00154	NE  	2006	6	16	CA060425003      	2	20060402	G	7200		ENGINE          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  						DAMAGED         	W				O				OTHER                   				X	T	J	ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   	WARNING INDICATION        	NR	NOT REPORTED   	1			CA								BB0084			DURING FLIGHT, THE ENGINE EMITTED TWO LOUD NOISES ACCOMPANIED BY A CHIP DETECTOR WARNING INDICATION.  TWO MINUTES LATER 	THE ENGINE FLAMED OUT ON APPROACH.  INSPECTION REVEALED INTERNAL ENGINE DAMAGE, FRACTURE OF AN ENGINE CASE AND RELEASE O	F A SEGMENT OF AN ACCESSORY DRIVE GEAR.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2006061600158	20060616	00158	NE  	2006	6	16	CA060425004      	2	20060405	G	7261		OIL SYSTEM      			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA								DB0706			DURING CRUISE, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE ACCOMPANIED BY SMOKE AND ODOR IN THE CABIN AIR.  ENGINE OIL PRE	SSURE SUBSEQUENTLY REDUCED TO ZERO AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVI	SE OF ROOT CAUSE, ONCE DETERMINED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006061600159	20060616	00159	EA  	2006	6	16	CA060425005      	2	20060404	G	7200		ENGINE          			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  						POWER LOSS      	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT.  	P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006061600161	20060616	00161	NE  	2006	6	16	CA060425006      	2	20060405	G	7260		TOWERSHAFT      			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					AGB	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT DOWN.  SUBSEQUENT INSPECTION REVEALED A DISTRESSED ACCESSORY D	RIVE TOWER SHAFT.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006061900052	20060619	00052	EA  	2006	6	19	CA060425007      	2	20060402	G	7200		ENGINE          			PIPER 	PA46  	PA46350P    	7104602	SO  	PWA   	PT6   	PT6*        	52043	EA  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								RR0052			DURING CRUISE, ENGINE SPEED INCREASED UNCOMMANDED ACCOMPANIED BY A MANUAL OVERRIDE LIGHT INDICATION.  THE ENGINE WAS SHU	T DOWN IN FLIGHT.  FOLLOWING TWO UNSUCCESSFUL ATTEMPTS, THE ENGINE WAS RE-STARTED IN FLIGHT AND THE AIRCRAFT CONTINUED T	O DESTINATION.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2006061900054	20060619	00054	NE  	2006	6	19	CA060425008      	2	20060410	G	7200		ENGINE          			MRCHTI	S205  	S20522R     	8120412	EU  	PWA   	JT15  	JT15*       	52060	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								98023			DURING TAXI, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT AND SUBSEQUENTLY EXPERIENCED AN UNCOMMANDED POWER RED	UCTION.  THE ENGINE WAS SHUT DOWN.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	1 	3O	4	T		A9EU    	E1NE				 
2006061900059	20060619	00059	EA  	2006	6	19	CA060425009      	2	20060409	G	7200		ENGINE          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA								PE0126			ON APPROACH, ENGINE TORQUE AND FUEL FLOW WERE SEEN TO FLUCTUATE.  THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT.  P&WC	 WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006061900062	20060619	00062	NE  	2006	6	19	CA060425010      	2	20060408	G	7200		ENGINE          			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305B      	52128	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA								305031			DURING CRUISE, THE ENGINE SURGED FOLLOWED BY AN UNCOMMANDED POWER REDUCTION TO IDLE.  THE WAS NO SUBSEQUENT RESPONSE TO 	THROTTLE INPUT.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2006061900065	20060619	00065	NE  	2006	6	19	CA060425011      	2	20060407	G	7250		TURBINE BLADES  			BEECH 	45    	T34C1       	1152016	CE  	PWA   	PT6   	PT6A25      	52043	NE  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				B	R	X	SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	NR	NOT REPORTED   	1			CA								48053			DURING A TRAINING FLIGHT, THE ENGINE WAS REPORTED TO EMIT NOISES AND SMOKE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION AN	D FLAME OUT.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  P&WC WILL INVESTIGATE THE EVENT AND WILL A	DVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	3T	3	T		A26CE   	E4EA				 
2006061900258	20060619	00258	NE  	2006	6	19	CA060425012      	2	20060416	G	7261		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					OIL SYS	LEAKING         	W				A				UNSCHED LANDING         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA											DURING CLIMB, ENGINE LOW OIL PRESSURE WARNING ACTIVATED.  ENGINE SUBSEQUENTLY EMITTED A NOISE AND EXPERIENCED AN UNCOMMA	NDED POWER REDUCTION.  POST-FLIGHT INSPECTION REVEALED NO OIL REMAINING IN THE ENGINE AND SEIZURE OF THE HIGH PRESSURE R	OTOR.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006061900260	20060619	00260	NM  	2006	6	19	CA060425013      	1	20060425	G	2913	623337	PUMP            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					HYD SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											AFTER TAKEOFF, CREW NOTICED A LOW HYDRAULIC PRESSURE INDICATION WHEN THE LANDING GEAR WAS RETRACTED.  LATER IN THE CLIMB	 THERE WAS AN INDICATION FOR LOSS OF HYDRAULIC PRESSURE FROM THE NR 1 ENGINE DRIVEN PUMP.  THE CREW ELECTED TO RETURN TO	 BASE FOR MAINTENANCE DUE TO THE UNAVAILABILITY OF REPLACEMENT PARTS AT THEIR DESTINATION.  THE AIRCRAFT RETURNED AND LA	NDED WITHOUT INCIDENT.  MAINTENANCE REPLACED THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP.  AFTER SUCCESSFUL LEAK AND PRESSURE 	CHECKS, THE AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061900145	20060619	00145	NE  	2006	6	19	CA060425014      	2	20060416	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								PC0880			DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  A DEADSTICK LANDING WAS SUCCESSFULLY ACCOMPLISHED.  P&WC 	WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006061900146	20060619	00146	NE  	2006	6	19	CA060425015      	2	20060405	G	7240		TURBINE BLADES  			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  					ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											ON TAKEOFF, THE ENGINE WAS SEEN TO EMIT SMOKE AND SPARKS FROM THE EXHAUST.  SUBSEQUENT INVESTIGATION REVEALED FRACTURED 	COMPRESSOR TURBINE BLADES.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	L	7	1 	3T	4	T		A3SW    	E4EA				 
2006061900147	20060619	00147	NE  	2006	6	19	CA060425016      	2	20060417	G	7230		COMPRESSOR      			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	STALLED         	W				A				UNSCHED LANDING         				B	R	J	SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA								500037			DURING CLIMB, THE ENGINE EXPERIENCED COMPRESSOR STALLS ACCOMPANIED BY AN UNCOMMANDED POWER ROLL-BACK AND FUMES IN THE CA	BIN AIR.  THE FLIGHT WAS DIVERTED.  SUBSEQUENT INSPECTION REVEALED LP COMPRESSOR BOOST ROTOR DAMAGE.  P&WC WILL INVESTIG	ATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006061900269	20060619	00269	NE  	2006	6	19	CA060425017      	2	20060420	G	7200		ENGINE          			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  						MALFUNCTIONED   	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											ON TAKEOFF AND CLIMB, THE ENGINE WAS REPORTED TO EXHIBIT PARTIAL POWER LOSS AND WAS SHUTDOWN IN FLIGHT.  POST-FLIGHT INS	PECTION REVEALED NO ANOMALIES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006061900275	20060619	00275	NE  	2006	6	19	CA060425018      	2	20060424	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											ON TAKEOFF, THE NR 1 ENGINE AUTOFEATHERED AND THE NR 2 ENGINE UP TRIMMED.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. 	 MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061900276	20060619	00276	CE  	2006	6	19	CA060425019      	1	20060425	G	5414	999800007	SKIN            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33536								VISUAL INSPECTION INDICATED A CRACK ON LT ENGINE NACELLE IB SKIN JUST FORWARD OF WING LEADING EDGE.  CRACK RAN VERTICALL	Y JUST AFT OF IB NACELLE INSPECTION PANEL.  A RIVET THAT ATTACHES THE NACELLE FILLET STRIP TO THE WING WAS INCLUDED IN T	HE CRACK.  THERE WAS NO REPORT OF A HARD LANDING AND NO ADJACENT STRUCTURE IS DAMAGED.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006061900277	20060619	00277	NE  	2006	6	19	CA060425020      	2	20060422	G	7320		HMU             			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	F	J	PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         	WARNING INDICATION        	CR	CRUISE         	1			CA											ON TAKEOFF ROLL, ENGINE POWER ROLLED BACK MARGINALLY AND WAS CORRECTED BY A THROTTLE ADJUSTMENT.  POWER FLUCTUATIONS WER	E REPORTED DURING CLIMB.  IN CRUISE, POWER ROLLED BACK UNCOMMANDED AND THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE I	NPUT.  THE AIRCRAFT DIVERTED AND ON DESCENT ENGINE THROTTLE AUTHORITY WAS REGAINED.  MFG WILL INVESTIGATE THE EVENT AND 	WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2006080700052	20060807	00052	CE  	2006	8	7	CA060426001      	1	20060405	G	7120	7120000101	MOUNT           			SYMPHO	SA160 	SA160       	05619SU	CE  	LYC   	O320  	O320D2A     	41508	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION FOR ISSUANCE OF A C OF A AIRCRAFT TOTAL TIME: 2.8 HRS DURING THE INSPECITON OF THIS AIRCRAFT BY CIVIL A	VIATION INSPECTOR, IT WAS NOTED THAT AN ENGINE CONTROL SUPPORT BRACKET WAS CONTACTING THE LOWER TUBE OF THE ENGINE MOUNT	.  NO DAMAGE TO THE ENGINE MOUNT WAS NOTICED BUT THE PAINT FINISH WAS MARKED BY CHAFFING.  ACTION TAKEN; ENGINE MOUNT BR	ACKET 760-02043-01 WAS SLIGHTLY RELOCATED ON 760-02041-01 CONTROL SUPPORT BRACKET TO ADD CLEARANCE FOR ENGINE VIBRATIONS	 AND MOVEMENTS. (TC# 20060426001)		1	H	7	1 	3O	3	O	NT	A46CE   	E274				 
2006062100089	20060621	00089	GL  	2006	6	21	CA060426003      	2	20060424	G	7200		ENGINE          			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  		FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA				5056 				501636			(CAN) DURING CRUISE, THE CREW NOTICED THE TIT SPIKED TO 1100 DEGRESS F. THE HORSEPOWER DECREASED AND THE ZONE 1 FIRE BEL	L SOUNDED. THE E HANDLE AWAS PULLED AND THE ENGINE WAS SHUT DOWN AND THE PROPELLER FEATHERED. THE AIRCRAFT LANDED. MAINT	ENANCE CREW INSPECTED THE AIRCRAFT AND NO STRUCTURAL DAMAGE WAS NOTED. THE ENGINE QEC WILL BE REPLACED WITH A SERVICEABL	E UNIT. THE ENGINE IS BEING RETURNED AND WILL BE INSPECTED TO DETERMINE THE CAUSE OF THE FAILURE. (TC NR 20060426003)			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2006062100116	20060621	00116	CE  	2006	6	21	CA060427000      	1	20060403	G	7120	50980002185	MOUNT           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH LOWER ENGINE MOUNT FITTINGS P/N 50-980002-185 CONTAINING THE ENGINE MOUNT BARREL NUTS WERE FOUND LOOSE BY LIF	TING ON THE NON ENGINE MOUNT AND OBSERVING THE LOWER LEGS OF THE MOUNT IN RELATION TO THE FIREWALL. THE OB FITTING HAD M	ORE MOVEMENT THAN THE IB.  AN ENGINE MOUNT WOULD TAKE A HARDER LIFT TO SHOW MOVEMENT. THE FASTENERS ARE VISIBLE THROUGH 	THE NACELLE SIDE HATCHES. IF LOOSE THEY COULD EXHIBIT HEAVY SMOKING AND A BLACK GREASE LIKE BUILDUP AT EACH FASTENER. (T	C NR 20060427000)		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006062100117	20060621	00117	EA  	2006	6	21	CA060427001      	2	20060419	G	8520	13S19646	GEAR            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					CRANKSHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2154 	2154 				L2866351A			(CAN) CRANKSHAFT GEAR HAD TWO SMALL MPI INDICATIONS ON ONE GEAR TOOTH. THE GEAR ALSO HAD VISUAL DAMAGE TO 3 GEAR TEETH. 	CRANKSHAFT GEAR WAS REMOVED FROM SERVICE AND REPLACED WITH NEW GEAR. (TC NR 20060427001)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006062100118	20060621	00118	EA  	2006	6	21	CA060427002      	2	20060413	G	8520	74502	CONNECTING ROD  			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2B5    	41532	EA  					ENGINE	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				192  				L893440			(CAN) CONNECTING RODS REMOVED FROM ENGINE AT 192.0HRS DUE TO PROP STRIKE. RODS INSPECTED IAW SB439A, AND ALL 6 RODS HAD 	FRETTING AND GALLING ON THE CONNECTING ROD BEARING BORE SURFACE. THE RODS WERE REPAIRED AND RETURNED TO SERVICE. THE PRE	VIOUS OVERHAUL RECORDS HAD NOT INDICATED COMPLIANCE WITH SB439A. (TC NR 20060427002)				1	L	7	1 	3O	3	O		2A10    	E295				 
2006062100120	20060621	00120	SW  	2006	6	21	CA060427003      	1	20060419	G	2910	27810061011	LINE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT WAS SITTING IN THE HANGER WHEN MAINTENANCE NOTICED A PUDDLE OF HYD FLUID ON THE GROUND UNDER THE AIRCRAFT	 BY THE LT CENTER SECTION, STATION 27.103.  THE LINE HAD A HAIRLINE CRACK AT THE FWD BEND INSIDE THE WING CENTER SECTION	.  THE LINE WAS PART OF THE GEAR UP PRESSURE SYSTEM.  THE LINE WAS REPLACED AND GEAR SWINGS CARRIED OUT SERVICIBLE. (TC 	NR 20060427003)			2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2006062100122	20060621	00122	NM  	2006	6	21	CA060427004      	1	20060425	G	2130		SHUTOFF VALVE   			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGH FL20 THE F/E ADVISED OF PRESSURIZATION PROBLEMS. AFTER REDUCING TO 10,000 FT. CABIN INDICATED 10,	000 WITH 3 PSI DIFF.WHEN THRUST REDUCED THE DIFF WAS 0. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACE	D THE PRESSURIZATION CONTROL PANEL AND THE PRESSURE CONTROL MODULATING SOV. THE SYSTEM WAS FUNCTION CHECKED AND THE AIRC	RAFT RETURNED TO SERVICE. (TC NR 020060427004)			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006062100124	20060621	00124		2006	6	21	CA060427005      	4	20060425	G	3497	688160	WIRE            			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SWITCH	CORRODED        	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			9201 								(CAN) DURING CLIMB FLIGHT CREW SMELLED AND VISUALLY CONFIRMED SMOKE IN COCKPIT. THEY SHUTOFF WINDSHIELD HEAT AND PITOT/S	TALL HEAT AND SMOKE DISSIPATED. FLIGHT RETURNED TO POINT OF DEPARTURE FOR INVESTIGATION. MAINTENANCE FOUND SURFACE CORRO	SION ON PITOT/STALL HEAT SWITCH WIRING CONNECTORS. CONNECTORS AND SWITCH REPLACED NEW. OPERATIONS CHECK C/O SATISFACTORY	 AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060427005)			1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2006062100127	20060621	00127	EA  	2006	6	21	CA060427007      	1	20060425	G	2910	AN62498	CHECK VALVE     			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	HYD SYSTEM	SEPARATED       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			4050 	4050 							(CAN) AFTER COMPLETING A WATERDROP, BOTH WATERDOORS FAILED TO CLOSE AND LOCK. AC EXPERIENCED A COMPLETE HYDR FAILURE CAU	SED BY FAILURE OF ONE-WAY CHECK VALVE IN MAIN PRESSURE LINE AT WING STA 54 ON RT WING LE. THIS CHECK VALVE'S PURPOSE IS 	TO STOP HYD PRESSURE FLOWING BACK TO ENG DRIVEN PUMP WHEN USING GROUND TEST EQUIPMENT, AUXILARY HYD PUMP.  AC PERFORMED 	EMERGENCY LANDING GEAR EXTENSION, RETURNED TO BASE, LANDED SAFELY.  CHECK VALVE HSG IS CONSTRUCTED OF ALUMINUM. AFTER RE	CEIVING REPORTS OF FAILURE OF THIS CHECK VALVE, MFG PRODUCED SB 215-0466(STAINLESS STEEL CHECK VALVES)TO RECTIFY THIS PR	OBLEM. OUR ORGANIZATION WILL EMBODY THIS SB.  ORDERED THESE CHECK VALVES(2 PER AC) TO BE INSTALLED. (TC NR 20060427007)	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2006062100128	20060621	00128	WP  	2006	6	21	CA060428001      	2	20060427	G	7261	P1070	OIL FILTER      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			45   								(CAN) DURING A ROUTINE DAILY INSPECTION THE OIL FILTER BYPASS PIN WAS FOUND POPPED INDICATING AN OBSTRUCTED OIL FILTER. 	UPON INSPECTION OF THE FILTER IT WAS FOUND TO BE BROKEN AT THE OIL INLET MOUNTING FLANGE. PREVIOUS SDR'S HAVE BEEN ISSUE	D FOR THIS PROBLEM, REFERENCE SDR NR 20031024003, 20031024002, 20031024004. A OIL SAMPLE WAS COMPLETED ON THE ENGINE.  T	HE FILTER WHICH WAS REMOVED WAS A PMA FILTER WITH A PART NUMBER OF P-1070.  OEM FILTER NORMALLY USED IS A 3001436-1. (TC	 NR 20060428001)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2006062100130	20060621	00130		2006	6	21	CA060428002      	4	20060428	G	3421	175E28CT	TRANSFORMER     			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					INDICATOR	INOPERATIVE     	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) LOSS OF NR 1 MASI, NR 1 ALTIMETER, FDR, NR 1 ADI PITCH AND ROLL INFO, COMPASS INFO, NR 1 ESSENTIAL BUS AND LOSS 26	 VAC. CAUSE OF FAULT FOUND TO BE BROKEN WIRES AT T2XD POST NR 3.  TRANSFORMER LOCATED ON BACK OF C/B PANEL C. (TC NR 200	60428002)				2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006062100131	20060621	00131	SO  	2006	6	21	CA060428003      	1	20060425	G	2912	460635	FILTER          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) ON LANDING THE AIRCRAFT LOST HYD PRESSURE AND A EMERGENCY EXTENTION WAS SUCCESSFULLY CARRIED OUT.  ON INSPECTING T	HE CAUSE OF THE HYD LEAK THE RT FILTER BOWL WAS FOUND TO BE LEAKING. WHEN REMOVING THE BOWL THE THIRD THREAD DOWN FROM T	HE TOP OF THE BOWL WAS FOUND CRACKED (ABOUT HALF WAY AROUND THE BOWL) ALLOWING THE FILTER BOWL TO TIP TO A ANGLE ALLOWIN	G THE HYD PRESSURE TO BLOW THE FLUID OUT.  A NEW ASSY WAS INSTALLED WITH NO MORE PROBLEMS REPORTED. (TC NR 20060428003)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062300041	20060623	00041	NE  	2006	6	23	CA060501001      	2	20060426	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								19265			(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED POWER LOSS.  THE ENGINE WOULD NOT RESP	OND TO THROTTLE INPUT.  A SUCCESSFUL DEAD-STICK LANDING WAS ACCOMPLISHED.   MFG WILL INVESTIGATE THE EVENT AND WILL ADVI	SE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060501001)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006062300153	20060623	00153	EA  	2006	6	23	CA060501002      	2	20060426	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						FLAMED OUT      	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA								FA0130			(CAN) ON TAKEOFF ROTATION THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  TAKEOFF WAS ABORTED.  MFG WILL INVESTIGATE TH	E EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060501002)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006062300154	20060623	00154	EA  	2006	6	23	CA060501003      	2	20060407	G	7321	324475520	FUEL CONTROL    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				1650 							(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE FUEL	 CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC NR 20060501003)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062300155	20060623	00155	SW  	2006	6	23	CA060501004      	1	20060428	G	5610	3600151	WINDOW          			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COCKPIT LT OVERHEAD WINDOW SHOWED SIGNS OF PRESSURIZATION LEAK.  WINDOW REMOVED TO REPLACE GASKET AND FOUND WINDOW	 CRACKED.  CRACKS ORIGINATING FROM 4 SCREW ATTACHMENT HOLES.  NEW WINDOW INSTALLED. (TC NR 20060501004)					1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2006062300156	20060623	00156	SW  	2006	6	23	CA060501005      	1	20060428	G	5610	3600152	WINDOW          			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COCKPIT RT OVERHEAD WINDOW REMOVED FOR INSPECTION AFTER FINDING THE LT WINDOW CRACKED.  WINDOW FOUND TO HAVE 2 CRA	CKS ORIGINATING FROM 2 SCREW ATTACHMENT HOLES. WINDOW REPLACED WITH NEW. (TC NR 20060501005)					1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2006062300158	20060623	00158	CE  	2006	6	23	CA060501006      	1	20060417	G	7160	1019100203	VANE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	MCAULY	3AF34C	3GFR34C703  	GL  	INTAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VANE FOUND SEVERELY CRACKED ON VISUAL INSPECTION. CRACK APPEARS TO HAVE STARTED AT LEADING EDGE OF VANE FROM THE H	INGE AREA. HINGE WAS FOUND CRACKED ALSO.  DAMAGE POSSIBLY ACCELERATED DUE TO FLUTTER OF THE DAMAGED VANE. (TC NR 2006050	1006)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P60GL	 
2006062300159	20060623	00159	CE  	2006	6	23	CA060502000      	1	20060424	G	5730	5012016318	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKIN CRACKED AT HILOC FASTENERS ATTACHING SKIN TO AFT FLANGE OF WING ATTACH FITTING. CONDITION EVIDENT ON BOTH LT 	AND RT SKINS OF WING CENTER SECTION.  MFG HAS A FIELD REPAIR TO DEAL WITH THESE CRACKS. CRACKS FOUND VISUALLY WITH WING 	BOLT COVERS REMOVED. (TC NR 20060502000)				1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006062300190	20060623	00190	EU  	2006	6	23	CA060502002      	1	20060427	G	2497		WIRE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  						BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION, FOUND THE ELECTRICAL OUTLET WIRE FIN 8ME CHAFED ON FRAME 17 BETWEEN STR 28 AND 29 RT SI	DE. THE GROMMET PROTECTION HAD FALLEN OFF FROM THE FRAME AND WIRE WAS HANGING ON THE FRAME WITH THE RESULT OF ARCING AND	 FRAME DAMAGE. THE WIRING AND FRAME WAS REPAIRED. A FLEET CAMPAIGN HAS BEEN INITIATED TO INSPECT THIS AREA ON ALL A-310.	  (TC NR 20060502002)			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2006062600063	20060626	00063	EU  	2006	6	26	CA060502003      	1	20060422	G	3397		WIRE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					NAV LIGHT	BURNED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING AIRCRAFT TOWING, THE NAV 2 POSITION LIGHT CB POPPED. UNABLE TO RESET. DURING INVESTIGATION, FOUND THE 4 WIR	ES FROM THE LIGHT UNIT ASSY (7LA) BURNED ABOUT 8 INCHES LONG. WIRING WAS REPLACED AND LIGHT ASSEMBLY AND RELAY WERE REPL	ACED AS PRECAUTIONARY MEASURE. SB 30-0627-33-SB01 WILL BE INCORPORATED IN ALL AIRCRAFT TO UPGRADE THE NAVIGATIONAL LIGHT	 SYSTEM AND PREVENT THIS TYPE OF PROBLEM. (TC NR 20060502003)			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2006070300003	20060703	00003	NE  	2006	7	3	CA060502004      	2	20060424	G	7250	3020159	SHROUD          								PWA   	PT6   	PT6A135     	52043	NE  					TURBINE	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE35094			DURING HOT SECTION KIT REPAIR OF A PT6A-135 ENG, CT SHROUD SEGMENT-RETAINING RING WAS FOUND LOOSE AND PARTIALLY DISENGAG	ED FROM CT SHROUD HOUSING RETAINING GROOVE.  MINOR SHIFTING OF CT SHROUD SEGMENTS WERE NOTED (SEE PHOTOGRAPH NR 1 AND 2)	. THE CT SHROUD SEGMENT-RETAINING RING (P/N 3020159) WAS OF PRE SB 1627 CONFIG AND CT SHROUD SEGMENTS (P/N 3053094) WERE	 OF PRE SB 1628 CONFIGURATION QTY 7-RUB SPOTS WERE NOTED ON THE CT SHROUD SEGMENTS WITH RUB ON CT BLADES.  CT SHROUD SEG	MENT-RETAINING RING WAS FOUND DISTORTED AND PARTIALLY DISENGAGED FROM THE RETAINING GROOVE OF CT SHROUD HOUSING.  NO OVE	R HEATING/BURNING OF HOT SECTION PARTS NOTED.  INSPECTION OF CT SHROUD HOUSING WAS DONE AND ROUNDNESS OF ALL CRITICAL DI						4	T			E4EA				 
2006070300004	20060703	00004		2006	7	3	CA060502005      	1	20060428	G	3240	266278	BRAKE ASSY      																	MLG	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2855 	658  							FOLLOWING MX ONE OF OUR AME NOTICED THAT ONE OF OUR SPARE BRAKE ASSY P/N 2-1605-2 S/N 0378 MADE BY GOODRICH SEAM DIFFERE	NT FROM THE ONE REMOVED FROM THE A/C.  THE REMOVED BRAKE SHOWN 2 INNER SUPPORT FLANGE OF .5 INCH AND THE SPARE ONE SHOWN	 ONE SINGLE FLANGE OF 1.375 INCHES.  THE DOUBLE FLANGE IS WELL IDENTIFIED ON THE MANUFACTURER CMM BUT NO SPECIFICATION O	F THE SINGLE ONE.  THE MANUF REQUIRED THE UNIT FOR INVESTIGATION.  ON THE PRELIMINARY STATUS THIS UNIT IS NOT PER MANUF 	SPEC DRAWING.  INVESTIGATION STILL IN PROGRESS.  THIS BRAKE ASSY IS SHOWING THE FOLLOWING DATA, P/N 266-278 CHG C,  P/N 	260-903 CHG B, S/N 0378 DATE OF MAN 08-01, INSP NR 04-90.														 
2006072000321	20060720	00321	EA  	2006	7	20	CA060502006      	1	20060430	G	2913	6307901	PUMP            			DHAV  	DHC4  	DHC4A       	2800304	EA  										HYDRAULIC SYS	FAILED          	W				O				OTHER                   				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											AFTER REPLACING A PUMP DUE TO TIME-EX, NEXT 3 PUMPS INSTALLED FAILED.  ALL FAILED DUE TO SHAFT SHEARING.  FILTERS PULLED	 AFTER 1ST FAILURE, THERE WAS ONLY TRACE EVIDENCE OF METAL AND NOTHING ELSE.  FILTER WAS CLEANED, REINSTALLED IAW MM.  A	FTER NEXT 2 FAILURES FILTERS PULLED AGAIN WITH NO METAL FINDINGS.  FIRST FAILED PUMP, DISASSEMBLED IT TO TRY AND FIND CA	USE FOR FAILURE.  DISASSEMBLY FOUND 2 OF PISTONS SEIZED DUE TO OVERHEATING AND SEPARATED FROM SWASH PLATE.  1 PISTON HAD	 END TORN OFF AND HAD GENERATED A FAIR AMT OF METAL CONTAM INTERNALLY TO PUMP.  STILL INVESTIGATING CAUSE OF OVERHEATING	 THAT FAILED ORIG PUMP.  UNABLE TO CHECK OTHER 2, SHIPPED ALREADY.  AWAITING THE REPAIR SHOPS REPORT.	2	H	7	2 	4R				1A19    					 
2006070500031	20060705	00031		2006	7	5	CA060502008      	4	20060427	G	2562	MN1300	BATTERY         	ACK         		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	ELT	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			5    			026049					(CAN) ELT BATTERIES LEAKED. (TC NR 20060502008)						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
2006070300037	20060703	00037	SW  	2006	7	3	CA060503001      	1	20060426	G	2997	212075369001	WIRE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CLOG INDICATOR	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA			181  								DURING ROUTINE INSPECTION, THE INDICATOR WAS SHOWING RED INDICATING FILTER BYPASS CONDITION.  UPON INVESTIGATION BY AME 	NONE OF THE FILTERS HAD BYPASSED ON THE INTEGRATED VALVE AND FILTER ASSEMBLY.  AT THIS TIME IT WAS DETERMINED THAT THE C	LOGGING INDICATOR WAS THE PROBLEM AND THIS WAS REPLACED AND FUNCTION CHECKED OK.  6.1 HOURS LATER THE SAME CONDITION WAS	 NOTICED ON THE CLOG INDICATOR AND THE WIRES WERE FOUND TO HAVE BROKEN OFF.  THE WIRES WERE SOLDERED BACK AND INDICATOR 	REPLACED AT A LATER DATE.		1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006070300038	20060703	00038	CE  	2006	7	3	CA060503002      	1	20060501	G	2435	23078019	STARTER GEN     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT ENGINE	SEIZED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				30704							IN CRUISE, LT GEN FAIL LIGHT ILLUM.  ATTEMPT TO RESET GEN, IT WOULD NOT COME ON LINE.  AFTER GEN FAILURE, LT ENG FIRE WA	RN IND ALSO CAME ON.  LT ENG WAS SHUT DOWN AND ENG FIRE BOTTLE WAS DISCHARGED AS PER RELATED CHECKLIST.  LANDED SAFELY. 	 MX INSPECTED A/C, FOUND LT STARTER-GEN FAILED INTERNALLY AND PAINT ON UNIT BLISTERED INDICATING IT HAD DRASTICALLY OVER	HEATED.  INVESTIGATION REVEALED STARTER-GEN DRIVE SPLINE HAD SHEARED.  APPROPRIATE INSPECTIONS CARRIED OUT PER MM.  STAR	TER GEN AND FIRE BOTTLE REPLACED, A/C RETURNED TO SERVICE.  FIRE WIRE IS LOCATED IN CLOSE PROX STARTER-GEN.  STARTER-GEN	 INSTALLED PREV DAY IN REPAIRED CONDITION, AT TIME OF FAILURE STARTER-GEN HAD ONLY ACCUMULATED 1.6 HOURS SINCE REPAIR.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006070300039	20060703	00039	CE  	2006	7	3	CA060503003      	1	20060501	G	2435	23078019	STARTER GEN     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											IN CRUISE, LT GEN FAIL LIGHT ILLUM.  CREW ATTEMPT RESET, GEN BUT WOULD NOT COME ON LINE.  AFTER GEN FAILURE,  LT ENG FIR	E WARNING INDICATION ALSO CAME ON.  LT ENG WAS SHUT DOWN AND ENG FIRE BOTTLE DISCHARGED PER CHECKLIST.  A/C LANDED SAFEL	Y.  MX INSPECT A/C AND FOUND LT STARTER-GEN FAILED INTERNALLY AND PAINT ON UNIT WAS BLISTERED INDICATING DRASTICALLY OVE	RHEATED. INVESTIGATION REVEALED, STARTER-GEN DRIVE SPLINE SHEARED.  INSPECTIONS PER MM.  STARTER GEN AND FIRE BOTTLE REP	LACED, A/C RETURNED TO SERVICE.  FIRE WIRE IS LOCATED IN CLOSE PROXIMITY TO STARTER-GEN.  STARTER-GEN INSTALLED PREVIOUS	 DAY IN A REPAIRED CONDITION, AT TIME OF FAILURE STARTER-GEN HAD ONLY ACCUMULATED 1.6 HOURS SINCE REPAIR.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006062600010	20060626	00010	CE  	2006	6	26	CA060503004      	1	20060501	G	2435		SHAFT           	LEARSIEGLER 		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	STARTER GEN	SHEARED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				307  		94094					IN CRUISE, LT GEN FAIL LIGHT ILLUMINATED.  ATTEMPTED TO RESET GEN BUT IT STILL WOULD NOT COME ON LINE.  SHORTLY AFTER GE	N FAILURE, LT ENG FIRE WARNING IND ALSO CAME ON.  LT ENG WAS SHUTDOWN AND ENG FIRE BOTTLE WAS DISCHARGED.  MX INSPECTED 	A/C. FOUND LT STARTER GEN HAD FAILED INTERNALLY AND PAINT ON UNIT WAS BLISTERED INDICATING IT HAD DRASTICALLY OVERHEATED	.  ALSO REVEALED STARTER GEN DRIVE SPLINE HAD SHEARED.  INSP CARRIED OUT IAW MM.   STARTER GEN, FIRE BOTTLE WERE REPLACE	D, AND A/C RETURNED TO SERV.  NOTED FIRE WIRE IS LOCATED IN CLOSE PROX TO STARTER/GEN.  STARTER/GEN WAS INSTALLED PREVIO	US DAY IN A REPAIRED CONDITION, AT TIME OF FAILURE STARTER/GEN HAD ONLY ACCUMULATED 1.6  HRS SINCE REPAIR.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006070300040	20060703	00040	NM  	2006	7	3	CA060503007      	1	20060427	G	5270	AE4888100	SWITCH          			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					CARGO DOOR	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											AT FL380, MAIN CARGO DOOR LIGHT ILLUMINATED ACCOMPANIED BY "LATCH LOCK PIN NOT ENGAGED" ON DOOR CONTROL PANEL.  A/C TURN	ED BACK AND DURING DESCENT LIGHTS REMAINED ILLUMINATED UNTIL CABIN PRESSURE WAS REDUCED TO MINIMUM AT WHICH POINT BOTH L	IGHTS HAVE EXTINGUISHED. UPON ARRIVAL, MAINTENANCE FOUND THAT FORWARD LATCH PIN MICRO-SWITCH TRIGGER PLATE COTTER PIN WA	S INFERRING WITH A RIVET TAIL ON THE DOOR SKIN DOUBLER. THIS WAS A POSSIBLE CAUSE FOR DOOR INDICATION. AFTER ACCESS TO T	HE AREA WAS PROVIDED BY REMOVING THE ACCESS PANEL, TRIGGER PLATE WAS FREED UP BY REPOSITIONING THE COTTER AND OPERATIONA	LLY CHECKED SERVICEABLE. SWITCH AND PLATE ASSY REPLACED AS A PRECAUTION.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006070300041	20060703	00041	NE  	2006	7	3	CA060503008      	2	20060428	G	7310		B-NUT           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE FUEL	LOOSE           	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											DURING T/S OF START SYS OF SISTER A/C, START INJECTOR ON RT SIDE OF ENG WAS REMOVED FOR COMPARISON INSPECTION.  AFTER IN	SPECTION ORIG INJECTOR WAS INSTALLED.   NO CROSS CHECK INSPECTION, NOR GROUND-RUN WERE COMPLETED.  NEXT DAY PILOT NOTED 	A STAGNATED/HUNG START, AND ADVANCED THROTTLE TO EMERG POSITION TO LIGHT OFF ENGINE.  ENG WAS THEN SHUT DOWN AND MX WAS 	CALLED.  ENGINEER ON SITE GOT PILOT TO  ATTEMPTED ANOTHER START AND VISUALLY NOTICED SPRAYING FUEL IN ENG BAY, START WAS	 ABORTED.  UPON CLOSE INSPECTION, B-NUT ON START INJECTOR LINE WAS FOUND TO HAVE NO TQE AND LOOSE ON TEE FITTING.  TIGHT	ENED LINE TO PROPER TQ AND THE START WAS ATTEMPTED AGAIN.   PERFORMED START/GROUND-RUN/LEAK CHECK ALL SYSTEMS FUNCTIONIN	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006070300042	20060703	00042	CE  	2006	7	3	CA060503009      	1	20060402	G	7800	780000	EXTRACTOR       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					EXHAUST GAS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING INSPECTION THE ENGINEER NOTICED A CRACK IN ONE OF THE EXHAUST GAS EXTRACTORS.  FURTHER INVESTIGATION ON THE REMAI	NING EXHAUST GAS EXTRACTORS REVEALED CRACKS AS WELL.  THE PARTS WERE REPAIRED AND REINSTALLED.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006070300043	20060703	00043	EA  	2006	7	3	CA060503010      	1	20060420	G	5610	601R3303318	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			DE	DESCENT        	1			CA											RIGHT FORWARD WINDSHIELD CRACKED DURING DESCENT FROM 350 TO 330.  REMOVED AND INSTALLED F/O'S WINDSHIELD.  RIGHT FORWARD	 WINDSHIELD CRACKED DURING DESCENT FROM 350 TO 330.  REMOVED AND INSTALLED F/O'S WINDSHIELD.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006071900015	20060719	00015		2006	7	19	CA060504001      	2	20060317	G	7321	442324	HMU             			BOMBDR	BD700 	BD7001A10   	1390006	GL  										LT ENGINE	ACTIVATED       	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			173  								(CAN) CREW TAXIED OUT,TESTED THRUST REVERSER JUST PRIOR TO TAKEOFF.  PLACED BOTH PWR LEVERS IN T/O DETENT, STARTED T/O R	OLL.  FELT AC SWERVE LT OF CTR LINE.  CREW NOTICED LT ENG WAS STILL AT IDLE WITH PWR LEVER IN TAKEOFF DETENT.  CREW ABOR	TED TAKEOFF.  NO EICAS MESSAGES WERE POSTED DURING THIS EVENT.  LT AND RT N1 BUGS BOTH TARGETED T/O PWR ON DISPLAY DURIN	G THIS EVENT.  CREW TAXIED OFF RUNWAY.  CREW TRIED TO RUN-UP LT ENG ON RAMP, IT WOULD NOT ACCELERATE. NO EICAS MESSAGES 	POSTED. CHECKED TIME LIMITED DISPATCH, STATUS CLEAR FOR LT ENG.  LT ENG EEI DOWNLOAD REVEALED THAT HMU METERING VALVE DI	D NOT APPEAR TO RESPOND TO THRUST COMMAND.  HMU REMOVED AND REPLACED.  BOTH ECU'S ALSO REPLACED.  (TC NR 20060504001)	2	L	7	2 	4F			RT	T00003NY					 
2006070300097	20060703	00097	EA  	2006	7	3	CA060504002      	1	20060327	G	2730	4006719904	DRIVE ASSY      			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ELEVATOR SERVO	FAILED          	W				O				OTHER                   				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											CLIMB TO FL 120, AT FL 085 COMMUNICATION ESTABLISHED WITH APPROACH, AND INSTRUCTED TO MAINTAIN FL 080.  CAPT TOLD GO TO 	DESCENT AND MAINTAIN 080, AUTOPILOT WAS ENGAGED, CAPT REALIZED A/C WAS STILL CLIMBING AND THE WHEEL TRIM WAS TRIMMING FU	LL NOSE-UP, FO PUSHING ON CONTROL COLUMN, CAPT IMMEDIATELY DISENGAGE AUTO-PILOT, RESULT WAS A SUDDEN PITCH ATTITUDE CHAN	GE, A/C STARTED TO VIBRATE AND A VERY SCARY MOVEMENT OF A/C FOLLOWED.  FLT RESUMED NORMALLY AFTERWARD, AND LANDED SAFELY	 AT AIRPORT. THE FOLLOWING WAS CARRIED OUT TO T/S & RECTIFY SNAG.  AUTO-PILOT FUNCTION CHECKED, FOUND TOUCH CONTROL STEE	RING NOT WORKING.  AUTO-PILOT COMPUTER REPLACED, ELEVATOR SERVO REPLACED, AS PER MM 22-10-00.  AUTO-PILOT FUNCTION CHECK	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006070300108	20060703	00108	GL  	2006	7	3	CA060504003      	2	20060428	G	7260	23005747	BEARING CAGE    	ALLSN       	23005655    						ALLSN 	250C  	250C30P     	03013	GL  					GEARBOX	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6078 			CAG95018					BEARING, REMOVED FROM GEARBOX DURING 3500 HOURS INSPECTION, HAS BEEN PREVIOUSLY ASSEMBLED WITH ONE BALL NOTICEABLY SMALL	ER THAN THE OTHER BALLS IN THE BEARING ASSEMBLY.  REF ROLLS-ROYCE IPC, 14W4, 72-60-00, FIG.2, P.5, ITEM 39.										3	U			E1GL				 
2006070300109	20060703	00109	SO  	2006	7	3	CA060504004      	2	20060426	G	7200		ENGINE          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  						FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA											ENGINE QUIT ON APPROACH, ONCE LANDED THE PILOT RESTARTED THE ENGINE AND TAXIED TO THE PARKING AREA.  THE AIRCRAFT WAS IN	SPECTED AND IT SEEMS TO BE FUEL PRESSURE THAT WAS THE CAUSE OF THE ENGINE FAILURE.  RIGGING AND MULTIPLE TESTS WERE COND	UCTED AND THE PROBLEM DID NOT RE-APPEAR.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20080520			2008	5	20	CA060504005      	4	20060421	G	2562	GS21	BATTERY         			AYRES 	S2    	S2RR1820    	0970215	SO  	WRIGHT	R1820 	R182099     	67020	EA  	HAMSTD	23E	23E50       	NE  	ELT	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FOUND CORROSION AROUND BATTERY. (TC NR 20060504005)						1	L	7	1 	4R	4	R		A4SW    	5E10	6	C	P603	 
2006070300110	20060703	00110	CE  	2006	7	3	CA060504006      	1	20060503	G	5520	11561010325	TORQUE TUBE     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			176  								WHILE CHECKING THE ELEVATOR SYSTEM FOR FREEDOM OF MOVEMENT, EXCESSIVE PLAY WAS NOTICED IN THE LEFT ELEVATOR.  THE PLAY W	AS ISOLATED TO THE ELEVATOR TORQUE TUBE FITTING.  THE TORQUE TUBE WAS REPLACED WITH A NEW ASSEMBLY. THE TORQUE TUBE WAS 	INSPECTED AND FOUND TO HAVE OVER-SIZED TAPER PINS INSTALLED FROM THE MANUFACTURE.				1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2006070300111	20060703	00111	EA  	2006	7	3	CA060504007      	1	20060425	G	2760	600913563	BRACKET         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					TRANSMITTER	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3261 								PRIOR TO A/C DEPARTURE, AND DURING A GROUND CHECK OF THE FLIGHT SPOILERS, THE LT SPOILER INDICATED IT WAS EXTENDED WHILE	 SURFACE WAS PHYSICALLY IN STOWED POSITION (AS COMMANDED BY SPOILER LEVER).  FLIGHT SPOILER POSITION TRANSMITTER WAS INS	PECTED AND FOUND TO BE LOOSE.  MAINTENANCE SECURED TRANSMITTER, AND ITEM WAS DEFERRED IN ACCORDANCE WITH  MEL.  BRACKET 	WAS REPLACED UPON RETURN IN ACCORDANCE WITH AMM.  BRACKET WAS FOUND WITH FRACTURES IN TWO PLACES ON BORE OF PART.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006070300112	20060703	00112	SW  	2006	7	3	CA060504008      	1	20060503	G	6410	206016201131	BLADE           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAIL ROTOR	OUT OF TOLERANCE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			548  								THE BLADE WAS SENT TO ROTOR BLADES INCORPORATED FOR INSPECTION AS REQUIRED BY ASB 206L-04-127 REVISION C PART 3 AND BY A	D CF-2004-05R1 PART D. ROTOR BLADES INCORPORATED HAS REPORTED THAT THE BLADE HAS FAILED THE INSPECTION AND IS BELOW TOLE	RANCE.  THE BLADE IS HELD FOR DISPOSAL AT ROTOR BLADES INCORPORATED AT THE REQUEST OF BELL HELICOPTER.  ROTOR BLADES INC	ORPORATED HAS PROBABLY FILED AN SDR IN THE USA.			1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006070500001	20060705	00001	EA  	2006	7	5	CA060504009      	2	20060504	G	8520	76097	CAMSHAFT        	LYC         	O320E2A     	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2069 			L1929227A					CYLINDERS REMOVED FOR ON CONDITION INSPECTION, CAMSHAFT FOUND TO HAVE SEVERE CORROSION AND DAMAGE TO ALL LOBES.  ENGINE 	DISASSEMBLED FOR OVERHAUL, AND THE FOLLOWING WAS FOUND; BOTH INTAKE LOBES ON CAMSHAFT DESTROYED, ALL TAPPET BODIES DAMAG	ED, OIL PUMP HOUSING P/N 78528 DAMAGED BEYOND REPAIR, AND OIL PUMP IMPELLERS DAMAGED.  ALL INTERNAL COMPONENTS OF THE EN	GINE HAD MINOR DAMAGE FROM METAL CONTAMINATION IN THE OIL.			1	L	7	1 	3O	3	O		2A13    	E274				 
2006070500004	20060705	00004	CE  	2006	7	5	CA060505003      	1	20060505	G	5712		RIB             			CESSNA	185   	185F        	2072820	CE  										LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA											RIB ASSEMBLY ON WING CRACKED AT ATTACHMENT POINT TO SPAR.  SPAR WAS UNDAMAGED BUT TRACK WAS REPLACED.  AIRCRAFT HAS 1087	0.3 HOUR ON IT AT TIME OF REPAIR POSSIBLE TIME FATIGUED PART.					1	H	7	1 	3O				3A24    					 
2006070500007	20060705	00007	SO  	2006	7	5	CA060508001      	2	20060504	G	7310	630662	FUEL LINE       	CONT        	IO360G      	CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	REAR ENGINE	BROKEN          	W				A				UNSCHED LANDING         				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA						355960					SHORTLY AFTER TAKEOFF, THE PILOT OF A CESSNA 337 NOTICED THAT FUEL PRESSURE ON THE REAR ENGINE BEGAN TO DROP OFF AND THE	 ENGINE BEGAN TO RUN ROUGH. TURNED ON THE ELECTRIC BOOST PUMP AND THE ENGINE CONTINUED TO RUN NORMALLY.  ELECTED TO RETU	RN TO THE AIRPORT AND LANDED WITHOUT INCIDENT.  AN INSPECTION OF THE REAR ENGINE REVEALED A BROKEN FUEL INJECTOR LINE FO	R THE NUMBER SIX CYLINDER.  THE LINE HAD SEVERED COMPLETELY OFF FROM THE FUEL MANIFOLD SPIDER.  A SERVICEABLE LINE WAS I	NSTALLED AND LEAK CHECKS CARRIED OUT.  THE AIRCRAFT WAS RETURNED TO SERVICE.		1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2006070500011	20060705	00011	NM  	2006	7	5	CA060508002      	1	20060506	G	5610	58935734	WINDOW          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											ON APPROACH FLIGHT, CREW REPORTED THAT THE FIRST OFFICERS NR 4 EYEBROW WINDOW HAD CRACKED.  ON ARRIVAL, WINDOW WAS INSPE	CTED AND REPLACED.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006070500017	20060705	00017	NE  	2006	7	5	CA060508003      	2	20060508	G	7321	CL12068161	RELAY           			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  					NR 1 ECU	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A "C" CHECK INSPECTION, DURING THE OPERATIONAL CHECK OF "DUPLICATED ECU POWER SUPPLIES AND INTEGRITY OF DIODES CH	ECK" (TASK 73-20-02), THE BASE OF THE RELAY 7611-K3 (ENG NR 1 ECU) WAS FOUND UNGLUED.  WITH THIS RELAY DISCONNECTED, THE	 ECU OF THIS ENGINE GOES IN MANUAL MODE DUE TO THE FULL LOSS OF POWER.  IN ADDITION, THE FREE RELAY BASE RESULT IN A HI-	RISK OF SHORTING WITH THE STRUCTURE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006070500112	20060705	00112	EU  	2006	7	5	CA060508004      	1	20060501	G	2932	973811430	PRESSURE SWITCH 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYDRAULIC SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CL	CLIMB          	1			CA			10610								AFTER TAKEOFF AND GEAR UP SELECTION WAS COMPLETED, THE CREW HAD A HYD. LIGHT ON THERE CAWS.  RETURNED AND UPON GEAR DOWN	 SELECTION THE GEAR MOTOR FAILED TO RUN.  GEAR DID A FREE FALL AND LOCKED DOWN.  ONCE IN HANGAR IT WAS NOTED THAT HYDRAU	LIC CONTROL CB WAS OUT.  CB WAS RESET AND THE DEFECT COULD NOT BE DUPLICATED.  PLEASE NOTE THIS AIRCRAFT HAD BEEN EXPERI	ENCING HYDRAULIC LIGHTS ON LANDING. (THIS NOTIFIED CREW THE PUMP HAD RUN MORE THAN SIX TIMES IN THE PAST HOUR OF FLIGHT)	 THIS DEFECT COULD NEVER BE DUPLICATED IN THE HANGAR EITHER.  MAINTENANCE REPLACED THE HYDRAULIC SYSTEM PRESSURE SWITCH 	AS A PRECAUTIONARY MEASURE AND NEITHER DEFECT HAS SINCE REOCCURRED.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006070500116	20060705	00116	NE  	2006	7	5	CA060508006      	2	20060508	G	7321	CL12068161	RELAY           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					NR 2 ECU	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING THE ACCOMPLISHEMENT OF THE TASK 7320/02 (OPERATIONAL CHECK OF DUPLICATED ECU POWER SUPPLIES AND INTEGRITY OF DIOD	ES), THE 7611-K4 (ENG NR 2 ECU) RELAY BASE WAS FOUND UNGLUED.  THIS SITUATION REMOVED ALL THE POWER FOR THE ECU AND LIVE	 THE ENGINE IN MANUEL MODE.  IN ADDITION, THE FREE RELAY BASE GIVE THE OPPORTUNITY OF SHORTING TO THE ELECTRICAL PINS WI	TH THE ADJACENT STRUCTURE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006062600126	20060626	00126	SO  	2006	6	26	CA060508007      	1	20060418	G	2710	62701123	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING EVENT INSPECTION OF DETAILED WING (RT) BROKEN STRANDS WERE OBSERVED ON RT AILERON BALANCE CABLE AS IT PASSED OVER	 A PULLEY AT WING STATION 22.00.  CABLE AND PULLEY WERE REMOVED.  CABLE WAS REPLACED NEW, PULLEY WAS CLEANED INSPECTED, 	LUBRICATED AND RETURNED TO SERVICE.  THERE IS VERY LITTLE CONTROL CABLE DEFLECTION OVER THE PULLEY'S IN THIS LOCATION.  	ROUTINE CLEANING AND LUBRICATION OF PULLEY MAY FORESTALL CONTROL CABLE WEAR IN THIS AREA.			1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062600128	20060626	00128	SO  	2006	6	26	CA060508008      	1	20060418	G	5343	86444800	SPAR            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3585 								DURING COMPLETION OF PIPER SB 1143 A 3/4" CRACK WAS OBSERVED RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE NLG DRAG 	LINK TRUNNION MOUNTING.  FURTHER INVESTIGATION REVEALED A 1/2" CRACK RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE R	T DRAG LINK TRUNNION MOUNTING.  AIRCRAFT LT AND RT NOSE SPAR ASSEMBLIES WERE REPLACED NEW.				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062600011	20060626	00011	SO  	2006	6	26	CA060508009      	1	20060424	G	5343	86444800	SPAR            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4063 								DURING COMPLETION OF SB1143, A 1 INCH CRACK WAS OBSERVED RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE LT DRAG LINK 	TRUNNION MOUNTING.  FURTHER INVESTIGATION REVEALED A .5 INCH CRACK RADIATING OUT FROM LOWER AFT BOLT HOLE OF RT DRAG LIN	K TRUNNION MOUNTING.  AIRCRAFT LT AND RT NOSE SPAR ASSEMBLIES WERE REPLACED NEW.				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062600012	20060626	00012	SO  	2006	6	26	CA060508010      	1	20060418	G	5712	7847506	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	WS 49.25	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3599 								DURING COMPLETION OF INSPECTION REQUIRED SB 1161, A 2 INCH LONG CRACK WAS OBSERVED IN THE LT WING RIB AT STN 49.25.  THE	 CRACK WAS LOCATED IN THE BEND RADIUS UNDER THE MAIN LANDING GEAR (MLG) SIDE BRACE ASSEMBLY (PN 95643-08).  A NEW RIB WA	S INSTALLED.  BEFORE RE-INSTALLATION SHARP CORNERS ON THE SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CH	AFING THE RIB IN THE AFFECTED AREA.			1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062600013	20060626	00013	SO  	2006	6	26	CA060508011      	1	20060418	G	5712	7847507	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	WS 49.25	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3599 								DURING COMPLETION OF INSPECTION REQUIRED SB 1161, A 3 IN LONG CRACK WAS OBSERVED IN THE RT WING RIB AT STN 49.25.  THE C	RACK WAS LOCATED IN THE RIB BEND RADIUS UNDER THE MLG SIDE BRACE MOUNT (PN 95643-09).  A NEW RIB WAS INSTALLED.  BEFORE 	RE-INSTALLATION SHARP CORNERS ON SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING WITH THE RIB IN THI	S AREA.			1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062600014	20060626	00014	SO  	2006	6	26	CA060508012      	1	20060424	G	5712	7847507	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	WS 49.25	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4099 								DURING COMPLETION OF INSPECTION REQUIRED BY PIPER SB 1161, A 2.5 INCH LONG CRACK WAS OBSERVED IN THE RT WING RIB AND 3 I	NCH LONG IN THE LT WING RIB AT STN 49.25.  THE CRACKS WERE LOCATED IN THE BEND RADIUS UNDER THE MLG SIDE BRACE MOUNT (PN	 95643-09).  NEW RIBS WERE INSTALLED.  BEFORE RE-INSTALLATION SHARP CORNERS ON SIDE BRACE MOUNT WERE POLISHED TO REDUCE 	THE POSSIBILITY OF CHAFING THE RIBS IN THIS AREA.			1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006070500191	20060705	00191	WP  	2006	7	5	CA060508013      	1	20060506	G	6730		SEAL            	ROBSIN      	D2121       	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			731  			4655					(CAN) SERVO FOUND TO HAVE AN EXCESSIVE OIL LEAK FROM THE UPPER SEAL.  THE SERVO WAS REPLACED WITH A SERVICEABLE UNIT.  T	HIS SERVO HAD BEEN REMOVED 109.4 HOURS BEFORE FOR A SEAL LEAK.  THE SERVO WAS RETURNED AT THAT TIME TO MFG FOR REPAIR. (	TC NR 20060508013)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006070500192	20060705	00192	SW  	2006	7	5	CA060508014      	1	20060508	G	3213	MS1699799	BOLT            			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67      	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	MLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			189  								(CAN) DURING THE ACCOMPLISHMENT OF THE ANNUAL INSPECTION OF THE LANDING GEAR, MAINTENANCE STAFF NOTICED THAT THE LT IB A	ND RT OB TORQUE PLATES THAT SECURE THE BRAKE CALIPERS WERE LOOSE. THE 6 BOLTS TAHT SECURE THE TORQUE PLATES TO THE MAIN 	WHEEL AXLE ASSEMBLY WERE LOOSE CAUSING THE PLATES TO SHIFT AS THE WHEELS WERE ROTATED BACK AND FORTH. THE OTHER AIRCRAFT	 IN THE FLEET WILL BE INSPECTED TO ENSURE ALL THE BOLTS ARE TIGHT. (TC NR 20060508014)			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2006070500193	20060705	00193	CE  	2006	7	5	CA060509000      	1	20060501	G	5330	5012015682	SKIN            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKIN P/N 50-120156-82 (PRESSURE VESSEL) EXIBITING WEAR MARK ALONG FASTENER ROW ATTACHING FILLET P/N 50-420023-24 T	O IT. WEAR MARK NOT READILY VISIBLE WITHOUT PULLING AWAY FILLET FROM SURFACE OF SKIN. WEAR MARK IS CAUSED BY LOOSENING O	F FILLET TO SKIN FASTENERS AND SUBSEQUENT CHAFFING. UN-NOTICED, THIS CONDITION COULD LEAD TO PRESSURE VESSEL RUPTURE. (T	C NR 20060509000)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006070500195	20060705	00195	CE  	2006	7	5	CA060509001      	1	20060502	G	5753	122101015	FLAP TRACK      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT IB FLAP TRACK, FWD ANGLES, AGAINST SPAR FOUND CRACKED AT BEND RADIUS, LOWER END. (TC NR 20060509001)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006070500198	20060705	00198	CE  	2006	7	5	CA060509002      	1	20060428	G	3340	S21604	SWITCH          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LANDING LIGHT	DEFECTIVE       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOT WAS IN CRUISE WITH LANDING LIGHT ON, WHEN SHE SMELLED SMOKE AND NOTICED SMOKE COMING FROM LANDING LIGHT SWIT	CH. SMOKE STOPPED WHEN SWITCH TURNED OFF AND PILOT SQUAWKED 7700 FOR HELP AND SHE WAS ADVISED TO LAND. AGAIN IT WAS CONF	IRMED THAT THE SWITCH WOULD SMOKE WHEN TURNED ON, BUT NOT WHEN OFF. PILOT FLEW AIRCRAFT HOME WITH LANDING LIGHT OFF, WHE	RE MAINTENANCE CONFIRMED PROBLEM AND REPLACED THE SWITCH.  NOTE: THIS IS NOT AN UNCOMMON PROBLEM WITH THESE SWITCHES. (T	C NR0 20060509002)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006070500199	20060705	00199	CE  	2006	7	5	CA060509003      	1	20060501	G	2410	DOFF10300F	ALTERNATOR      			CESSNA	150   	150C        	2071808	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STATOR AND RECTIFIER DEFECTIVE. (TC NR 20060509003)						1	H	7	1 	3O	3	O		3A19    	E252				 
2006070500117	20060705	00117	EU  	2006	7	5	CA060509004      	1	20060508	G	2434	AN960JD616	WASHER          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	STARTER GEN	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14635								WHILE CONDUCTING A VISUAL INSPECTION OF THE PORT STARTER GENERATOR GROUND POINT SEALANT REMOVED.  IT WAS DISCOVERED THAT	 THE ALUMINUM WASHERS, P/N AN960JD616, BETWEEN THE GROUND POINT ATTACH BOLT AND THE BRACKET HAD MELTED.  THE GROUND POIN	T BRACKET SHOWED EVIDENCE OF ARCING AND THE GROUND POINT ATTACH BOLT SHOWED EVIDENCE OF CORROSION.  INSPECTION OF A SECO	ND AIRCRAFT C-GMNM S/N 340B-364 REVEALED CORROSION ON THE ALUMINUM WASHERS P/N AN960JD616.  AN INSPECTION OF THE BALANCE	 OF SAAB 340 FLEET IS ON GOING.		2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2006070500288	20060705	00288	EA  	2006	7	5	CA060509006      	2	20060504	G	8530	SL32006WAZOP	CYLINDER HEAD   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1800 								(CAN) ONE CRACK RUNNING BETWEEN UPPER SPARK PLUG HOLE AND EXHAUST VALVE.  SECOND CRACK FROM LOWER SPARK PLUG HOLE EXTEND	ING APPROX 1 INCH INTO CYL HEAD. (TC NR 20060509006)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006071100121	20060711	00121	WP  	2006	7	11	CA060509007      	1	20060504	G	3213	369H600131	STRUT           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A 100 HOUR INSPECTION OF THE AIRCRAFT THE ENGINEER NOTICED SOME CRACKED PAINT ON THE BOTTOM SIDE OF TH	E STRUT EMINATING FROM THE LANDING GEAR BRACE BOLT HOLE.  HE THEN REMOVED SOME OF THE PAINT AND REVEALED A CRACK 1.5 INC	HES LONG GOING OUTWARDS TOWARD THE LANDING GEAR DAMPER ATTACH POINT. (TC NR 20060509007)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006070500289	20060705	00289	EU  	2006	7	5	CA060509008      	1	20060505	G	3320	E033601	BALLAST         			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	LIGHT	OVERHEATED      	W				O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) LAMP SOCKET OVERHEATED AT BALLAST 27LG CAUSING SMOKE ODOR IN CABIN. (TC NR 20060509008)						2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006070500132	20060705	00132	NE  	2006	7	5	CA060509009      	2	20060414	G	7260	0235237790	CHIP DETECTOR   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	SHORTED         	W				O				OTHER                   				N			FALSE WARNING             			HO	HOVERING       	1			CA			1649 								IN FLIGHT, THE PILOT NOTICED THE ENGINE CHIP LIGHT ILLUMINATE.  LANDED AND THE ENGINEER LOOKED AT THE CHIP DETECTORS AND	 NO METAL WAS FOUND.  THEN RE INSTALLED THE CHIP DETECTORS AND CARRIED OUT A GROUND RUN.  AFTER 10 MINUTES OF GROUND RUN	NING ANOTHER CHIP LIGHT OCCURRED.  AFTER THE ENGINE COOLED OFF THE CHIP LIGHT WOULD GO OUT.   THE ELECTRICALLY OPERATED 	CHIP DETECTOR WAS FOUND TO CAUSE A LIGHT WHEN HOT AND THEM EXTINGUISH WHEN COOLED OFF.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006070500290	20060705	00290	NE  	2006	7	5	CA060510001      	2	20060508	G	7314	B8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PUMP WAS FOUND TO BE NOISY DURING ENGINE PRIMING.  WHEN THE PUMP WAS REMOVED THE HOUSING AROUND THE ELECTRIC MOTOR	 WAS ALSO FOUND TO BE LOOSE. (TC NR 20060510001)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006070500133	20060705	00133	CE  	2006	7	5	CA060510002      	1	20060502	G	5541	24130015	RIB             			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7635 	7635 							AT A 100 HOUR INSPECTION A CRACK WAS FOUND UNDER THE LEFT INBOARD RUDDER BAR BLOCK, AT THE MOST FORWARD BOLT HOLE.  RUDD	ER BLOCK HAD ABNORMAL MOVEMENT.  CRACK COULD ONLY BEEN SEEN AFTER BLOCK WAS REMOVED.					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2006070500134	20060705	00134	NE  	2006	7	5	CA060510003      	2	20060503	G	7321	430128806	FCU             			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				A	M		FLAME/FIRE                	OVER TEMP                 		TX	TAXI/GRND HDL  	1			CA			3283 	1218 							ON SECOND START OF THE DAY, A FLAME WAS SEEN COMING OUT OF EXHAUST AND A RAPID INCREASE IN TURBINE OUTLET TEMPERATURE.  	AFTER SEVERAL MINUTES, A SECOND ATTEMPT WAS GIVEN WITH SIMILAR RESULTS.					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2006070500135	20060705	00135	EA  	2006	7	5	CA060510004      	2	20060510	G	7250		BLADE           								PWA   	PT6   	PT6*        	52043	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3721 								FAILED ENGINE SENT TO O/H SHOP WHERE ALL CT BLADES WERE FOUND DAMAGED/BROKEN.  SIGNIFICANT DOWNSTREAM DAMAGE WAS EVIDENT	.  CAUSE OF CT BLADE FAILURE NOT DETERMINED BUT LUGS WERE BROKEN OFF THE CT STATOR AS A RESULT OF HEAVY CONTACT BETWEEN 	CT DISK AND CT STATOR.   ENGINE OEM IS CURRENTLY INVESTIGATING RECENT RASH OF CT BLADE FAILURES ON THIS PT6A-114 ENGINE 	FAMILY.								3	T			E2NE				 
2006070500136	20060705	00136	CE  	2006	7	5	CA060510007      	1	20060507	G	5220		SHAFT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	EMERGENCY EXIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											INTERNAL CABIN PORTION OF PHASE 3 INSPECTION FOUND BOTH RT EMERG EXIT DOORS WOULD NOT OPEN FROM INSIDE.  BOTH DOORS WERE	 REMOVED VIA EXT HANDLE AND DISASSEMBLED, UPON INSPECTION, FOUND RT COUPLING P/N 129-514065-2 WAS MATED TO SHAFT P/N 129	-514033-2 AT ALL TIMES.  HANDLE LINKAGE WAS REMOVED AND DISASSEMBLED.  FOUND THERE WAS JUST ENOUGH SURFACE CORROSION ON 	EXT SURFACE OF THE SHAFT AND INTERNAL SURFACE OF COUPLER TO KEEP EXTERIOR HANDLE ENGAGED AT ALL TIMES WHICH IN TURN USED	 THE OUTSIDE HANDLE AS A STOP WHEN TRYING TO OPEN THE EXIT FROM INSIDE.  COUPLER WAS REMOVED FROM THE SHAFT AND SURFACE 	CORROSION REMOVED.  UNIT WAS REASSEMBLED AND EMERG EXIT HANDLE FUNCTION TESTED SERVICEABLE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006071100137	20060711	00137		2006	7	11	CA060510009      	1	20060508	G	8011	629435	SHAFT           	CONT        							CONT  	O520  	IO520MB     	17032	SO  					STARTER ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						277948R					THREE GEAR TEETH BROKEN OFF AND MISSING.  ONE OTHER TOOTH CRACKED.											3	O			E5CE				 
2006062600016	20060626	00016	NE  	2006	6	26	CA060510010      	2	20060503	G	7200	ARRIEL1D1	ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA			6081 	92   				9135			ON ENGINE STARTUP, THE PILOT NOTICED A FLICKERING ENGINE CHIP LIGHT, SECONDS LATER THE CHIP LIGHT CAME ON SOLID.  ENGINE	 WAS SEEN SMOKING AND OIL COMING FROM EXHAUST STACK.  ENGINE WAS SHUTDOWN AFTER APP 1 MINUTE OF OPERATION.  ENGINE HAS B	EEN SENT TO OVERHAUL COMPANY FOR INVESTIGATION AND REPAIR.  ENGINE HAD 91.9 HOURS SINCE OVERHAUL.  ENGINE IS AT THE OVER	HAUL COMPANY AT THE MOMENT AND A DETAILED REPORT WILL BE COMING AT A LATER DATE.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006071100138	20060711	00138	CE  	2006	7	11	CA060510011      	1	20060502	G	3213	5041000206	TRUNNION        			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	RT MLG	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			12920								THE RT MAIN LANDING GEAR OLEO WENT FLAT AFTER LANDING.  A CRACK WAS NOTICED ON THE UPPER TRUNNION, JUST UNDER THE SIDE B	RACE ATTACH FITTING.  THE UPPER TRUNNION WAS REPLACED.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006062600017	20060626	00017	SO  	2006	6	26	CA060510013      	1	20060509	G	5511	46530003	RIB             			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A ROUTINE INSPECTION, THE LT OB STABILIZER RIB WAS FOUND CRACKED NEAR THE HINGE ATTACH AREA.  THE RIB WAS REPLACE	D AND THE AIRCRAFT WAS RETURNED TO SERVICE.					1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2006062600018	20060626	00018	WP  	2006	6	26	CA060510014      	1	20060503	G	2400	B2804	RELAY           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					GOVERNOR	STUCK           	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			560  								THE GOVERNOR (OFF) WARNING LIGHT WAS STAYING ON, REGARDLESS OF THE STATUS OF THE GOVERNOR.  BY ALL CHECKS THE GOVERNOR W	AS WORKING WHEN TURNED ON, AND TURNING OFF WHEN THE SWITCH WAS TURNED OFF, HOWEVER THE (GOVERNOR OFF) LIGHT STAYED ON AT	 ALL TIMES.  THE CONTROL RELAY FOR THE LIGHT WAS FOUND TO BE STICKING, KEEPING THE LIGHT ON.  RELAY WAS REPLACED, AND NO	 FURTHER DEFECTS WERE FOUND.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006071100139	20060711	00139	CE  	2006	7	11	CA060511001      	1	20060511	G	5310	12118061	DOOR FRAME      			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520M    	17040	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13791								.5 INCH CRACK FOUND IN LOWER LT DOOR POST JAMB DURING ROUTINE INSPECTION.						1	H	7	1 	3O	3	O		A16CE   	E8CE				 
2006071100140	20060711	00140	EU  	2006	7	11	CA060511002      	1	20060510	G	3520	630130018	MANIFOLD        			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					PAX OXYGEN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AIRCRAFT HAD 22 MANIFOLDS FOUND CRACKED.  LOOKED AT ANOTHER AIRCRAFT TO PROVIDE SPARES, BUT FOUND MOST OF ITS MANIFOLDS 	CRACKED TOO.  DRAGER (VENDOR) CONTACTED, AND WILL PROVIDE REPLACEMENTS.  MANIFOLD IS MADE OF A VARIETY OF PLASTIC, WHICH	 IS BRITTLE.				2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2006071100141	20060711	00141	SW  	2006	7	11	CA060511004      	1	20060509	G	3211	AN324A	BOLT            	FRCHLD      	2751500001  	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TRUNNION	SHEARED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						946					PILOT REPORTED LOSS OF GREEN LIGHT AND TRANSIT LIGHT ON THE NOSE GEAR DURING TAXI INTO AIRPORT.  PILOT SHUTDOWN AC AND E	MPTIED AIRCRAFT.  MAINTENANCE MOVED AIRCRAFT TO SAFE LOCATION AND WHILE JACKING THE AIRCRAFT NOTICED THAT NOSE WHEEL PIV	OTED SIDEWAYS.  UPON INVESTIGATION IT WAS NOTED THAT THE UPPER GEAR TRUNNION PIN RETAINING BOLTS WERE SHEARED AND MISSIN	G.  THEY WERE STILL IN PLACE YET THE HEADS WERE SHEARED OFF.  REMOVED AND INSPECTED THE LOWER PIN RETAINING BOLTS AND FO	UND THEM CORRODED AND READY TO SHEAR.  ALL UNSERVICEABLE BOLTS REPLACED AND GEAR SWINGS CHECKED SERVICEABLE AND AIRCRAFT	 RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006071100166	20060711	00166	CE  	2006	7	11	CA060511005      	1	20060414	G	5330	11443007529	SKIN            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HEAVY CORROSION BETWEEN SKIN AND STRINGERS (BONDED) AT STRINGER SPLICES IN BELLY AT CENTERLINE STRINGER AND 2 LT A	ND RT OF CENTER. (TC NR 20060511005)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006071100185	20060711	00185	CE  	2006	7	11	CA060511006      	1	20060418	G	5730	1141200487374	SKIN            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OB FWD CORNER OF COLLECTOR TANK OPENING. SKINS P/N 114-120048-73 AND 74 FOUND CRACKED. HEAVY SKIN .071 (TC NR 2006	0511006)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006071100186	20060711	00186	SW  	2006	7	11	CA060511007      	1	20060509	G	3260	2751000305	STRIKER         			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT GEAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER GEAR SWING TO CHECK FOR HYD LEAK IT WAS NOTED THAT THE LT GEAR DID NOT EXTEND.  THE LT OB STRIKER ON THE LT 	CAM ASSY WAS LOOSE AND NOT CONTACTING ACTUATOR AREA FOR UPLOCK RELEASE.  THE BOLT WAS REMOVED FROM STRIKER AND FOUND TO 	BE STRIPPED AND THE NUT HAD BACKED OFF CAUSING THE STRIKER TO BE VERY SLOOPY AND NOT CONTACTING THE ACTUATOR ARM ON UPLO	CK INTERMITTANTLY. NEW BOLT AND NUT INSTALLED AND SWINGS ACCOMPLISHED SERVICIBLE.  AIRCRAFT RETURNED TO SERVICE. (TC NR 	20060511007)		2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2006071100187	20060711	00187	CE  	2006	7	11	CA060511008      	1	20060426	G	5730	11412004854	DOUBLER         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DOUBLER P/N 114-120048-54 FOUND CRACKED AT FWD OB CORNER. CAN NOT SEE CRACK UNLESS COLLECTOR FUEL TANK IS REMOVED.	 (TC NR 20060511008)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006071100188	20060711	00188	CE  	2006	7	11	CA060511009      	1	20060511	G	3230		LANDING GEAR    			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  		MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) GEAR WAS RETRACTED AND GEAR HORN AND GEAR HANDLE LIGHT STAYED ON. (TC NR 20060511009)						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006071100189	20060711	00189	CE  	2006	7	11	CA060512001      	1	20060501	G	5620	3541029114	WINDOW          			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	EMERGENCY EXIT	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			5338 								(CAN) EMERGENCY EXIT WINDOW OPENED ON TAKEOFF. WINDOW WENT FROM VENT POSITION TO EXIT POSITION INTO FREE AIR AND HINGE B	ROKE OFF AND WINDOW DETACHED FROM AIRCRAFT.   IT IS POSSIBLE THAT AT SOME PRIOR FLIGHT THE WINDOW WAS OPENED INCORRECTLY	. WE HAVE OPERATED A FLEET OF 7 AIRCRAFT WITH THE SAME TYPE WINDOW WITH NO PRIOR PROBLEMS.  (TC NR 20060512001)				1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
2006071900022	20060719	00022	GL  	2006	7	19	CA060512002      	3	20060510	G	6112	4E220010	BOOT            	HARTZL      	HCB3TN3B    	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BLADE DEICE	DEPARTED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BUA27150			BUA27150		(CAN) DURING MAINT WALK AROUND,  COMPLETE PROP BLADE DE-ICE BOOT HAD DEPARTED AC. AIRFRAME, ENG WAS INSPECTED FOR FOD DA	MAGE FROM DE-ICE BOOT. DETERMINED THAT BOOT HAD SEPERATED FROM AC DAY BEFORE DURING TAKE-OFF.  PILOT FELT VIBRATION FROM	 LT ENG DURING RUN-UP, DURING TAKE-OFF FLUCTUATION OF TORQUE INDICATION FOR ENG, THEN SETTLED OUT FOR REST OF FLIGHT BEC	AUSE VIBRATION WENT AWAY.  FURTHER INVESTIGATION SHOWS DE-ICE BOOT WAS THROWN ALONG LENGTH OF BLADE THEN DEPARTED AC (RU	BBER STREAKS OUT TO BLADE TIP).  GLUE ON BLADE LOOKED TO BE IN NORMAL CONDITION, NO DETERIORATION OF GLUE BED.  DETERMIN	ED 2 BOOTS ON THAT PROP WERE CHANGED, CANNOT DETERMINE IF IT WAS ONE OF  REPLACED BOOTS.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006071100190	20060711	00190	EA  	2006	7	11	CA060512003      	1	20060509	G	3246	C3US1563	BOLT            			DHAV  	DHC3  	DHC3        	2800202	EA  	GARRTT	TPE331	TPE33112UHR 	 	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	RT WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			106  								(CAN) WHILE PERFORMING A 100 HOUR INSPECTION ON THE MLG WHEEL SKIS, MAINTENANCE FOUND THE RT WHEEL SKI ATTACH BOLT P/N:C	3US156-3 TO BE BENT AND CRACKED.  BOLT ATTACHES THE SKI BRACKET ASSEMBLY LINK P/N: C3US108-34 TO THE MLG STRUT AND AXLE.	 THE BOLT HAS CRACKED AT THE START OF THE RADIUS WHERE THE DIAMETER OF THE BOLT CHANGES FRON .500 NR DIA TO .750 IN DIA 	IT APPEARS THAT THE CRACK OCCURED ON THE TOOLING MARK.  (TC NR 20060512003)			1	H	7	1 	3R	4	T		A815    	E4WE	6	C	P40EA	 
2006071100191	20060711	00191	GL  	2006	7	11	CA060512006      	1	20060508	G	7160	C2E1079	FLAP            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	CARB HEAT	CRACKED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			23102								(CAN) THE CARB HEAT FLAP ASSEMBLY HAD CRACKED UNDER THE DOUBLER PLATE, ALONG THE RIVET ATTCH LINE THAT CONNECTED THE FLA	P/DOOR TO THE ACTUATING SHAFT BRACKET.    (TC NR 20060512006)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006071100192	20060711	00192	CE  	2006	7	11	CA060514001      	1	20060513	G	3220	12436351	TORQUE LINK     	CESSNA      	1243800205  	CESSNA	207   	207         	2073602	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2019 	2019 							(CAN) NOSE LANDING GEAR UPPER TORQUE LINK FOUND CRACKED ON BOTH LT AND RT SIDE OF LWR WEB.  CRACK WAS DETECTED VISUALLY 	DURING 50 HR INSP AND LUBRICATION OF NOSE LANDING GEAR. THIS PART WAS INSTALLED NOVEMBER 2001, PREVIOUS PART HAD SAME CR	ACKS IN SAME LOCATION.  (TC NR 20060514001)				1	H	7	1 	3O	3	O		A16CE   	E3SO	5	C	P36EA	 
2006071900043	20060719	00043	SO  	2006	7	19	CA060514002      	2	20060511	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			798  	798  				291018R			(CAN) CYLINDERS NR 2 AND NR 4 WHERE FOUND TO BE CRACKED IN THE CYLINDER HEAD DURING A 200 HR INSPECTION. CYLINDER NR 2 H	AD 798.1 HOURS SINCE NEW. CYLINDER NR 4 HAD 897.8 HOURS SINCE NEW.  TOTAL TIME ON ENGINE IS 1504.2 HOURS SINCE OVERHAUL.	 ALL CYLINDERS WHERE INSTALLED NEW AT OVRHAUL. CYLINDER NR 4 WAS REPLACED AT 606.4 HRS DUE TO CRACKED CYLINDER HEAD. AT 	706.0 HRS CYLINDERS 1,2,3,5,6 WHERE ALL REPLACED DUE CRACKED CYLINDER HEADS DETECTED IN CYLINDER ASSY NR 2,3, AND 6 (TC 	NR 20060514002)		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006071900044	20060719	00044	SO  	2006	7	19	CA060514003      	2	20060429	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			884  	884  				572522			(CAN) DURING 200 HR INSPECTION CYLINDERS 1,2, AND 5 WHERE FOUND TO BE CRACKED IN THE CYLINDER HEAD CRACKS WHERE DETECTED	 VISUALLY AND WITH THE AID OF CYLINDER LEAKAGE CHECK AND SOAP WATER SOLUTION.  (TC 20060514003)					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006071900045	20060719	00045	SO  	2006	7	19	CA060514004      	2	20060412	G	8530	TIST712ACA	CYLINDER HEAD   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			968  	968  				282670R			(CAN) CYLINDERS 3, 1, AND 3 REPLACED DUE TO CRACKED CYLINDER HEAD.  ALL CYLINDERS ON THIS ENGINE WHERE REPLACED AT 347.7	 HRS SINCE OVERHAUL IAW E.C.I. SB 04-1. (TC NR 20060514004)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2006071900046	20060719	00046	EA  	2006	7	19	CA060514005      	1	20060510	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			1786 								(CAN) RT WINDSHIELD CRACKED ON CLIMBOUT AT 7000 FT,  A/C RETURNED TO BASE. WINDSHIEL WAS REPLACED IAW AMM. THIS WAS A PO	ST SB WINDHIELD. (TC NR 20060514005)					2	L	7	2 	4F			RT	A21EA   					 
2006071900047	20060719	00047	EA  	2006	7	19	CA060515001      	1	20060510	G	7110	2285008114	PANEL           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NOSE COWL	MISSING         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			22295								(CAN) DURING FLT NR 1 ENG NOSE COWL LWR ACCESS PNL DEPARTED AC (ACCESS PNL). FLIGHT EXPERIENCED A SLIGHT BUFFET DURING F	LT. UPON LANDING, FLT CREW DISCOVERED NOSE COWL LWR ACCESS PNL WAS MISSING.  DAMAGE TO TRANSLATING COWL, UPPER NOSE COWL	 ACCESS PNL, CAUSED BY DEPARTING LWR ACCESS PNL. NR OF LWR ACCESS PNL FASTENERS WERE FOUND STILL ATTACHED MAIN ENG COWLI	NG.  PORTION OF DEPARTED ACCESS PNL WAS FOUND 1500 FT SHORT OF RUNWAY (REMAINDER OF PNL SEC WAS NOT RECOVERED).  NEW LWR	 COWL ACCESS PNL WAS INSTALLED, DAMAGED TRANSLATING COWLING, UPPER NOSE COWL ACCESS PNL WERE REPLACED.   SHORTS SB (INSP	 OF COWLING ACCESS PNL FASTENERS ISSUED SEPT/05) IS PRESENTLY BEING CARRIED OUT ON FLEET.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071900048	20060719	00048	EA  	2006	7	19	CA060515002      	1	20060503	G	2810	600626401	VENT LINE       			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF341A      	 	NE  					FUEL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14534								(CAN) MASTER REFUEL PANEL CHECK TO CHECK VALVE FOR OP, FUEL CAME OUT OF LT NACA SCOOP APPROX 2 GALLON, THEN STOP. MAINT 	WAS ADVISE THIS WAS ONLY HAPPEN WHEN AC WAS PARKED OVERNIGHT. FIGURED THERE WAS A BAD O-RING IN VENT SYS. FUEL WAS DRAIN	ED, FUEL PANELS REMOVED. NOTICED ON VENT LINE, FUEL WAS LEAKING THRU IT. FOUND PIPE HAD A HOLE, CORRODED. PIPE HAD A CAP	 INTALLED TO THIS VENT LINE, AN UNNAPROVED MOD WAS C/O ON VENT SYS.  SB CAME OUT YEARS EARLIER TO REMOVE DRAIN LINE THAT	 WAS CONNECTED TO PIPE TO DRAIN ANY FUEL THAT COLLECTED IN VENT SYS BY USE OF EJECTOR PUMP. THIS UNAPPROVED MOD, WATER C	OLLECTED AT BOTTOM OF PIPE, CORRODED THRU. SB WAS COMPLIED WITH, SYSTEM CHECK SERVICABLE (TC NR 20060515002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006071900049	20060719	00049	EA  	2006	7	19	CA060515003      	1	20060503	G	2810	600626401	VENT LINE       			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  						CORRODED        	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			14534								(CAN) REFUELLING WAS C/O, MASTER REFUEL PANEL CHECK C/O TO CHECK VALVE FOR OPERATION, WHAT WAS NOTICED, FUEL CAME OUT OU	T OF THE LT NACA SCOOP APPROXIMATE 2 GALLON, THEN STOP. MAINT WAS ADVISED,THIS WAS ONLY HAPPENING WHEN A/C WAS PARK OVER	NIGHT. SO MAINT CREW FIGURED THAT THERE WAS A BAD O-RING IN VENT SYS. A/C RETURED TO MAINT, FUEL WAS DRAINED AND FUEL PA	NELS REMOVED, FOUND VENT LINE, FUEL WAS LEAKING THRU IT. PIPE WAS REMOVED, FOUND PIPE HAD A HOLE THRU IT, CORRODED.  PIP	E HAD AN A CAP INTALLED TO THIS VENT LINE, A UNAPPROVED MOD WAS C/O ON VENT SYS.   BY DOING THIS UNAPPROVED MOD WATER CO	LLECTED AT BOTTOM OF PIPE AND CORRODED THRU. S/B WAS COMPLIED WITH AND SYSTEM CHECK SERVICABLE. (TC NR 20060515003)	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006071900050	20060719	00050	SW  	2006	7	19	CA060515004      	1	20060508	G	6410	212010750105	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			582  								(CAN) AT REASSEMBLY OF T/R BLADES IT WAS NOTED THAT WHITE POWDER WAS PRESENT IN THE CUFF AREA OF THE BLADES. BLADES QTY 	2 WERE SENT TO COMPOSITE TECHNOLOGY FOR EVALUATION. BOTH BLADES WERE SCRAPPED DUE TO DEEP CORROSION INSIDE OF UPPER AND 	LOWER GRIP PLATES. TOTAL TIME ON THE BLADES 582.4 HOURS SINCE NEW. (TC NR 20060515004)				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006071900051	20060719	00051	CE  	2006	7	19	CA060515005      	1	20060501	G	5511	107326022	SPAR            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1535 								(CAN) 1) SPAR (P/N 0732602-2 2) REINFORCEMENT (P/N 0732603-1 3) BRACKETS (P/N 0732101-4  ALL 3 OF ABOVE ITEMS WERE FOUND	 CRACKED AND REPLACED.  (TC NR 20060515005).					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006071900052	20060719	00052	NE  	2006	7	19	CA060515006      	2	20060514	G	7321		FCU             			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  						INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) UPON RIGGING OF FCU, LOW IDLE STOPS ON THE THROTTLE QUADRANT WERE ADJUSTED TO ACHIEVE DESIRED 20 DEGREES ON THE FC	U.  THIS ADJUSTMENT WOULD NOT PHYSICALLY ALLOW THE QUADRANT TO DEPLOY THE THRUST REVERSERS.  ENGINES WERE GROUND RUN AND	 FOUND TO BE SERVICEABLE, ALTHOUGH THRUST REVERSERS WERE NOT CHECKED DURING GROUND RUN.  THE THROTTLE QUADRANT ONLY ALLO	WS FOR THE THRUST REVERSERS TO BE DEPLOYED IN ONE POSITION.   NOTE THAT THE ENGINE FCU MUST BE RIGGED AT THE IDLE POSITI	ON ON THE QUADRANT TO ALLOW THE THRUST REVERSER TO BE DEPLOYED AND TO SET THE IDLE POSITION. (TC NR 20060515006)		2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2006071900053	20060719	00053	CE  	2006	7	19	CA060515007      	1	20060512	G	2150		BLADE           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ACM	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			6800 								(CAN) THE PILOTS REPORTED THAT THEY HEARED A HUM COMING FROMTHE A/C SYSTEM. THE ACM WAS INSPECTED AND FOUND ONE COMPRESS	OR BLADE BROKEN OFF NEAR THE ROOT AND THE OTHER BLADES HAD LEADING EDGE DAMAGE.  (TC NR 20060515007)					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2006060600228	20060606	00228	CE  	2006	6	6	CA060516001      	1	20060514	G	2422	100160001	INVERTER        		100160001   	RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					ELECT SYS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			791  			1350					AIRCRAFT DEPARTED AND DURING CLIMB-OUT AN INDICATION OF XS1 BUS FAILURE.  THE CREW COMPLETED THE COCKPIT ABNORMAL CHECK 	LIST FOR THE ITEM AND RETURNED TO DEPARTURE.  MAINTENANCE WAS ADVISED AND MET THE AIRCRAFT UPON ITS RETURN.  INVESTIGATI	ON FOUND THE ODOR OF BURNT ELECTRICAL UPON OPENING OF THE AFT EQUIPMENT BAY DOOR.  FURTHER INVESTIGATION REVEALED THE NR	 1 STATIC INVERTER TO BE FAILED.  AN HOUR HAD ELAPSED SINCE THE AIRCRAFT WAS SHUT DOWN AND THE INVERTER WAS STILL HOT TO	 THE TOUCH AND THE ODOR OF BURNT ELECTRICAL WAS MOST EVIDENT.  THE INVERTER WAS REPLACED AND THE AC ELECTRICAL SYSTEM WA	S FUNCTION TESTED SERVICEABLE.  THE AIRCRAFT WAS RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2006101800074	20061018	00074	EA  	2006	10	18	CA060516002      	1	20060516	G	3260	1EN243R1	INDICATOR       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	MLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) INDICATOR ON THE LT MAIN LANDING GEAR ALWAYS INDICATES UP AFTER SELECTING DOWN. THE UP LOCK INDICATOR SWITCH HAS B	EEN REPLACED. AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006060600227	20060606	00227	CE  	2006	6	6	CA060516003      	1	20060515	G	2752	505211984	ACTUATOR        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  					RT OB FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ROUTINE VISUAL INSPECTION OF THE FLAP ACTUATORS INDICATED THAT THE OUTBOARD ATTACHMENT FLANGE OF THE RT OUTBOARD FLAP AC	TUATOR WAS CRACKED.  THERE WAS NO EVIDENCE OF THE ACTUATOR BEING DROPPED OR OTHERWISE ABUSED.  THE FLANGE WAS BENT SLIGH	TLY INBOARD AND THERE WAS EVIDENCE OF THE ACTUATOR CHAFFING ON THE MOUNTING FRAME DURING ITS NORMAL OPERATING CYCLE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006060600237	20060606	00237	CE  	2006	6	6	CA060516004      	1	20060513	G	5510	07321014	REINFORCEMENT   	CESSNA      	12320008    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					STABILIZER	CRACKED         	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											EXCESSIVE MOVEMENT FOUND AT AFT LT HINGE ASSY, INSIDE REINFORCEMENT P/N 0732106-1, ALSO FOUND CRACKED.						1	H	7	1 	3O	3	O		3A24    	E5CE				 
2006060600238	20060606	00238	SO  	2006	6	6	CA060516005      	1	20060503	G	7931	AS349101	GASKET          	LYC         	LIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			CA						L217368A					WHILE FLYING CRUISE FLIGHT NOTICED ENGINE OIL PRESSURE DROPPING.  SHUT DOWN RT ENGINE AND RETURNED TO BASE.  UPON INVEST	IGATION FOUND THAT THE GASKET UNDERNEATH VACUUM PUMP DAMAGED.  VACUUM PUMP CHANGED PRIOR TO FLIGHT.  OIL LEAK NOT DETECT	ED ON RUN UP.  GASKET P/N AS3491-01 REPLACED.  AIRCRAFT GROUND RUN LEAK CHECKED OK.  NO FURTHER DAMAGE FOUND.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006060600240	20060606	00240	NM  	2006	6	6	CA060516007      	1	20060513	G	5610	141480149	WINDSCREEN      	PPG         	141480149   	BOEING	767   	767*        	       	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA						93026H4349					LOCATION APPROX 30 DEGREES WEST AT FL 320 - IAS M .8 AS REPORTED BY THE FLIGHT CREW: WHILE IN CRUISE THE FLIGHT CREW NOT	ICED A CRACK STARTING IN THE UPPER LEFT CORNER OF THE CAPTAINS FORWARD WINDOW (NR 1) WITH IN A FEW MINUTES THE CRACK HAD	 SPREAD ALMOST ALL THE WAY TO THE FAR RIGHT.  SHORTLY AFTER THAT THE CREW OBSERVED ARCING OF THE WINDOW HEATER ELEMENT A	ND LEFT THE WINDOW HEAT IN THE OFF POSITION.  APPROXIMATELY ONE MINUTE LATER THE ENTIRE VIEWING AREA OF THE WINDOW CRAZE	D.  THE FLIGHT CREW OBSERVED THE CRAZING TO BE THE OUTER PLY AND CONTINUED THE FLIGHT WITHOUT FURTHER INCIDENT.		2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006060700236	20060607	00236	WP  	2006	6	7	CA060516008      	1	20060512	G	2497		WIRE HARNESS    	GENDYN      	CV580A      	CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					ELT WIRING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						374					DURING INSTALLATION OF  ELT REMOTE SWITCH WIRING, ROUTING OF THE WIRE BEHIND THE FORWARD RT EQUIPMENT SHELF, SEVERAL WIR	ES WERE FOUND CHAFING INTO THE WIRE BUNDLE THAT RUNS VERTICALLY BEHIND THE SHELF.  THE WIRES WERE CHAFING ON THE BACK ED	GE OF THE FLOOR.  THE WIRING WAS REPAIRED AND SECURED AND THE FLOOR WAS TRIMMED TO ENSURE ADEQUATE CLEARANCE.  ALL OTHER	 AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO OTHER DAMAGE REPORTED.			2	L	7	2 	4R	4	T		6A6     	E282				 
2006060700237	20060607	00237	SO  	2006	6	7	CA060516009      	1	20060424	G	3230	6750200	PIN             	PIPER       	7872322     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4099 								DURING LT MLG GEAR REMOVAL A SUBSTANTIAL AMOUNT OF WATER WAS OBSERVED INSIDE MLG RETAINER PIN ASSY.  FURTHER INVESTIGATI	ON REVEALED DEEP PITTING ON INNER SURFACE OF PIN, LOSS OF APPROX 50 PERCENT OF CHROME PLATING ON EXT OF PIN AND ASSY RET	ENTION BOLT HAD LOST APPROX 35% OF IT'S SHANK DIAMETER NEAR TO IT'S HEAD.  FAILURE OF THIS BOLT WOULD ALLOW RETAINER PIN	 TO MIGRATE OUT OF POSITION AND RESULT IN MLG COLLAPSE.  THIS DAMAGE BEARS RESEMBLENCE TO A SERVICE DIFFICULTY ALERT AL-	2004-06 REPORTED IN 2004.  RT RETAINER PIN ASSY ALSO SHOWED SEVERE CORROSION.  MLG RETAINER PIN ASSEMBLIES WERE REPLACED	 WITH NEW AND UPON INSTALLATION RETAINER PIN CAVITIES WERE PACKED WITH GREASE TO EXCLUDE WATER FROM THIS AREA.	1	L	7	2 	3O	3	O		A19S0   	E286				 
2006060700238	20060607	00238	SO  	2006	6	7	CA060516010      	1	20060418	G	3211	6750200	PIN             	PIPER       	7872322     	PIPER 	PA44  	PA44180     	7104402	SO  										LT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3599 								DURING LT MLG REMOVAL SEVERE CORROSION WAS OBSERVED ON THE INNER SURFACE OF THE MLG RETAINER PIN.  FURTHER INVESTIGATION	 REVEALED LOSS OF APPROXIMATELY 50% OF THE OUTER CHROME SURFACE AND THE PIN RETENTION BOLT HAD LOST 20% OF IT'S SHANK DI	AMETER NEAR TO THE HEAD.  INSPECTION OF THE RT RETAINER PIN ASSEMBLY ON THIS AIRCRAFT ALSO SHOWED SIMILAR DAMAGE.  FAILU	RE OF THIS BOLT WOULD ALLOW MIGRATION OF THE RETAINER PIN AND COLLAPSE OF THE MLG ASSEMBLY.  BOTH MLG RETAINER PIN ASSEM	BLIES WERE REPLACED WITH NEW AND UPON INSTALLATION THE RETAINER PIN CAVITIES WERE PACKED WITH GREASE TO EXCLUDE WATER FR	OM THIS AREA.	1	L	7	2 	3O				A19S0   					 
2006060700239	20060607	00239	EA  	2006	6	7	CA060517002      	1	20060516	G	6123	78249047	PCU             	HAMSTD      	78249047    	DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 1 PROP SYS	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F	R		FLT CONT AFFECTED         	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			1753 	1753 		970834					SHORTLY AFTER TAKEOFF, NR 1 PROP WENT SLOWLY IN AND OUT OF FEATHER (GENTLY) THREE TIMES.  PRECAUTIONARY SHUT DOWN OF NR 	1 ENGINE CARRIED OUT.  AIRCRAFT DIVERTED TO NEAREST AIRPORT.  MAINTENANCE INSPECTED AND REPLACED NR 1 PROP CONTROL UNIT,	 GROUND RUN AND LEAK CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006060700245	20060607	00245	NE  	2006	6	7	CA060517003      	1	20060505	G	2720	S616561500	DAMPER          	SKRSKY      	S616561500  	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					YAW CONT SYS	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				K	F		FLUID LOSS                	FLT CONT AFFECTED         		AP	APPROACH       	1			CA			19511	256  		990281					PILOT FELT A YAW ON APPROACH, AND AFTER CONFIRMING A YAW HARDOVER, SWITCHED OFF AUX HYDRAULICS, AND CONTINUED TO LAND.  	ON INSPECTION IT WAS FOUND THAT THE PEDAL DAMPER WAS LEAKING EXCESSIVELY DUE TO A BROKEN BOLT AND CAP.					2	G	7	2 	4U	4	U		1H15    	1E3				 
2006060700246	20060607	00246	WP  	2006	6	7	CA060518001      	1	20060512	G	8010	72566	RING GEAR       	LYC         	31M22972    	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			572  								THE PILOT REPORTED DIFFICULTY STARTING THE AIRCRAFT.  UPON INSPECTION TEETH WERE NOTED TO BE MISSING OFF THE STARTER RIN	G GEAR.  THE ASSEMBLY WAS REPLACED.  THE STARTER DID NOT HAVE ANY DEFECTS ON THE DRIVE GEAR, AND WAS NOT REPLACED.  ROBI	NSON KNOWS THERE IS A PROBLEM WITH THE STARTER RING GEARS.  THEY HAVE CHANGED THE BRANDS OF STARTERS INSTALLED AT THE FA	CTORY FROM B&C TO SKYTEC.  THIS AIRCRAFT HAS THE B&C STARTER INSTALLED.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062600019	20060626	00019	WP  	2006	6	26	CA060518002      	1	20060502	G	8011	72566	GEAR            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			634  								PILOT REPORTED DIFFICULTY STARTING THE AIRCRAFT.  TEETH WERE FOUND TO BE MISSING FROM THE STATER RING GEAR.  THE STARTER	 RING GEAR ASSEMBLY WAS REPLACED.  AIRCRAFT TAFT 1187.3.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006060700247	20060607	00247	CE  	2006	6	7	CA060518003      	1	20060511	G	3246	34A2000204	STRUT           		3450A       	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					ATTACH FITTING	SHEARED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA			260  			34122					DURING TOUCH DOWN,  INSTRUCTOR HEARD THE VOICE ADVISORY SYSTEM WITH THE MESSAGE "CHECK GEAR" AND LOST THE LIGHT ON THE B	LOCK INDICATOR P/N 2A11179-001 ON THE RIGHT AND SIDE.  DECIDED TO LAND ON LAKE WITH SMALLER WAVE WITH NO PROBLEM.  THE I	NSTRUCTOR FOUND THE FORWARD STRUT RT P/N 34A2000-204 BROKEN AT THE ATTACHMENT FITTING UPPER FORWARD RT P/N 34A2062-014.				1	H	7	1 	3O	3	O		3A24    	E5CE				 
2006062600020	20060626	00020	CE  	2006	6	26	CA060518004      	1	20060508	G	5610	10138402523	WINDSCREEN      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4401 								WINDSCREEN INSIDE PANE SHATTERED IN FLIGHT.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006060800287	20060608	00287	EA  	2006	6	8	CA060519001      	1	20060518	G	5314	NAS110410	BOLT            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	KEELBEAM	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											LT AND RT FWD (STN387) KEEL BEAM (STR 31L/31R) TO FRONT SPAR ATTACH BOLTS MISSING (X2).  BOLTS NOT INSTALLED BY MANUFACT	URER REF IPC 53-41-00 FIG 10 ITEMS 330, 333 AND 335.  A/C TOTAL TIME 14.0 HRS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061200329	20060612	00329	SO  	2006	6	12	CA060519002      	2	20060518	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			1390 	1390 				293447R			CYLINDERS 5 - 6 WERE FOUND TO HAVE CRACKED CYLINDER HEADS DURING A CYLINDER LEAKAGE CHECK.  A SOAP WATER SOLUTION WAS US	ED TO AID IN LOCATING THE CRACKS.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006061200331	20060612	00331	NM  	2006	6	12	CA060519003      	1	20060518	G	2710	82740037101	SPRING          	DHAV        		DHAV  	DHC8  	DHC8202     	2809007	NM  										GUST LOCK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											1 OF 2 AILERON GUST LOCK SPRINGS FOUND BROKEN WHEN PANELS REMOVED TO PERFORM OTHER MAINTENANCE REF IPC 27-12-00 FIG 20, 	ITEM 210.  AIRCRAFT TOTAL TIME 19575 HOURS, 12119 CYCLES.					2	H	7	2 	4T			RT	A13NM   					 
2006061200333	20060612	00333	NE  	2006	6	12	CA060521001      	2	20060518	G	7314	6272017203	SUPPORT BRACKET 			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  						BROKEN          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											PRIOR TO FLT, PILOTS CALLED TO HAVE RT SERVICED WITH OIL.  MECHS NOTICED RT HAD BEEN SERVICED SEVERAL TIMES IN RECENT HI	STORY. INVESTIGATION FOUND BROKEN BRACKET THAT HOLDS EDP OUTLET HYD LINE TO AGB.  BROKEN BRACKET HAD CHAFED A HOLE IN AG	B CASING CAUSING OIL LEAKAGE. ACCORDING TO LOGBOOK IN RDU 3 QTS OIL WAS ADDED TO RT ENG BEFORE FERRY FLT.  NO ENG RUNS B	EFORE FERRY TO DESTINATION WHERE IT WAS NOTED, HYD LINE WAS NOT SECURED NOR WAS BRACKET REMOVED.  OIL LVL PER EICAS WAS 	14%.  OIL ALL OVER COWLING AND BACK OF ENG.  14% LOW OIL LVL IS CONSISTENT WITH LOW OIL PRESS IN FLT AND QRH PILOT COMMA	NDED IFSD.  MESA HAVE GE A/C SERV ON SITE TO ROB AN AGB FROM A SPARE ENG AND INSTALL THIS A/C 10104 RT.  INITIAL "ROOT C	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061200334	20060612	00334	EA  	2006	6	12	CA060523001      	1	20060522	G	7830	22850291109	ARM             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THRUST REVERSER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NA					DURING AN "R" CHECK, LINE MAINTENANCE FOUND THE LT THRUST REVERSER BLOCKER DOOR AT THE 5 O'CLOCK POSITION TORN OUT.  THE	 ACTUATING ROD (P/N 228-50291-109) WAS STUCK THROUGH THE DIVERTER FAIRING IPC REF 78-34-01.  AREA INSPECTED FOR POSSIBLE	 DAMAGE TO FAN CASE, NONE FOUND.  DIVERTER FAIRING (LOWER PORTION) REPLACED.  BLOCKER DOOR AND ACTUATING ROD REPLACED.  	LEFT THRUST REVERSER CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061200335	20060612	00335	NM  	2006	6	12	CA060523002      	1	20060519	G	5610	5893543129	WINDOW          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											CAPTAINS NR 1 WINDOW SPIDER CRACKED AT 34,000 FT, WINDOW CRACKED THROUGH OUT 50% OF THE WINDOW IN THE OUTER PANE ONLY.  	AIRCRAFT FERRIED TO BASE FOR NR 1 WINDOW CHANGE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061200336	20060612	00336	EA  	2006	6	12	CA060523003      	2	20060418	G	7314	AF15472	PUMP            			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3H     	41508	EA  	SNSNCH	74D	74DM        	EA  	FUEL SYS	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											THIS MECHANICAL FUEL PUMP HAS BEEN INSTALLED NEW.  ENGINE RUN-UP DONE WITHIN PARAMETER WITH FUEL PRESSURE NORMAL AT ALL 	RPM ON GROUND STATIC RUN-UP.  OWNER RUN-UP BEFORE FLIGHT FOUND FUEL PRESSURE NORMAL.  INFLIGHT IN CRUISE DURING CIRCUIT 	AT THE AIRPORT ENGINE QUIT AND RESTART AFTER WITH ELECTRIC PUMP ON.  THE FUEL GAUGE PRESSURE SHOWING FULL 10 PSI AND STA	Y AT 10.  ON GROUND FUEL SYSTEM CHECK WITH GROUND EQUIPMENT TESTER SHOWING RIGHT INDICATING ON AIRCRAFT GAUGE.  PUMP REP	LACED WITH NEW LYCOMING PUMP, RUN-UP DONE AND FLIGHT TEST OK.  DEFECTIVE PUMP RETURNED TO ENGINE SHOP.		1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006062600035	20060626	00035	WP  	2006	6	26	CA060523004      	1	20060512	G	2510	C6284	BUCKLE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					STRAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) METAL STRAP BETWEEN MOUNTING POINT AND BUCKLE IS CRACKED IN TWO.  TIME ON THIS PART IS UNKNOWN.  TAFT 5902  MFG HA	S DEVELOPED A NEW SEAT BELT BUCKLE THAT REPLACES THE STAINLESS STEEL STRAP WITH A FABRIC STRAP. (TC NR 20060523004)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006061200338	20060612	00338	CE  	2006	6	12	CA060523005      	1	20060516	G	5340	NAS57712A	NUT             			MTSBSI	MU2   	MU2B36A     	5780413	CE  	GARRTT	TPE331	TPE3315     	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17439								WHILE CARRYING OUT A WINGS OFF INSPECTION AND COMPLYING WITH SERVICE BULLETIN 103/57-004 WING ATTACHMENT HARDWARE.  INSP	ECTION, THE RT LOWER FORWARD WING ATTACH BOLT BARRELL NUT WAS FOUND CRACKED THROUGH THE ENTIRE THREADED PORTION OF THE N	UT.  THE NUT WAS REPLACED AND TORQUED IN ACCORDANCE WITH THE S/B RECOMMENDATIONS.				1	H	7	2 	3T	4	T		A10SW   	E4WE	6	C	P40EA	 
2006062600036	20060626	00036	WP  	2006	6	26	CA060523006      	1	20060522	G	2497	C05914	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  											LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17   								(CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL W	AS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523006	)				1	G	7	1 	3O				H11NM   					 
2006062600037	20060626	00037	WP  	2006	6	26	CA060523007      	1	20060522	G	2497	C05914	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  											LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17   								(CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL W	AS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523007	)				1	G	7	1 	3O				H11NM   					 
2006062600038	20060626	00038	WP  	2006	6	26	CA060523008      	1	20060522	G	2497	C05914	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  											LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17   								(CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL W	AS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523008	)				1	G	7	1 	3O				H11NM   					 
2006062600039	20060626	00039	WP  	2006	6	26	CA060523009      	1	20060522	G	2497	C05914	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  											LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17   								(CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL W	AS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523009	)				1	G	7	1 	3O				H11NM   					 
2006061200340	20060612	00340	NM  	2006	6	12	CA060523010      	1	20060523	G	5315	14A55067	FLOORBEAM       			BOEING	737   	737724      	13844BY	NM  										BS 986	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							F001924				FOUND FLOORBEAM AT BS 986 CORRODED AT CLIPNUT HOLES BETWEEN RBL 47 AND RBL 18.						2	L	7	2 	4F			RT	A16WE   					 
2006061200341	20060612	00341	NM  	2006	6	12	CA060523011      	1	20060523	G	5315	141A550424	FLOORBEAM       			BOEING	737   	737724      	13844BY	NM  										BS 328	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							28786				FOUND FWD CABIN AREA FLOORBEAM AT 328 BRL 41 CORRODED.						2	L	7	2 	4F			RT	A16WE   					 
2006061200342	20060612	00342	NM  	2006	6	12	CA060523012      	1	20060523	G	3350	7002246001	LIGHT           			BOEING	737   	737724      	13844BY	NM  										SEAT ROW 14ABC	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FOUND SEAT ROW 14ABC RED EMERG EXIT LIGHT DOES NOT ILLUMINATE.						2	L	7	2 	4F			RT	A16WE   					 
2006061300046	20060613	00046	SW  	2006	6	13	CA060524001      	1	20060519	G	6320	212030154101	FITTING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  						CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AIRCRAFT WAS ON SEISMIC DRILL MOVE JOB.  THE ENGINEER WAS DOING HIS DAILY INSPECTION WHEN NOTICED THAT ONE EAR OF THE LI	FT LINK FITTING WAS APPEARED CRACKED.  A CLOSER VISUAL LOOK CONFIRMED IT WAS CRACKED.  INVESTIGATING IF  THE BUSHING WAS	 WRONG FOR THIS INSTALLATION.  THE BELL 205 PARTS MANUAL AND TB 205-91-88 ARE NOT TO CLEAR OF THE DIFFERENT BUSHINGS NEE	DED.			1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006061300124	20060613	00124	GL  	2006	6	13	CA060524002      	1	20060512	G	3246	VALTBS12091	WHEEL           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R98539A     	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			804  								THIS PART WAS INSTALLED MAY 31/04 IN ACCORDANCE WITH VIKING AIR GROSS WEIGHT INSTRUCTION.  IT WAS NOTICED THAT EARLY COR	ROSION HAD BEGUN AT THE WHEEL GEAR ATTACHMENT HOLE.  THE CORROSION WAS DEEP AND THE PART WAS REPLACED WITH A NEW UNIT.  	POSSIBLE CAUSE FOR THE PREMATURE CORROSION IS WHEN THE STEEL BUSH WAS INSTALLED, REMOVING THE ANNODIZING FROM THE MACHIN	ED HOLE, THAN ALLOWING DISSIMILAR CORROSION TO HAPPEN.			1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006062600040	20060626	00040	EU  	2006	6	26	CA060524003      	1	20060519	G	6220	350A37122823	YOKE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					M/R HEAD & MAST	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINEER WAS LOOKING AT THE AIRCRAFT AND NOTICED THE THE M/R STATIC STOP YOKE BROKEN OFF AND MISSING OUT OF 3.	  THE OTHER STATIC STOPS  WERE INSPECTED AND FOUND ONE CRACKED. THE AC WAS GROUNDED AND APPROPRIATE PARTS WERE ORDERED. 	 (TC NR 20060524003)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006062600041	20060626	00041	SO  	2006	6	26	CA060524004      	1	20060521	G	2822	A10014D44	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL BOOST	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1097 								(CAN) PILOT REPORTED RT FUEL BOOST PUMP UNSERVICEABLE.  TROUBLESHOOTING FOUND POWER TO THE PUMP.  WHEN THE PUMP WAS CHEC	KED, THERE WAS NO CONTINUITY THROUGH THE PUMP.  THE REPLACMENT PUMP WAS CHECKED AND FOUND TO HAVE 13 OHMS. (TC NR 200605	24004)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061300126	20060613	00126	SO  	2006	6	13	CA060524005      	1	20060514	G	8120	4066109020	TURBOCHARGER    			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				872  							DURING INSPECTION, OIL WAS FOUND IN BOTH THE COMPRESSOR AND TURBINE SECTIONS OF THE TURBO.  THIS INDICATES THAT THE CENT	ER SECTIONS OIL SEALS WERE FAILING.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061300128	20060613	00128	EA  	2006	6	13	CA060524006      	2	20060514	G	7314	200F5002	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	LOW PRESSURE    	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				980  							DURING GROUND RUN, FUEL PRESSURE OUTPUT FROM THE LEFT ENGINE WAS BELOW NORMAL, AND WOULD FLUCTUATE AT LOWER IDLE SPEEDS.	  THE FUEL SERVO SCREEN WAS CHECKED DURING THE INSPECTION AND BITS OF METAL WERE FOUND.  THE PUMP WAS REMOVED AND WHEN T	HE DRIVE SPLINE WAS ROTATED BY HAND A RESISTANCE TO ROTATION WAS FELT AT A CERTAIN POINT.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062700085	20060627	00085	SW  	2006	6	27	CA060524007      	1	20060519	G	2841	51509002	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL QTY IND	MALFUNCTIONED   	W				O				OTHER                   				L			NO TEST                   			CR	CRUISE         	1			CA											(CAN) TROUBLESHOOTING A FUEL QUANTITY INDICATING A/C SYSTEM DEFECT. WITH BOTH POWER SECTIONS RUNNING THE FUEL QUANTITY I	NDICATION WOULD CHANGE WITH NO FUEL ADDED. FUEL QUANTITY SELECTOR WOULD BE POSITIONED TO LT TANK AND VERY SLOWLY THE IND	ICATOR WOULD SHOW THE CORRECT QUANTITY. THEN MOVE THE SELECTOR TO RT TANK AND THE FUEL QUANTITY WOULD REACT VERY SLOWLY 	THE FUEL INDICATOR WOULD READ THE CORRECT QUANTITY. THEN MOVE THE SELECTOR BACK TO THE LEFT TANK AND THE READING WOULD B	E DIFFERENT THAN THE ORIGINAL FUEL INDICATION.  WHAT WAS FOUND THE LEFT DC CONTROL UNIT WAS AFFECTING THE A/C FUEL QUANT	ITY INDICATING SYSTEM. UNIT REPLACED, FUNCTIONAL/ OPERATIONAL TEST, A/C RETURNED TO SERVICE. (TC NR 20060524007)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062800219	20060628	00219	SW  	2006	6	28	CA060524008      	1	20060524	G	6320	214030606005	SPINDLE         			BELL  	214   	214B        	1182100	SW  	LYC   	T55   	T5508D      	41555	NE  					TRANSMISSION	BROKEN          	W				A				UNSCHED LANDING         				Z			SIGNIFICANT FAILURE REPORT			HO	HOVERING       	1			CA				1928 		AME52013					DONT HAVE ANY OTHER INFO AT THIS TIME, AS THIS INCIDENT JUST OCCURRED THIS MORNING.  WILL ADD INFORMATION AS IT COMES IN	.  THIS INCIDENT SEEMS VERY SIMILAR TO ONE 16 OCT 1996 NTSB REPORT NUMBER A96P0231.  WITH ONE GOOD DIFFERENCE, NO LOSS I	N FLIGHT CONTROL AND SAFE LANDING.  PART WAS NOTED AND X-RAYED AT TIME OF OVERHAUL.				2	G	7	1 	4U	4	U		H6SW    	E4NE				 
2006061300131	20060613	00131	NE  	2006	6	13	CA060524009      	2	20060520	G	7250	9609000408	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					GAS GEN	FLAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1284 			10050TEC					WHILE IN CRUISE, THE PILOT HAD AN ENGINE CHIP INDICATION AND RETURNED TO BASE.  THE AME LOOKED AT THE REAR BEARING CHIP 	DETECTOR AND FOUND METAL ON THE PLUG.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006061300133	20060613	00133	NM  	2006	6	13	CA060525001      	1	20060517	G	5610	07802	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											UPON DESCENT BETWEEN 8000 FT AND 9000 FT, THE CREW NOTICED SPARKS COMING FROM THE LT WINDSHIELD.  SIMULTANEOUSLY, THE WI	NDSHIELD DEVELOPED A CRACK.  THE WINDSHIELD HEAT WAS IMMEDIATELY TURNED OFF AND THE AIRCRAFT WAS DEPRESSURIZED.  THE AIR	CRAFT LANDED SAFELY 10 MINUTES LATER WITH NO FURTHER INCIDENT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300134	20060613	00134	NM  	2006	6	13	CA060525002      	1	20060513	G	7931		O-RING          	JANITROL    		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	OIL COOLER	FAILED          	W				A				UNSCHED LANDING         				J		O	WARNING INDICATION        		OTHER                     	CL	CLIMB          	1			CA				560  		L86026903					AIRCRAFT DEPARTED NORMALLY AND ON CLIMB-OUT, THE NR 2 OIL PRESSURE ANNUNCIATOR ILLUMINATED BRIEFLY, AIRCRAFT THEN RETURN	ED TO DEPARTURE AIRPORT.  MAINTENANCE INVESTIGATION REVEALED THAT THE NR 2 OIL COOLER WAS LEAKING OIL AND OIL WAS LEAKIN	G FROM THE VERNATHERM VALVE ASSEMBLY.  THE OIL COOLER WAS REPLACED AND THE VERNATHERM VALVE ASSEMBLY (45E04-1) WAS TRANS	FERRED TO THE NEW OIL COOLER WITH NEW O-RINGS (25C85-128/129/130).  GROUND RUNS CARRIED OUT AND NO LEAKS EVIDENT.  AIRCR	AFT RETURNED TO SERVICE.  OIL COOLER REMOVED IS OUT FOR REPAIR AT THIS TIME.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061300138	20060613	00138	WP  	2006	6	13	CA060525003      	2	20060525	G	7200		ENGINE          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  					RIGHT	MALFUNCTIONED   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											IN CRUISE, RT ENGINE TORQUE INCREASED TO 104.5%, WHEN TTL TURNED OFF WENT TO 120%.  FUEL FLOW ON RT ENG DROPPED TO 200LB	S.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE				 
2006062600042	20060626	00042	CE  	2006	6	26	CA060525004      	1	20060524	G	5753	35165050271	BRACKET         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7347 								(CAN) DURING A BASE INSPECTION THE RT OB FLAP ACTUATOR BRACKET WAS FOUND CRACKED. WHEN THE BRACKET WAS REMOVED FROM THE 	SKIN, IT WAS DISCOVERED THAT THE SKIN WAS ALSO CRACKED. FURTHER INSPECTION REVEALED THAT THE RIB UNBER THE SKIN WAS ALSO	 DAMAGED. THE FLAP WILL BE REPLACED.  (TC NR  20060525004)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006061300139	20060613	00139	NM  	2006	6	13	CA060525005      	1	20060525	G	5330		SKIN            			BOEING	737   	7372Q8C     	138448S	NM  										BS 245	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FOUND SKIN GOUGE AT BS 245 2" INBD OF STR 25L.  REPAIRED IAW CUSTOMER EA.						2	L	7	2 	4F				A16WE   					 
2006061300141	20060613	00141	NM  	2006	6	13	CA060525006      	1	20060525	G	5330		SKIN            			BOEING	737   	7372Q8C     	138448S	NM  										BS 1016-1028	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											EXISTING REPAIR AT BS 1016 AND 1028 FROM STR 15L TO 12L DAMAGED BEYOND LIMITS (DENTED) AND REPAIR IAW CUSTOMER EA.						2	L	7	2 	4F				A16WE   					 
2006061300143	20060613	00143	NM  	2006	6	13	CA060525007      	1	20060525	G	5311		FRAME           			BOEING	737   	7372Q8C     	138448S	NM  										BS 490 S24R	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FWD PIT DOOR WAY AFT FRAME BS 490 STR 24R CRACKED AND REPAIRED IAW CUSTOMER EA.						2	L	7	2 	4F				A16WE   					 
2006061300192	20060613	00192	EA  	2006	6	13	CA060526001      	2	20060525	G	7250	3037347	SHROUD          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	LOOSE           	W				C				ABORTED TAKEOFF         				M	J		OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			CA			90   								DURING TAKEOFF ROLL IT WAS NOTED, RT ENG ITT WAS AT RED LINE AND ENG TQ WAS BELOW REQUIRED T/O VALUE.  T/O WAS ABORTED A	ND A/C RETURNED TO RAMP.  DURING MX INVESTIGATION, LARGE INCREASES IN ITT READINGS COULD BE SEEN WHEN SELECTING BLEED AI	R ON OR ACCELERATING ENG.  ENGINE WAS SPLIT AT THE C FLANGE AND THE CT VANE SHROUD SEGMENTS WERE FOUND TO BE LOOSE AND C	ONTACTING THE CT DISC BLADES.  PART OF ONE SEGMENT WAS MISSING AND THERE WAS IMPACT DAMAGE NOTED ON THE PT TURBINE WITH 	METAL IN THE EXHAUST STACKS.  ENGINE IS BEING REPLACED AND SENT FOR INVESTIGATION AND REPAIR TO AN APPROVED ENGINE OVERH	AUL FACILITY.  THE ENGINE HAS COMPLETED 90 HOURS SINCE THE LAST HOT SECTION REPAIR.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006061300193	20060613	00193	SO  	2006	6	13	CA060526002      	1	20060406	G	8120	LW1277885	BYPASS VALVE    	GARRTT      		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	CRACKED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			3118 	3118 							RIGHT ENGINE NOT DEVELOPING INCHES OF HG.  AFTER RUN-UP AND ATTEMPTED TO ADJUST DENSITY CONTROLLER, WASTEGATE (VALVE - E	XHAUST BYPASS) WAS CHECKED AND BUTTERFLY VALVE FOUND TO BE ROTATING FREELY ON ITS SHAFT.  AFTER REMOVAL OF SAID PART, TH	E WASTEGATE VALVE WAS INSPECTED AND SHOWED SIGNS OF CORROSION, CRACKING AND CORRODED/SHEARED HOLDING STUD.  ENGINE WAS O	N CONDITION, NORMAL OPERATION WAS ACHIEVED AFTER REPLACEMENT OF PART.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062600043	20060626	00043	GL  	2006	6	26	CA060526003      	2	20060524	G	7510	1885M24601	DUCT            			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2*    	 	GL  					11TH STAGE	RUPTURED        	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			10356	497  							(CAN) L GEN CONT MSG ILLUMINATED, IN FLIGHT CHECKLIST C/O, L GENERATOR CONTROL REMAINED OFF. ON CLIMB OUT, L OIL PRESS E	ICAS FLASHED RED NUMBERS DECREASING WENT BLANK - OIL TEMP INCREASING -QRH FOLLOWED ENGINE SHUT DOWN.  FOUND CB FOR LEFT 	ENGINE OIL PRESSURE TRANSMITTER TRIPPED.  FOUND BLEED DUCT RUPTURED AT A PREVIOUS REPAIR.  THE TRIANGULAR SHAPED HOLE AP	PROX 2" ALONG EACH SIDE ALLOWED 11TH STAGE AIR FOR THE TURBINE CASE COOLING SYSTEM TO BE DIRECTED ONTO WIRING BUNDLES.  	WIRES WERE DAMAGED INCLUDING THOSE FOR THE PERMANET MAGNET GENERATOR AND FOR THE IDG.  WIRE P/NS DAMAGED: W5302-301B-18 	W5302-301R-18 W5302-301Y-18 (TC# 20060526003)	2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006061300195	20060613	00195	SO  	2006	6	13	CA060526004      	2	20060519	G	7414	M3050	IMPULSE COUPLING	SLICK       		CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  					MAGNETO	BROKEN          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			2157 			93120288					DURING FLT, PILOT NOTICED A VERY SLIGHT RPM DROP AND SLIGHT ROUGHNESS.  UPON LANDING A GROUND RUN WAS PERFORMED AND WHEN	 THE IGNITION SWITCH WAS SELECTED TO RT MAG, ENGINE DIED OFF BEFORE SELECTING BACK TO LT OR BOTH.  WHEN COWLS WERE REMOV	ED IT WAS EVIDENT THAT RT MAG HAD SEPARATED FROM ATTACH FLANGE AND WAS LAYING JUST FWD OF ITS ATTACHMENT POINT.  UPON IN	SPECTION OF MAG IT APPEARS THAT IMPULSE COUPLING HAD FAILED INTERNALLY AND THROUGH ROTATION AND CENTRIFICAL FORCE HAD WO	RN AWAY THE CASING OF THE MAG TO THE POINT OF SEPARATION.   MAG WAS REPLACED WITH A NEW UNIT, THE ACCY CASE GEARS WERE V	ISUALLY INSPECTED, AND THE OIL AND FILTER WERE CHANGED AT THAT TIME AND AGAIN 3 HOURS LATER.	1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006062800220	20060628	00220		2006	6	28	CA060526005      	1	20060509	G	6320	6107435000060	FREEWHEEL UNIT  	SKRSKY      																M/R GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				789  							LT P/N 61074-35000-061 S/N C144-00286 RT P/N 61074-35000-060 S/N C144-00279 THESE UNITS WERE CHANGED UPON REQUEST OF THE	 CUSTOMER AFTER A SUSPECTED FREEWHEEL SLIP.  SEE ATTACHED REPORT AND DIGITAL PICTURES FOR DETAILS.  UNABLE TO ATTACH FIL	ES, WILL E-MAIL THEM.  THESE UNITS HAVE BEEN SENT TO WALDRON AND COMPANY FOR ANALYSIS.																	 
2006061400126	20060614	00126		2006	6	14	CA060529004      	4	20060428	G	6122	8210263C	FLANGE          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	PROP GOVERNOR	SPLIT           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											FOUND OIL DRIPPING UNDER RIGHT ENGINE AFTER SHUT DOWN, ENGINE CLEANED AND CASE NEGATIVE PRESSURE CHECKED, FOUND SERVICEA	BLE.  ENGINE GROUND RUN/MAX POWER CARRIED OUT.  OIL FOUND TO BE LEAKING FROM THE PROP GOVERNOR.  PROP GOVERNOR REPLACED 	WITH SERVICEABLE UNIT P/N 8210-263C, S/N 1812067.  GROUND RUN CARRIED OUT SATISFACTORY.				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2006061400199	20060614	00199	NE  	2006	6	14	CA060529005      	2	20060529	G	8550	493476	O-RING          			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	NR 4 ENGINE	DISPLACED       	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA				1783 							NR 4 ENGINE OUTBOARD UPPER OIL TRANSFER TUBE PLUG FOUND LOOSE AND THE O-RING WAS FOUND DISPLACED, CAUSING RAPID OIL DEPL	ETION COVERING THE COWLS WITH OIL.  MAINTENANCE STAFF NOTED THIS DEFECT DURING GROUND OPERATION BETWEEN FLIGHTS.  THE PL	UG WAS REMOVED AND THE THREADS WERE CHECKED SERVICEABLE.  THE O-RING WAS REPLACED.  THE PLUG WAS INSTALLED AND TORQUED I	AW MAINTENANCE MANUAL.  THE ENGINE WAS GROUND RUN, PROP FEATHER OPERATIONAL CHECK COMPLETED.  A LEAK CHECK WAS COMPLETED	 SERVICEABLE.  A LEAK CHECK WAS ALSO COMPLETED UPON COMPLETION OF FLIGHT AND AIRCRAFT WAS SERVICEABLE.		2	L	7	4 	4R	4	R		6A4     	E264	6	C	P871	 
2006061400200	20060614	00200	NE  	2006	6	14	CA060529006      	2	20060529	G	8550	493476	O-RING          			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	DISPLACED       	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA				1784 							DURING GROUND OPERATION BETWEEN FLIGHTS, MAINTENANCE CREW DISCOVERED OIL ON THE COWL FLAPS.  UPON INVESTIGATION IT WAS D	ISCOVERED THAT THE UPPER OUTBOARD OIL TRANSFER TUBE PLUG WAS LOOSE.  THE O-RING HAD BECOME DISPLACED.  THE PLUG WAS REMO	VED AND THE THREADS WERE INSPECTED AND FOUND SERVICEABLE.  THE O-RING WAS REPLACED.  THE PLUG WAS RE-INSTALLED AND TORQU	ED IAW MM.  THE ENGINE WAS GROUND RUN, A PROP FEATHER FUNCTION CHECK AND LEAK CHECK WERE ACCOMPLISHED.  ENGINE WAS SERVI	CEABLE.  THE AIRCRAFT COMPLETED A FLIGHT AND A LEAK CHECK WAS ACCOMPLISHED WITH NO SIGNS OF FURTHER LEAKAGE NOTED.		2	L	7	4 	4R	4	R		6A4     	E264	6	C	P871	 
2006061400202	20060614	00202	GL  	2006	6	14	CA060529008      	1	20060524	G	2820	C2P1551A	VENT            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R98539A     	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FUEL SYSTEM	WRONG PART      	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			10645								THIS FRONT TANK FUEL VENT TUBE FOUND TO HAVE DISCONNECTED FROM THE RUBBER BLADDER.  THE HOSE CLAMP WAS TIGHT BUT THE TUB	E WAS ABLE TO WORK ITSELF FROM THE BLADDER CAUSING FUEL LEAKAGE AND GASES TO ESCAPE FROM THE BLADDER.  IN INVESTIGATING 	THIS OCCURRENCE IT WAS NOTICED THAT THIS VENT LINE WHICH HAD A DEHAVILLAND P/N DID NOT HAVE A BULK ON THE END, EVEN THOU	GH THE DEHAVILLAND DRAWING P/N C2P1551A CLEARLY SHOWS THIS BULBED END.  THIS PART WAS REPLACED WITH A NEW DEHAVILLAND UN	IT.		1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006062600045	20060626	00045	CE  	2006	6	26	CA060529009      	1	20060518	G	2913	HP3001	PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYDRAULIC SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) MAINTENANCE INSPECTED THE AIRCRAFT, FOUND MAIN 60A CB TRIPPED  RESET CB AND SYSTEM APPEARED TO FUNCTION NORMAL  FU	RTHER INVESTIGATION FOUND HYDRAULIC PUMP WOULD INTERMITTENTLY (ONLY OCCUR ON FIRST SYSTEM POWER UP) INTERNALLY BYPASS CA	USING LOW PRESSURE OUTPUT AND PUMP RUN-ON UNTIL CB WOULD TRIP  INVESTIGATION OF THE SYSTEM FOUND WIRE (SPRING MATERIAL) 	IN FIRST CHECK VALVE OFF PUMP AND MAIN FILTER  HYDRAULIC PUMP REPLACED, SYSTEM FLUSHED AND FUNCTION CHECKED. (TC NR 2006	0529009)		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006062700252	20060627	00252	CE  	2006	6	27	CA060529010      	1	20060521	G	3241	991230512	SERVO           			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					BRAKE ANTI-SKID	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			4017 								DURING LANDING, ANTI-SKID INOP ANNUNCIATOR ILLUMINATE THEN EXTINGUISH. ROLLOUT WAS UNEVENTFUL AND DUE LONG RUNWAY, NO BR	AKE APPLICATION AT ALL BUT AT END OF RUNWAY RT TURN TO TAXIWAY, BRAKES WERE NON-RESPONSIVE BUT PEDALS WERE EXTREMELY HAR	D.  MX FOUND PRESS STILL LOCKED IN SYS FROM A/S SERVO "UPSTREAM" SEVERAL HOURS POST INCIDENT.  NO BRAKE PRESS AVAILABLE 	AT BRAKE UNITS. PWR BRAKE MOTOR NOT CYCLING AS USUAL DUE PRESS LOCK. EVEN WITH ANTI-SKID SWITCHED OFF, BRAKES WOULD NOT 	RETURN TO MANUAL, MASTER CYLINDER HYD BRAKE SYS AS PER SYS DESIGN.  PRESS DID BLEED OFF HOURS LATER AND SYS RETURNED TO 	NORM OPS W/O EXT ACTIONS. UNKNOWN WHY TEMP ANTI-SKID LITE DURING LANDING WHICH SEEMS TO HAVE CAUSED ENTIRE BRAKE SYSTEM 	1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2006062700253	20060627	00253	EU  	2006	6	27	CA060530001      	1	20060527	G	6320	4638001001	TRANSMISSION    			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											DURING CRUISE, MAIN ROTOR TRANSMISSION METAL PARTICLES LIGHT ILLUMINATE IN COCKPIT.  LAND IMMEDIATELY IN SMALL CLEARING 	NEAR A ROAD.  IT WAS A SECOND EVENT TO OCCUR WITHIN LAST 10 MINS, BUT FIRST TIME, WARNING LIGHT HAD EXTINGUISHED WHEN PI	LOT ACTIVATED PULSE CHIP DETECTOR SWITCH.  FOUND A HAIR LIKE PIECE OF METAL, VERY SMALL.  PROBABLY REMAINS OF A .003'' I	N OF WIRE USE TO VERIFY OPERATION OF PULSE SYSTEM DURING PREVIOUS SCHEDULE INSPECTION.  THE DETECTOR WAS CLEANED AND REI	NSTALLED, THE LIGHT REMAIN OFF.  A 20 MINUTES GROUND RUN WAS CARRIED OUT.  WARNING LIGHT REMAIN OFF.  DETECTOR WAS REMOV	ED, INSPECTED (NO PARTICLE FOUND) AND REINSTALLED.  A/C WAS THEN RETURNED TO SERVICE.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2006062600046	20060626	00046	SO  	2006	6	26	CA060530003      	1	20060520	G	2912	MS2877816	O-RING          			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYDRAULIC FILTER	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) O-RING IN HYDRAULIC FILTER BOWL BLEW OUT SIDE BETWEEN THE BOWL SEATS. THERE ARE 2 DIFFERENT TYPES SIZES OF O-RING 	FOR THIS SET UP AS THERE ARE 2 SLIGHTLY DIFFERENT BOWL TYPES. THE O-RINGS ARE THE SAME COLOR AND VERY CLOSE IN SIZE MAKI	NG IT REAL EASY TO PUT THE LARGER O-RING ON THE SMALLER BOWL. THE SMALLER O-RING WILL WORK ON THE LARGER BOWL BUT NOT VI	SE VERSA. ONCE INSTALLED IT IS IMPOSSIBLE TO TELL WHICH O-RING IS THERE.  (TC NR 20060530003)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006061400203	20060614	00203	CE  	2006	6	14	CA060530004      	1	20060512	G	7160	055211313	AIR BOX         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		DE	DESCENT        	1			CA											STUDENT REMOVED CARB HEAT AFTER EXERCISE AND A/C RPM RESPONDED BY DROPPING, SO CARB HEAT WAS REAPPLIED.  ENG CONTINUED T	O GET ROUGHER AND POWER WAS ADDED.  ENDED UP WITH FULL POWER/CARB HOT AND ENGINE RESPONSE WAS 1900 RPM/75 KTS DESCENDING	.  ANY CHANGE TO PUT CARB HEAT CAUSED RPM TO DROP SIGNIFICANTLY (BELOW 1500 RPM) LEFT AT POWER FULL/CARB HOT.  ALL ENG I	NSTRUMENTS READING NORM. A/C WAS NOTICEABLY SHAKING DUE TO ROUGH ENG. ENG RESPONSE STAYED THIS WAY UNTIL ON FINAL, WHERE	 RESPONSE BECAME NORMAL AND LANDING UNEVENTFUL. UPON EXAM FOUND CARB AIR BOX HAD BEEN REPAIRED PREVIOUSLY, THE PATCH REP	AIR RIVETS FAILED, CAUSING REPAIR PATCH TO FALL INSIDE AIR BOX AND PARTIALLY BLOCK CARBURETOR INTAKE. APPLICATION OF CAR	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061400204	20060614	00204	EA  	2006	6	14	CA060530005      	2	20060516	G	8530	72242	ROCKER COVER    			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				Y	B		ENGINE STOPPAGE           	SMOKE/FUMES/ODORS/SPARKS  		TO	TAKEOFF        	1			CA				314  							DURING TAKEOFF, THE CREW NOTED THE LT ENGINE SURGING AND SMOKE FROM THE EXHAUST.  THE AIRCRAFT COMPLETED THE TAKEOFF AND	 CAME BACK FOR LANDING WITHOUT ANY TROUBLE.  CLOSER INVESTIGATION FOUND THE TAB THAT IS ATTACHED TO THE ROCKER COVER HAD	 COME OFF.  THIS TAB HOLDS BOTH INTAKE AND EXHAUST ROCKER SHAFTS IN PLACE.  THE EXHAUST ROCKER SHAFT WAS OUT OF PLACE AN	D THE INTAKE SHAFT HAD COME OUT AND BROKE THE BOSS OFF THE CYLINDER HEAD.  THE ROCKER COVERS ARE MANUFACTURED BY MILLENI	UM, THE  ORIGINAL LYCOMING COVERS HAVE THE TAB BONDED ALONG THE ENTIRE MATING SURFACE.  MILLENIUM COVERS HAVE ONLY TWO S	MALL SPOT WELDS.  ORDERED ALL NEW CYLINDER COVERS TO REPLACE THESE LIFTER COVERS.	1	L	7	2 	3O	3	O		A12SW   	E14EA	5	C	P33EA	 
2006062600047	20060626	00047	EA  	2006	6	26	CA060530006      	2	20060525	G	8500		ENGINE          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  		FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								RL114176T			(CAN) ON TAKE-OFF THE AIRCRAFT WOULD NOT DEVELOP FULL POWER SO THE PILOT ABORTED THE TAKE-OFF.  AIRCRAFT WAS BROUGHT INT	O THE HANGER AND AME'S REMOVED COWLING AND REMOVED VALVE COVERS. IT WAS NOTED THAT ALL THE CLEARANCES ON THE VALVES WERE	 TOO LOOSE. AIRCRAFT HAD A NEW ROLLER LIFTERS AND CAM INSTALLED IAW STC SE 03-3 ONLY 24.0 HRS BEFORE BY AN APPROVED ENGI	NE SHOP. ENGINE SHOP WAS CONTACTED AND THEY CONTACTED OWNER OF STC. OWNER OF THE STC WAS CONTACTED AND THEY REQUESTED TH	AT THE ENGINE BE SHIPPED TO THEM FOR REPAIR. (TC NR 20060530006)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006062700087	20060627	00087	WP  	2006	6	27	CA060530007      	2	20060515	G	7200	3582681	CARRIER ASSY    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			32814	1894 				P54019			(CAN) OIL SAMPLE RECEIVED FROM WEAR CHECK INDICATING HIGH OIL FILTER WEIGHT W/MAJOR ALUMINUM, MINOR CARBON STEEL IN SAMP	LE. ENG REMOVED FOR INSP.  DURING TEARDOWN: PLANETARY CARRIER SPLINE LOCKS STRIPPED/DESTROYED.  CARRIER WORN DUE TO EXCE	SS PIN LOADING. ALL CARRIER GEARS EXCESS GEAR WEAR.  INSP REVEALED THAT BOLT NR180 IN REDUCTION GEARBOX LOOSENED, CAME I	N CONTACT W/ACCESSORY SPUR GEAR CAUSING SPUR GEAR DAMAGE, OIL DETECTOR DAMAGE. MOST COMPONENTS IN REDUCTION GEAR BOX EXI	BITED SIGNS OF EXCESS VIBRATION, BOLTS WHICH WERE UNDER TORQUE AS INDICATED BY WEAR PATTERNS ON WASHERS HAD LOOSENED.   	PROP INSTALLED ON THIS ENG WAS INSPECTED AND FOUND SERVICEABLE. REASON FOR VIBRATION NOT DETERMINED. (TC NR 20060530007)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2006062600048	20060626	00048	EA  	2006	6	26	CA060530008      	2	20060530	G	7310	3027039	LINE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL CONTROL	CRACKED         	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT HAD TAXIED TO RUN-UP AREA PRIOR TO TAKEOFF. WHILE COMMENCING ENGINE RUN-UP NOTICED THAT THERE WAS NO THRO	TTLE RESPONSE ON THE RT ENGINE. CREW CONTACTED MAINTENANCE AND REQUESTED A TOW BACK TO THE HANGER. MAINTENANCE FOUND THA	T THE FUEL FEED LINE FROM THE FCU TO THE FUEL FLOW DIVIDER WAS CRACKED AND SPRAYING FUEL INSIDE THE ENGINE NACELLE. CRAC	K WAS AT THE FCU END OF THE FUEL LINE, CRACK RAN PARALLEL WITH THE SWAGGED FERRULE. FUEL LINE REPLACED AND AIRCRAFT RETU	RNED TO SERVICE. (TC NR 20060530008)		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006062700088	20060627	00088	NM  	2006	6	27	CA060530009      	1	20060525	G	6123	JV5	ACTUATOR        			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AUTOFEATHER SYS	INOPERATIVE     	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PRE-FLIGHT CHECKS WHEN PROP AUTOFEATHER, ON EITHER ENG, WAS SET TO TEST AND PWR LEVER ADVANCED, PROP WOULD 	GO INTO TEST (FEATHER) AND STAY THERE, RELEASING TEST SWITCH, SETTING PWR LEVERS TO IDLE DID NOT UN-FEATHER PROP. AUTOFE	ATHER SELECT SWITCH HAD TO BE SET TO (OFF) FOR SYS TO RETURN TO NORMAL. AUTOFEATHER WOULD ARM NORMALLY WHEN PWR LEVERS W	ERE ADVANCED TO TAKEOFF PWR, PROBLEM ONLY OCCURRED WHEN SYS WAS SET TO TEST.  SYS WAS DE-ACTIVATED, AC WAS OPERATED UNDE	R MEL. MAINT FOUND PIECE OF ACTUATOR (JV5) FOR NR 1 PWR CNTRL MICROSWITCH (S13) HAD BROKEN OFF, WAS KEEPING MICOSWITCH (	S13) CLOSED ALL THE TIME. MICROSWITCH AND ACTUATOR WERE REPLACED, AUTOFEATHER SYS TESTED NORMAL.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006061400205	20060614	00205	NM  	2006	6	14	CA060531001      	1	20060530	G	5610	58935734	WINDOW          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											ON APPROACH, THE F/O'S NR 4 EYEBROW WINDOW SHATTERED.  APPROACH CONTINUED AND AN UNEVENTFUL LANDING FOLLOWED.  WINDOW RE	PLACED.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006061400206	20060614	00206	NE  	2006	6	14	CA060531003      	2	20060525	G	8530	899353	CYLINDER HEAD   			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					NR 2	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1345 							CYLINDER ASSEMBLY NR 2 HEAD FOUND CRACKED BETWEEN SPARK PLUG HOLES.  OH ASSEMBLY INSTALLED.						1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006062600049	20060626	00049	EA  	2006	6	26	CA060531004      	2	20060426	G	7250		SCOOP           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 5 BEARING	DETERIORATED    	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) THE ENGINE FLAMED OUT ON ROTATION RESULTING IN AN ABORTED TAKE-OFF.  SUBSEQUENT INVESTIGATION REVEALED DAMAGE TO T	HE HPT STUB SHAFT AS A RESULT OF NR 5 BEARING OIL SCOOP DETERIORATION. (TC NR 20060531004)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006062600050	20060626	00050	EA  	2006	6	26	CA060531005      	2	20060407	G	7321	324475520	FUEL CONTROL    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					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 ENGINE WAS SHUT DOWN IN FLIGHT AND THE AI	RCRAFT DIVERTED.  THE FUEL CONTROL WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE O	NCE DETERMINED. (TC NR 20060531005)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062700090	20060627	00090	NE  	2006	6	27	CA060531007      	2	20060427	G	7321		SPLINE          			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  					FUEL CONTROL	WORN            	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			1828 			C3106					(CAN) ENGINE TORQUE WAS REPORTED TO FLUCTUATE IN CRUISE BY AS MUCH AS 50 PERCENT AND THE ENGINE WAS SHUTDOWN IN FLIGHT. 	 SUSEQUENT INVESTIGATION REVEALED WORN MECHANICAL FUEL CONTROL DRIVE SPLINES. (TC NR 20060531007)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006062700091	20060627	00091	NE  	2006	6	27	CA060531008      	2	20060428	G	7200		ENGINE          			AIRTRC	AT500 	AT502       	0390303	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  						FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER IN FLIGHT LEADING TO A FORCED LANDING AND RESULTANT AIRFRAME DAMAGE.  M	FG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531008)					1	L	7	1 	3T	4	T	NC	A9SW    	E4EA				 
2006062600051	20060626	00051	NE  	2006	6	26	CA060531009      	2	20060508	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PS0125			(CAN) DURING TAKE-OFF ROLL THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY SEIZURE OF THE POWER SECTION.  SU	BSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE O	NCE ESTABLISHED. (TC NR 20060531009)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006062600052	20060626	00052	SW  	2006	6	26	CA060531010      	1	20060404	G	6200		ROTOR           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FOLOWING CLIMB THE MAIN ROTOR SPEED DECREASED UNCOMMANDED AND THE LOW ROTOR RPM WARNING ACTIVATED.  AN EMERGENCY L	ANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE.  NR WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE E	STABLISHED. (TC NR20060531010)				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062600053	20060626	00053	NE  	2006	6	26	CA060531011      	2	20060511	G	7200		ENGINE          			PILATS	PC7   	PC7         	7090401	EU  	PWA   	PT6   	PT6A25      	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								PF0037			(CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER FOLLOWING TAKE-OFF, RESULTING IN A FORCED LANDING.						1	L	7	1 	3T	3	T	RT	A50EU   	E4EA				 
2006062700092	20060627	00092	EA  	2006	6	27	CA060531012      	2	20060527	G	7200		ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER SECTION	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA				320  				PCE40252			(CAN) IN CRUISE, THE CHIP LIGHT ACTIVATED ON THE LT ENGINE.  THE ENGINE WAS SHUTDOWN AS A PRECAUTION AND THE AIRCRAFT DI	VERTED TO NEAREST FIELD FOR NORMAL LANDING. CFR WAS REQUESTED TO BE ON STANBY.  THERE WAS NO OTHER INDICATIONS OF ENGINE	 PROBLEMS.  THE CHIP PLUG WAS REMOVED AND CLEANED.  THE OIL SYSTEM WAS FLUSHED AND CHECKED AGAIN FOR CONTAMINATION.  AS 	A PRECAUTION THE AIRCRAFT WAS FLOWN TO AN ENGINE OVERHAUL FACILITY WHERE THE ENGINE WAS REMOVED.  DETAILS OF THE OVERHAU	L FINDINGS WILL BE FORWARDED WHEN AVAILABLE. (TC NR 20060531012)		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006062600054	20060626	00054	NE  	2006	6	26	CA060531013      	2	20060427	G	7200		ENGINE          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  						SURGES          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								94609			(CAN) DURING CRUISE THE ENGINE WAS REPORTED TO SURGE AND SUBSEQUENTLY FLAME OUT.  MFG WILL INVESTIGATE THE EVENT AND WIL	L ADVISEOF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531013)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062700093	20060627	00093	NE  	2006	6	27	CA060531014      	2	20060517	G	7270		PANEL           			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					BYPASS DUCT	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CA0339			(CAN) DURING GROUND INSPECTION METAL DEBRIS WAS FOUND LODGED IN THE ENGINE BYPASS DUCTING.  THE ENGINE'S INNER BYPASS DU	CT PANELS WERE FOUND FRACTURED. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 2006	0531014)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006062700095	20060627	00095	NE  	2006	6	27	CA060531015      	2	20060521	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MAKING METAL    	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			R	A		PARTIAL RPM/PWR LOSS      	FLAME/FIRE                		DE	DESCENT        	1			CA								114336			(CAN) DURING DESCENT THE ENGINE WAS REPORTED TO LOSE POWER ACCOMPANIED BY A FIRE.  THE CREW DEPLOYED FIRE EXTINGUISHERS 	AND SHUT THE ENGINE DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE EXHAUST.  MFG WILL INVESTIGATE T	HE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006062700149	20060627	00149	NE  	2006	6	27	CA060531016      	2	20060530	G	7250		BLADE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA				5771 							(CAN) UPON APPLYING TAKEOFF POWER FOR DEPARTURE, THE PILOT HEARD A LOUD BANG. HE THEN INITIATED A SUCCESSFULL REJECTED T	AKEOFF.  UPON STOPPING, A PASSENGER CAME FORWARD AND STATED THAT HE THOUGHT SOMETHING FELL OFF THE RT WING.  THE RT ENGI	NE WAS SECURED. THE AIRCRAFT TAXIED BACK TO THE GATE AND PASSENGERS DISEMBARKED. UPON INVESTIGATION BY MAINTENANCE THE R	T ENGINE SEEMS TO HAVE SUFFERED A POWER TURBINE BLADE FAILURE. THE DEBRIS FROM THE BLADES IS WHAT THE PASSENGERS WOULD H	AVE SEEN. ENGINE WILL BE FORWARDED TO THE MFG FOR INVESTIGATION. SDR WILL BE LEFT OPEN AND UPDATED WITH INVESTIGATION FI	NDINGS. (TC NR20060531016)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006062700150	20060627	00150	NE  	2006	6	27	CA060531017      	2	20060521	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA								120632			(CAN) ON APPROACH, ENGINE TORQUE WAS REPORTED TO FLUCTUATE AND THE ENGINE WAS SUBSEQUENTLY SHUTDOWN IN FLIGHT.  MFG WILL	 INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062700153	20060627	00153	NE  	2006	6	27	CA060531018      	2	20060522	G	7532		BLEED VALVE     			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE ENGINE EXPERIENCED COMPRESSOR STALLS ACCOMPANIED BY A RISE IN INTER-TURBINE TEMPERATURE AND ODORS	 IN THE CABIN.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE ENGINE BLEED VALVES AND BLEED VALVE SOLENOID WERE SUBSEQUENTLY R	EPLACED. (TC NR 20060531018)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006062700161	20060627	00161	NE  	2006	6	27	CA060531019      	2	20060522	G	7320		EEC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE ENGINE EEC FAULT LIGHT ACTIVATED FOLLOWED BY A LOUD NOISE AND A LOSS OF POWER.  THE ENGINE WAS SH	UTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE EEC WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIG	ATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531019)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006062700168	20060627	00168	EA  	2006	6	27	CA060531020      	2	20060515	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A21      	52043	EA  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								24774			(CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A NOISE AND WAS SHUT DOWN IN FLIGHT.  AN EMERGENCY WAS DECLARED AND T	HE AIRCRAFT DIVERTED. THE AIRFRAME WAS DAMAGED IN THE SUBSEQUENT LANDING (OVERSHOOT).   MFG WILL INVESTIGATE THE EVENT A	ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531020)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062700170	20060627	00170	NE  	2006	6	27	CA060531021      	2	20060523	G	7250		TURBINE BLADES  			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					TURBINE SECTION	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF CLIMB, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION AND A FIRE WAR	NING.  THE ENGINE WAS SHUTDOWN IN FLIGHT, AT WHICH POINT THE FIRE WARNING DEACTIVATED. THE AIRCRAFT DIVERTED TO POINT OF	 DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF	 ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531021)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062700175	20060627	00175	NM  	2006	6	27	CA060531022      	1	20060524	G	7931	30B296301	SEAL            			PROPJT	200   	200A        	0140304	NM  	PWA   	306   	PW306B      	 	NE  					ACCESSORY GBOX	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE LOW OIL PRESSSURE WARNING ACTIVATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT	 DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INVESTIGATION REVEALED A DAMAGED AND LEAKING ACCESSORY GEARBOX LIP SEAL. (T	C NR 20060531022)				1	L	7	1 	3O	4	F		3A18    	E35NE				 
2006062700254	20060627	00254	EA  	2006	6	27	CA060531023      	2	20060524	G	7200		ENGINE          								PWA   	PT6   	PT6A27      	52043	EA  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PG0018			DURING CRUISE, ENGINE OIL PRESSURE WAS REPORTED TO DECREASE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE ENGIN	E WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR AND AN INABILITY 	TO ROTATE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.									4	T			E4EA				 
2006062700184	20060627	00184	NE  	2006	6	27	CA060531024      	2	20060429	G	7250		TURBINE BLADES  			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA								PS0139			(CAN) DURING TAKEOFF ROLL, THE ENGINE WAS REPORTED TO VIBRATE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  TAKEOFF	 WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT 	AND REPORT ON ROOT CAUSE ONCE DETERMINED. (TC NR 20060531024)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006062700185	20060627	00185	SO  	2006	6	27	CA060531025      	1	20060531	G	3221	4033600	LINK ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16119								(CAN) FOUND PART CRACKED ON 1 LUG EXACTLY WHERE NOTED IN PIPER SERVICE LETTER 1088. THIS CRACK WAS VISIBLE WITH THE NAKE	D EYE, BUT ONLY AFTER THE PAINT WAS REMOVED. (TC NR 20060531025)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006062700186	20060627	00186	GL  	2006	6	27	CA060601001      	2	20060531	G	7510		GASKET          			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	J		WARNING INDICATION        	WARNING INDICATION        		CL	CLIMB          	1			CA								500934			(CAN) DEPARTING, CREW OBSERVED A NACELLE OVER HEAT INDICATION ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT R	ETURNED TO POINT OF DEPARTURE. ON APPROACH THE LT MAIN GEAR FAILED TO INDICATE DOWN AND LOCKED, AFTER VISUAL CONFIRMATIO	N THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE GASKET AT THE UPPER MANIFOLD 14TH STAGE BLEED A	ND THE LT MAIN GEAR DOWNLOCK SWITCH. THE AFFECTED SYSTEMS WERE FUNCTION CHECKED AND THE THE AIRCRAFT RETURNED TO SERVICE	. (TC NR 20060601001)		2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2006062700187	20060627	00187	EA  	2006	6	27	CA060601002      	2	20060531	G	7220		DUCT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DEVELOPED IN THE DOMED PORTION OF THE SMALL EXIT DUCT BESIDE THE WELD.  FOUND DURING THE BOROSCOPE INSPECTIO	N. (TC NR 20060601002)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006062700188	20060627	00188	NE  	2006	6	27	CA060601003      	2	20060527	G	7261		PACKING         			PROPJT	200   	200A        	0140304	NM  	PWA   	306   	PW306B      	 	NE  					OIL CAP	MISINSTALLED    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECT	ION REVEALED OIL LOSS ASSOCIATED WITH A MISINSTALLED OIL CAP O-RING PACKING. (TC NR 20060601003)					1	L	7	1 	3O	4	F		3A18    	E35NE				 
2006062700189	20060627	00189	EU  	2006	6	27	CA060601004      	1	20060530	G	7931		PRESSURE VALVE  			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  					OIL SYSTEM	INOPERATIVE     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) IN TAKE-OFF CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE AIRCR	AFT RETURNED TO POINT OF DEPARTURE.  THE ENGINE OIL PRESSURE REGULATING VALVE WAS REPLACED. (TC NR 20060601004)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006062700190	20060627	00190	NE  	2006	6	27	CA060601005      	2	20060531	G	7250		TURBINE BLADES  			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	FRACTURED       	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PS0117			(CAN) DURING TAKE-OFF ROLL THE ENGINE EMITTED A LOUD NOISE AND TAKE-OFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED FRA	CTURED POWER TURBINE BLADES AND RESULTS, EXHAUST STUB DAMAGE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE	 ONCE ESTABLISHED. (TC NR 20060601005)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006062700191	20060627	00191	SW  	2006	6	27	CA060601006      	1	20060327	G	7714	2090753261	DETECTOR        			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					RPM LIMIT	FAILED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA				83   							(CAN) ENGINE OUT LIGHT STAYS ON AFTER ENGINES STARTED. RPM LIGHT INTERMITTENT WITH RPM IN NORMAL OPERATING RANGE.THE REL	IABILITY OF THESE UNITS ARE NOT GOOD.IN OUR FLEET OF 4 BELL 212'S WE GO THROUGH 6 RPM BOXES IN 1 SUMMER (TC NR 200606010	06)				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062700198	20060627	00198	SO  	2006	6	27	CA060602002      	1	20060526	G	2140	30670000	TUBE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	HEATER EXHAUST	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REMOVAL OF A BIRDS NEST IN THE FRESH AIR INTAKE LOCATED IN THE NOSE OF THE AIRCRAFT THE HEATER EXHAUST TUBE	 WAS FOUND TO BE UNSERVICEABLE.  THE TUBE ITSELF IS A (WOUND) TUBE AND THE WINDINGS NEAR THE ATTACH POINT HAD SEPARATED 	THAT WOULD ALLOW HOT EXHAUST TO CONTACT THE TUBE SHROUD. (TC NR 20060602002)				1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2006062700199	20060627	00199	SO  	2006	6	27	CA060602003      	2	20060602	G	7322	991026720	THROTTLE CABLE  			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DOING UPPER AIR WORK, IT WAS NOTICED THEIR WAS NO THROTTLE RESPONSE FROM RT ENGINE. THE ENGINE WAS RUNING NORMAL S	O THE CREW RETURNED TO AIRPORT AND DID A NORMAL LANDING AND SHUTDOWN OF ENGINE ON TOUCHDOWN. MAINTENANCE FOUND THE THROT	TLE CABLE BROKEN AT THE FUEL CONTROL UNIT WHERE THE FLEX CABLE IS CRIMPED INTO THE SOLID ROD. PARTS ON ORDER. (TC NR 200	60602003)			1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
2006062700219	20060627	00219	SW  	2006	6	27	CA060602004      	1	20060529	G	6220	204011179003	DRAG BRACE      			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7778 	704  							(CAN) THE DRAG BRACE WAS IN THE COMPONENT SHOP GETTING ITS 1200 HR INSPECTION/24 MONTH INSPECTION. THE DRAG BRACE ASSEMB	LY WAS PREPARED FOR NDT MAGNETIC PARTICLE INSPECTION. THE NDT SHOP FOUND THIS FITTING WAS CRACKED ON THE IB CURVE. (TC N	R 20060602004)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006062700220	20060627	00220	EA  	2006	6	27	CA060604001      	1	20060522	G	2460	S69381	BUSS BAR        			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  						DAMAGED         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) C/B 1D6 (DC 1 FEED) POPPED ON SHORT FINAL CAUSING VARIOUS SYSTEMS TO GO INOP.  THEY DID A GO AROUND RESETTING THE 	C/B, IT POPPED AGAIN ON SHORT FINAL. MAINT FOUND THE BUS BAR BETWEEN CBP-D1 AND CBP-1-D7 (IPC 24-08-01, ITEM 275)WAS NOT	 SECURED DAMAGING THE CIRCUIT BREAKER. MAINT REPLACED THE DAMAGED CIRCUIT BREAKER AND TIGHTENED THE BUS BAR.  OPS GOOD. 	(TC NR 20060604001)			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006062700221	20060627	00221	EA  	2006	6	27	CA060604002      	1	20060525	G	4920	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						INOPERATIVE     	W				F				ACTIVATE FIRE EXT.      				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXING IN PREPARATION FOR TAKEOFF, CREW NOTED SMOKE AROUND AC, TOWER REPORTED SMOKE, FLAMES COMING FROM AFT 	AREA OF AC UNDER NR 2 ENG.  APU WAS SHUTDOWN, CREW THEN ELECTED TO TAXI OFF ACTIVE TAXIWAY TO A NON ACTIVE TAXIWAY. SHOR	TLY AFTER STOPPING AC, AN APU FIRE MESSAGE WAS POSTED ON EICAS. CREW COMPLETED QRH PROCEDURE FOR APU FIRE. CREW DISCHARG	ED AT LEAST ONE FIRE BOTTLE, AND FIRE INDICATIONS EXTINGUISHED. CFR RESPONDED AND DISCHARGED HALON INTO APU ENCLOSURE. C	REW THEN EVACUATED PASSENGERS THROUGH MAIN CABIN DOOR EXIT USING QRH PROCEDURE. ONE PASSENGER SUSTAINED A CUT FINGER. NO	 OTHER INJURIES REPORTED.  THE APU WAS REPLACED, AC RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062700222	20060627	00222	EA  	2006	6	27	CA060605001      	1	20060530	G	3510	S694603	LINE            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					OXYGEN SYS	RUPTURED        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) PASSING ABOUT 17000 FT ON CLIMBOUT FROM DFW AN QXYGEN LEAK OCURRED FROM OBSERVERS MASK COMPARTMENT AND DEPLETED AL	L THE QXYGEN. FOLLOWED OXY LO PRESS PROCEDURE, DECLARED EMERGENCY, DESCENDED AND RETURNED TO DFW.  TROUBLESHOT A/C AND F	OUND O2 LINE BEHIND OBSERVERS O2 MASK RUPTURED. REPLACED LINE IAW CRJ MM 35-11-03. INSTALLED SERVICEABLE CREW O2 BOTTLE 	IAW CRJ MM 35-11-03. NO LEAKS NOTED.   LINE REF TO AIPC 35-13-01 FIG 01-A01 PAGE 2 ITEM 70. (TC NR 20060605001)			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006062700223	20060627	00223	EU  	2006	6	27	CA060605002      	1	20060523	G	6300	350A35105901	DISK            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4734 								(CAN) DURING A 500 HOUR INSPECTION, WHILE INSPECTING THE ENGINE TO MGB ASSY IAW MM, WC 63-00-00-601, AME NOTICED BLACK M	ARKS AROUND 3 OUT OF 6 BOLTS LINKING DISK ASSY TO POWER SHAFT (MARKS LIKE (SMOKING RIVETS). USING A 13MM WRENCH, COULD E	ASILY ROTATE THOSE 3 BOLTS BY THE HEAD. THE COTTER PINS WERE NORMALLY INSTALLED BUT THE BOLTS HAD LOST THEIR TORQUE. AFT	ER REMOVAL, BUSINGS OF THE DISK ASSY SHOWED FRETTING MARKS, AND WERE PARTIALLY UNCRIMPED. REPLACED DISK ASSY AND ASSOCIA	TED HARDWARE PLUS INSPECTIONS ASKED FOR BY WC 63-00-00-601 C/O. (TC NR 20060605002)		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006062700255	20060627	00255	SO  	2006	6	27	CA060605003      	2	20060601	G	8530	SA52000A1	CYLINDER HEAD   			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TO	TAKEOFF        	1			CA			382  								AIRCRAFT HAD JUST TAKEN OFF WHEN THE PILOT HEARD A LOUD BANG, HE TURNED AROUND AND LANDED AGAIN.  UPON INSPECTION OF THE	 ENGINE, FOUND THE NR 4 CYLINDER WAS CRACKED AT THE HEAD JUST ABOVE THE THREADS WHERE THE HEAD AND CYLINDER ARE JOINED. 	 CYLINDER WAS REMOVED AND REPLACED.  HAD ENCOUNTERED THE SAME PROBLEM WITH NR 6 AND NR 2 ABOUT 160 HOURS EARLIER HAD TRO	UBLE WITH NEW PILOTS AND THOUGHT THIS WAS CAUSING PROBLEM.  OVERHAUL WAS CARRIED OUT AT AERO RECIP, THEY WERE CONTACTED 	AND WILL BE INSTALLING 6 NEW CYLINDERS.		1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006062700224	20060627	00224	EA  	2006	6	27	CA060605004      	1	20060603	G	7830	22850809801	THRUST REVERSER 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) FLIGHT CREW REPORTED THAT THEY RECEIVED A  (L REV UNLOCKED) CAUTION MESSAGE ON RUNWAY AND LINED UP FOR TAKEOFF WIT	H NO REPORTED CHANGE TO THE N1 OR N2 INDICATIONS. MESSAGE THEN FLICKERED ON AND OFF. WHILE TAXIING BACK TO THE GATE THE 	MESSAGE WENT OUT. AFTER AC SHUTDOWN MESSAGE REAPPEARED. REV LOCKED OUT IAW MEL 78-30-02 AND TASK 78-30-00-040-802. TRACK	 ASSY NOTED TO BE CRACKED IAW REO 601R-78-30-3253. AC FERRIED, TRACK ASSY REPLACED. AC RELEASED INTO SERVICE. (TC NR 200	60605004)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062700225	20060627	00225	SW  	2006	6	27	CA060605005      	1	20060601	G	3246	206020110005	SKID            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12163								(CAN) DURING A ROUTINE 300 HR INSP OF THE AC, IT WAS NOTED THAT A SMALL PIECE OF PAINT HAD FALLEN OFF OF THE LOWER AFT E	ND OF THE TAIL SKID ASSY, AT THE LOWER WELD BEAD JOINT. UPON FURTHER INVESTIGATION, IT WAS NOTED THAT A SMALL HOLE (APPR	OX .1875) WAS PRESENT. WHEN THE WELD AREA WAS INSPECTED ON THE OPPOSITE SIDE, A SMALL AREA OF CORROSION WAS ALSO NOTED, 	BUBBLING UNDER THE PAINT. THE CORROSION WAS REMOVED WHICH REVEALED ANOTHER SMALL HOLE (APPROX .1875). THIS AREA OF THE T	AIL SKID ASSY IS ALSO THE LOWEST POINT, WHERE WATER AND CONDENSATION CAN BE TRAPPED. A NEW TAIL SKID ASSY WAS PURCHASED 	AND INSTALLED ON THE AIRCRAFT. (TC NR 20060605005)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062700226	20060627	00226	SW  	2006	6	27	CA060605006      	1	20060531	G	5320	206031121023	WEB             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12163								(CAN) DURING A ROUTINE 300 INSP ON THE AIRFRAME, A CRACK WAS NOTED ON UPPER AFT SECTION OF THE SEAT WEB ASSY. THIS AREA 	IS PRONE TO STRESS AND CRACKS WHEN THE SEAT PANEL (THAT IS ATTACHED TO IT) IS REMOVED, AND NO SUPPORT IS ADDED TO THE TO	P OF THIS WEB ASSY. PEOPLE TEND TO LEAN OVER THIS AREA, PUTTING THEIR HANDS ON THE TOP OF THE WEB AND THE WEB ENDS UP SU	PPORTED THE PERSONS WEIGHT. THIS IS THE PROBABLE CAUSE OF THE CRACK, WHICH CAN HAPPEN OVER TIME. THE WEB ASSY WAS REPLAC	ED WITH A NEW PIECE, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060605006)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062700227	20060627	00227	GL  	2006	6	27	CA060605007      	2	20060603	G	7210	7636109103104	SHAFT           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THREADED END BROKEN OFF DURING ASSY.  (ENGINE POWER OUTPUT ADAPTOR SHAFT) (TC NR 20060605007)						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2006062700228	20060627	00228	SW  	2006	6	27	CA060605008      	1	20060531	G	5313	206031123059	LONGERON        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12163								(CAN) DURING A ROUTINE 300 HR INSP, A CRACK WAS FOUND ON THE LONGERON ABOVE THE LT REAR PASSENGER DOOR, AT THE FWD ATTAC	HMENT TO THE ROLLOVER BULKHEAD. THE CRACK ORIGINATED AT THE ATTACHING RIVETS. THE LONGERON WAS REPLACED WITH A NEW PIECE	, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060605008)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062700229	20060627	00229	EU  	2006	6	27	CA060605009      	1	20060603	G	2497		WIRE            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	AC GEN	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WE HAD BEEN HAVING TROUBLES WITH NR 2 AC GENERATOR FAULTS IN FLIGHT. AFTER READING SDR NR 20050427005, WE CHECKED 	OUR ATR AND DISCOVERED NR 2 AC GEN WIRING CHAFING AND ARCING ON NR 2 STARTER GENERATOR COOLING DUCT. WIRING REPAIRED AND	 INSULATED AS REQUIRED. WIRING SECURED TO PREVENT FUTURE CHAFING. (TC NR 20060605009)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006062700230	20060627	00230	SW  	2006	6	27	CA060605010      	1	20060513	G	6320	204040009061	TRANSMISSION    			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION.  NO CHIP LIGHT INDICATION. OIL DRA	INED WITH NEW FILTER INSTALLED, AIRCRAFT RUN FOR ONE HOUR ON GROUND WITH METAL PARTICLES FOUND IN INTERNAL AND INLINE FI	LTER ASSY.  NO CHIP LIGHT INDICATION. TRANSMISSION WAS REMOVED WITH T.S.N. 6631.1 T.S.O. 472.3 (TC NR 20060605010)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006062700231	20060627	00231	NE  	2006	6	27	CA060605011      	2	20060529	G	7323	430110116	GOVERNOR        			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					MAIN ROTOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2334 							(CAN) HELICOPTER STARTED NORMALLY BUT WHEN THE THROTTLE WAS ADVANCED TO THE GATE (100 PERCENT NR), THE MAIN ROTOR STARTE	D OVERSPEEDING (400 RPM APPROX). THE THROTTLE WAS THEN PULLED BACK AND THE ROTOR SPEED DROPPED. WHEN THE THROTTLE WAS AD	VANCED INTO THE GATE AGAIN, THE NR STARTED OSCILLATING BETWEEN 360 AND 400 NR WITH NO INPUT FROM THE THROTTLE OR COLLECT	IVE. THE GOVERNOR WAS REPLACED AND THE PROBLEM WENT AWAY. (TC NR 20060605011)			1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2006062700232	20060627	00232	SW  	2006	6	27	CA060605012      	1	20060525	G	6210	212015501115	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3417 								(CAN) MAIN ROTOR BLADE SMALL DEBOND FOUND ON LOWER SURFACE APPROX 81.5 INCHES FROM BUTT END JUST AFT OF THE STAINLESS ST	EEL LEADING EDGE STRIP ON DISASSEMBLY. (APRIL 07 2006) BLADE WILL BE INSPECTED WHEN ARRIVING BACK FOR REPAIR EVALUATION.	 PAINT REMOVED FROM DEBOND AREA WITH A SMALL CRACK FOUND CHORD WISE APPROX .7500 OF AN INCH LONG.(MAY 25 2006)  (TC NR 2	0060605012)			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062700233	20060627	00233	WP  	2006	6	27	CA060606001      	1	20060605	G	6240	B3203	WARNING HORN    			ROBSIN	R44   	R44RAVENII  	7640122	WP  										COCKPIT	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			17   								(CAN) WARNING HORN WOULD NOT BE TRIGGERED BY THE COLLECTIVE MICRO SWITCHES.  THE UNIT WOULD ONLY CLICK WHEN ACTIVATED AN	D TAPPING DIRECTLY ON THE UNIT WOULD THEN TRIGGER THE HORN.  WIRING WAS CORRECT, AND NOT PART OF THE SNAG. (TC NR 200606	06001)				1	G	7	1 	3O				H11NM   					 
2006062700234	20060627	00234	WP  	2006	6	27	CA060606002      	1	20060512	G	6240	B3203	WARNING HORN    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			31   								(CAN) LOW ROTOR RPM WARNING HORN NOT SOUNDING.  REPLACED WITH A SERVICEABLE UNIT, NO FURTHER FAULTS FOUND. (TC NR 200606	06002)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062700235	20060627	00235	SW  	2006	6	27	CA060606004      	1	20060605	G	3240	20700600	LINE            	CLEVELAND   	3098C       	AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	BRAKE ASSY	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1910 								(CAN) PILOT REPORTED RT BRAKE ALWAYS GOES SOFT WHILE TAXING. AFTER INSPECTING ENTIRE BRAKE INSTALLATION FOR LEAKS,  FOUN	D THE FWD AND AFT BRAKE CALIPER INTERCONNECT HOSE, FWD FITTING CRACKED. THIS CRACK WAS ONLY APPARENT WHEN THE BRAKES HEA	T UP AND THE CRACK OPENED AS IT EXPANDED, CAUSE FLUID TO LEAK. THE HOSE WAS REPLACED WITH NEW UNIT AND BRAKES BLED WITH 	NO FURTHER FAULTS. (TC NR 20060606004)			1	L	7	1 	3T	4	T	NC	A17SW   	E4EA	6	C	P15EA	 
2006062700236	20060627	00236	WP  	2006	6	27	CA060606005      	1	20060512	G	7720	624600718	GAUGE           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CYLINDER HEAD	STICKING        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			31   								(CAN) CHT WAS REPORTED TO BE STICKING.  THE GAUGE WAS FOUND TO BE NOT INSTALLED PROPERLY, CAUSING THE NEEDLE TO RUB ON T	HE FACE.  THE GAUGE WAS REINSTALLED, AND NO FURTHER FAULTS WERE FOUND. (TC NR 20060606005)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006062700237	20060627	00237	NE  	2006	6	27	CA060606006      	2	20060605	G	7310		FILTER          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	FUEL SYS	CLOGGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT CREW NOTICED NR 1 ENGINE FUEL FILTER CLOG LIGHT ON. AIRCRAFT RETURNED TO BASE. MAINTENANCE REMOVE	D NR 1 ENGINE LP AND HP FUEL FILTERS FOR INSPECTION. LARGE AMOUNTS OF CONTAMINENTS FOUND IN LP. FILTERS WERE REPLACED. G	ROUND RUN CARRIED OUT. THIS IS THE SECOND OCCURANCE OF FUEL CLOG WARNING. 1ST AFTER 25 HRS FOLLOWING C-CHECK INSP. THE S	ECOND 1000HRS FOLLOWING C-CHECK. (TC NR 20060606006)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006062700238	20060627	00238	EA  	2006	6	27	CA060606007      	1	20060602	G	2913	848847	PUSH-PULL CABLE 	BOMBDR      	848847      	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HYDRAULIC PUMP	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			5103 	5103 		MX564379					(CAN) DURING CLIMB CREW RECEIVED NR 3 HYDRAULIC HIGH TEMPERATURE CAUTION LIGHT. CREW ELECTED TO RETURN TO ORIGINATING AI	RPORT.  MAINTENANCE REPLACED NR 3 B HYDRAULIC PUMP.  A/C RETURNED TO SERVICE. (TC NR 20060606007)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062700239	20060627	00239	CE  	2006	6	27	CA060606008      	1	20060527	G	5697	MS24166D1	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LOW HEAT	DAMAGED         	W				H				DEACTIVATE SYST/CIRCUITS				L			NO TEST                   			NR	NOT REPORTED   	1			CA											(CAN) WHEN GROUND POWER WAS APPLIED TO THE AIRCRAFT IT WAS NOTICED THAT THE LT HEATED WINDSHIELD WAS WARM AND ANTI-ICE S	WITCH WAS OFF. POWER TO WINDSHIELD, LIMITER IN LT NACELLE, WAS PULLED. INSP OF THE LT WINDSHIELD ANTI-ICE HI/LO RELAYS, 	BEHIND INSTRUMENT PANEL, REVEALED THAT TERMINAL A2 OF LO HEAT RELAY HAD HEAT DAMAGE AND WAS NO LONGER ATTACHED TO RELAY,	 IT WAS STILL ATTACHED TO WIRE H16A8, WIRE WAS NO LONGER ATTACHED TO RELAY AND ABOUT ONE INCH OF THE INSULATION FROM WIR	E END WAS MISSING. RELAY INTERNAL CONTACTS A1 TO A2 SHOW EXCESSIVE PITTING AND ARCING. RELAY MS24166-D1 WAS REPLACED AND	 WIRE H16A8 WAS ALSO REPLACED.  (TC NR  20060606008)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006062700240	20060627	00240	GL  	2006	6	27	CA060606009      	2	20060529	G	7322	412B0220	CONTROL CABLE   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					THROTTLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7112 								(CAN) CABLE BROKE APPROXIMATELY 9.5 FROM END. (TC NR 20060606009)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006062700241	20060627	00241	CE  	2006	6	27	CA060606010      	1	20060603	G	2910	GPP125040	PRESSURE SWITCH 			CESSNA	208   	208         	2073702	CE  										HYD SYSTEM	FAILED          	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA			38   								(CAN) UPON APPROACH FOR LANDING, WHEELGEAR WOULD NOT EXTEND (AMPHIBIAN AIRCRAFT) ABORTED APPROACH , AICRAFT LANDED ON FL	OATS AT WATER BASE. AIRCRAFT PLACARDED (FLOATPLANE OPERATION ONLY). (TC# 20060606010)					1	H	7	1 	3T			NT	A37CE   					 
2006062700242	20060627	00242	EA  	2006	6	27	CA060606011      	2	20060605	G	7261	130F0014S0314	LINE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					OIL	LEAKING         	W				C				ABORTED TAKEOFF         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TO	TAKEOFF        	1			CA											(CAN) WHILE APPLYING TAKEOFF POWER THE PILOTS NOTICED SMOKE IN THE CABIN AND ABORTED THE TAKEOFF WITHOUT INCIDENT. DURIN	G INVESTIGATION MAINTENANCE DISCOVERVED THAT A RECENTLY REPLACED OIL PRESSURE LINE TO THE TORQUE TRANSMITTER MANIFOLD WA	S LEAKING AT THE FLARE FITTING. THE HOSE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060606011)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006062700243	20060627	00243	SW  	2006	6	27	CA060606012      	1	20060530	G	3246		BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT MAIN WHEEL	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) MAINT WAS ADVISED BY BASE AT DEPARTURE THAT LT IB MAIN WHEEL ASSY HAD FALLEN OFF AC ON TAKEOFF.  AC CONTINUED TO M	AINT BASE WHERE IT DID FLY BY TO DETERMINE IF WHEEL WAS MISSING.  IT WAS DETERMINED THAT WHEEL ASSY WAS NOT ON THE AC.  	AC LANDED WITHOUT INCIDENT.  LWR GEAR ASSY WAS REMOVED AND REPLACED WITH SERVICEABLE LWR GEAR, WHEEL ASSEMBLIES INCLUDIN	G BRAKES.  AC RETURNED TO SERVICE.  UPON INVESTIGATION OF LWR GEAR IT WAS DISCOVERED THAT OUTER WHEEL BRG WAS HEAT DISCO	LORED,  OUTER RACE AND CAGE WERE MISSING.  INNER RACE SHOWED NO SIGNS OF HEAT DISCOLORATION, CAGE WAS STILL ON THE INNER	 RACE ALTHOUGH QUITE DAMAGED.  FOR AN UNDETERMINED REASON OUTER RACE FAILED AND CAUSED ALL DAMAGE.  (TC NR 20060606012)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006062700244	20060627	00244	NE  	2006	6	27	CA060607001      	2	20060523	G	7200		ROTOR           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE N2	SEIZED          	W				A				UNSCHED LANDING         				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) AS THE AIRCRAFT WAS CLIMBING, FLIGHT CREW HEARD A LOUD BANG AND LOST THE LT ENGINE.  THEY NOTICED THAT THE ITT WAS	 AT 998 DEGREES AND AN ENGINE (VIB) ON THE N2 GAUGE.  IT WAS FOUND THAT THE LT ENG N2 ROTOR WAS FOUND SEIZED WITH HAVING	 THE LT ENGINE REPLACED IAW AMM 71-00-00.  ALL ENGINE PERFORMANCE, FUNCTION AND OPERATIONAL CHECKS CARRIED OUT. ALL ENGI	NE POST GRD RUN LEAK CHECKS CARRIED OUT.  AS FOR NOW, THE PROBLEM IS STILL YET TO BE DETERMINED AND THIS SDR WILL BE UPD	ATED AS SOON AS THERE IS MORE INFORMATION AVAILABLE.  (TC NR 20060607001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062700245	20060627	00245	EA  	2006	6	27	CA060607002      	1	20060605	G	3213	13A04270006	METERING TUBE   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STRUT	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			753  								(CAN) FRACTURED AT LOWER THREAD WHERE THE TUBE SCREWS INTO THE PISTON. THIS ALLOWED THE UPPER AND LOWER SECTIONS OF THE 	SHOCK STRUT TO DISENGAGE CAUSING GEAR COLLAPSE. THE FAILED TUBE IS MADE OF ALUMINUM ALLOY. PART AND PICTURES AVAILABLE U	PON REQUEST (TC NR 20060607002)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006062700246	20060627	00246	NE  	2006	6	27	CA060607003      	2	20060604	G	7200	CF343A1	ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA			21944	21944							(CAN) DURING CLIMB AT 2000 FT THE NR1 ENGINE FAILED, N1 DROPPED OFF AND TGT PEGGED.  EMERGENCY WAS DECLARED AND AC RETUR	NED AND LANDED SAFELY. THIS REPORT IS INITIAL ONLY, FURTHER INFORMATION WILL BE FORWARDED ON RECEIPT OF THE TEARDOWN REP	ORT FROM THE MANUFACTURER. (TC NR 20060607003)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006080300258	20060803	00258	SO  	2006	8	3	CA060607004      	1	20060606	G	2150	C180559A	BLOWER          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					VENT	BURNED OUT      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA				662  							(CAN) SHORTLY AFTER START UP, THE GROUND VENTILATION FAN WAS TURNED ON AND SMOKE STARTED TO ENTER THE AIRCRAFT CABIN. MA	INTENANCE FOUND THE GROUND VENT BLOWER TO BE AT FAULT. THE GROUND VENT BLOWER WAS REMOVED AND DEFERRED. THE AIRCRAFT WAS	 THEN RETURNED TO SERVICE. THE BLOWER WILL BE SENT OUT FOR A STRIP REPORT. (TC# 20060607004)				1	L	7	2 	4T	4	T		A21SO   	E4EA				 
2006062700247	20060627	00247	EA  	2006	6	27	CA060607005      	1	20060520	G	5610	NP13932212	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			3580 								(CAN) DESCENDING THROUGH 11,000 FEET, F/O SIDE WINDOW CRACKED MX REMOVED AND REPLACED SIDE WINDOW IAW CRJ 700 AMM 56-12-	01.  W/S HEAT CHECKS GOOD, NO LEAKS NOTED. (TC NR 20060607005)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006062700248	20060627	00248	EU  	2006	6	27	CA060607006      	1	20060607	G	7930	704A37642043	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE OIL IND	ERRATIC         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			300  								(CAN) TRANSMITTER PRODUCED ERRATIC AND ABNORMALLY LOW  OIL PRESSURE INDICATIONS AT ENGINE IDLE SPEED. (TC NR 20060607006	)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006062700256	20060627	00256	NM  	2006	6	27	CA060608001      	1	20060604	G	5270		SWITCH          			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CARGO DOOR	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											AFTER DEPARTURE ON AN ACCEPTANCE FLIGHT AFTER HEAVY MAINTENANCE, THE CREW OBSERVED A NR 1 CARGO DOOR UNSAFE INDICATION. 	 THE WARNING LIGHT EXTINGUISHED AT 7.2 PSID AFTER REDUCING ALTITUDE TO 11K FT.  THE AIRCRAFT RETURNED TO POINT OF DEPART	URE WHERE THE SWITCH WAS ADJUSTED AND THE AIRCRAFT RELEASED FOR RETURN TO SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006062700257	20060627	00257	EA  	2006	6	27	CA060608002      	2	20060607	G	8530	LW12416	CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NR 2	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3994 	831  				L1487939A			OIL LEAK FOUND COMING FROM ENGINE COWLING.  AFTER FURTHER INVESTIGATION A CRACK WAS DISCOVERED IN THE NR 2 CYLINDER BARR	EL.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20080520		CE  	2008	5	20	CA060608003      	1	20060608	G	2701	041321318	SHAFT           			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	AFT END	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3561 								(CAN) ON INSP, IT WAS FOUND THAT THE RT AND LT CONTROL WHEELS WERE LOOSE ON THE CONTROL SHAFTS. AVION RESEARCH STC 00709	LA HAD PREVIOUSLY BEEN INSTALLED TO REPLACE THE CONTROL WHEELS, HOWEVER, THE INSTALLATION INSTRUCTIONS CW-8001 REV1 FEB2	6/98 DO NOT ADDRESS THE DIFFERENCE IN FASTENER SIZES BETWEEN THE ORIGINAL AND REPLACEMENT CONTROL WHEELS. THE STC HOLDER	 WAS CONTACTED AND A REVISED INSTRUCTION PAGE WAS SUPPLIED THAT REQUIRED ASSEMBLY OF THE CONTROL WHEELS WITH LOCTITE APP	LIED TO THE CONTROL SHAFT. NO REVISION DOCUMENT WAS PROVIDED FOR THE ORIGINAL INSTUCTIONS.		1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006062700258	20060627	00258	SW  	2006	6	27	CA060608004      	1	20060511	G	5302		BOLT            			BELL  	427   	427         	1182207	SW  										TAIL BOOM	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1606 								THE VERTICAL FIN WAS FOUND LOOSE DURING A SCHEDULE INSPECTION.  ONE ATTACHMENT BOLT WAS SHANKED-OUT.  ANOTHER BOLT WAS L	OOSE BUT NOT SHANKED.  NO OTHER DAMAGE WAS REPORTED.					1	G	7	1 	3U				R00001RC					 
2006062700334	20060627	00334	GL  	2006	6	27	CA060608005      	2	20060130	G	7230	23064613	IMPELLER        	ALLSN       		DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47M     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3469 			CAC44183					(CAN) PILOT REPORTED HIGH TURBINE TEMPERATURES IN FLIGHT, RETURNED TO MAINTENANCE FACILITY AND FOUND CRACK IN COMPRESSOR	 SCROLL AREA UPON VISUAL INSPECTION AFTER LANDING.  ENGINE ASSY WAS REMOVED AND COMPRESSOR INLET WAS INSPECTED AND FOUND	 TO HAVE A DAMAGED IMPELLER BLADE.  COMPRESSOR ASSY WAS REMOVED AND SENT FOR FURTHER INSPECTION. IT WAS LATER DETERMINED	 THE BLADE HAD FAILED FROM A PREVIOUS REPAIR CARRIED OUT TO REMOVE FOD DAMAGE TO THAT BLADE.  SPARE ENGINE WAS INSTALLED	 AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060608005)		1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2006062700335	20060627	00335	NM  	2006	6	27	CA060608006      	1	20060321	G	5302	600N3500505	TAIL BOOM       			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47M     	03013	GL  						SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA			3615 								(CAN) AIRCRAFT INVOLVED IN EXTERNAL LIFT OPERATIONS.  TAIL BOOM ASSY SEPARATED FROM FUSELAGE IN FLIGHT, AIRCRAFT CRASHED	 ON RT SIDE OF FUSELAGE IN A REMOTE CLEARING. CAUSE OF FAILURE IS UNDER INVESTIGATION. (TC NR 20060608006)					1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2006062700259	20060627	00259	WP  	2006	6	27	CA060608007      	1	20060527	G	5302		STRUCTURE       			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAILBOOM	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING SCHEDULED MANDATORY REPLACEMENT OF THE HORIZONTAL STABILIZER IT WAS DETERMINED THAT THE NEW PART SUPPLIED BY THE 	MANUFACTURE WAS INCORECTLY MANUFACTURED.  THE MOUNTING HOLES FOR THE ATTACHMENT OF THE VERTICAL STABILIZERS WERE FOUND T	O BE INCORRECTLY LOCATED AND THE ASSOCIATED ANCHOR NUTS WERE MISALIGNED FROM THE HOLES.  PART WAS RETURNED TO THE MANUFA	CTURE TO DETERMINE THE CAUSE OF THE DEFECT.			1	G	7	1 	3O	3	O		H11NM   	E295				 
2006062700249	20060627	00249	NM  	2006	6	27	CA060608008      	1	20060606	G	2622	898052	EXTINGUISHER    			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7450 								THE A/C WAS AT CRUISE WHEN A HISSING SOUND WAS HEARD.  IT WAS DETERMINED TO BE LEAKAGE FROM THE PORTABLE FIRE EXTINGUISH	ER IN THE FLIGHT DECK.  THE HISS CHANGED TO A LOUD WHISTLE AS IT INCREASED.  THE CAPTAIN GRABBED THE TOP OF THE EXTINGUI	SHER AND TWISTED IT AND THE LEAK STOPPED.  THE EXTINGUISHER HAS BEEN RETRIEVED AND IS BEING SENT TO THE VENDOR FOR COMPL	ETE INVESTIGATION AND ANALYSIS.  ONCE THOSE RESULTS HAVE BEEN RECEIVED THEY WILL BE ADDED TO THIS POSTING.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062700250	20060627	00250	CE  	2006	6	27	CA060608009      	1	20060602	G	5610	99143809	WINDSHIELD      			CESSNA	750   	750         	2076810	CE  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			2532 								AIRCRAFT IN CRUISE AT 41000 FT, SMALL CRACK STARTED AT BOTTOM OB LOWER CORNER.  WITHIN 15 SECONDS THE CRACK EXTENDED ABO	UT 3 INCHES THEN WITHIN ABOUT 30 SECONDS THE OUTER PANE SHATTERED.  THE AIRCRAFT WAS FLOWN TO A  AIRPORT AND LANDED WITH	OUT INCIDENT.  THE AIRCRAFT WAS FERRIED TO A SERVICE CENTER UNPRESSURIZED AND A NEW WINDSHIELD INSTALLED.				2	L	7	2 	4J			RT	T00007WI					 
2006062700251	20060627	00251	CE  	2006	6	27	CA060608010      	1	20060531	G	2720	5565096	CHANNEL         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RUDDER PEDAL	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			367  								PILOTS REPORTED THAT WHEN THE RUDDER PEDALS ARE BOTH PUSHED, THE CO-PILOT'S INSTRUMENT LIGHTS DIM.  INVESTIGATION REVEAL	ED THAT THE PILOT'S RUDDER SUPPORT BRACKET WAS BROKEN AT THE TOP OF THE ATTACH CHANNEL.  THE CO-PILOTS INSTRUMENT LIGHT 	RHEOSTAT WAS ALSO DAMAGED.  THE SUPPORT CHANNEL AND THE RHEOSTAT WERE BOTH CHANGED.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006062700336	20060627	00336	NE  	2006	6	27	CA060608011      	1	20060518	G	6320	S613520060103	COVER           	SKRSKY      		SKRSKY	S61   	S61L        	8142102	NE  	GE    	CT58  	CT581401    	30011	NE  					M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				233  		A14964					MAIN GEAR BOX WAS BEING REMOVED FOR INPUT FREEWHEEL REPLACEMENT.  A CRACK WAS DETECTED ON THE RT FOOT OF REAR COVER, AS 	WELL AS A CRACK ON THE RT REAR AIRFRAME FITTING.  THE  ALIGNMENT FIXTURE WAS USED TO CHECK THE BOX BEAM, AND FOUND TO BE	 MISALIGNED.  THE RT REAR AND LT FRONT FITTINGS WERE REPLACED TO CORRECT ALIGNMENT, AND GEAR BOX WAS REPAIRED AND REINST	ALLED.			2	G	7	2 	4U	4	U		1H15    	1E3				 
2006062700338	20060627	00338	EU  	2006	6	27	CA060609002      	1	20060406	G	7712	1004PGSB	TRANSMITTER     			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	TORQUETRANSMTTER	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) TAKEOFF WAS REJECTED WHEN THE RT ENGINE TORQUE GAUGE BEGAN TO INDICATE ERRATICALLY, MEL 77-02 WAS USED FOR RELIEF 	AND THE AIRCRAFT CONTINUED ITS TRIP.  MAINTENANCE DETERMINED THAT THE TORQUE TRANSMITTER HAD FAILED. THE TRANSMITTER WAS	 REPLACED, TESTED SERVICEBLE , MEL CLEARED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060609002)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2006062700339	20060627	00339	NE  	2006	6	27	CA060609004      	2	20060607	G	7510	320115	ANTI-ICE VALVE  			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  						INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											IN CLIMB, THE PORT ENGINE COWL ANTI-ICE LITE ILLUMINATED BRIGHT.  THE AIRCRAFT RETURNED TO BASE.  THE PORT ANTI-ICE VALV	E WAS REPLACED, CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006062700340	20060627	00340	EU  	2006	6	27	CA060612001      	1	20060606	G	3230		WIRE HARNESS    			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	LT MLG	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											DURING DEPARTURE, THE LANDING GEAR WOULD NOT RETRACT.  THE AIRCRAFT RETURNED TO POINT OF DEPATURE AND LANDED WITHOUT INC	IDENT.  MAINTENANCE REPLACED THE UPPER WIRING HARNESS ON THE LT MAIN LANDING GEAR AND THE AIRCRAFT WAS RETURNED TO SERVI	CE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006070500014	20060705	00014	SW  	2006	7	5	CA060612003      	1	20060605	G	5410	NAS12918	NUT             			BELL  	430   	430         	1182150	SW  										PYLON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ONE (1X) NUT FOUND CRACKED.						1	G	7	2 	3U			RT	H9SW    					 
2006070500015	20060705	00015	SO  	2006	7	5	CA060612004      	1	20060609	G	2910	HYC5005	POWERPACK       			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					HYD SYS	FAILED          	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA				902  							HYDRAULIC POWER PACK BRUSHES FAILED, PART REPLACED.						1	L	7	1 	3O	3	O		2A13    	1E10				 
2006070500016	20060705	00016	EA  	2006	7	5	CA060612005      	1	20060612	G	2932	215T752322	PRESSURE SWITCH 	BOMBDR      		CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	ELEVATOR SYS	INTERMITTENT    	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			2856 								DURING A FLIGHT, HAD 3 SUCCESS IFS INPUTS FROM THE ELEVATOR SYSTEM THEY WERE IN NORMAL MODE AND SUDDENLY ITS WENT TO MAN	UAL MODE AND BACK TO NORMAL IN A COUPLES OF A FEW SECONDS WITHOUT ANY ACTION FROM THE CREWS .					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006070500018	20060705	00018	EU  	2006	7	5	CA060612006      	1	20060610	G	5100		UNKNOWN         			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  						UNKNOWN         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA											ON FINAL APPROACH, APPROX 300 FT AGL, PILOT HEARD LOW ROTOR HORN ACTIVATE AND ENG LOOSE PWR. A SUCCESSFUL AUTOROTATION W	AS COMPLETED WITH NO FURTHER INCIDENT.  AFTER LANDING, ENG WAS STILL RUNNING AND ONCE COLLECTIVE WAS LOWERED, ENG RETURN	ED TO FULL PWR.  PILOT TRIED RAISING COLLECTIVE AND EVERY TIME DID SO, ENG WOULD DECELERATE AND M/R RPM WOULD DECAY UNTI	L COLLECTIVE WAS LOWERED AGAIN.  A/C WAS SHUT DOWN AND EXAMINED BY ENGINEER. NO DEFECTS FOUND, AIRCRAFT WAS STARTED AND 	OPERATED NORM.  PILOT WAS ABLE TO HOVER A/C W/OUT RE-EXPERIENCING PREVIOUS SYMPTOMS.  SYMPTOMS COULD NOT BE DUPLICATED A	ND CAUSE OF DECEL COULD NOT BE DETERMINED THEREFORE ALL ENG CONTROL COMPONENTS WERE REPLACED BEFORE FURTHER FLT.	1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2006062700260	20060627	00260	EA  	2006	6	27	CA060612007      	1	20060610	G	3210	C6U1180	LEG ASSY        			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					MLG	DAMAGED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											DURING A NORMAL LANDING PROCEDURE, THE LEFT MAIN LANDING GEAR BROKE OFF FOR A REASON UNKNOWN TO US.  THE AIRCRAFT CONTIN	UED TO SKID ON THE STUD OF THE GEAR UNTIL COMING TO A COMPLETE STOP.  AT THE END, THE AIRCRAFT TIPPED TO THE LEFT AND DA	MAGED THE LEFT WING TIP.  THERE WERE NO PERSONAL INJURIES.  THE DAILY INSPECTION HAD BEEN PERFORMED AS USUAL AND THE PRE	 FLIGHT DID NOT SHOW ABNORMALITIES EITHER. THE TOTAL WEIGHT WAS WITHIN LIMITS.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006070500019	20060705	00019	CE  	2006	7	5	CA060613001      	1	20060608	G	5340	504200337	SUPPORT BEAM    			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	RUDDER QUAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18490	18490							UNDER THE PILOTS FLOORBOARDS AT FLIGHT STATION 107, THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED.  THESE CR	ACKS WERE FOUND AT 2 OF THE 4 NUT PLATES.  FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS.	  THE BEAM WAS REPLACED.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2006070500020	20060705	00020	EU  	2006	7	5	CA060613002      	1	20060613	G	3110		WARNING LIGHT   			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					WARNING PANEL	FALSE INDICATION	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											UNIT RECEIVED AS INSPECTED.  INSTALLED THE WARNING PANEL IN THE HELICOPTER AND ON GROUND RUN DISCOVERED THAT THE MAIN GE	AR BOX RED PRESSURE LIGHT WOULD NOT EXTINGUISH.  WARNING PANEL REPLACED AND THE LIGHT GOES OUT.					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006080300259	20060803	00259	GL  	2006	8	3	CA060613003      	2	20060611	G	7261	6844716	SEAL            			LKHEED	188   	188A        	5262602	WP  	ALLSN 	501D  	501D13      	03004	GL  					NR 2 ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AFTER A WATER BOMBING RUN CLIMB OUT NR 2 ENGINE WAS SHOWING TWO GALLONS LOW ON OIL. THERE WAS NO OTHER ABNORMAL IN	DICATIONS, THE CREW DID A PRECAUTIONARY SHUT DOWN. MAINTENANCE FOUND THE SCAVENGE PUMP SEAL TO BE LEAKING OIL BY, THE SE	AL WAS REPLACED AND THE ENGINE RUN CHECKED TO BE SERVICABLE.				2	L	7	4 	4T	4	T	RT	4A22    	E282				 
2006062700276	20060627	00276	CE  	2006	6	27	CA060613004      	1	20060612	G	3233	50380043	BEARING         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG ACTUATOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											DURING ACT ENDPLAY CHECK AND LUBE OF N/G ACT 50-820208-5,  NOTICED THRUST BEARING IMPROPERLY INSTALLED.  INSTRUCTIONS IN	 COMPONENT MM ARE TO INSTALL BEARING WITH P/N AWAY FROM GEAR, THIS BEARING HAD BEARING MANUF P/N AND WORD THRUST ON ONE 	SIDE AND RAYTHEON P/N ON OTHER, ALLOWING YOU TO FOLLOW INSTRUCTIONS AND HAVING A 50% CHANCE OF GETTING IT RIGHT. THIS BE	ARING WAS INSTALLED BACKWARDS WITH RAYTHEON P/N AWAY FROM GEARS PUTTING ACTUAL THRUST SIDE TOWARDS GEARS OPPOSITE TO THR	UST LOADS.   ACT WAS FURTHER INSPECTED AND SMALL AMT OF SPALLING FOUND ON GEARS.  ACT IS BEING RETURNED TO OVERHAUL FACI	LITY WERE BEARING AND GEARS WILL BE REPLACED. THIS ACT WAS REMOVED FOR IT FIRST ENDPLAY CHECK SINCE LAST OVERHAUL WITH A	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006062700277	20060627	00277		2006	6	27	CA060614001      	1	20060614	G	7921	JR28548A	OIL COOLER      	RROYCE      	JR28548A    						RROYCE	TAY   	TAYMK6118   	 	NE  					FUEL OIL	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						VARIOUS					5 FUEL COOL OIL COOLERS (FCOC) RE-CALLED FROM SOUTHWEST COOLER SERVICE INC, APPROVED SUPPLIER FOR ROLLS-ROYCE CANADA) DU	E TO FAA UNAPPROVED PART NOTIFICATION NR  2005-00187.  ROLLS-ROYCE CANADA HAVE RE-ROUTED 5 SUSPECT UNAPPROVED FCOCS TO S	ERCK AVIATION (OEM APPROVED SUPPLIER) FOR RE-OVERHAUL.  SERCK AVIATION HAS REPORTED FCOC WITH MISSING; THERMO ADAPTOR, N	UTS AND WASHERS FROM END COVERS AND ALSO ONE FCOC MATRIX (CORE) THAT FAILED PRESSURE TEST DUE TO 11 TUBES JOINT (FERRULE	) LEAKS.  THE FCOC WERE PREVIOUSLY DECLARED OVERHAULED CONDITION BY SOUTHWEST COOLER SERVICE INC UNDER RRC PURCHASE ORDE	R.  RRC ENGINEERING AND ROLLS-ROYCE OEM ARE EVALUATING IN SERVICE COOLERS OVERHAULED BY SOUTHWEST COOLER INC.						4	F			A25NE				 
2006121300128	20061213	00128	SW  	2006	12	13	CA060614004      	1	20060224	G	6320	212030154101	FITTING         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED A FORE-AFT KICK IN THE CYCLIC, AT THE SAME TIME THEY HEARD A NOISE. ON ARRIVAL OF THE AC, INSPECTED	 THE M/R SYSTEM, SWASHPLATE, SCISSORS AND SLEEVE, TRANSMISSION MOUNTS AND NO DAMAGE WAS FOUND. A/C WAS FLOWN AGAIN AND T	HE PILOT REPORTED AN INTERMITTENT LATERAL VIBRATION. ON FURTHER INSPECTION, FOUND BOTH EARS ON THE LOWER LIFT LINK FITTI	NG WERE CRACKED. A/C WAS DISASSEMBLED TO ALLOW REPLACEMENT OF THE FITTING, A/C REASSEMBLED AND RETURNED TO SERVICE.  FAI	LURE OF THIS FITTING WAS A RESULT OF AN INCORRECT FITTING/ATTACH BOLT CONFIGURATION, THERE ARE 2 LOWER LIFT LINK CONFIGU	RATIONS POSSIBLE.    (TC NR 20060614004)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006062700278	20060627	00278	NE  	2006	6	27	CA060614005      	2	20060609	G	7200		CASE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA				4833 							APPROX 20 MIN INTO CRUISE FLIGHT, THE LT LOW OIL PRESSURE LIGHT CAME ON .  THE ENGINE WAS SHUT DOWN AS IT REACHED 50 PSI	.  ELECTED TO RETURN TO PLACE OF DEPARTURE AND A SUCCESSFUL LANDING WAS MADE.  UPON STOPPING A LARGE QUANTITY OF OIL WAS	 FOUND UNDERNEATH LT ENGINE COWL.  MAINTENANCE WAS DISPATCHED AND A COMPLETE REPORT WILL FOLLOW WITH FURTHER FINDINGS.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006121300129	20061213	00129	CE  	2006	12	13	CA060615001      	1	20060613	G	8000	6041H190	RELAY           			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STARTER	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT WAS ON A OPS 1 INSPECTION BASE . WHILE WORKING ON SNAG 1769A (OIL COMING FROM A/C COMPRESSOR). AFTER REMO	VING THE UNSERVICEABLE A/C COMPRESSOR A VISUAL OF THE SURROUNDING AREA REVEALED THAT THE AIR CONDITIONER START RESISTOR 	PHENOLIC P/N 100-364190-31 WAS BURNED ON BOTH SIDES AND THAT ONE OF THE TERMINALS WAS BROKEN ON THE START RELAY. WE ARE 	GOING TO REPLACE A/C COMPRESSOR P/N ER206R-25202 , START RELAY P/N 6041H190 , PHENOLIC  P/N 100-364190-31 THAT IS MOUNTE	D ON BOTH SIDES OF THE A/C START RESISTOR AND SERVICE SYSTEM . (TC NR 20060615001)		1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
2006062700280	20060627	00280	EU  	2006	6	27	CA060615002      	1	20060604	G	5514	F50B381003111	GUIDE           			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					HORIZONTAL STAB	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8351 								GUIDE PLATE SEPARATED FROM HORIZONTAL STAB FILLET, WAS FOUND LYING BETWEEN VERTICAL STABILIZER AND HORIZONTAL STABILIZER	.  UNIT HAD BEEN CRUSHED BETWEEN HORIZONTAL STAB AND VERTICAL STAB AS STAB WAS TRIMMED POTENTIAL THAT GUIDE PLATE COULD 	HAVE MOVED AFT AND JAMMED ELEVATOR LINKAGE.  UNIT WAS REMOVED STRAIGHTENED AND REATTACHED TO HORIZONTAL STAB FILLET ASSE	MBLY PER MANUFACTURERS INSTRUCTIONS "SRM SI-20-05, S0-10-04, HORIZONTAL STAB WAS TRIMMED THROUGHOUT ITS ENTIRE RANGE AND	 NO DISCREPANCIES FOUND.		2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2006062700281	20060627	00281	EA  	2006	6	27	CA060615003      	2	20060615	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LEFT	SURGES          	W				A				UNSCHED LANDING         				X	M	J	ENGINE FLAMEOUT           	OVER TEMP                 	WARNING INDICATION        	CL	CLIMB          	1			CA				6914 				PCE32506			ON CLIMB-OUT, THE AIRCRAFT EXPERIENCED A LEFT ENGINE SURGE WITH HIGH ITT AND LOW OIL PRESSURE INDICATIONS. THE CREW SHUT	 DOWN THE ENGINE IN FLIGHT AND RETURNED FOR AN UNEVENTFUL LANDING.  MAINTENANCE PERSONNEL REPORTED DEBRIS IN THE EXHAUST	 AND OIL LEAKING FROM THE ENGINE.  THERE IS ALSO AN UNUSUAL NOISE WHEN THE PROPELLER IS ROTATED BY HAND.  THE ENGINE WIL	L BE REMOVED TO AN APPROVED OVERHAUL FACILITY FOR INVESTIGATION.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006121300130	20061213	00130	SO  	2006	12	13	CA060615004      	1	20060609	G	7603	2489418	THROTTLE CABLE  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AC DEPARTED  AND A SHORT TIME LATER THE PILOT REPORTED THE LT ENGINE THROTTLE / MANIFOLD WAS SET AT 38 AND WAS NOT	 RESPONDING. THE PILOT DIVERTED BACK. ON DECENT THE LT ENGINE MANIFOLD STAYED CONSTANT AT 38, THE EGT BEGAN TO RISE, ALO	NG WITH THE CYLINDER HEAD, AND OIL TEMPERATURE. THE AIRCRAFT LANDED SAFELY WITH BOTH ENGINES RUNNING. ONCE ON THE GROUND	 THE LT ENGINE WAS SHUTDOWN, TAXIED TO RAMP ON RT ENGINE.   THE LT ENGINE WAS INSPECTED, FOUND TO HAVE LOST ALL ENGINE O	IL. THE ENGINE SUSTAINED EXTENSIVE DAMAGE. MAINTENANCE DETERMINED THE LT THROTTLE CABLE IN THE CABIN PEDESTAL HAD FAILED	. THE THROTTLE CABLE WIRES HAD SEVERED APPROXIMATELY .3125 FROM THE SWAGED PORTION OF THE ROD END. UNFORTUNATELY ON A RO	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006080300260	20060803	00260	EA  	2006	8	3	CA060615005      	1	20060613	G	3246	C3US1563	BOLT            			DHAV  	DHC3  	DHC3        	2800202	EA  										MLG WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING MAIN LANDING GEAR (MLG) WHEEL/SKI REMOVAL AND CHANGE TO WHEELS ONLY, MAINTENANCE FOUND THE RIGHT 	HAND WHEEL/SKI ATTACH BOLT P/N: C3US156-3 TO BE BROKEN. THE BOLT ATTACHES THE SKI BRACKET ASSEMBLY LINK P/N: C3US108-34 	TO THE MLG STRUT AND AXLE. THE BOLT HAS FAILED AT THE START OF THE RADIUS WHERE THE DIAMETER OF THE BOLT CHANGES FROM .5	00" DIAMETER, TO .750" DIAMETER. IT APPEARS THAT THE BOLT FAILURE OCCURRED ON THE TOOLING MARK.  THIS IS OUR SECOND OCCU	RRENCE WITHIN 59.4 HOURS AND 115 CYCLES. (TC# 20060615005)		1	H	7	1 	3R				A815    					 
2006062700283	20060627	00283		2006	6	27	CA060615006      	1	20060614	G	2720	M4612BFG	ROD END         								WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  		BROKEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA				1243 							DURING GROUND OPERATION THE PILOT FELT A "CLUNK" IN THE RUDDER SYSTEM WHILE OPERATING THE SERA SYSTEM.  MAINTENANCE CREW	S INVESTIGATED AND FOUND THE SERA LOCK ACTUATOR ROD END HAD BROKEN.  THE ROD END WAS REPLACED, THE SYSTEM WAS FUNCTION C	HECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.									4	R			E259	6	C	P8879	 
2006121300131	20061213	00131	EU  	2006	12	13	CA060616001      	1	20060326	G	6220	704A33633211	SPHERICAL STOP  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			3065 								(CAN) A/C HAD ABNORMAL VIBRATION AND WOULD NOT STAY IN TRACK. SPHERICAL STOPS HAD EXCESSIVE RUBBER LOSS AND SEPARATION. 	INSTALLED NEW SPHERICAL STOPS AND M/R COULD BE BALANCE AND TRACKED WITH NO ABNORMAL VIBRATION. (TC NR 20060616001)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006062700287	20060627	00287	CE  	2006	6	27	CA060616003      	1	20060530	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LANDING LIGHT	HOT             	W				H				DEACTIVATE SYST/CIRCUITS				M			OVER TEMP                 			CR	CRUISE         	1			CA			2006 								WHEN THE PILOT WENT TO TURN OFF LANDING LIGHT SWITCH, FOUND TO BE HOT AND THE LANDING LIGHT WOULD NOT TURN OFF, THE SWIT	CH FINALLY TURNED OFF.  THE SWITCH WAS REPLACED WITH A NEW UNIT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006062700289	20060627	00289		2006	6	27	CA060616004      	1	20060524	G	3246	40289	WHEEL           																	MLG	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											PURCHASED EIGHT CLEVELAND 40-289 WHEEL ASSEMBLIES NEW FROM FACTORY, RETURNED FIVE ASSEMBLIES DUE TO WHEELS INSPECTED BY 	EDDY CURRENT AND FOUND SEVERAL CASTING FLAWS (VOIDS) IN BEAD AREAS.  WHEEL ASSEMBLIES RETURNED TO FACTORY FOR INVESTIGAT	ION BY THEIR QA DEPARTMENT, HAVE NOT RECEIVED ANY RESPONSE FROM PARKER AEROSPACE AS OF JUNE 9/06.  TWO WHEEL ASSEMBLIES 	RETURNED THROUGH KADEX AERO SUPPLY, NO SERIAL NUMBERS LISTED.  THREE WHEEL ASSEMBLIES RETURNED THROUGH AVIALL (CALGARY),	 SERIAL NUMBERS AS FOLLOWS: 4553/4578, 4581/4554, 4575/NSN.															 
2006070500023	20060705	00023	EU  	2006	7	5	CA060616005      	2	20060614	G	7200		ENGINE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 2	SHUTDOWN        	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA				7971 				192902			(CAN) IN CRUISE, ENROUTE TO DESTINATION, THE NR 2 ENGINE AUTO FEATHERED AND SHUTDOWN.  THE AIRCRAFT DIVERTED AND LANDED 	WITHOUT FURTHER PROBLEM.  THE NR 2 ENGINE WILL BE REPLACED ON SITE. NO CONCLUSION AS TO THE CAUSE HAVE BEEN ARRIVED AT. 	   (TC NR 20060616005)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2006080300261	20060803	00261	WP  	2006	8	3	CA060616006      	2	20060615	G	7297		CONNECTOR       			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA				6916 				P63111			(CAN) AFTER DEPARTURE CLIMBING THROUGH 7500FT THE RIGHT ENGINE TORQUE STARTED TO FLUCTUATE.CREW PULLED THE QRH AND FOLLO	WED THE DRILLS AND WERE GETTING 10-20% FLUCTUATION CAUSING THE A/C TO YAW RADICALLY LEFT AND RIGHT AT ALL POWER SETTINGS	 WITH TTL ON OR OFF SO A PRECAUTIONARY SHUTDOWN WAS PERFORMED AND RETURNED TO BASE WITHOUT INCIDENT. MTCE ENGINE RUNUPS 	CONFIRMED THE TQ FLUCTUATIONS AND TROUBLESHOOTING FOUND A LOOSE PIN CONNECTION ON THE RT ENGINE STRAIN GAUGE CONNECTOR. 	THE CONNECTION WAS REPAIRED AND THE A/C WAS RUN UP AND RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2006062700290	20060627	00290	EA  	2006	6	27	CA060616008      	1	20060610	G	5610	NP1393222	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			16406								THE RT SIDE WINDOW CRACKED WHILE IN CRUISE.  FLIGHT WAS DIVERTED TO MAINTENANCE BASE.  WINDOW REPLACED IN ACCORDANCE WIT	H AMM.  THIS WINDOW IS A PRE-SERVICE BULLETIN.					2	L	7	2 	4F			RT	A21EA   					 
2006062700292	20060627	00292	EA  	2006	6	27	CA060616009      	1	20060611	G	5610	NP139221	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  											CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			9276 								THE INNER PLY OF THE LT WINDOW CRACKED WHILE ON APPROACH.  WINDOW WAS REPLACED IN ACCORDANCE WITH AMM.  THE WINDOW IS A 	PRE-SERVICE BULLETIN.					2	L	7	2 	4F			RT	A21EA   					 
2006062700293	20060627	00293	WP  	2006	6	27	CA060617001      	1	20060609	G	3250	10150	STEERING SYS    			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	NLG	MALFUNCTIONED   	W				O				OTHER                   				S			AFFECT SYSTEMS            			LD	LANDING        	1			CA			10605								AFTER T/O, DURING L/G RETRACTION, NOSE WHEELS ENTERED W/W IN A RT TURN ATTITUDE, EVIDENT FROM WEAR MARKS ON TIRES AND RU	BBER ON INTERIOR WALLS OF W/W.  WHEN A/C LANDED, NOSE WHEELS WERE STILL TURNED TO THE RIGHT, UNKNOWN TO AIRCREW.  CAPT T	RIED TO STRAIGHTEN NOSE WHEELS OUT BUT HAD TO TRY A COUPLE TIMES BECAUSE THERE WAS NO RESPONSE FROM STEERING ACTUATOR.  	NOSE WHEEL STEERING DID RESPOND TO INPUTS AND AIRCRAFT WAS ABLE TO TAXI.  IT APPEARS THAT ACTUATOR HAD AN UNCOMMANDED ST	EERING INPUT UPON TAKEOFF AND LOCKED IN THAT POSITION UNTIL LANDING.  ACTUATOR WAS CHANGED AND AIRCRAFT DEEMED SERVICEAB	LE.  ACTUATOR WAS SENT BACK TO TYPE CERTIFICATE HOLDER OF AIRCRAFT FOR ANALYSIS.	2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2006062700294	20060627	00294	WP  	2006	6	27	CA060618001      	2	20060616	G	7250		TURBINE         			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ENGINE	NICKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A WALK AROUND, MAINTENANCE PERSONNEL NOTICED A PAINT CHIPPED INSIDE THE LT THRUST REVERSER.  FURTHER INVESTIGATIO	N FOUND OVER A DOZEN NICKS ON THE 3ND STAGE TURBINE.  ENGINE WILL BE REMOVED AND SENT TO AN HEAVY MAINTENANCE FACILITY A	ND A LOANER ENGINE WILL BE INSTALLED.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062700296	20060627	00296	CE  	2006	6	27	CA060618002      	1	20060617	G	5753		SKIN            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RT TE FLAP	BIRD STRIKE     	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											ON APPROACH, ON FLAIR AIRCRAFT HIT A BIRD.  ONCE ON THE GROUND THE CREW REPORTED TO MAINTENANCE PERSONAL WHO AFTER INSPE	CTING THE AIRCRAFT FOUND A DENT ON THE RT FLAP BOTTOM SKIN.  DUE TO THE LOCATION OF THE DENT WHICH WAS NOT COVERED UNDER	 SRM.  SUPPORT ENGINEERING WAS CONTACTED AND A ENGINEERING DISPOSITION WAS ISSUED TO RETURN THE AIRCRAFT INTO SERVICE.  	AN INSPECTION OF THE AREA IS REQUIRED APPROXIMATELY EVERY 50 HOUR UNTIL REPAIR IS COMPLETED OR ANOTHER FLAP IS INSTALLED	.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062700297	20060627	00297	GL  	2006	6	27	CA060619001      	3	20060217	G	6111	S90AT4	BLADE           	MCAULY      	D2A34C58NO  	CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				800  		705814			705814		PROPELLER D2A34C58, SERIAL NR 705814, WORK ORDER NR T68807, C-FYJJ.  PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.  LAST OVER	HAUL MARCH 1996, NOW 800.5 HOURS SINCE OVERHAUL.  FOUND BLADE S-90AT-4, SERIAL NR C75151YS, CRACKED IN BLADE THREADS, FO	UND WITH EDDY CURRENT.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2006080300262	20060803	00262	CE  	2006	8	3	CA060619002      	1	20060612	G	2731	5061001736	TAB             			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DISCOVERED ON LOWER TAB SURFACE SKIN ADJACENT TO TAB HORN ATTACH RIB. SEE PICTURES ATTACHED.TRIM TAB ASSEMBL	Y P/N 50-610017-36 REPLACED WITH NEW. ELEVATOR AND TAB ASSEMBLY BALANCED (21.33 IN LBS TAIL HEAVY) AND REINSTALLED. INDE	PENDENT CHECK ON R/H TAB AND ELEVATOR INSTALLATION CARRIED OUT - TAB TRAVELS 9.5 DEG NOSE DOWN AND 20.5 DEG NOSE UP. (TC	# 20060619002)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006062700298	20060627	00298	GL  	2006	6	27	CA060619003      	3	20060217	G	6114	D4716	HUB             	MCAULY      	D2A34C58NO  	CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				800  		705814			705814		(CAN) PROPELLER D2A34C58-NO, SERIAL NR 705814, WORK ORDER NR T68807, C-FYJJ.  PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.  	LAST OVERHAUL MARCH 1996, NOW 800.5 HOURS SINCE OVERHAUL.  FOUND HUB D4716, SERIAL NR 705814, CRACKED IN THREADS THAT TH	E BLADE RETENTION NUT SCREW INTO, FOUND WITH EDDY CURRENT.				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2006080300263	20060803	00263	CE  	2006	8	3	CA060619004      	1	20060615	G	7110	1099100531516	CHANNEL         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE P/N 109-910053-15 AND -16 COWL SUPPORT CHANNELS WERE FOUND CRACKED IN THE LOWER FLANGE AREA, AND SUBSEQUENTLY 	REPAIRED. MANY OF THE REPAIRS HAVE ALSO FAILED. IT APPEARS THAT A SUBSTANTIAL AMOUNT OF COWLING WEIGHT RESTS ON THESE CH	ANNELS. THE REPEAT DAMAGED SUGGESTS THAT THIS AREA IS UNDER DESIGNED. SEVERAL OTHER OPERATOR C90A AIRCRAFT HAVE SHOWN SI	MILAR FAULTS. (TC# 20060619004)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006062700299	20060627	00299	EA  	2006	6	27	CA060619005      	1	20060606	G	2910	B030212604	B-NUT           			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF34*       	 	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											AFTER TAKEOFF, "NR 2 HYD LOW PRESS" CAUTION MESSAGE WAS DISPLAYED.  THE AIRCRAFT RETURNED TO THE ORIGINATING AIRPORT AND	 PERFORMED AN EMERGENCY LANDING.  MAINTENANCE FOUND THE FORWARD NR 2 BRAKE ACCUMULATOR CONNECTING HYDRAULIC LINE'S NUT L	OOSE (CRJ700/900 IPC 29-17-06, FIG.23-AA1, ITEM NR 90).  THE NUT WAS RE-TORQUED AS PER STANDARD PRACTICES AND NR 2 ENGIN	E DRIVEN PUMP (P/N 66190-3, S/N K0651) WAS REPLACED AS A PRECAUTION.  NR 2 HYDRAULIC SYSTEM WAS SERVICED AND AIRCRAFT RE	TURNED TO SERVICE.  NO MAINTENANCE HAS BEEN PREVIOUSLY PERFORMED ON THE HYDRAULIC LINE, NEITHER ON NR 2 BRAKE ACCUMULATO	R.  AIRFRAME HOURS WERE: 2625:04 AND CYCLES WERE: 1280.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006062700300	20060627	00300	GL  	2006	6	27	CA060619006      	3	20060606	G	6114	C2343	HUB             	MCAULY      	2A36C29     	CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3564 	442  		591003					MCCAULEY PROPELLER 2A36C29-AG, SERIAL NR 591003, WORK ORDER NR T69972, C-FLVF.  PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.	  LAST OVERHAUL 1996, NOW 442.5 HOURS SINCE OVERHAUL.  FOUND HUB C2343, SERIAL NR 591003, CRACKED IN THREADS THAT THE BL	ADE RETENTION NUT SCREW INTO, FOUND WITH EDDY CURRENT.				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P880	 
2006080300264	20060803	00264	GL  	2006	8	3	CA060619007      	1	20060425	G	3340	10128	LIGHT           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					EXTERIOR	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			29   								(CAN) PILOT REPORTED STROBE CIRCUIT BREAKER (C/B) POPPED DURING FLIGHT, TROUBLESHOOTING REVEALED INCORRECT C/B INSTALLED	 (5AMP INSTEAD OF 7.5AMP). NEW C/B INSTALLED AT THAT TIME AND GROUND CHECKED SERVICEABLE. SEVERAL MONTHS LATER PROBLEM R	E-OCCURRED DURING FLIGHT BUT GROUND CHECKED OK. WING TIPS REMOVED AND NOTED EVIDENCE OF ARCING FROM TANK INBOARD WALL/RI	B AND WING TIP BOSS TERMINAL STRIP STUDS, STATICALLY THERE WAS NO CONTACT, WITH TANKS FULL DURING FLIGHT CONTACT OCCURRE	D. THE STUDS ON BOSS BAR HAS SUFFICIENT LENGTH TO TRIM 0.25" AND REMAIN IN SAFETY. TIPS RE-INSTALLED WITH PUTTY ON STUDS	 AND REMOVED TO REVEAL APPROXIMATELY 0.3" CLEARANCE. (TC# 20060619007)	1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006080300254	20060803	00254	NE  	2006	8	3	CA060619008      	2	20060425	G	8550	C2L293A	ADAPTER         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE OIL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT STATICALLY LEAKING ABOVE AVERAGE AMOUNT OF OIL ON HANGAR FLOOR. LOWER BELLY FAIRING/PANEL REMOVED BELOW R	UDDER PEDALS, OIL ADAPTER BETWEEN OIL SHUT OFF AND FIREWALL NOTED TO BE SEVERE OF LEAK. ADAPTER REMOVED AND SILVER SOLDE	R JOINT FOUND CRACKED/LOSS OF ADHESION TO BASE METAL. ADAPTER REPLACED WITH NEW. (TC# 20060619008)				1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006062700303	20060627	00303	EU  	2006	6	27	CA060619009      	1	20060608	G	7120		MOUNT           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					COMPRESSOR CASE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			45932	4340 							WHILE CARRYING OUT MAINTENANCE ON THE RT ENGINE, MAINTENANCE PERSONNEL FOUND LOOSE HARDWARE WHILE OPENING UP THE LOWER P	ORTION OF THE ENGINE COWLING.  FURTHER INVESTIGATION REVEALED THAT THIS HARDWARE, CONSISTING OF ONE NUT AND ONE BROKEN S	TUD WITH THE NUT STILL ATTACHED, CAME FROM THE OUTBOARD ENGINE MOUNT FOOT.  AT THIS TIME, IT WAS ALSO DISCOVERED THAT TH	E OTHER RETAINING NUTS ON THIS FOOT WERE ALSO SLIGHTLY LOOSE.  THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERV	ICE.  AN IN-FIELD REPAIR WILL BE CARRIED OUT ON THE ENGINE.		2	L	7	2 	3T	4	T		A24EU   	A196				 
2006080300267	20060803	00267	NM  	2006	8	3	CA060619010      	1	20060618	G	2497	286A1062002	WIRE HARNESS    			BOEING	737   	737         	UTILSYS	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					NR 2 ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2265 	2265 							(CAN) ON 18 JUNE 06 DURING TROUBLESHOOTING OF A RECURING NR 2 SOURCE OFF LIGHT ILLUMINATED SNAG, WIRE CHAFFING CAUSING A	RCING WAS FOUND BETWEEN FEEDER WIRE HARNESS PART NUMBER 286A1062-002 BOEING IPC 24-11-51-01A ITEM NR 35 AND THE COWLING 	HINGE PART NUMBER 314-2241-1 BOEING IPC 71-11-02-10 ITEM 76.   INVESTIGATION ALSO REVEALED SOME MINOR CHAFFING ON THE WI	RE SHIELDING OF THE NUMBER ONE ENGINE HARNESS IN THE SIMILAR AREA.   A FLEET CAMPAIGN IS RAISED TO INSPECT THE FLEET AND	 CONFIRM IF THIS IS AN ISOLATED EVENT. BOEING HAS BEEN INFORMED AND WILL BE KEPT ADVISED OF ALL FINDINGS AS THEY COME TO	 LIGHT.   THIS SDR WILL BE UPDATED WITH ADDITIONAL INFORMATION WHEN AVAILABLE.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006080300269	20060803	00269	CE  	2006	8	3	CA060619012      	1	20060530	G	5311	FS227	FRAME           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FRAME, F.S. 227 LOWER FLANGE CRACKED AT RADIUS. CRACK WAS APPROX 4.5 INCHES LEFT AND RIGHT OF A/C CENTRELINE. (TC#	 20060619012)					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006121300132	20061213	00132	CE  	2006	12	13	CA060619013      	1	20060530	G	5220	115430100605	SKIN            	BEECH       		BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	EMERGENCY EXIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B8					(CAN) INNER SURFACE LOWER CENTER AREA BETWEEN WINDOW AND LOWER FRAME. CORROSION SPOT 1CM WIDE. WHEN BLENDED MATERIAL THI	CKNESS WAS INSUFFICIENT. (TC NR 20060619013)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006121300133	20061213	00133	CE  	2006	12	13	CA060619014      	1	20060530	G	5730	5012006896	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CENTER WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKIN P/N 50-120068-96 CRACKED AT HIGH SHEAR FASTENERS ATTACHING SKIN TO WING ATTACH FITTING. CRACKS (2) ORIGINATE 	FROM EDGE OF FASTENER COUNTERSINKS AND HEAD TOWARD NEXT FASTENER LOCATION. (TC NR 20060619014)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006062700306	20060627	00306	EU  	2006	6	27	CA060620001      	1	20060614	G	6123		SOLENOID VALVE  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FEATHERING	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1981 							FEATHERING SOLENIOD VALVE STICKING INTERMITTENTLY IN FEATHER POSITION AND THEREFORE PROP STAYS FEATHERED AFTER ENGINE ST	ART.  FAULT ONLY OCCURS DURING QUICK TURN AROUNDS ON HOT DAYS.  AFTER ENGINE COOLS VALVE OPERATES NORMALY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006062700308	20060627	00308	EU  	2006	6	27	CA060620002      	1	20060615	G	6123	1310160	SOLENOID VALVE  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FEATHERING	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OVERSPEED GOVERNOR REPLACED WITH AN OVERHAULED UNIT (DUE TO FEATHERING VALVE STICKING INTERMITTANTLY SEE SDR 20060	620001) AND DURING FEATHER CHECK THE PROP WOULD NOT COME OUT OF FEATHER.  ELECTRICAL SYSTEM CHECKED.  NO FAULTS FOUND.  	ANOTHER SERVICEABLE OVERSPEED GOV.  INSTALLED AND OPERATION CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006080300271	20060803	00271	NM  	2006	8	3	CA060620003      	1	20060620	G	2422	100201022	STATIC INVERTER 			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					E & E BAY	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J	B		WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA				149  							(CAN) ON THE 20 JUNE 06 WHILE CONDUCTING A SCHEDULED PHASE 3 CHECK. MAINTENANCE FOUND ELEC LIGHT ILLUMINATED ON THE OVER	HEAD PANEL. DURING THE TROUBLESHOOTING AN ODOR OF SMOKE WAS NOTICED IN THE E & E BAY. A BITE CHECK WAS CARRIED OUT AND F	OUND THE STATIC INVERTER PN 1-002-0102-2090 SN CJ003551 AT FAULT. THE UNIT WAS REPLACED IAW AMM 24-34-21 AND TESTED SERV	ICEABLE.   PREVIOUS HISTORY: ON 03 MAY 06 THE UNIT WAS SENT OUT ON REPAIR ORDER 64509 TO GET ALERT SB 737-24-1165 CARRIE	D OUT. THIS MODIFIES THE UNIT FROM A S282T004-10 TO A 1-002-0102-2090. THIS SERVICE BULLETIN GIVES INSTRUCTIONS TO REPLA	CE THE STATIC INVERTER WITH A NEW OR CHANGED STATIC INVERTER. BOEING AND FEDERAL AVIATION ADMINISTRATION (FAA) RECEIVED 	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006062700309	20060627	00309	CE  	2006	6	27	CA060620004      	1	20060615	G	2750	6901315	CONTROL LEVER   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA				102  							ON APPROACH INTO TUCSON WHEN FLAP WAS SELECTED TO 8 DEGREE "FLAP FAILED " AMBER CAS ILLUMINATED.  AIRCRAFT LANDED UNEVEN	TFULLY AND LEARJET INC, TUCSON REPLACED THE FLAP CONTROL LEVER ASS'Y AND RETURNED THE AIRCRAFT INTO SERVICE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062800198	20060628	00198	CE  	2006	6	28	CA060620005      	1	20060618	G	2750		FLAP SYSTEM     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											DURING DESCENT FROM 41,000 FT, AT -54 DEGREES TO 26,000 FT WITH NO FLAP SELECTION.  "FLAP FAILED" AMBER CAS MESSAGE ILLU	MINATED.  AT 5000 FT, THE CREW WAS ABLE TO RESET THE FLAP SYSTEM AND AN UNEVENTFUL LANDING WAS MADE. TECHNICIAN FROM LEA	RJET INC WAS DISPATCHED TO INSPECT AND RETURN THE AIRCRAFT TO SERVICE, AFTER WHICH THE AIRCRAFT FOR FURTHER TROUBLESHOOT	ING.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006062800199	20060628	00199	CE  	2006	6	28	CA060620006      	1	20060620	G	8011	51577A1	SOLENOID        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	STARTER	STUCK           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA			11455								UPON DESCENT TO LAND FROM A .4 HRS FLIGHT, THE ELECTRICAL POWER WENT OUT AND WAS UNABLE TO BE RESET BY CYCLING THE MASTE	R SWITCH.  THE PILOT C/O NORDO PROCEDURES AND LANDED WITHOUT INCIDENT.  UPON INVESTIGATION IT WAS FOUND THAT THE START S	OLENOID HAD REMAINED CLOSED UPON START UP CAUSING THE MASTER SOLENOID TO OVERHEAT AND FAIL CAUSING ELECTRICAL POWER TO G	O OUT.  THE START SOLENOID AND MASTER SOLENOID WERE REPLACED NEW.  ALL WIRING WAS INSPECTED AND FOUND TO BE GOOD.  AS A 	PRECAUTIONARY MEASURE THE STARTER AND STARTER DRIVE WERE REPLACED.  THE A/C WAS GROUND RUN AND SYSTEMS CHECKED SERVICEAB	LE.	1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P25EA	 
2006062800200	20060628	00200	NE  	2006	6	28	CA060621001      	2	20060615	G	7200		ENGINE          			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  						FAILED          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			CA											A/C INVOLVED IN HELI-LOGGING OPS WITH A/C IN HOVER MADE A MODERATE PWR REDUCTION TO REPOSITION GRAPPLE ON A LOG. AS PWR 	WAS REDUCED A "WHOOSH" SOUND WAS HEARD AND N1 WARNING HORN ACTIVATED FOR NR 2 ENG.  FLT CREW IDENTIFIED AND CONFIRMED TH	AT NR 2 ENG ENCOUNTERING A ROLL-BACK AND PROCEEDED TO SHUT ENG DOWN TO COUNTER RISING ENG T5 TEMP. WITH ENG SECURED AND 	NR T5 TEMP LIMITS EXCEEDED FLT CREW ELECTED TO RESTART NR 2 ENG SINCE A/C HAD 15 KILOMETER FERRY FLT BACK TO ITS SERV LA	NDING.  ENG WAS SUCCESSFULLY RESTARTED AND A/C RETURNED TO SERV LANDING W/O FURTHER INCIDENT.  A COMPLETE INSPECTION OF 	ENG AND RELATED LINKAGES REVEALED NOTHING ABNORM.  ENG FUEL FILTER WAS INSPECTED FOR CONTAM WITH NO FAULT FOUND.  AS STA	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006080300272	20060803	00272	SO  	2006	8	3	CA060621002      	1	20060610	G	3233	7LM1025013	ACTUATOR        			GRUMAN	G73   	G73T        	3951902	SO  	LYC   	O320  	O320D1D     	41508	EA  					MLG	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12308								(CAN) ON THE LT MAIN LANDING GEAR ACTUATOR, THE DOWN LOCK PISTON PIN CIRLIP HAS A LID OVER ITS GROOVE LEAVING THE ACTUAT	OR UNLOCKED WHEN THE GEAR IS DOWN. ALSO, BECAUSE THE PISTON PIN HAS EXCEEDED ITS LIMIT, THE  SWITCH HAS BEEN DAMAGE LEAV	ING THE LT INDICATING GREEN LIGHT UNILLUMINATED. THE AIRCRAFT LANDED WITH NO OTHER INCIDENT. AFTER INVESTIGATION: THE SI	DE GROVE RETAINING THE CIRCLIP HAS BEEN FOUND WORN, THE ACTUATOR BODY HAS BEEN REPLACED. (TC# 20060621002)			1	H	7	2 	3R	3	O		A783    	E274				 
2006062800202	20060628	00202	EA  	2006	6	28	CA060621003      	2	20060620	G	8530	CL41CCST041CA	CYLINDER HEAD   			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	ENGINE	CRACKED         	W				C				ABORTED TAKEOFF         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA			1023 					L2430227A			ENGINE RUNNING ROUGH FOUND NR 1 CYLINDER HEAD CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2006080400019	20060804	00019	NM  	2006	8	4	CA060621004      	1	20060619	G	2751	9660022001	TRANSMITTER     			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, CREW OBSERVED AN OUTBOARD FLAP ASYMMETRY INDICATION. A/C RETURNED TO BASE WHERE MAINTENANCE DISCO	VERED A FAULTY POSITION TRANSMITTER. PART WAS REPLACED AND A/C RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051600161	20070516	00161	EA  	2007	5	16	CA060621005      	2	20060620	G	7322	86245023	FLANGE          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	CARB MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1120 								(CAN) DURING ROUTINE INSPECTION OF RT ENGINE A .5 INCH CRACK WAS OBSERVED ALONG A SCRIBE LINE ON THE FORWARD FACE OF THE	 CARB AIR BOX NEAR TO THE LOWER MOUNTING BOLT HOLE . AFTER REMOVAL, (2) ADDITIONAL CRACKS WERE OBSERVED ALONG A SCRIBE M	ARK NEAR TO THE UPPER MOUNTING HOLES. THESE CRACKS TRAVERSED NEARLY COMPLETELY ACROSS THE MOUNTING FLANGE FACE. IN ADDIT	ION THE MOUNTING HOLE ALIGNMENT BETWEEN THE MOUNTING FLANGE AND THE INNER DOUBLER WERE OFFSET BY APPROXIMATELY .0312 INC	H. THIS MAY HAVE INDUCED STRESS THAT LED TO CRACK FORMATION ALONG THESE SCRIBE MARKS. BEFORE A NEW ASSEMBLY WAS INSTALLE	D THE MOUNTING HOLES WERE REAMED TO ALIGN THE HOLES IN BOTH PLATES. (TC NR 20060621005)	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006062800203	20060628	00203	EU  	2006	6	28	CA060621006      	1	20060621	G	7334	9550179130	PRESSURE SWITCH 			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					FUEL LOW	LEAKING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											DURING A START, PILOT NOTICED A FUEL PRESSURE WARNING LIGHT NOT EXTINGUISHING.  CONTINUED WITH THE START THROUGH TO IDLE	.  THEN SHUT THE AIRCRAFT DOWN AFTER 10 SECONDS AT IDLE.  AFTER SHUT DOWN OPENED UP THE ENGINE COWLING AND NOTICED FUEL 	ON THE ENGINE DECK.  FUEL WAS COMING FROM THE WEEP HOLE OF THE PRESSURE SWITCH WITH AIRCRAFT BOOST PUMP ON.				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006070300005	20060703	00005	EA  	2006	7	3	CA060622001      	2	20060621	G	7313	LW18853	NOZZLE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CONTAMINATED    	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA				592  				L785461A			TOWER ADVISED PILOT OF SMOKE FROM LEFT ENGINE ON CLIMB-OUT.  MAINTENANCE FOUND CONTAMINATION IN 1 OF THE FUEL INJECTION 	NOZZLES.  SOURCE COULD NOT BE DETERMINED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006080400021	20060804	00021	CE  	2006	8	4	CA060622002      	1	20060620	G	2810	CCA1550	DRAIN           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUEL SYS	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER FUELING THE AIRCRAFT THE FIRST OFFICER HEARD A SPLASH AND FOUND FUEL LEAKING FROM UNDER THE LEFT WING.  THE 	T PORTION OF THE FUEL DRAIN HAD FALLEN OUT AND THERE WAS NO WAY TO SHUT THE QUICK DRAIN VALVE OFF.  THE TOP PART OF THE 	VALVE AND ORING WERE RECOVERED WHEN THE DRAIN VALVE WAS REPLACED. (TC# 20060622002)				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006080400023	20060804	00023	SW  	2006	8	4	CA060622003      	1	20060621	G	5302	206031418001	SUPPORT         			BELL  	206   	206B        	1181511	SW  										TAIL BOOM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6856 								(CAN) FIN ATTACH POINTS WERE BEING INSPECTED AS PER ASB 206-06-107, CF2006-12.  A LARGE CORROSION PIT WAS FOUND ON THE B	OTTOM BOLT HOLE.  THE SUPPORT INSTALLATION IS TO BE REPLACED AS PER THE ASB WITH A ONE-PIECE CASTING. (TC# 20060622003)					1	G	7	1 	3U				H2SW    					 
2006080400024	20060804	00024	WP  	2006	8	4	CA060622004      	1	20060622	G	7720	A0582	SWITCH          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					OVERTEMP	STUCK           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			21   								(CAN) MAIN ROTOR TRANSMISSION OVER TEMP LIGHT CAME ON.  PILOT LANDED AND LET THE AIRCRAFT COOL DOWN.  LIGHT STAYED ON.  	TRANSMISSION WAS INSPECTED FOR SIGNS OF OVER TEMP, AND NO DEFECTS WERE FOUND.  OVERTEMP SWITCH WAS FOUND TO BE STUCK IN 	THE CLOSED POSTION. (TC# 20060622004)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006080400025	20060804	00025	SW  	2006	8	4	CA060622005      	1	20060621	G	2497	206075265103	CABLE           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					STARTER GEN	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TURN AROUND CHECK BY THE AME, THE WIRES TO THE STARTER GENERATOR WERE FOUND TO BE SUBJECTED TO  HEAT DAMAGE	.  THERE WAS NO INDICATION TO THE PILOT OF ANY DEFECT.  FURTHER INVESTIGATION FOUND THE STARTER GENERATOR WIRE BUNDLE BE	LOW THE ENGINE DECK TO BE BURNT.  CAUSE OF THE DEFECT IS NOT KNOWN AT THIS TIME.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006080400026	20060804	00026	SO  	2006	8	4	CA060623001      	1	20060620	G	2752	1216001	DRIVE ASSY      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FLAP XMSN	SHEARED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				3105 							(CAN) DURING PRE-DEPARTURE CHECK PILOTS NOTED THAT THE RH FLAP WAS NOT RESPONDING TO DOWN SELECTION, LH FLAP MOVEMENT WA	S NORMAL. MAINTENANCE CONFIRMED THE SNAG AND T/S REVEALED THE RH FLAP TRANSMISSION WAS NOT DRIVING THE FLAP, FLAP MOTOR 	AND DRIVE CABLES WERE CHECKED SERVICEABLE. REPLACED RH FLAP TRANSMISSION,FLAPS RIGGED PER PIPER MM AND AIRCRAFT DISPATCH	ED.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006080400028	20060804	00028	CE  	2006	8	4	CA060623002      	1	20060619	G	5540	1015000573	FASTENER        	BEECH       		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RUDDER SHAFT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						UB71					(CAN) RUDDER QUADRANT P/N 101-500057-3 FOUND LOOSE ON INSPECTION. THREE MONEL BLIND RIVETS ATTACHING QUADRANT TO SHAFT A	SSY. P/N 114-524025-1 WERE FOUND LOOSE AND DETERMINED TO BE THE CAUSE OF THE QUADRANT LOOSNESS. (TC# 20060623002)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006080400029	20060804	00029	WP  	2006	8	4	CA060623003      	1	20060528	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYDRAULIC SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1570 								(CAN) UPON INSPECTION THE AFT SERVO WAS FOUND TO BE LEAKING FROM THE PILOT VALVE.  SERVO REPLACED WITH A SERVICEABLE UNI	T. (TC# 20060623003)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006121300134	20061213	00134	CE  	2006	12	13	CA060624001      	1	20060615	G	2711	130909B20	BOLT            	BEECH       		BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC3Y	HCC3YF2     	GL  	AILERON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2554 	2554 							(CAN) AILERON TRIM BOLT FOUND MIGRATING OUT OF LINKAGE ARM ON LT AILERON TRIM TAB ASSEMBLY. BOLT WAS NOTED TO BE FINGER-	TIGHT ONLY AND NOT SET INTO LOCKING DEVICE. NOTE: BOLT WAS FOUND IN THIS CONDITION AFTER FLIGHT CONTROLS WERE INSTALLED 	AFTER AIRCRAFT WAS PAINTED BY A THIRD PARTY CONTRACTOR. AS BOLT WAS BEING TIGHTENED DURING RECERTIFICATION, RESISTANCE W	AS NOTED ENSURING THE LOCKING PROVISIONS WERE SERVICEABLE.COMPANY PROCEDURES ON AIRCRAFT ACCEPTANCE AFTER THIRD PARTY CO	NTRACT MAINTENANCE TO BE REVISED TO PREVENT RE-OCCURENCE (TC NR 20060624001)		1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P25EA	 
2006080400031	20060804	00031	NM  	2006	8	4	CA060626001      	1	20060621	G	5712	66191042	RIB             			BOEING	727   	727225      	1384077	NM  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTON, MAINTENANCE FOUND THE NR 1 LEADING EDGE SLAT ACTUATOR WING RIB ATTACH POINT CRACKED. C	RACKED MOUNT SUPPORT REPLACED.					2	L	7	3 	4F				A3WE    					 
2006080400033	20060804	00033	NE  	2006	8	4	CA060626002      	2	20060620	G	7414	SB9RU3	MAGNETO         			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				36   							(CAN) INTERNAL FAILURE OF MAGNETO - VISUAL DAMAGE TO GEAR. THIS IS THE SECOND MAGNETO TO FAIL ON THIS OVERHAULED ENGINE 	(PURCHASED FROM TULSA AERO ENGINE). FIRST MAGNETO FAILED AT 30.3 HOURS FROM TSO. SECOND MAGNETO FAILED AT 36.2 HOURS TSO	. S/N ON 1ST MAGNETO IS B33715. BOTH MAGNETOS APPEAR TO HAVE THE SAME INTERNAL PRT FAILURE. (TC# 20060626002)				1	L	7	2 	3R	3	R		A765    	5E1				 
2006080400038	20060804	00038		2006	8	4	CA060626004      	4	20060622	G	6122	4V1827	GOVERNOR        			CNDAIR	CL215 	CL2151A10   	1900320	EA  										PROPELLER	OVERSPEED       	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA				266  							(CAN) AFTER WATER SCOOP, THE LEFT PROP WENT TO OVERSPEED, PROP WAS CONTROLABLE WITH THROTTLE AND POWER LEVER AT 2800 RPM	. ENGINE WAS SHUT DOWN AND SECURED. THE A/C RETURNED FOR MAINTENANCE. THE PROP GOVERNOR WAS REPLACED AND THE A/C RETURNE	D TO SERVICE.				2	H	7	2 	4R			RT	A14EA   					 
2006080400042	20060804	00042	NE  	2006	8	4	CA060626005      	3	20060622	G	6114		SEAL            			BAG   	JETSTM	JETSTM3212  	1500217	EU  						MCAULY	4HFR34	4HFR34C652  	NE  	RT PROP	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			5209 	1462 					881759		(CAN) DURING THE WALK AROUND, THE PILOTS NOTICED OIL DRIPPING DOWN ONE BLADE OF THE RT PROPELLER.  MAINTENANCE WAS NOTIF	IED AND THE AME WAS DISPATCHED TO ASSESS. IT WAS DETERMINED THAT A BLADE SEAL HAD FAILED. THE PROPELLER WAS REMOVED FROM	 THE AIRCRAFT AND SENT TO WESTERN PROPELLER IN EDMONTON FOR REPAIRS. A VERBAL REPORT INDICATED THAT THERE WAS NO DAMAGE 	OR OBVIOUS CAUSE. ALL SEALS WERE REPLACED. THE PROPELLER WAS RE-INSTALLED AND RETURNED TO BASE THE FOLLOWING DAY.			2	L	7	2 	4T			RT	BA15CAA 		6	C	3PNE	 
2006080400044	20060804	00044	EA  	2006	8	4	CA060626006      	1	20060622	G	2130	1305221	SELECTOR PANEL  			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CABIN PRESSURE	UNKNOWN         	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA			23742	23742							(CAN) DURING FLIGHT CABIN PRESSURE WARNING LIGHT ILLUMINATED AT FLT LVL 230, F/A REPORTED MAIN CABIN DOOR SEAL LEAKING. 	AIRCRAFT COMMENCED RAPID DECENT AT 3000`/MIN . AFTER NORMAL LANDING AT DESTINATION , AIRCRAFT DEPARTED UNDER MEL FOR UNP	RESSURIZED FLIGHT. AFTER ARRIVAL AT MAINTENANCE BASE, MAINTENANCE INSPECTED MAIN CABIN DOOR SEAL AND FOUND SERVICEABLE. 	CABIN PRESSURE SELECTOR PANEL REPLACED, AIRCRAFT GROUND RUN AND ABLE TO OBTAIN AND MAINTAIN MAXIMUM DIFFERENTIAL. AIRCRA	FT RETURNED TO SERVICE. AIRCRAFT HAD PREVIOUS HISTORY OF PRESSURIZATION ISSUES IN AUTO MODE,  CABIN PRESSURE COMPUTER PR	EVIOUSLY REPLACED, (TC# 20060626006)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006080400048	20060804	00048	EA  	2006	8	4	CA060627001      	2	20060623	G	7250	310427801	SNAP RING       			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE BEARING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2998 				PCE24983			(CAN) WHILE TURNING PROPELLER DURING MAINTENANCE, A METAL-ON-METAL GRINDING NOISE WAS COMING FROM INSIDE L/H ENGINE EXHA	UST DUCT. MAINTENANCE REACHED IN THRU EXHAUST STACK OPENING AND TAPPED EXHAUST DUCT "SKI SLOPE" AREA AND HEARD A RATTLE 	SOUND. ENGINE SPLIT, PT DISC REMOVED AND FOUND BEARING COVER SNAP RING MISSING. THE ENGINE HAS SB1389 COMPLIED WITH AT L	AST ENGINE O/H. THIS SB CUTS SLOTS TO KEEP BEARING COVER FROM ROTATING. THE SLOTS IN THE PT SHAFT HOUSING WERE FOUND WOR	N, WHICH ALLOWS BEARING COVER TO SHIFT CAUSING WEAR IN SNAP RING WHICH RETAINS COVER. OVER THE PERIOD OF ENGINE OPERATIO	N FROM O/H `TILL NOW WE SUSPECT THIS HAS CAUSED THE FAILURE OF THE SNAP RING. THIS IN TURN ALLOWED THE BEARING COVER TO 	1	L	7	2 	3T	4	T		3A20    	E4EA				 
2006080400049	20060804	00049	GL  	2006	8	4	CA060627002      	2	20060618	G	7261	23070328	OIL TANK        			EMB   	145   	EMB145ER    	3260211	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	RUPTURED        	W				E	F	B		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	EMER. DESCENT           		K	Y	A	FLUID LOSS                	ENGINE STOPPAGE           	FLAME/FIRE                	CR	CRUISE         	1			CA			7913 					CAE312063			(CAN) A/C N14930/145011, ENGINE NR 2 S/N CAE312063 SUFFERED A COMMANDED IN-FLIGHT SHUTDOWN (CIFSD) DUE TO AN OIL TANK RU	PTURE THAT LED TO OIL LEAKAGE AND SUBSEQUENT FIRE.  THE ENGINE WAS SHUT DOWN BY THE CREW AFTER LAV SMOKE, ENGINE FIRE, L	OW OIL QUANTITY AND HIGH OIL TEMPERATURE INDICATIONS WERE OBSERVED ENROUTE FROM CRP TO IAH.  THE AIRCRAFT DIVERTED TO VC	T SAFELY W/O INCIDENT WHERE THE ENGINE IS BEING REMOVED.  METAL DEBRIS WAS FOUND IN THE EXPOSED OIL TANK THAT APPEARS TO	 BE FROM INTERNAL WEAR. ENGINE IS PRESENTLY AT ROLLS-ROYCE CANADA UNDER INVESTIGATION.		2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2006080400050	20060804	00050	SW  	2006	8	4	CA060627003      	1	20060625	G	6220	214030606005	SPINDLE         			BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					M/R GEARBOX	BROKEN          	W				B				EMER. DESCENT           				J			WARNING INDICATION        			HO	HOVERING       	1			CA				694  		AME28043					(CAN) TRANSMISSION SPINDLE ASSY P/N 214-040-606-005 S/N A12-01304 BROKE IN HALF DURRING FLIGHT, AND THE PILOT HEARD A LO	UD BANG AND BEGAN A EMERGENCY LANDING. APON SUCSESSFULL LANDING THE ENGINEER FOUND THE SPINDLE CRACKED IN HALF. DURRING 	THE SHORT TIME IN THE AIR FOR LANDING THE MAIN DRIVESHAFT OVERTEMPED, ONE OF THE TAIL ROTOR DRIVESHAFTS SCRAPED HALF THE	 WAY THROUGH, AND THE FORWARD DRIVESHAFT COUPLING WAS REMOVED FOR INSPECTION. NEW SPINDLES, LEFT AND RIGHT, AND DRIVESHA	FTS WERE INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. THIS IS THE SECOND SPINDLE FALURE WE HAVE HAD THIS MONTH.  THE 	TWO SPINDLES HAVE BEEN REQUESTED TO BE SENT TO BELL IN TEXAS BY BELL HELICOPTER AND WILL BE SENT OUT THIS WEEK. (TC# 200	2	G	7	1 	4U	4	U		H6SW    	E4NE				 
2006080400051	20060804	00051	WP  	2006	8	4	CA060627004      	2	20060627	G	7260	31035851	BEARING         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					TORQUE SENSOR	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			964  					P54156			(CAN) THE FRONT SCAVENGE PUMP DRIVE GEAR SHAFT SHEARED IN THE SCAVENGE PUMP, DUE TO THE SCAVENGE PUMP BUSHING THAT SEIZE	D FROM OIL STARVATION AND METAL CONTAMINATION CAUSED BY THE TORQUE SENSOR BEARING. THE OIL PRESSURE PUMP SHAFT AND BUSHI	NG ALSO HAVE WEAR ON THEM DUE TO OIL STARVATION. THE TORQUE SENSOR BEARING PART NUMBER 3103585-1 FAILED JAMMING UP THE G	EAR CAUSING THE BEARING OUTER RETAINER TO HAVE EXCESSIVE WEAR ON IT. THE INNER AND OUTER BEARING RACES AND BALLS HAVE WE	AR DAMAGE ON THEM ALSO DUE TO THE FAILED BEARING.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20081229		CE  	2008	12	29	CA060627005      	1	20060624	G	2701		ROLLER          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	CONTROL YOKE	DISLODGED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) CO-PILOTS CONTROL YOKE GUIDE ROLLER ASSY FELL OUT AND ON INVESTIGATION WAS FOUND THAT WRONG SIZE BOLT WAS INSTALLE	D. FURTHER INVESTIGATION OF THE REST OF THE FLEET IT WAS FOUND THAT 2 OTHER ACFT HAD THE WRONG BOLT PN AND SIZE INSTALLE	D. CORRECT BOLT INSTALLED AND ACFT RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006080400060	20060804	00060	EA  	2006	8	4	CA060627006      	1	20060625	G	5244	2153300688	DOOR            			CNDAIR	CL215 	CL2151A10   	1900320	EA  										LT ACCESSORY	SEPARATED       	W				O				OTHER                   				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		NR	NOT REPORTED   	1			CA			4124 								(CAN) AIRCRAFT WAS COMPLETING A SCOOPING RUN WHEN THE LT HAND DOOR ASSEMBLY PN 215-33006-882 OPENED AND DEPARTED THE AIR	CRAFT. CREW WERE ABLE TO LIFT AIRCRAFT OFF WATER AND RETURNED TO BASE WITHOUT FURTHER INCIDENT. INVESTIGATION TO FOLLOW 	TO DETERMINE THE CAUSE OF DOOR OPENING.				2	H	7	2 	4R			RT	A14EA   					 
2006080400062	20060804	00062	EA  	2006	8	4	CA060628001      	2	20060411	G	7414	M3008	GEAR            	SLICK       		ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					DISTRIBUTER	UNSERVICEABLE   	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			1185 			04040517					(CAN) DURING POST REMOVAL TEARDOWN INSPECTION OF MAGNETO ELECTRODE FINGER FOUND BROKEN OFF OF THE DISTRIBUTER GEAR.						1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2006080400063	20060804	00063	WP  	2006	8	4	CA060628002      	1	20060621	G	7810	D3171	HEAT SHIELD     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			140  								(CAN) DURING A ROUTINE 50 HR ENGINE INSPECTION, IT WAS NOTED THAT THE SUBJECT HEAT SHIELD, THAT IS INSTALLED ON THE EXHA	UST TAILPIPE, WAS FOUND CRACKED. THE CRACK ORIGINATED IN A DOUBLER AREA WHERE THE FORWARD CLAMP IS ATTACHED. THE CRACK L	OOKS AS THOUGH IT STARTED FROM A RIVET WHICH ATTACHES THE DOUBLER AND BRACKET, WHICH PROVIDES A MEANS TO ATTACH THE CLAM	P TO THE EXHAUST TAIL PIPE. THE PART IN QUESTION HAS 140.3 HRS TIME SINCE NEW. THE AIRCRAFT IN QUESTION HAS 343.5 HOURS 	SINCE NEW. THE PART HAS BEEN SUBMITTED TO ROBINSON HELICOPTER FOR WARRANTY. (TC# 20060628002)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006080400066	20060804	00066	WP  	2006	8	4	CA060628003      	1	20060621	G	7810	C1695	COLLECTOR RING  			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					EXHAUST	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			344  								(CAN) DURING A ROUTINE 50 HOUR ENGINE INSPECTION, IT WAS NOTED THAT THE L/H EXHAUST COLLECTOR WAS BENT AT THE AFT DOWNPI	PE CREASE AREA. DURING FURTHER INVESTIGATION, IT WAS NOTED THAT A CRACK HAD FORMED IN THE SUBJECT AREA. DURING REMOVAL O	F THE SUBJECT PART, IT WAS ALSO NOTED THAT THE OUTLET FLANGE THAT FITS INTO THE MUFFLER, WAS DEFORMED AND CRACKED AS WEL	L. THE SUBJECT PART HAS NOT BEEN REMOVED OR ALTERED SINCE NEW. THE PART HAS BEEN RETURNED TO MANUFACTURER FOR WARRANTY. 	CONSIDERATION IS BEING MADE THAT THE PART MAY HAVE BEEN PUT IN A STRESSFUL CONDITION WHEN INSTALLED AT THE FACTORY. THE 	AIRCRAFT HAS 343.5 HOURS SINCE NEW.	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006080400067	20060804	00067	EU  	2006	8	4	CA060628004      	1	20060628	G	3320	BVO320204114	SOCKET          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	RT WINDOW LIGHT	OVERHEATED      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) LAMP SOCKET P/N BVO3202-04-114 OVERHEATED AND SMOKE SMELL NOTED AT R/H CABIN SIDE WINDOW LIGHT. LAMP SOCKET REPLAC	ED. TESTED SERVICEABLE. (TC# 20060628004)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006080400070	20060804	00070	NE  	2006	8	4	CA060628007      	2	20060608	G	8530	282992	COVER           			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					PUSHRODS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				512  		210872					(CAN) DURING ENGINE DIS-ASSEMBLY FOR CYLINDER REPAIRS, THE PUSHROD COVERS (TUBES) WERE FOUND TO BE HEAVILY DAMAGED UNDER	 THE CONTACT AREA OF THE SEAL PACKINGS.  THESE PUSHROD COVERS HAD BEEN CHROME PLATED AT THE PREVIOUS OVERHAUL, AND THIS 	CHROME WAS FOUND TO HAVE BONDED TO THE PACKINGS AND HAD LIFTED AWAY FROM THE PARENT MATERIAL, CAUSING A SERIOUS POTENTIA	L LEAK PATH AND/OR BREAKAGE POINT.  I AM NOT AWARE OF ANY APPROVED PROCESS TO CHROME THESE TUBES.  ALL TUBES WERE REPLAC	ED WITH NEW. (TC# 20060628007)		1	L	7	2 	3R	3	R		A765    	5E1				 
2006080400072	20060804	00072	EU  	2006	8	4	CA060629001      	1	20060626	G	3260		UPLOCK          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA				2781 							(CAN) WHEN THE CREW SELECTED GEAR UP ALL POSITIONS FAILED TO SHOW UP AND LOCKED. THE CREW RETURNED TO POINT OF DEPARTURE	 AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE RIGHT HAND MAIN LANDING GEAR UPLOCK BOX ASSY. AND THE WEIGHT ON W	HEELS UPPER WIRING HARNESS. THE LANDING GEAR WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20060629001	)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006080400075	20060804	00075	EU  	2006	8	4	CA060629002      	1	20060619	G	3297		CONTACT         			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	MLG	FOULED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			27455								(CAN) DEPARTING THE LANDING GEAR LEVER WOULD SELECT TO THE UP POSITION. THE AIRCRAFT REURNED TO POINT OF DEPARTURE AND L	ANDED WITHOUT FURTHER INCIDENT. MAINTENANCE DETERMINED THE GROUND CONTACT FOR THE GEAR LEVER LOCKOUT SOLENOID WAS FOULED	. THE CONTACT WAS CLEANED AND A FUNCTION CHECKED PERFORMED PRIOR TO THE AIRCRAFT BEING RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006080400078	20060804	00078	CE  	2006	8	4	CA060629003      	1	20060628	G	3610	24538400	FLANGE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TUBE	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7216 								(CAN) WELDED TUBE ASSEMBLY REMOVED FROM AIRCRAFT TO GAIN ACCESS FOR INSPECTION.  WELDED TUBE ASSEMBLY INSPECTED - FLANGE	 ATTACHED APPEARED TO BE BONDED TO TUBE.  UPON INSTALLATION ON AIRCRAFT - WHEN CLAMP ATTACHING WELDED TUBE ASSEMBLY TO C	ABIN VENTILATION JUNCTION BOX WAS TORQUED.  THE WELDED TUBE ASSY WAS FREE TO PULL OUT OF FLANGE.  INSERTED WELDED TUBE A	SSY BACK INTO FLANGE AND RELEASE THE CLAMP.  FOUND FLANGE HAD A TIGHT METAL TO METAL FIT.  ABLE TO PULL OFF FLANGE WITH 	SOME FORCE.  FLANGE IS BONDED TO WELDED TUBE ASSEMBLY WITH ADHESIVE.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006080400080	20060804	00080	CE  	2006	8	4	CA060629004      	1	20060629	G	5310	12139881	DOOR FRAME      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C402   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5952 								(CAN) FORWARD DOOR POST BULKHEAD CRACK DETECTED DURING ACCOMPLISHMENT OF SEB 93-5 CESSNA SERVICE KIT SK206-42 LOWER FORW	ARD DOORPOST BULKHEAD AND WING STRUT FITTING REINFORCEMENT TO BE INSTALLED. (TC# 20060629004)					1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P47GL	 
2006080400082	20060804	00082	NE  	2006	8	4	CA060629005      	2	20060628	G	8530	356996	CYLINDER        			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				808  				NK510094			(CAN) DURING CRUISE, NR 1 ENGINE BMEP INDICATION WAS FLUCTUATING, AIRCRAFT HAD A SLIGHT YAW. THE RETARDANT LOAD WAS JETT	ISONED AND THE ENGINE WAS SHUT DOWN AND PROP FEATHERED. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION NR 15 CYLINDER	 EAR WAS FOUND CRACKED. THE CYLINDER WAS REPLACED, ENGINE WAS GROUND RUN AND LEAK CHECKED AND THE AIRCRAFT WAS RETURNED 	TO SERVICE.			2	L	7	4 	4R	4	R		6A4     	E264	6	C	P871	 
2006101800075	20061018	00075	EU  	2006	10	18	CA060629006      	1	20060627	G	6320	DHS43911142	RETAINING NUT   	UROCOP      		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					M/R GEARBOX	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA			1392 			M149					(CAN) RETAINING NUT FOR THE INPUT FLANGE ON THE TRANSMISSION (MAIN GEARBOX) BROKE IN 2 PIECES CAUSING THE SPLINED ADAPTE	R TO BACK OFF, WHICH CAUSED THE HYDRAULIC BELT TO RUN ON THE EDGE OF THE PULLEY. (TC NR 20060629006)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006080400084	20060804	00084	CE  	2006	8	4	CA060629007      	1	20060620	G	2133	10138001313	OUTFLOW VALVE   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN PRESSURE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				16   			BB170				(CAN) THE AIRCRAFT EXPERIENCED A LEAK DOWN OF CABIN PRESSURE.  THE TROUBLE WAS TRACED TO THE FLOW CONTROL PACK UNITS.  B	OTH CONTROL UNITS WERE REPLACED WITH OVERHAULED UNITS.  THE UNITS THAT WERE INSTALLED NEVER PROVIDED ENOUGH FLOW FOR PRE	SURIZATION, HEATING AND COOLING.  WHEN THE OVERHAULER OF THE UNITS WAS CONTACTED, THEY INFORMED US THAT THEY HAD PROBLEM	S WITH THEIR CALIBRATION SYSTEM WHICH MADE THE FLOW PACKS PUT OUT MINIMUM AIR.  THEY HAD KNOWN ABOUT THIS PROBLEM FOR TW	O MONTHS OR MORE HOWEVER THEY CONTINUED TO PRODUCE AND SELL OVERHAULED UNITS.  OUR COMPANY RECEIVED TWO OVERHAULED UNITS	 TO REPLACE THESE THAT WERE OVERHAULED IMPROPERLY ALSO.  THE COMPANY SPECIFIED THAT ANY PACKS OVERHAULED BEFORE MAY 19 W	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006080400086	20060804	00086		2006	8	4	CA060629008      	4	20060620	G	2562		CONTACT         	ACK         		CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755B2      	35007	SW  					ELT BATTERY	DEFECTIVE       	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						2385					(CAN) THE GOLD PLATING ON THE BATTERY CONTACT IS FLAKING OFF. THE EXPOSED METAL IS NON-CONDUCTIVE AND THEREFORE THE UNIT	 NO LONGER FUNCTIONS. (TC# 20060629008)					1	H	7	1 	3R	3	R		A790    	E237				 
2006101800076	20061018	00076	EU  	2006	10	18	CA060630001      	1	20060405	G	3246	350A41101606	SKID            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKID TUBE FOUND CRACKED AT 2 LOCATIONS FORWARD OF THE FORWARD CROSSTUBE AND BOTH FOUND CORRODED BEYOND REPAIRABLE 	LIMITS WHILE PERFORMING 5000 HR LANDING GEAR INSPECTION. TUBES P/N 350A41-1016-1063 AND-1163 REPLACED WITH SAME. (TC NR 	20060630001)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006080400087	20060804	00087	CE  	2006	8	4	CA060630002      	1	20060629	G	5347	05112421	STOP            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					SEAT TRACK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE SEAT REMOVAL PROCEDURE IT WAS NOTICED THAT THE SEAT STOP WAS BROKEN APART AROUND THE FASTENING SC	REW HOLE. THERE IS NOT MUCH MATERIAL BETWEEN THE SCREW HOLE AND THE EDGE OF THE STOP WHICH COULD HAVE LED TO A FAILURE O	F THIS AFT POSITIONED SEAT STOP. (TC# 20060630002)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006080400090	20060804	00090	NM  	2006	8	4	CA060630003      	1	20060629	G	2782	1U109592	ACTUATOR        			BOEING	727   	727225      	1384077	NM  										SLAT	INOPERATIVE     	W				J	A			DUMP FUEL               	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA			8225 								(CAN) SHORTLY AFTER TAKEOFF, CREW NOTICED THAT THE #8 LEADING EDGE SLAT WAS NOT INDICATING THAT IT WAS RETRACTED. THE CR	EW REQUESTED FUEL DUMP AND TURN BACK TO DEPARTURE. MAINTENANCE TESTED THE SLAT AND FOUND THE INDICATION SWITCH IN THE AC	TUATOR WAS AT FAULT. MAINTENANCE INSTALLED THE INLINE SLAT JUMPER P/N B2T-27-001-01 AND THE SYSTEM TESTED SERVICEABLE. T	HE AIRCRAFT WAS DISPATCHED WITHOUT FURTHER FAULTS. ACTUATOR TO BE REPLACED ON THE WEEKEND LAYOVER. (TC# 20060630003)			2	L	7	3 	4F				A3WE    					 
2006080400092	20060804	00092	CE  	2006	8	4	CA060630004      	1	20060630	G	2510	05141823	SEAT            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION OF SEAT FRAME ASS`Y DURING SCHEDULED MAINTENANCE REVEALED A CRACKED SUPPORT LEG. SAFETY OF SEAT ASS`Y M	AY BE COMPROMISED DUE TO THE WEAKENED SUPPORT LEG. (TC# 20060630004)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2006080400096	20060804	00096	EU  	2006	8	4	CA060630006      	1	20060627	G	6520	350A33020005	GEARBOX         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			5846 	2489 							(CAN) TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED IN FLIGHT. AIRCRAFT LANDED AND CHIP DETECTOR EXAMINED, MALL AMOUNT OF FE	RROUS MATERIAL ON DETECTOR.  DETECTOR CLEANED AND SERVICEABILITY CHECK CARRIED OUT.  ON RETURN TO LANDING SITE, SMALL AM	OUNT OF FINE HAIR LIKE PARTICLES DISCOVERED.  TAIL ROTOR GEARBOX REMOVED AND SENT TO OVERHAUL FACILITY FOR TEARDOWN AND 	REPAIR.  SERVICABLE GEARBOX INSTALLED, AIRCARFT RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006080400102	20060804	00102	EU  	2006	8	4	CA060702001      	1	20060613	G	3246	16103000	WHEEL           			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					MLG	CRACKED         	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI AFTER LDG, A VIBRATION WAS NOTED ORIGINATION ON THE LH LDG GEAR.  IT WAS ORIGINALLY THOUGHT TO BE A WHEEL 	OUT OF BALANCE.  ON INSPECTION, A CRACK WAS OBSERVED ON THE INNER WHEEL 1/2 OUTBOARD ASSEMBLY.  THE CRACKED RIM WAS REPL	ACED WITH NEW CLEAVLAND INNER WHEEL 1/2 PN 161-03000. (TC# 20060702001)				1	H	7	2 	3O	3	O		A17EU   	E295				 
2006080400105	20060804	00105	NE  	2006	8	4	CA060704001      	2	20060506	G	7321		FUEL CONTROL    			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67      	52043	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING FORMATION FLIGHT THE PILOT REDUCED POWER.  WHEN POWER WAS RE-APPLIED THE ENGINE WOULD NOT RESPOND INITIALLY	 TO THROTTLE INPUT.  POWER INCREASED AFTER 7 TO 8 SECONDS.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.  PWC WILL I	NVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2006080400107	20060804	00107	EA  	2006	8	4	CA060704002      	2	20060527	G	7210		GEARBOX         			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					ENGINE	SPALLED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								40252			(CAN) THE ENGINE CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT.  THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT DIVERTED TO AN 	ALTERNATE AIRPORT.  SUBSEQUENT INSPECTION REVEALED SPALLING OF THE FIRST STAGE REDUCTION GEARBOX GEARING. (TC# 200607040	02)				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006080400109	20060804	00109	NE  	2006	8	4	CA060704003      	2	20060530	G	7261		ENGINE          			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  						LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								AK0001			(CAN) DURING CLIMB THE ENGINE WAS REPORTED TO LOSE OIL PRESSURE.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DI	VERTED TO POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 2006070400	3)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006080400110	20060804	00110	EA  	2006	8	4	CA060704004      	2	20060515	G	7250		TURBINE BLADES  			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					TURBINE SECTION	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT.  THE AIRCRAFT DIVERTED FOR AN UNSCHEDULE	D LANDING WHICH RESUTED IN AIRFRAME DAMAGE.  SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES.  P&WC W	ILL MONITOR INVESTIGATION OF THE BLADES AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704004)				1	L	7	2 	3T	4	T		3A20    	E4EA				 
2006080400156	20060804	00156	EA  	2006	8	4	CA060704005      	2	20060606	G	7321		FUEL CONTROL    			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE ENGINE WAS REPORTED TO EXHIBIT TORQUE FLUCTUATIONS IN CLIMB AND WAS SHUT DOWN IN FLIGHT. THE FUEL CONTROL UNIT	 WAS SUBSEQUENTLY REMOVED FOR INVESTIGATION.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE	 ONCE ESTABLISHED. (TC# 20060704005)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006080400157	20060804	00157	NE  	2006	8	4	CA060704006      	2	20060607	G	7320		EEC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE FLAMED OUT IN DESCENT.  THE EVENT WAS LATER DUPLICATED DURING FLIGHT TEST.  THE EEC WAS EXCHANGED AND T	HE PROBLEM COULD NOT BE DUPLICATED.  THE AIRCRAFT WAS RETURNED TO SERVICE.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVIS	E OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704006)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006080400158	20060804	00158	EA  	2006	8	4	CA060704007      	2	20060611	G	7230		COMPRESSOR      			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								RB0182			(CAN) IN CRUISE, THE ENGINE WAS REPORTED TO EMIT A NOISE FOLLOWED BY A LOSS IN POWER.  THE ENGINE WAS SHUT DOWN IN FLIGH	T AND THE AIRCRAFT DIVERTED.  POST FLIGHT INSPECTION REVEALED COMPRESSOR DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND AD	VISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704007)				1	L	7	2 	3T	4	T		3A20    	E4EA				 
2006080400159	20060804	00159	NE  	2006	8	4	CA060704008      	2	20060609	G	7261	310047001	ELBOW           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	OIL SYSTEM	FRACTURED       	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 SHUT DOWN IN FLIGHT AND THE AIRCRAF	T DIVERTED FOR AN UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION REVEALED THE REDUCTION GEARBOX PRESSURE OIL ELBOW IMPROPER	LY SECURED AND FRACTURED.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704008)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006080400162	20060804	00162		2006	8	4	CA060704009      	4	20060613	G	3418		STALL WARNING   			CNDAIR	CL601 	CL6013A     	8070802	EA  											FALSE ACTIVATION	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE FOLLOWING WAS REPORTED BY THE PILOT; "THE STALL WARNING HORN SOUNDED, STICK SHAKER ACTIVATED FOLLOWED BY THE P	USHER AT FL320 DURING CLIMB.  R AFCS WAS ENGAGED AND COUPLED TO CO-PILOTS FD AT THE TIME.  WHEN THE PILOT GRABBED THE Y	OKE THE SHAKER ACTIVATED ONE MORE TIME.  THE AFCS WAS DISENGAGED AND THE NOSE WAS LEVELLED. THE STALL HORN AND STALL LIG	HTS REMAINED ON.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED TO OWN BASE.  LANDING WAS UNEVENTFUL."   THE FOLLO	WING FLIGHT TO THE SERVICE CENTRE WAS UNEVENTFUL AND THE STALL PROTECTION SYSTEM WAS TROUBLESHOT WITH NO FAULT FOUND. TH	E FDR DATA WAS ANALYSED AND SHOWED THAT, DURING CLIMB OUT, AT FL327 THE AIRSPEED HAD SLOWED TO 155 KIAS, A SPEED CONSIST	2	L	7	2 	4F			RT	A21EA   					 
2006080400166	20060804	00166	NE  	2006	8	4	CA060704010      	2	20060613	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA								305269			(CAN) IN CLIMB THE CREW REPORTED SMOKE AND OIL SMELL IN THE CABIN ACCOMPANIED BY AN ENGINE CHIP DETECTOR WARNING.  THE C	REW DECLARED AN EMERGENCY AND THE FLIGHT WAS DIVERTED TO POINT OF ORIGIN.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVIS	E OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704010)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006080400173	20060804	00173	NE  	2006	8	4	CA060704011      	2	20060628	G	7321	7045402L2	FUEL CONTROL    			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			4527 	313  				672488			(CAN)  AFTER SETTING A TURN OF LOGS DOWN ON LOG LANDING WITH A LT CROSS WIND, ACFT TURNED FULLY INTO WIND & BEGAN A CLIM	B BACK UP HILL TO LOGGING UNIT WITH APPROXIMATELY 60% TORQUE INDICATED. AFTER ABOUT 7-10 SECONDS INTO CLIMB, N1 UNDERSPE	ED WARNING HORN SOUNDED. FLT CREW REDUCED POWER & OBSERVED N2 NEEDLE FOR NR 2 ENG DECREASING ON TRIPLE TACH. CO-PILOT NO	TICED NR 2 ENG N1 SPEED AT 35% & T5 TEMP STABLE AT 465 DEGREES C. CREW ELECTED TO SHUTDOWN NR 2 ENG & MOTOR TO COOL T5. 	AN ATTEMPT TO RESTART ENG MADE & THEN ABORTED DUE TO ENG NOT ACCELERATING PAST 35% N1. ACFT LANDED WITHOUT FURTHER INCID	ENT. A COMPLETE INSPECTION REVEALED NOTHING ABNORMAL. AN ENGINE START ATTEMPTED & ABORTED DUE TO ENG NOT BEING ABLE TO A	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006080400176	20060804	00176	NE  	2006	8	4	CA060704012      	2	20060615	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								100208100209			(CAN) DURING CRUISE AT FL380 (AND APPROACHING CLOUD TOP) BOTH ENGINES WERE THROTTLED BACK IN POWER BY THE CREW PRIOR TO 	ENGAGING ANTI-ICE.  BOTH ENGINES FLAMED OUT.  THE ENGINES WERE SUBSEQUENTLY RE-STARTED IN FLIGHT AND THE AIRCRAFT DIVERT	ED. POST-EVENT INSPECTION REVEALLED NO ENGINE ANOMOLIES. P&WC WILL INVESTIGATE THE EVENT AND WILL REPORT ON ROOT CAUSE O	NCE ESTABLISHED.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006080400178	20060804	00178	NE  	2006	8	4	CA060704013      	2	20060619	G	7250		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE THE ENGINE WAS REPORTED TO EXHIBIT TORQUE AND POWER TURBINE SPEED FLUCTUATIONS.  THE ENGINE WAS SHUT DOW	N IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE O	NCE ESTABLISHED. (TC# 20060704013)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006080400179	20060804	00179	NE  	2006	8	4	CA060704014      	2	20060618	G	7321	8237002	FUEL CONTROL    			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUTS FOR POWER REDUCTION.  THE ENGINE WAS SHUT DOWN ON 	FINAL APPROACH.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC# 20060704014)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006080400181	20060804	00181	NM  	2006	8	4	CA060704015      	1	20060619	G	2120		SMOKE           			DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					CABIN	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								CD0228			(CAN) ON DESCENT THE CREW REPORTED SMOKE IN THE CABIN AIR.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED AT POINT O	F DESTINATION.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704015)					2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006080400183	20060804	00183	NE  	2006	8	4	CA060704016      	2	20060621	G	7310	3031829	TUBE            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					FUEL SYS	FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE FLAMED OUT IN CRUISE.  SUBSEQUENT INSPECTION REVEALLED A FRACTURED FUEL SYSTEM P3 AIR TUBE. (TC# 200607	04016)					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2006080400185	20060804	00185	NM  	2006	8	4	CA060704017      	1	20060625	G	7931	312244801	PRESSURE SWITCH 			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					OIL SYS	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN FLIGHT, THE CREW OBSERVED A LOSS OF ENGINE OIL PRESSURE INDICATION AND THE ENGINE WAS SHUTDOWN.  THE ENGINE OIL	 PRESSURE SWITCH WAS SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20060704017)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006080400186	20060804	00186	NE  	2006	8	4	CA060704018      	2	20060627	G	7261	3007389	ADAPTER         			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					OIL SYS	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AT TOP OF CLIMB, ENGINE TORQUE WAS SEEN TO FLUCTUATE FOLLOWED BY AN ENGINE LOW OIL PRESSURE WARNING.  THE ENGINE W	AS SHUT DOWN IN FLIGHT AND A DEAD-STICK LANDING ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE ASSOC	IATED WITH A FRACTURED REDUCTION GEARBOX PRESSURE OIL ADAPTER.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT 	CAUSE ONCE ESTABLISHED. (TC# 20060704018)			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2006080400188	20060804	00188	NE  	2006	8	4	CA060704019      	2	20060627	G	7532		BLEED VALVE     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					ENGINE	DIRTY           	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY FLAMES FROM THE EXHAUST AND POWER FLUCTUATIONS.  THE	 PILOT REDUCED ENGINE POWER AND ACCOMPLISHED AN UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION FOUND THE ENGINE COMPRESSOR 	BLEED VALVE TO BE STIFF AND FULL OF SAND,  THE BOV WAS CLEANED AND THE ENGINE RAN NORMALLY. (TC# 20060704019)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006080400190	20060804	00190	EA  	2006	8	4	CA060704020      	1	20060703	G	2910	AN62498	CHECK VALVE     			CNDAIR	CL215 	CL2151A10   	1900320	EA  										HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			96   	96   							(CAN) DURING FIRE FIGHTING OPERATIONS WATERDROP , HYDRAULIC FAILURE OCCURRED. AIRCRAFT LANDED AFTER EMERGENCY LANDING GE	AR EXTENSION WITH BOMB DOORS OPEN AND WAS TOWED OFF RUNWAY. THIS IS THE SECOND FAILURE  ON THE SAME AIRCRAFT IN THE SAME	 POSITION WE HAVE HAD THIS SUMMER FROM CHECK VALVE FAILURE. NEW STAINLESS VALVES HAVE BEEN ORDERED TO COMPLY WITH SUGGES	TED CANADAIR SERVICE BULLETIN BUT HAVE NOT ARRIVED. WE HAD TO USE THE OLD STYLE ALUMINUM CHECKVALVE WHEN IT WAS REPLACED	 EARLIER IN THE SPRING. SEE REFERENCE PREVIOUS SDR #20060427007 DATED MAY 12, 2006. (TC# 20060704020)		2	H	7	2 	4R			RT	A14EA   					 
2006080400192	20060804	00192	EA  	2006	8	4	CA060704021      	1	20060702	G	2910	82970009325	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        		DE	DESCENT        	1			CA											(CAN) ENROUTE AIRCRAFT REPORTED LOSS OF NR 2 HYDRAULIC SYSTEM QUANTITY. ALTERNATE GEAR EXTENSION SELECTED FOR ARRIVAL , 	NORMAL LANDING. MAINTENANCE INSPECTION FOUND NR 2 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE LEAKING, LINE REPLACED. HYD	 PUMP REPLACED DUE TO UNKNOWN TIME OPERATING WITHOUT FLUID. AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006080400196	20060804	00196	EA  	2006	8	4	CA060705001      	1	20060702	G	7931	4120T16P01	TRANSDUCER      			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348E5     	30015	NE  					OIL PRESSURE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			2    					GEE194466			(CAN) DURING RIGHT ENGINE WINDMILL RELIGHT, RIGHT ENGINE OIL PRESSURE AT 0 PSI UNTIL 24% N2. AT 34% N2, RIGHT OIL PRESSU	RE AT 3 PSI. ENGINE SHUT DOWN AND RTB SINGLE ENGINE. NOTE: DURING CRUISE PRIOR TO ENGINE SHUTDOWN, RIGHT ENGINE OIL PRES	SURE WAS CONSTANTLY 10 PSI BELOW LEFT ENGINE OIL PRESSURE. (TC# 20060705001)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2006080400197	20060804	00197	NE  	2006	8	4	CA060705002      	2	20060705	G	7230		COMPRESSOR      								PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	BIRD INGESTION  	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)   DAMAGE TO ENGINE COMPRESSOR CAUSED BY BIRDSTRIKE. COMPRESSOR DAMAGE WAS REPAIRED AND ENGINE RETURNED TO SERVICE.	 (TC# 20060705002)										4	T			E4EA				 
2006080400198	20060804	00198	NM  	2006	8	4	CA060705004      	1	20060704	G	6120	87620130101	SHAFT           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1 PROPELLER	BROKEN          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			20301								(CAN) LOSS OF PROPELLER CONTROL DUE TO BROKEN ENGINE CONTROL SPRING STRUT; THE FAILURE OCCURRED DURING FLIGHT AND DISABL	ED CONTROL OF THE NO 1 PROPELLER. THE EMERGENCY FUEL SHUT-OFF HAD TO BE OPERATED TO SHUT THE ENGINE DOWN AFTER LANDING. 	AT THE TIME OF THE INCIDENT, THE AIRCRAFT HAD ATTAINED 20301:00 HOURS AND 39275 CYCLES. THE OPERATOR IS PRESENTLY CARRYI	NG OUT A CAMPAIGN OF THEIR FLEET IN AN EFFORT TO AVOID ANY RECURRENCE.   (TC# 20060705004)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006080400199	20060804	00199	CE  	2006	8	4	CA060705005      	1	20060705	G	3320	S18802	RHEOSTAT        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  					CABIN LIGHTS	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3560 								(CAN) AIRWORTHINESS DIRECTIVE SEARCH ON TRANSPORT CANADA`S WEB SITE DID NOT SHOW 93-24-15 APPLYING TO THIS AIRCRAFT. IT 	APPEARS THAT THE MODEL APPLICABILITY SECTION OF THE FAA AIRWORTHINESS DIRECTIVE IS INCORRECT. (TC# 20060705005)					1	H	7	1 	3O	3	O		3A24    	E5CE				 
2006080700002	20060807	00002	CE  	2006	8	7	CA060705008      	1	20060628	G	3230	M710501	MOTOR           			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					HYD SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				388  							(CAN) DURING APPROACH LANDING GEAR WOULD NOT EXTEND NORMALLY AND 2 AMP CONTROL CIRCUIT BREAKER HAD OPENED. LANDING GEAR 	WAS LOWERED USING MANUAL SYSTEM AND UNEVENTFUL LANDING CARRIED OUT. MAINTENANCE FOUND 60 AMP LANDING GEAR CIRCUIT BREAKE	R OPEN (IN LH WING). REPLACED LANDING GEAR MOTOR (RIGHT POWER PACK) WITH OVERHAULED SPARE. RESET CIRCUIT BREAKERS AND GR	OUND TESTED LANDING GEAR OPERATIONS. EXPERIENCE HAS SHOWN THAT THESE MOTORS ARE PRONE TO PREMATURE FAILURE OR EXCESSIVE 	CURRENT DRAW.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006080700003	20060807	00003	NM  	2006	8	7	CA060706001      	1	20060703	G	2910	65C268091131	LINE            			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					HYDRAULIC SYS	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) #1 ENGINE HYDRAULIC PUMP CONTROL LIGHT ILLUMINATED IN FLIGHT ON CLIMB FROM LA GUARDIA. AIRCRAFT CONTINUED THE FLIG	HT. UPON INVESTIGATION IT WAS FOUND THAT A HYDRAULIC LINE FOR THE "A" SYSTEM PRESSURE MODULE WAS CRACKED. LINE REPLACED 	AND FLUID LEVEL SERVICED. AIRCRAFT RELEASED FOR SERVICE.  TIMES: 37201:46   CYCLES: 22712 (TC# 20060706001)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006080700009	20060807	00009	SW  	2006	8	7	CA060706002      	1	20060704	G	6210	204011250001	BLADE           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1988 								(CAN) CRACK ON BOTH SIDES OF BLADE BOLT BORE.  TRAVELLING IN CHORDWISE DIRECTION.  THE LEADING EDGE CRACK TRAVELS RIGHT 	TO THE LEADING EDGE AND THE TRAILING EDGE CRACK IS APPROXIMATLEY 6 INCHES LONG.  IT APPEARS ALL DOUBLERS ON THE LOWER PA	RT OF THE BLADE ARE CRACKED. (TC# 20060706002)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006080700020	20060807	00020	NE  	2006	8	7	CA060706003      	2	20060704	G	7532	310562601	CONNECTING ROD  								PWA   	JT15  	JT15D1      	52060	NE  					BLEED VALVE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PRATT & WHITNEY CANADA OVERHAUL MANUAL 3037323 REV.22, SECTION 72-30-07, PARAGRAPH 88-4 MISTAKENLY CALLS FOR NICKE	L PLATING IN ACCORDANCE WITH SPOP 62. SPOP 62 IS A FLORESCENT PENETRANT INSPECTION PROCEDURE. IT IS UNDERSTOOD THAT THE 	MANUAL SHOULD RATHER CALL FOR SPOP 26 WHICH IS A NICKEL PLATING SPEC. (TC# 20060706003)									4	F			E1NE				 
2006080700061	20060807	00061	NM  	2006	8	7	CA060706004      	1	20060702	G	2433	1032573	TRU             			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE AIRCRAFT WAITING ON THE GATE TO BOARD PASSENGERS FOR DEPARTURE, SMOKE WAS OBSERVED IN THE COCKPIT. CAUSE OF 	SMOKE WAS DETERMINED TO BE THE NR 2 TRANSFORMER RECTIFIER. UNIT REPLACED WITH NO FURTHER DEFECTS.  (TC# 20060706004)					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006080700064	20060807	00064	EU  	2006	8	7	CA060706005      	1	20060622	G	2150	9599060114	A/C PACK        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		FAILED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			5380 								(CAN) PILOT REPORTED THAT ECS WAS SELECTED ON AT PREFLIGHT CHECK. NO PROBLEM NOTICED. SOON AFTER ROUTINE TAKEOFF AN ODOU	R WAS PREVALENT IN COCKPIT. ECS SYSTEM WAS DEACTIVATED AND ODOUR DISSIPATED ALMOST IMMEDIATELY. AIRCRAFT RETURNED TO PLA	CE OF DEPARTURE WITH NO FURTHER FAULTS. PASSENGERS DEBOARDED AND CAPTAIN PERFORMED GROUND RUN TO TEST ECS. ODOUR RETURNE	D AS SOON AS ECS SELECTED ON. ECS SYSTEM WAS AGAIN DEAVTIVATED AND AIRCRAFT RETURNED TO BASE UNPRESSURIZED AND TROUBLESH	OT SYSTEMS INDICATING COLD AIR UNIT WAS AT FAULT. UNIT WAS REPLACED WITH SERVICEABLE PART. GROUND RUN PERFORMED WITH NO 	FAULT FOUND. AIRCRAFT RETURNED TO SERVICE. (TC# 20060706005)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006080700065	20060807	00065	EU  	2006	8	7	CA060706006      	1	20060706	G	3230	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD POWER	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			10555	10555							(CAN) LANDING GEAR WOULD NOT RETRACT FULLY AND HYDRAULIC LIGHT CAME ON AFTER LANDING GEAR WAS SELECTED UP IN CLIMB.  CRE	W CHECK HYDRAULIC CONTROL CB AND IT WAS IN.  CREW FOLLOWED CHECK LIST AND SELECTED GEAR DOWN AND HAND PUMPED LANDING GEA	R DOWN AND LOCKED.  A/C WAS FLOWN TO MAINTENANCE BASE WITH GEAR DOWN AND LANDED WITHOUT INSIDENCE.  HYDRAULIC SYSTEM TRO	UBLESHOOTING CARRIED OUT AND HYDRAULIC POWER CONTROL RELAY K601 FOUND TO BE AT FAULT.  RELAY REPLACED AND LANDING GEAR/H	YDRAULIC SYSTEMS FUNCTION CHECKED SERVICEABLE (TC# 20060706006)		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006080700086	20060807	00086	WP  	2006	8	7	CA060706007      	1	20060705	G	2910	89H1014738LGD4	LINE            			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	AT BEND	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE IT WAS NOTED THAT THE RH MLG DOOR ACTUATOR OPEN LINE WAS FOUND CHAFED BEYOND LIMITS. TH	E LINE WAS CHAFED BY AN ADJACENT FLEX LINE. THE AFFECTED LINE WAS REPLACED AND A GEAR SWING WAS COMPLETED. THE AIRCRAFT 	WAS RETURNED TO SERVICE. (TC# 20060706007)				2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2006080700094	20060807	00094	EA  	2006	8	7	CA060706008      	1	20060620	G	2913	66WA300	PUMP            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					HYD SYSTEM	BROKEN          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			AP	APPROACH       	1			CA				579  							(CAN) AIRCRAFT SUFFERED HYDAULIC FAILURE. PERFORMED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. HYDRAULIC LEAK FOUND ON 	ENGINE DRIVEN HYDRAULIC PUMP. THE END CAP FACEPLATE HAD A BROKEN BOLT AND THE BOLT IT WAS LOCKWIRED TO BESIDE IT HAD BAC	KED OFF. WITH BOTH BOLTS INEFFECTIVE, THE SEAL BLEW OUT BEHIND THE FACE PLATE AND ALL OF THE HYDRAULIC FLUID WAS PUMPED 	OVERBOARD. SUSPECTED PREVIOUS OVERTORQUING OF BOLT MAY HAVE CAUSED THE FAILURE (TC# 20060706008)			2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
2006092200106	20060922	00106	NM  	2006	9	22	CA060707001      	1	20060626	G	2497	2431154B10	WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TERMINAL END	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CREW REPORTED ELECTRICAL ODOR FROM BEHIND F/O`S SEAT DURING FLIGHT. LASTED FOR APPROX 10 MINUTES. MAINTENANCE FOUN	D OVERHEATED WIRES, CB`S AND BUS BARS ON THE RT SECONDARY DC CB PANEL. SPECIFIC ITEMS REPLACED AS FOLLOWS, (IPC 24-50-00	 FIG.10 PAGES 0 TO 6.  WIRE P/N 2431-154B10 FROM CB D1-RT FLARE LIGHT SECONDARY BUS REPLACED DUE TO ONE END OF WIRE AT T	ERMINAL END BADLY BURNED. APPEARS TO HAVE BEEN CAUSED BY ARCING OF THE WIRE.  WIRE MAY HAVE LOOSENED OVER TIME DUE TO VI	BRATION AS THERE DOES NOT APPEAR TO HAVE BEEN ANY RECENT WORK COMPLETED IN THIS AREA.  WIRE P/N 2431-156A10 FROM CB C1-B	UFFET POWER TO SECONDARY BUS LINK ON SECONDARY BUS BAR BETWEEN ROWS 4 AND 5 REPLACED DUE TO ONE END OF WIRE AT TERMINAL 	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006081100054	20060811	00054	NE  	2006	8	11	CA060707002      	2	20060626	G	7314	8187B	MOTOR           	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL PUMP	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			987  			110738					(CAN) PILOT WAS UNABLE TO USE THE ELECTRIC PUMP TO PRIME THE ENGINE.  TROUBLESHOOTING REVEALED THE PUMP WAS GETTING POWE	R.   FUEL PUMP ASSEMBLY WAS REPLACED, AND NO FURTHER DEFECTS FOUND. (TC NR 20060707002)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006081100055	20060811	00055	CE  	2006	8	11	CA060707005      	1	20060704	G	5530	04310093	FITTING         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	VERTICAL FIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8896 								(CAN) DURING 100 HOUR INSPECTION AME FOUND WHAT APPEARED TO BE A CRACK IN THE RADIUS OF THE LT FLANGE OF THE LT FITTING 	ATTACHING THE VERTICAL FIN TO THE HORIZONTAL STABILIZER.  WHEN THE PART WAS REMOVED FROM THE AIRCRAFT THE LT FLANGE WAS 	FOUND TO BE BENT TOWARDS THE RT FLANGE, AND WHEN MOVED AWAY FROM THE RT SIDE, IT BROKE FROM THE BASE OF THE FITTING REVE	ALING INTERGRANULAR CORROSION. (TC NR 20060707005)			1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006081100056	20060811	00056	EA  	2006	8	11	CA060708001      	1	20060624	G	2150	GG670950099	ACM             			CNDAIR	CL600 	CL6002C10   	1390015	EA  										RIGHT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			6557 			00660					(CAN) CREW NOTED THAT THEY GOT RT PACK AUTO FAIL CAUTION AND THEN HAD A STRONG ELECTRICAL BURNNG SMELL /SMOKE IN REAR SE	CTION OF CABIN. THE PACK WAS REMOVE AND REPLACED IAW AMM.   PLEASE ADD THE MFG IN THE MANUFACTURER MENU.   THANK YOU  (T	C  20060708001)				2	L	7	2 	4F			RT	A21EA   					 
2006081400100	20060814	00100	SO  	2006	8	14	CA060710002      	1	20060707	G	3213	MS28775335	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	CUT             	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON THE RAMP AFTER REFUELLING, PILOTS NOTED THE LT MLG OLEO WAS LEAKING FLUID AND DEFLATING. MAINTENANCE FOUND THE 	LT OLEO COMPLETELY DEFLATED AND APPROX. 1 LITRE OF HYDRAULIC FLUID ON THE RAMP UNDER THE LT OLEO. AFTER OLEO REMOVAL, FO	UND THE LOWER OLEO BEARING INNER O-RING SEAL SPIRAL CUT APPROX. 1 INCH ALONG THE SEAL. REPLACED SEAL AND OLEO SERVICED B	Y AMO 128-94. (TC NR 20060710002)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006081400101	20060814	00101	SO  	2006	8	14	CA060710003      	2	20060707	G	7322	S122210	THROTTLE CONTROL			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  						SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			370  								(CAN) DURING A SCHEDULED 50 HOUR INSPECTION THE THROTTLE CONTROL WAS FOUND TO BE SEPARATED AT THE SWAGE AREA JUST AFTER 	THE CLAMP AREA ON THE ROD END END ALLOWING THE CONTROL GUIDE TO MOVE ALONG WITH THE CONTROL END POSSIBLY RESULTING IN CO	NTROL JAMMING. (TC NR 20060710003)				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006080900193	20060809	00193	EU  	2006	8	9	CA060710005      	1	20060622	G	6720	350A75111720	SHIM            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					TAIL ROTOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION OF AN A-STAR IN THE FIELD, THE ENGINEER PERFORMING THE INSPECTION FOUND THAT THE T/R SE	RVO FRICTION/GUIDE SHIM (PAD) WAS INSTALLED ON THE FORWARD BOLT AND NOT ON THE AFT ONE.  WHEN RT PEDAL IS APPLIED THE SE	RVO FRICTION/GUIDE SHIM (PAD) SLIDES .7500 PERCENT OF THE WAY OUT OF THE FIXED GUIDE TAILBOOM). THIS CONDITION COULD POT	ENTIALLY CAUSE THE SERVO TO JAM.   THE FRICTION/GUIDE SHIM (PAD) WAS RELOCATED THE THE AFT BOLT IAW THE MM AND THE SERVO	 WAS CHECKED FOR CORRECT OPERATION. (TC NR 20060710005)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006080900194	20060809	00194	NE  	2006	8	9	CA060710006      	2	20060706	G	7320	3031829	LINE            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	P3	CRACKED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA			1748 								(CAN) DURING THE APPROACH TO THE AIRPORT, THE ENGINE LOST POWER. THE AIRCRAFT WAS DAMAGED ON LANDING. DURING PRELIMINARY	 INVESTIGATION, IT IS SUSPECTED THAT THE P3 LINE CRACKED CAUSING THE ENGINE TO GO INTO FLIGHT IDLE. THE ENGINE HAS BEEN 	REMOVED FROM THE AIRCRAFT AND HAS BEEN SHIPPED FOR FURTHER INVESTIGATION AND EVALUATION. UPON RECEIPT OF FINDINGS, WILL 	ADVISE. (TC NR 20060710006)			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2006081000004	20060810	00004	NE  	2006	8	10	CA060711001      	2	20060711	G	7240		CASE            								PWA   	JD15  	JT15D1A     	 	NE  					GAS GENERATOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACKED GAS GENERATOR CASE WAS FOUND CRACKED AT THE LONGITUDINAL WELD AND CIRCUMFERENTIAL WELD.  SB7240 IS AVAILAB	LE AND WILL REPLACE THE GAS GENERATOR CASE WITH A CASE WITH NO LONGITUDINAL WELDS. (TC NR 20060711001)										4	F			E25EA				 
2006081000005	20060810	00005	CE  	2006	8	10	CA060711002      	1	20060710	G	2497	D4FF10316GA	WIRE            	FORD        		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	VOLT REGULATOR	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			4088 								(CAN) WHILE ON A LOCAL VFR FLIGHT OVER, THE PILOT SMELLED FUMES AND SAW SMOKE COMING FROM BEHIND THE INSTRUMENT PANEL. T	HE PILOT ALSO NOTICED THAT THE HIGH VOLTAGE WARNING LIGHT WAS ON AND THE AMMETER SHOWING A DISCHARGE. THE PILOT REPORTED	 THE SITUATION TO THE FSS OPERATOR AND SUBSEQUENTLY TURNED OFF THE MASTER SWITCH, LANDING WITHOUT FURTHER INCIDENT. MAIN	TENANCE PERSONNEL DISCOVERED A BURNED WIRE FROM THE VOLTAGE REGULATOR TO THE HIGH VOLTAGE LIGHT. PARTS OF THE REGULATOR 	CIRCUIT BOARD SHOWED HEAT DAMAGE. THE VOLTAGE REGULATOR, HIGH VOLTAGE SENSOR HIGH VOLTAGE LIGHT AND BURNED WIRE WERE REP	LACED. AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20060711002)	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006091300291	20060913	00291	NM  	2006	9	13	CA060711003      	1	20060711	G	2433	9498828VS20	TRU             			DHAV  	DHC8  	DHC8102     	2809003	NM  										NR 1	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) THE EVENT OCCURRED DURING C-CHECK PROCEDURE AT THE EXTERNAL POWER APPLICATION. THE NR 1 TRU START TO PRODUCE HEAVY	 SMOKE AND SOME COPPER PARTICLES IN FUSION. COPPER PARTICLES PRODUCE SOME BURNING  HOLES IN THE EXHAUST COOLING DUCT. TH	E NORMAL CAUTION LIGHT NEVER COME ON BEFORE THE ELECTRICAL POWER MANUALLY CUT OFF. (TC NR 20060711003)				2	H	7	2 	4T			RT	A13NM   					 
2006081000006	20060810	00006	EA  	2006	8	10	CA060711004      	2	20060710	G	7414		DISTRIBUTOR GEAR	CONT        		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	DAMAGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA						E01HA039R					(CAN) AC WAS ON FINAL APPROACH WHEN PILOT HEARD A CHANGE IN ENGINE NOISE FOLLOWED BY LOW ROTOR HORN. INITIATED AN AUTORO	TATION, NOTICED THAT ENGINE, M/R RPM`S RETURNED TO NORMAL. CONTINUED HIS APPROACH AS INITIALLY PLANED, LANDED HELICOPTER	 WITHOUT FURTHER INCIDENT. ONCE ON GROUND,  PILOT DID A MAG CHECK WHEN LT MAGNETO WAS SELECTED, ENGINE QUIT. LT MAGNETO 	WAS REPLACED, AC RETURNED TO SERVICE. UPON REMOVAL OF MAGNETO, DISTRIBUTOR GEAR IN MAGNETO WAS FOUND TO HAVE SEVERAL TEE	TH WORN OR BROKEN OFF.  HAVE DECIDED TO HAVE MAGNETOS O/H EVERY 500 HRS. O/H WILL INCLUDE REPLACING DISTRIBUTOR GEAR, EV	ENTHOUGH MANUAL DOES NOT CALL FOR IT. (TC NR 20060711004)	1	G	7	1 	3O	3	O		H11NM   	E295				 
2006081000007	20060810	00007	EA  	2006	8	10	CA060711005      	2	20060706	G	8530	SLC36005F	CYLINDER HEAD   	LYC         		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1850 			L1067229A					(CAN) THIS THE 3RD CYLINDER IN 100 HOURS IS CRACKED THE SAME AS THE PREVIOUS 2. CRACKED APPROXIMATLY 30 PERCENT AROUND T	HE CYLINDER HEAD. CRACKED FROM THE OUTER MOST EXHAUST FLANGE STUD ROUGHLY 2 OR 3 INCHES TO THE EXHAUST VALVE SEAT. THEN 	CRACK CONTINUING FROM 180 DEGREE ACROSS THE EXHAUST VALVE SEAT TO THE SPARK PLUG HOLE (TC NR 20060711005).				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006081000008	20060810	00008	EA  	2006	8	10	CA060711006      	2	20060706	G	8530	SLC36005F	CYLINDER HEAD   	LYC         		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1850 			L1067239A					(CAN) THIS IS CYL NR 4 IN 100HRS. THE PREVIOUS 3 CYLINDERS EXHIBITED THE SAME TYPE AND LOCAL OF CRACKS. THIS CYLINDER HA	S A ONE AND A HALF INCH LONG CRACK AT THE OUTER MOST EXHAUST FLANGE STUD MOVING TOWARDS THE EXHAUST VALVE SEAT. ALSO A C	RACK BEGINNING AT THE EXHAUST VALVE SEAT AND MOVING TOWARDS THE SPARK PLUG HOLE (TC NR 20060711006)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006081000009	20060810	00009	GL  	2006	8	10	CA060711007      	3	20060707	G	6110	05503214	BULKHEAD        	CESSNA      		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS FORWARD SPINNER BULKHEAD HAS BEEN IN SERVICE WITH THE ORIGINAL (THIN MATERIAL) SPINNER. THE BULKHEAD HAS CRAC	KS TO 1.25 INCHES ACROSS EACH/ALL 6 PROP BOLK HOLES. (TC NR 20060711007)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006081000010	20060810	00010		2006	8	10	CA060711008      	4	20060710	G	6113	05503214	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			489  								(CAN) THE SPINNER FORWARD BULKHEAD WAS INSTALLED NEW ONE YEAR EARLIER, WITH THE NEW HEAVIER MATERIAL SPINNER IAW SNL03-9	 (ALTERNATE PROPELLER SPINNER INSTALATION) THE FWD BULKHEAD HAS CRACKS OF APPROXIMATLY 1.5 INCHES EACH  COMING ACROSS EA	CH PROP BOLT HOLE AT THE TOP OF AND JUST OUTSIDE OF THE BOLT WASHER CONTACT AREA, BUT NOT DIRECTLY INTERFACING WITH THE 	HOLE ITSELF. (TC NR 20060711008)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006081000011	20060810	00011	EA  	2006	8	10	CA060712000      	1	20060501	G	5610	NP13932114	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1436 								(CAN) THE RT SIDE WINDOW SHATTERED IN FLIGHT AT FL320, OUTTER SECTION. WINDOW IS POST SB (TC NR 20060712000)						2	L	7	2 	4F			RT	A21EA   					 
2006081000012	20060810	00012	SW  	2006	8	10	CA060712001      	1	20060710	G	6220	407310101101	BEARING         	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			5644 			A141					(CAN) AIRCRAFT DEVELOPED A VERTICIAL VIBRATION, VISUAL INSPECTION REVEALED A SEPERATED SHEAR BEARING. (TC NR 20060712001	)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006081100057	20060811	00057	SO  	2006	8	11	CA060712002      	1	20060704	G	2720	1582102	TUBE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10678								(CAN) DUE TO HIGH WINDS THAT HIT THE RUDDER (WITHOUT CONTROL LOCKS INSTALLED) INSTALLED THE AIRCRAFT FOR DAMAGE. THE RUD	DER PEDAL TUBE WAS FOUND CRACKED. THE PART WAS REPLACED. (TC NR 20060712002)					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2006081100058	20060811	00058	EA  	2006	8	11	CA060712003      	1	20060702	G	2497	WIRE2XA80ABBLU	FEEDER CABLE    			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					FS 625.30	ARCED           	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			6869 								(CAN) RT GEN TRIPPED OFFLINE DURING APPROACH. GEN OFF ANNUNCIATOR CAME ON, PWR AUTO TRANSFERED FROM GEN 1. NO LOSS OF PW	R ON ANY AC BUSES. AC FERRIED WITH GENERATOR 2 SELECTED OFF. ON 3RD ENGINE RUN, PROBLEM WAS DUPLICATED. PROBLEM WAS ISOL	ATED TO A WIRING PROBLEM. MAIN GEN FEED WIRES AWG 8 WERE INSPECTED. AT FS 625.30 JUST AFT OF AFT PRESURE BULKHEAD, EVIDE	NCE OF ARCING FROM FEEDER WIRE TO AC STRUCTURE WAS FOUND. ARCING REMOVED APPROX 0.780 SQUARE INCH OF MATERIAL. PROBLEM A	PPEARED TO BE INCORRECT INSTALLATION OF FEEDER WIRES DURING ORIGINAL AC BUILD. INADEQUATE CLEARANCE BETWEEN WIRING AND S	TRUCTURE. OPPOSITE SIDE WAS INSPECTED AND FOUND WIRING HAD A SAFE CLEARANCE TO STRUCTURE.  (TC NR 20060712003)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006081000013	20060810	00013	EA  	2006	8	10	CA060712004      	2	20060706	G	8530	A4871	RETAINER        			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					NR2 CYL BAFFLE	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) NR 2 AND NR 4 CYLINDER LOWER BAFFLE IB RETAINER BROKE CAUSING BAFFLE CONTACTING  NR 2 CYLINDER`S OIL RETURN LINE T	HUS CHAFED OIL LINE AND OIL SEEPAGE EVIDENT DURING DAILY CHECK.  NR 2 AND NR 4 CYLINDER BAFFLE RETAINER  P/N A4871  (TC 	NR 20060712004)				1	G	7	1 	3O	3	O		H10WE   	E274				 
2006081400059	20060814	00059	EA  	2006	8	14	CA060712005      	2	20060704	G	7200	3031300	ENGINE          			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 3	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA			11936	4012 				86585			(CAN) ABORTED TAKEOFF DUE TO NR 3 ENGINE FAILURE. DURING TAKEOFF ROLL AIRCRAFT REACHED APPROXIMATELY 45 KNOTS WHEN A JOL	T WAS FELT. THE PILOT NOTICED ABNORMAL READINGS ON THE NR 3 ENGINE GAUGES & LARGE AMOUNTS OF SMOKE COMING OUT OF THE NR 	3 ENGINE. EMERGENCY SHUT DOWN INCLUDING ACTIVATION OF NR 3 FIRE BOTTLE. THE AIRCRAFT CAME TO A SUCCESSFUL HALT ON THE RU	NWAY. UPON ARRIVING AT THE SIGHT OF THE INCIDENT & NOTICED OIL HAD BLOWN OUT THROUGH BOTH OF THE OPENINGS FROM THE BLEED	 AIR VALVES. INSPECTION REVEALED THAT THE COMPRESSOR HAD FAILED AND THROWN ONE BLADE. AS THE BLADE EXITED THE COMPRESSOR	 INTAKE IT RUPTURED ONE OF THE OIL TRANSFER TUBES ON THE RIGHT HAND SIDE OF THE ENGINE AND LARGE AMOUNT OF OIL CAME THRO	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006081000014	20060810	00014	CE  	2006	8	10	CA060712006      	1	20060707	G	3246	95442077	WHEEL           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER ONLY ONE TIRE CHANGE AND 9 MONTHS IN SERVICE THE NOSE WHEEL WAS REMOVED AND FOUND EXCESSIVE CORROSION THE BO	LT HOLES AND SURFACE CORROSION ON THE INNER WHEEL HALVES. (TC NR20060712006)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081104		SW  	2008	11	4	CA060712007      	1	20060710	G	6320	212040054007	CASE            			BELL  	212   	212         	1181420	SW  										M/R TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				234  							(CAN)  THE CRACKED SUPPORT CASE AT THE LIFT LINK FITTING. (TC NR 20060712007)						1	G	7	1 	4U				H4SW    					 
2006091300294	20060913	00294	CE  	2006	9	13	CA060712008      	1	20060706	G	5310	504200337	SUPPORT BEAM    			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THE	SE CRACKS WERE FOUND AT (2) OF THE (4) NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 4 OTHER OF OUR AIRCRAFT AROUND THE	 SAME LOCATIONS. THE BEAM WAS REPLACED. (TC NR 20060712008)				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006091300296	20060913	00296	WP  	2006	9	13	CA060712009      	1	20060711	G	6310	NAS4283A12	BOLT            	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH ACTUATOR	BENT            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			36   			3172					(CAN) A/C TAFT 36.5 HOURS.   MAIN BELT TENSION WAS TO BE ADJUSTED, WHEN IT WAS FOUND THAT THE ADJUSTMENT BOLT, ON THE CL	UTCH ACTUATOR, COULD NOT BE MOVED.  THE BOLT IS USUALLY HELD IN PLACE WITH A BACK UP NUT.  THE BACK UP NUT WAS IN PLACE,	 AND MOVED AS NORMAL.  THE HEAD OF THE BOLT, USED TO STOP A MICRO SWITCH, WAS TIGHT UP AGAINST THE FLANGE. VARIOUS ATTEM	PTS WERE MADE TO MOVE THE BOLT, UNTIL FINALLY THE ASSEMBLY WAS REMOVED FROM THE AIRCRAFT WHERE IT COULD BE MOVED, STILL 	WITH SOME DIFFICULTY.  THE BOLT WAS REPLACED WITH A SERVICEABLE PART, AND THE CLUTCH ACTUATOR WAS REINSTALLED.  NO OTHER	 DEFECTS WERE NOTED.  (TC NR 20060712009)	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006081000015	20060810	00015	NE  	2006	8	10	CA060713003      	2	20060703	G	8530	327628	CYLINDER        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	R2800CA3    	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON CLIMB AFTER SCOOP PILOT NOTICED FLICKER IN THE MANIFOLD PRESSURE GAUGE. ANOTHER A/C ADVISED PILOT OF A SMOKE TR	AIL. THE LOAD WAS PITCHED AND THE A/C WAS RETURNING WHEN ANOTHER A/C CONFIRMED THE SMOKE BUT NO FIRE. THE A/C RETURNED T	O BASE AND A CRACKED CYLINDER WAS FOUND AND CHANGED. THE A/C WAS RETURED TO SERVICE. (TC NR 20060713003)				2	H	7	2 	4R	4	R	RT	A14EA   	5E8	6	C	P871	 
2006081100059	20060811	00059	EA  	2006	8	11	CA060713004      	1	20060711	G	2810	21564075	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1384 								(CAN) AC 2032 DEVELOPED A FUEL LEAK IN THE LT WING ON JULY 10/2006.  ALL LT FUEL CELLS WERE REMOVED AND TESTED. CELLS NR	 8 PT NR 215-64075, NR 6 PT NR 215-64002-2, NR 4 PT NR 215-64002-4, NR 3 PT NR 215-64006-6 WERE FOUND TO BE LEAKING UPON	 TESTING. LEAKING CELLS WERE REPLACED. (TC NR 20060713004)				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006081000016	20060810	00016	NE  	2006	8	10	CA060714001      	2	20060705	G	7261	793651	LINE            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENGINE OIL SYS	LOOSE           	W				E				ENGINE SHUTDOWN         				W	K	J	INADEQUATE Q C            	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) CREW OBSERVED LOSS OF OIL QUANTITY NR 1 ENGINE. ENGINE SHUTDOWN PRIOR TO LOW OIL PRESSURE WARNING LIGHT ILLUMINATI	NG. MAINTENANCE DETERMINED UPON THE JUST COMPLETED NR6 OIL BEARING REPLACEMENT THE FORWARD END OF THE PRESSURE TUBE WAS 	NOT SECURED AND LOCK WIRED CAUSING LEAK. LINE SECURED AND LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20060714001)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006081000017	20060810	00017	SW  	2006	8	10	CA060714002      	1	20060605	G	2121	EM6081	BLOWER          			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	CABIN	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA				2624 							(CAN) DURING DESCENT FLIGHT CREW NOTED A STRONG ODOR FROM THE HEATER OUTLETS. CREW SELECTED RECIRCULATION BLOWER SWITCH 	OFF AND LANDED AIRCRAFT. GROUND OPERATION CHECK OF THE ENVIRO SYSTEM FOUND RT RECIRCULATION BLOWER INOPERATIVE. FURTHER 	INSPECTION OF THE BLOWER ASSEMBLY FOUND SIGNS OF MOTOR OVERHEATING AND ROUGHNESS. BLOWER ASSEMBLY REPLACED WITH OVERHAUL	ED ITEM. RECIRCULATION BLOWER NOT IN MAINTENANCE LIMITS SCHEDULE. PART IS ON CONDITION. (TC NR 20060714002)			1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2006081000018	20060810	00018	SW  	2006	8	10	CA060714003      	1	20060704	G	3010	3D249503	TIMER           			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	DEICE SYSTEM	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB FLIGHT CREW NOTED VISUALLYTHAT WING DE-ICER BOOTS WERE INFLATED AND WOULD NOT DEFLATE. FLIGHT CREW SE	LECTED BLEED AIR CLOSED RESULTING IN BOOTS DEFLATING AND RETURNED TO DEPARTURE BASE.  MAINTENANCE FOUND THE DE-ICE TIMER	 TO BE CAUSE OF FAULT. TIMER REPLACED WITH OVERHAULED ITEM AND SYSTEM CHECKED OKAY. (TC 20060714003)				1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2006081000019	20060810	00019		2006	8	10	CA060714007      	4	20060713	G	6113	C35325P	SUPPORT         	HARTZL      		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			392  			AC6880					(CAN) DURING 100 HR INSP REMOVED SPINNER AND FOUND THE INNER SUPPORT CRACKED. (TC NR 20060714007)						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006091300313	20060913	00313	CE  	2006	9	13	CA060716001      	1	20060714	G	5712	07221991	RIB             			CESSNA	185   	185D        	2072812	CE  	CONT  	O470  	IO470F      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3981 	3981 							(CAN) WING CENTER RIBS AT STATION 190.0 IN BOTH WINGS WERE FOUND CRACKED AT THE TRAILING EDGE WERE THEY ATTACH TO THE AU	X REAR SPAR OF THE WING. STN 190.0 IN THE OB AILERON HINGE ATTACH POINT. IT IS SUSPECTED THAT AT SOME TIME THIS AIRCRAFT	 WAS SUBJECTED TO WING GUSTS WITHOUT THE CONTROLS LOCKED.  SEE ATTACHED PHOTO`S OF THE CRACKED RIBS. (TC NR 20060716001)				1	H	7	1 	3O	3	O		3A24    	3E1	5	C	P3EA	 
2006080800088	20060808	00088	NE  	2006	8	8	CA060717001      	2	20060701	G	8530	11876	PUSHROD         			AYRES 	S2    	S2RHGT65    	0970110	SO  	PWA   	R1340 	AWASP       	52016	NE  	HAMSTD	12D	12D40       	NE  	ENGINE	LOOSE           	W				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) THE BALL END ON THE NR 5 EXHAUST VALVE PUSHROD WAS LOOSE. THIS CAUSED THE PUSHROD TO LENGTHEN REMOVING ANY VALVE C	LEARANCE. THIS CAUSED AN OPEN EXHAUST VALVE SITUATION WHICH ALLOWED EXHAUST FLAME TO ENTER THE NR 5 CYLINDER. WHEN THE N	R 5 INTAKE VALVE OPENED THIS ALLOWED THE FLAME TO BURN THE AIR/FUEL MIXTURE THROUGHOUT THE ENTIRE BLOWER AND MANIFOLD CA	USING THE ENGINE TO LOSE POWER AND THEN STOP. (TC NR 20060717001)			1	L	7	1 	3T	3	R	NC	        	ATC14	5	C	P257	 
2006080800090	20060808	00090	CE  	2006	8	8	CA060717002      	1	20060710	G	7820	05501579	HEATER          			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1A170	1A170DM     	GL  	MUFFLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5791 					14566D9A			(CAN) LT MUFFLER CRACKING, BURNING THROUGH. RT MUFFLER CRACKED. STACK CRACKED.  NOTE: CRACKS NOT VISIBLE WITH ATTACHMENT	S (SCROUNDS) ON.  MUFFLER HEATER - LT P/N 0550157-9, RT P/N 0550157-32 (TC NR 20060717002)					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P857	 
2006080900195	20060809	00195	CE  	2006	8	9	CA060717003      	1	20060706	G	7120	075100331	MOUNT           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				44   							(CAN) DURING ROUTINE INSPECTION, IT WAS DISCOVERED THAT THE FWD LT MOUNT PAD WAS CRACKED. THIS ENGINE MOUNT WAS INSTALLE	D 44.8 HRS AGO. REPLACED ENGINE MOUNT WITH SERVICEABLE P/N 075-1003-31, AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 2006071	7003)				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2006092600075	20060926	00075	NM  	2006	9	26	CA060717004      	1	20060714	G	3231	478441	SPRING          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) OPERATOR FOUND SPRING OF ALTERNATE NLG RELEASE BROKEN AT THE LOWER END. NEW SPRING INSTALLED. FLEET INSPECTION SCH	EDULED. (TC NR 20060717004)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006081100060	20060811	00060	EA  	2006	8	11	CA060717005      	1	20060715	G	5610	NP1393229	WINDOW          			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CAPTAIN SIDE FLIGHT DECK WINDOW OUTSIDE PANE SHATTERED ON TAKEOFF. A/C RETURNED. 721377 HAVE INSPECTED THE A/C AND	 FOUND TO BE SAFE FOR FERRY FLIGHT WITH ZERO STOPS IAW THE RESTRICTIONS CONTAINED IN THE ATTACHED FLIGHT PERMIT. CAPT. S	IDE WINDOW REPLACED, WINDOW HEAT AND PRESSURIZATION LEAK CHECKS COMPLETED AND CHECKED SERVICEABLE. (TC NR 20060717005)				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006092600079	20060926	00079	WP  	2006	9	26	CA060717006      	1	20060715	G	6220	369A7010	LOCK            			HUGHES	369   	369A        	4470503	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) PILOT NOTICED FEEDBACK THRU CYCLIC CONTROL FROM MAIN ROTOR HEAD.  HELICOPTER WAS LANDED AT MAIN BASE AND SERVICEAB	LE UNLOCK WAS INSTALLED TSO 00.0 AND TESTED SATISFACTORY.   UNSERVICEABLE UNILOCK WILL BE SENT IN FOR OVERHAUL WITH A TE	ARDOWN REPORT REQUESTED (TC NR 20060717006)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092600135	20060926	00135	EA  	2006	9	26	CA060717007      	1	20060703	G	3320	BAO80061	BALLAST         			DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  					CABINLIGHTS	OVERHEATED      	W				O				OTHER                   				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		IN	INSP/MAINT     	1			CA											(CAN) VP-FBQ (DASH 7, S/NO 111) FLUORESCENT TUBE LAMP HOLDER OVERHEATING PROBLEM  SHORTLY AFTER RE-INSTATING POWER DURIN	G A C CHECK, A STRONG SMELL OF BURNING WAS NOTED IN THE FWD SECTION OF THE AIRCRAFT. THE FAULT WAS TRACED TO A LAMP HOLD	ER AT THE FRONT OF THE CABIN IN THE OVERHEAD LIGHTING SYSTEM. THE LAMP HOLDER HAD SUFFERED SERIOUS OVERHEATING RESULTING	 IN THE MELTING OF THE CONTACTS WITH ASSOCIATED HEAT DAMAGE TO THE INSULATED PORTION OF THE HOLDER. THE FLUORESCENT TUBE	 HAD ALSO SUFFERED DAMAGE TO THE CONTACT PINS. THE FLUORESCENT TUBE HAD NOT BEEN DISTURBED DURING MAINTENANCE THE LIGHTI	NG CIRCUIT BREAKERS HAD NOT TRIPPED. THE BALLAST UNIT PART NR IS BA08006-1. THE AIRCRAFT IS FITTED WITH A MIXTURE OF BA0	2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
2006092600136	20060926	00136	WP  	2006	9	26	CA060717008      	1	20060709	G	5630	369350542	WINDOW          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					DOOR	DETACHED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) HELICOPTER WAS CLIMBING OUT AT 70 KTS WHEN THE RT FWD DOOR WINDOW IMPLODED INTO THE CABIN.  UPON INVESTIGATION IT 	WAS FOUND THE WINDOW INSTALLED REQUIRED A RUBBER GASKET TO HOLD IT IN. THINKING IT WAS A MD WINDOW IT WAS INSTALLED WITH	 THE ORIGINAL FRAME. THE WINDOW THAT USES THE GASKET IS ABOUT .25 SMALLER IN DIAMETER ALLOWING IT TO COME OUT OF THE FRA	ME INTO THE CABIN.  A NEW WINDOW WITH A RUBBER GASKET WAS INSTALLED AND STAYED IN SATISFACTORY. (TC NR 20060717008)			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006092600137	20060926	00137	NM  	2006	9	26	CA060718001      	1	20060714	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	SPLIT           	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR1 EDP FAILED DURING FLIGHT CAUSING NR1 HYDRAULIC SYSTEM DEPLETION. EMERGENCY CHECKLIST PERFORMED. UNEVENTFUL LAN	DING AND A/C STOPPED ON RWY AND LATER TOWED TO PARKING POSITION. PUMP HOUSING FOUND SPLIT. EDP REPLACED. GROUND RUNS AND	 LEAK CHECK CARRIED SERVICEABLE. A/C HAS BEEN RTS. (TC NR 20060718001)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006081100061	20060811	00061	NE  	2006	8	11	CA060718002      	3	20060714	G	6110	C459	THRUST PLATE    	HARTZL      	HCE4N3G     	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			435  			HH278			HH278		(CAN) UPON DISASSEMBLY OF THE PROPELLER, IT WAS FOUND TO HAVE A BROKEN THRUST PLATE SCREW (PN A3204). THE THRUST PLATE S	CREW WAS FOUND JAMMED BETWEEN THE THRUST PLATE AND THE BLADE BUTT. AS A RESULT OF THIS BROKEN SCREW IT ALSO DAMAGED THE 	BETA PICKUP PLATE (PN C459) AND GOUGED THE BETA ROD (PN C453).  THE THRUST PLATE, BETA PICKUP PLATE, BETA ROD, ALL FOUR 	THRUST PLATE SCREWS, ALL SEALS, LUBRICANTS AND HUB NUTS WERE REPLACED, PROPELLER WAS ASSEMBLED, LOCKED AND THE PROPELLER	 RETURNED TO CUSTOMER. (TC NR 20060718002)		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2006121300135	20061213	00135	WP  	2006	12	13	CA060718003      	1	20060717	G	6510	C0411	BEARING RACE    	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TAIL ROTOR	ROUGH           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			36   			1326					(CAN) IT WAS NOTICED THAT THE DAMPER BEARING HAD TURNED ON THE TAIL ROTOR DRIVE SHAFT.  SLIPPAGE MARKS WERE ABOUT .5 INC	H APART.  THE BEARING WAS REMOVED SO IT COULD BE INSPECTED, AND POSSIBLY REINSTALLED.   THE BEARING WAS FOUND TO BE ROUG	H.  IT WAS ALSO NOTED THAT THE GREASE IN THE BEARING WAS A DIFFERENT COLOR THAN THE GREASE IN THE SAME BEARING IN OTHER 	AIRCRAFT, AND PARTS IN STORES.   THE BONDED PLATES WERE THE BEARING SITS WERE MEASURED AND FOUND TO HAVE A TOTAL INDICAT	ED RUNOUT OF .0045 INCH.  MANUFACTURES LIMIT IS .003 INCH.   THE TAIL ROTOR DRIVE SHAFT ASSEMBLY IS TO BE REPLACED WITH 	A NEW UNIT. (TC NR 20060718003)	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006092600140	20060926	00140	EA  	2006	9	26	CA060719001      	2	20060714	G	7322	8198007	METERING UNIT   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1 ENG FUEL	SHEARED         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			6117 								(CAN) DURING CRUISE THE PILOT FELT A YAW-MOMENT AT THE SAME TIME THE TRQ NR 1 WENT TO 0 PERCENT, POWERPLANT MESSAGE APPE	ARED, ENG NR 1 PROP RPM DOWN TO 600 RPM, ENG NO.1 ITT APP. 200 DEGREES C LESS THAN ENG NR 2. PILOT CONTINUED WITH HIS CH	ECK LIST, MANUAL FEATHERED PROP NR 1 AND MANUAL SHUTDOWN THE ENG NR 1. AIRCRAFT LANDED SAFELY WITH SINGLE ENGINE OPS. CD	S FAULT READ OUT PERFORMED AND FOLLOWING CODES ARE STORED: 360, 907, 911, 935. FAULT CODES SUPPLIED SEEM TO INDICATE A F	UEL STARVATION FROM THE FMU. FOUND FMU SHAFT SHEARED.  FMU TO BE REPLACED. (TC NR 20060719001)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006081400060	20060814	00060	EU  	2006	8	14	CA060719002      	1	20060717	G	3233	9693001105	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				153  							(CAN) ORIGINAL MAIN LANDING GEAR ACTUATOR REPLACED WITH AN OVERHAULED UNIT.  (ORIGINAL ACTUATOR HAD AN INTERNAL LEAK) HY	DRAULIC SYSTEM FLUSHED BEFORE OVERHAULED ACTUATOR WAS INSTALLED. INTERNAL LEAK DEVELOPED IN TSO 153.3. HYDRAULIC SYSTEM 	FLUSHED AGAIN AND A REPAIRED ACTUATOR INSTALLED. NO CONTAMINATION NOTED IN FLUID AFTER EACH SYSTEM FLUSH.  HYDRAULIC SYS	TEM LEAK CHECKED SERVICEABLE (TC NR 20060719002)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006081400061	20060814	00061	CE  	2006	8	14	CA060719003      	1	20060718	G	2710	7020362	POTENTIOMETER   			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7418 								(CAN) VISUAL INSPECTION CARRIED OUT ON ELEVATOR FDR SYSTEM DUE TO A FAILURE OF THE FDR CORRELATION FLIGHT TEST. FLIGHT T	EST RECORDER SHOWED ELAVATOR SYSTEM NO RESPONSE TO SIGNAL. VISUAL INSPECTION REVEALED FAILED POTENTIOMETER SHAFT. REPLAC	ED WITH NEW PART IAW MM. FLIGHT TEST TO BE CONDUCTED (TC NR 20060719003)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006092600148	20060926	00148	EU  	2006	9	26	CA060719005      	1	20060719	G	3246	300720	WHEEL           			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING TOWING OF AIRCRAFT THE PIC AND GROUND HANDLERS NOTICED A WOBBLE ON THE RH MLG. MAINTENANCE WAS CONTACTED AN	D IT WAS DISCOVERED THAT A 10" PIECE OF THE EDGE OF THE INNER WHEEL RIM WAS MISSING. THE TIRE STILL REMAINED INFLATED. T	HE WHEEL AND TIRE WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. THE IMMEDIATE ADJACENT AREA WAS INSPECTED FOR SECOND	ARY DAMAGE, NONE OBSERVED.   (TC# 20060719005)			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2006081400062	20060814	00062	SO  	2006	8	14	CA060720001      	1	20060621	G	5524	4A314003	ATTACH BRACKET  			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 ROUTINE MAINTENANCE 2 CRACKS WERE DISCOVERED ON THE RT OB ELEVATOR HINGE ATTACH BRACKET. THE CRACKS WERE LO	CATED ON THE LOWER FORWARD PORTION OF THE BRACKET IN THE MOST FORWARD PORTION OF A 90 DEGREE BEND AND WERE APPROX .7500 	OF AN INCH IN LENGTH EACH. THE BRACKET WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060720001)				1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006092600149	20060926	00149	SO  	2006	9	26	CA060720002      	1	20060720	G	5411	4A27122201	CHANNEL         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT MAINTENANCE IN THE RT LANDING GEAR AREA, A CRACK WAS FOUND IN THE IB LOWER NACELLE CHANNEL. THI	S NACELLE CHANNEL IS THE ATTACH POINT FOR THE INBOARD  GEAR DOOR HINGE. THE CRACK WAS LOCATED IN AFT PORTION OF THE HING	E ATTACH AREA MEASURING APPROXIMATELY 3.5 INCHES IN LENGTH. THE CRACK WAS DIFFICULT TO SPOT DUE TO THE OBSTRUCTION CAUSE	 BY THE GEAR DOOR HINGE WHEN IT IS INSTALLED. THE NACELLE CHANNEL HAS BEEN REPLACED. (TC NR 20060720002)			1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006092600152	20060926	00152	NM  	2006	9	26	CA060723001      	1	20060717	G	5311	654653120	FRAME           			BOEING	737   	737400      	138449A	NM  										BS 500B S28R-25L	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FWD CARGO PIT FRAME TO SKIN AT BS 500B CORRODED BETWEEN STR 28R AND 28L (TC NR 20060723001).						2	L	7	2 	4F			RT	A16WE   					 
2006092600153	20060926	00153	NM  	2006	9	26	CA060723002      	1	20060717	G	5311	654653170	FRAME           			BOEING	737   	737400      	138449A	NM  										BS 500C S27-28R	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FWD CARGO PIT FRAME TO SKIN AT BS500C CORRODED STR 27R TO 28R (TC NR 20060723002).						2	L	7	2 	4F			RT	A16WE   					 
2006092600156	20060926	00156	NM  	2006	9	26	CA060723003      	1	20060717	G	5311	654653170	FRAME           			BOEING	737   	737400      	138449A	NM  										BS 500C S28R-28L	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FWD CARGO PIT FRAME CORRODED AT BS 500C AND STR 28R TO 28L (TC NR 20060723003)						2	L	7	2 	4F			RT	A16WE   					 
2006092600157	20060926	00157	NM  	2006	9	26	CA060723004      	1	20060717	G	5311	6546534	FRAME           			BOEING	737   	737400      	138449A	NM  										BS 520 S27-28R	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKIN TO FRAME ATTACH ANGLE CORRODED NR BS 520, STR 27R TO 28R (TC NR20060723004)						2	L	7	2 	4F			RT	A16WE   					 
2006092600160	20060926	00160	NM  	2006	9	26	CA060724001      	1	20060713	G	2740	MS28775232	O-RING          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					STABILIZER	SWOLLEN         	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			15409	15409							(CAN) ON DESCENT STABILIZER OUT OF TRIM LIGHT ILLUMINATED, STABILIZER WOULD NOT RESPOND TO COMMANDS FROM AUTOPILOT, MAIN	 ELECTRIC TRIM OR MANUAL TRIM. FLIGHT CREW ACCOMPLISHED THE STABILIZER JAM EMERGENCY CHECK LIST AND LANDED UNEVENTFULLY.	 UPON INSPECT MAINTENANCE FOUND WATER INGRESSION IN THE GEAR BOX AND BRAKE ASSEMBLY DUE TO DAMAGED O-RINGS. STABILIZER G	EAR BOX ASSEMBLY REPLACED IN ACCORDANCE WITH AMM 27-40-41. CONTRIBUTING FACTOR - EXCESSIVE RAIN EXPERIENCED DURING THE G	ROUND LAYOVER. (TC NR 20060724001)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006092600162	20060926	00162	NM  	2006	9	26	CA060724002      	1	20060713	G	7810	C5P156171	FLANGE          			DHAV  	DHC5  	DHC5A       	2803018	NM  										EXHAUST SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLANGE HEIGHT IS 0.25 INCH INSTEAD OF 0.36 INCH.  THIS COULD LEAD TO JET PIPE FAILURE, WHICH IN TURN, COULD LEAD T	O DAMAGE IN THE INTEGRITY OF THE WINGS AND SYSTEMS NEARBY.  CUSTOMERS ARE BEING NOTIFIED OF THIS NON-CONFORMANCE.  NOTE(	08AUG06): ONLY MILITARY CUSTOMERS WERE AFFECTED. CAUSE: FLANGE HEIGHT DIMENSION WAS OVERLOOKED BY OPERATOR AND INSPECTOR	. SPECIFIED FLANGE HEIGHT REQUIREMENT WILL BE FORMALLY STRESSED TO APPLICABLE OPERATORS AND INSPECTORS (DUE DATE: AUG/06	). (TC NR 20060724002)		2	H	7	2 	4T			RT	        					 
2006081400063	20060814	00063	NE  	2006	8	14	CA060724003      	2	20060715	G	7240	311583501	BURNER CAN      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			4515 	4    				PR0176			(CAN) BRIGHT FLASHES COMING FROM EXHAUST STACKS, NO CHANGE TO INDICATIONS. 15 FLASHES IN 2 HOUR PERIOD.  ENGINE OUTER BU	RNER CAN FOUND INOPERATIVE, CERAMIC COATING FLAKING OFF AND IGNITING. REPLACED WITH OVERHAULED UNIT. GROUND RUN AND RELE	ASED SERVICEABLE. P/N - ON/OFF 3115835-01 S/N OFF A0006973, S/N ON 2K962. (TC NR 20060724003)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006081400064	20060814	00064	EU  	2006	8	14	CA060724004      	1	20060717	G	7712	32448821	LIMITER         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			4516 	11   				PR0175			(CAN) PILOT SNAG: ENGINE POWER LOST IN FLIGHT HAD TO USE MANUAL OVERRIDE.  RECTIFICATION: REPLACED TORQUE LIMITER P/N 32	44882-1, S/N C50254 WITH REMOVED SERVICEABLE UNIT FROM ENGINE S/N PR0116 P/N 3244882-1 S/N C50621. ALL APPLICABLE ENGINE	 RUNS COMPLETED AND CHECKS SERVICEABLE. (TC NR 20060724004)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007051600162	20070516	00162		2007	5	16	CA060724006      	4	20060720	G	6113	05503214	BULKHEAD        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PROP SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			250  								(CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RA	DIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724006)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007051600163	20070516	00163		2007	5	16	CA060724007      	4	20060721	G	6113	05503214	BULKHEAD        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			750  								(CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RA	DIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724007)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006092600163	20060926	00163		2006	9	26	CA060725001      	4	20060722	G	3444	9650976003206	SWITCH          	HONEYWELL   		AIRBUS	A340  	A340313     	       	EU  	GE    	CFM56 	CFM565A     	13802	NE  					GPWS	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WHILE ENROUTE, ON A POLAR ROUTE IN THE MIDDLE OF HUDSON BAY, THE FLIGHT CREW REPORTED ACRID SMOKE COMING OUT OF OV	ERHEAD PANEL IN THE AREA OF THE TERRAIN SWITCH AND THE FAILURE OF THE GPWS.  THE SMOKE THEN DISSIPATED.  THE CREW DECLAR	ED A PAN PAN (URGENCY), AND RETURNED TO YYZ, WHERE THE FLIGHT LANDED 30,000 KG OVERWEIGHT. (TC NR 20060725001)				2	L	7	4 	4F	4	F	RT	A197    	E29NE				 
2006081400065	20060814	00065	NE  	2006	8	14	CA060725002      	2	20060721	G	7321	7436024	FUEL CONTROL    			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								708828			(CAN) ENROUTE THE CREW ELECTED TO RETURN TO POINT OF DEPARTURE DUE TO A SUSPECTED ENGINE VIBRATION. AFTER ARRIVING, THE 	MAINTENANCE PERSONNEL INITIALLY REPLACED THE FORWARD ENGINE MOUNT ISOLATORS WITH NO APPARENT REMEDY OF THE PROBLEM. THE 	FCU WAS REPLACED AND THE ENGINE RUN UP WITH NO FURTHER VIBRATION INDICATION.THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO	 FURTHER PROBLEMS. (TC NR 20060725002)			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006092600165	20060926	00165	CE  	2006	9	26	CA060725004      	1	20060720	G	2612	24412886	FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FIRE DETECTION	UNKNOWN         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE CREW RECEIVED A RT ENGINE FIRE ANNUCIATION. ALTHOUGH IT WAS DETERMINED THAT NO FIRE WAS P	RESENT, PROCEDURES WERE FOLLOWED TO SHUTDOWN AND SECURE THE ENGINE IN FLIGHT AND THE DISCHARGE OF THE FIRE EXTINGUISHING	 AGENT.  MAINTENANCE FOUND THAT EITHER THE FORWARD OR AFT FIRE WIRE LOOP CAUSED THE ANNUNCIATION ALTHOUGH IT COULD NOT B	E DETERMINED AS TO WHICH ONE AS THE FAULT MODE WAS NOT HARD AND THE SYSTEM RETURNED TO NORMAL OPS. BOTH LOOPS WERE REPLA	CED AS A PRECAUTION WITH NO REPEAT OF THE OCCURRENCE. IT IS ALSO POSSIBLE THAT THE FORWARD LOOP MAY HAVE BEEN TOO CLOSE 	TO THE STACK AND CAUSED THE FALSE WARNING AS WELL. (TC NR 20060725004)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007051600164	20070516	00164	NE  	2007	5	16	CA060725005      	2	20060723	G	7200		ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  						MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			4111 	1120 				9359			(CAN) ON APPROACH, THE ENGINE CHIP LIGHT ILLUMINATED. THE PILOT LANDED THE HELICOPTER NORMALLY. THE ENGINE CHIP PLUGS WE	RE ALL REMOVED AND DEBRIS (METAL) WAS FOUND ON ALL PLUGS. METAL WAS ALSO FOUND ENTRAPPED IN THE OIL FILTER. THIS ENGINE 	WAS LAST SHOPPED IN MAY 2005 FOR MO2, MO4, MO5 AND FREEWHEEL OVERHAUL. THE TSO OF THE OVERHAULED COMPONENTS IS 295.9 HOU	RS (TC NR 20060725005)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006081400098	20060814	00098	GL  	2006	8	14	CA060725006      	2	20060724	G	7323	23076061	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						INOPERATIVE     	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				372  							(CAN)  UNIT HAD ABOUT 25.0 HOURS THIS INSTALL. PILOT REPORTED THAT GOVERNOR WOULD BLEED OFF IN FLIGHT BY 4 TO 5 PERCENT 	THEN COME BACK TO NORMAL AFTER A FEW SECOND 10 TO 15 SECONDS. THEN IT WOULD BE FINE FOR SOME TIME. UPON REPORTING THIS T	HE AIRCRAFT WAS REMOVED FROM SERVICE AND A NEW GOVERNOR WAS INSTALLED. (TC NR 20060725006)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006092600169	20060926	00169	WP  	2006	9	26	CA060725007      	1	20060725	G	7820	C16932	MUFFLER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			398  								(CAN) DURING A ROUTINE 100 HR INSPECTION, IT WAS NOTED THAT THE MUFFLER/TAILPIPE ASSY WAS DISTORTED AND CRACKED AT THE O	UTLET PIPE. THE CRACK WAS NOTICED AFTER THE CABIN HEATER JACKET WAS REMOVED. THE CRACK WOULD NOT BE NOTICEABLE WITH THE 	CABIN HEATER JACKET INSTALLED. THE CABIN CARBON MONOXIDE DETECTOR SYSTEM SHOWED NO INDICATIONS OF EXCESSIVE CARBON MONOX	IDE. IT IS NOTED THAT IF THE AIRCRAFT WAS FLYING IN COLD CONDITIONS, WHERE THE CABIN HEAT WOULD BE SELECTED (TC NR 20060	725007)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006092600171	20060926	00171	WP  	2006	9	26	CA060725009      	1	20060720	G	2120	D0571	AIR BOX         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					OUTER HOUSING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			398  								(CAN) DURING A ROUTINE 100 HR INSPECTION, A CRACK WAS NOTICED IN THE ABOVE PART. THERE IS A CHANCE THAT THE CRACK COULD 	BE THE RESULT OF CLEARANCE ISSUES WHEN REMOVING AND INSTALLING THE AIRBOX FROM THE AIRFRAME. THE PART WAS REPLACED WITH 	A NEW PART, AND IT WAS NOTED THAT THE NEW PART IS NOW MADE FROM FIBERGLASS, WHERE THE ORIGINAL PART IS MADE FROM A PLAST	IC MATERIAL. THIS COULD ALSO BE ANOTHER REASON FOR THE CRACK, OR AN ATTRIBUTE. THE PART HAS 398.6 HRS SINCE NEW. THE AIR	CRAFT WAS MANUFACTURED NEW IN OCTOBER 2005. (TC NR 20060725009)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006092600172	20060926	00172	EA  	2006	9	26	CA060725010      	2	20060723	G	8530	416453	PUSHROD         			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	ENGINE	BROKEN          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				500  							(CAN) PUSHROD BROKE AT TOP BALLEND AT ROCKER ARM ON NR 1 CYLINDER EXHAUST VALVE. PUSH ROD REPLACED AND ENGINE GROUND RUN	, CHECKED OK. AIRCRAFT TEST FLOWN AND FOUND SATISFACTORY (TC NR 20060725010).					2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2006081400124	20060814	00124	NE  	2006	8	14	CA060726001      	2	20060720	G	7421	955075400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			515  					4396			(CAN) INSULATION WITHIN IGNITOR FOUND LOSE.  IN LIGHT OF PAST INCIDENCE OF ENGINE FOD, IGNITORS WERE CHANGED.  IGNITOR P	/N 955075400/CH34745 (TC NR 20060726001)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006081400109	20060814	00109	NE  	2006	8	14	CA060726002      	2	20060711	G	7250	2292253850	TURBINE BLADES  			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					1ST STAGE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			254  	254  							(CAN) THE PILOT SHUTDOWN THE AIRCRAFT TO HOOK UP HIS WATER BUCKET, AFTER A SHORT TIME PERIOD OF APPROXIMATE 8 TO 10 MINU	TES HE ATTEMPTED TO RESTART THE AIRCRAFT. THE STARTER WOULD NOT TURN THE ENGINE, A BORESCOPE WAS USED TO LOOK INSIDE THE	 ENGINE AND FOUND THAT THE 1ST STAGE TURBINE BLADE HAD RUBBED. THE M03 WAS THEN REPLACED AND THE AIRCRAFT RETURNED TO SE	RVICE. (TC NR 20060726002)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006092600174	20060926	00174	EU  	2006	9	26	CA060726003      	1	20060725	G	6310	35013001	FREEWHEEL UNIT  			SNIAS 	350   	AS350*      	       	EU  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5074 	61   							(CAN) AFTER INSTALLING A OVERHAULED FREEWHEEL, METAL WAS FOUND FOUR SEPARATE TIME IN 61.1 HOURS, SILVER FLAKES FOUND ON 	CHIP PLUG. (TC NR 20060726003)					1	G	7	1 	3U	3	U		H9EU    	E1GL				 
2006092600177	20060926	00177	NM  	2006	9	26	CA060726004      	1	20060726	G	2710	82742409001	CONTROL UNIT    			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AILERONS	WORN            	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA			1350 								(CAN) RT AILERON CABLES PN: 82742409-001 ( WS Y14.25-Y232.00) AND CABLE PN: 82742410-001 (WS Y14.25-Y258.00) WERE APPROA	CHING PERMISSIBLE WEAR LIMITS AT PULLEY CONTACT AREAS.  CABLES REPLACED  THIS PROBLEM IS ALREADY KNOWN BY MFG REF TO ALL	 OPERATOR MESSAGE NR AOM 122 AND SB 84-27-26.   INSPECTED THE A/C IN APRIL 2004 FOLLOWING RECEPTION OF AOM122 AND AILERO	N CABLES REPLACED DUE FOUND WORN.  WE ALSO REINSPECTED THE A/C IN MAY 2005 FOLLOWING RECEPTION OF THE S/B 84-27-26 AND A	ILERON CONTROL CABLES REPLACED AGAIN DUE STILL FOUND WORN.  IN JULY 2006 DURING A FLAP INSPECTION OUR AME (KNOWING THE A	ILERON CONTROL CABLE PROBLEMS) WIPE THE AILERON CABLES WITH A RAG TO FOUND THAT SOME WIRES WERE BROKEN.  THESE CABLES MU	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006080800091	20060808	00091	EA  	2006	8	8	CA060726005      	2	20060724	G	7261	ES48110	OIL FILTER      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL103161			(CAN) DURING POST RUN UP INSPECTION OF REGULAR INSPECTION APPROXIMATE ONE FLUID OZ OF OIL WAS NOTED LEAKING FROM THE NEW	LY INSTALLED OIL FILTER. IT IS SUSPECTED THAT A SIMILAR DEFECT BUT OF LESSER DEGREE MAY NOT BE PICKUP BY POST RUN UP INS	PECTION AND MAY CAUSE A FINE OIL MIST ON HOT TURBO CHARGER AND EXHAUST PARTS ON THIS AND SIMILAR ENGINE INSTALLATIONS. (	TC NR  20060726005)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2006080800092	20060808	00092	CE  	2006	8	8	CA060726006      	1	20060726	G	8011	EBB124A	DRIVE ASSY      	PRESTOLITE  		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	STARTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1102 		E042509					(CAN) PILOT TRIED TO START ENGINE BUT THE STARTER WOULD NOT ENGAGE. AIRCRAFT BROUGHT INTO HANGER AND STARTER WAS REMOVED	 FROM ENGINE. IT WAS DISCOVERED THAT THE TEETH ON THE BENDIX DRIVE THAT ENGAGE THE RING GEAR HAD SHEARED OFF. (TC NR 200	60726006)				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2006092600179	20060926	00179	CE  	2006	9	26	CA060726007      	1	20060724	G	2435	230760011	BRUSHES         	LEARSIEGLER 		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				3    		2004					(CAN) DURING BASE INSPECTION, LT ENGINE COWL WAS COVERED WITH BLACK DUST. UPON FURTHER INSPECTION THE STARTER/GEN WAS RE	MOVED AND THE BRUSHES INSPECTED TO BE WORN OVER HALF LIFE. STARTER/GEN HAD ONLY 2.7 HRS SINCE OVERHAUL. STARTER/GEN SENT	 FOR WARRANTY AND TEARDOWN REPORT. (TC NR 20060726007)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006092600181	20060926	00181	SW  	2006	9	26	CA060727001      	1	20060727	G	6220	204011116001	NUT             	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					M/R HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						ADA50015					(CAN) THIS IS AN ON CONDITION ITEM. SO HISTORY MAY NOT BE ACCURATE. M/R HUB ASSY HAS 18437.6 TIME SINCE NEW.  M/R HEAD A	SSY WAS IN FOR O/H AND REQUIRES  ACORN NUTS TO BE NDT. THIS ONE WAS FOUND CRACKED. (TC  NR 20060727001)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006092600183	20060926	00183	SW  	2006	9	26	CA060728001      	1	20060711	G	2910	206076437003	CHECK VALVE     			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYD SYS 2	JAMMED          	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) UPON FIRST GROUND RUN OF M412 DURING MANUFACTURING FTP`S (WITHOUT M/R BLADES INSTALLED), A NOISE (BANG) WAS HEARD 	TWICE AND HYDR PRESSURE RAISED TO +1300 PSI ON THE GAGE. PILOT SHUTDOWN THE HYDR SYSTEM AND ABORTED GROUND RUN FOR INVES	TIGATION.  FURTHER INVESTIGATION REVEALED THAT A SWIRL OF COPPER METAL (CHIPS) JAMMED THE HYDRAULIC CHECK VALVE IN AN OP	EN POSITION WHICH ALLOWED REVERSED FLOW AND AN HYDR LOCK BY PRESSURIZING THE PUMP CASE DRAIN, FOLLOWED BY A TEMPERATURE 	RISE. HYDRAULIC COMPONENTS REPLACED AND AIRCRAFT RETURNED TO SERVICE. FURTHER LAB TESTING WERE ABLE TO REPRODUCE THE PRO	BLEM AND TEMPERATURE WAS TWICE THE NORMAL RANGE WITHIN 4 MIN. OF OPERATION. THE SOURCE OF THE DEBRIS WAS NOT FOUND COULD	1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2006092600186	20060926	00186	NM  	2006	9	26	CA060728002      	1	20060725	G	5270		SWITCH          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					CARGO DOOR	OUT OF RIG      	W				J	A			DUMP FUEL               	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THROUGH FL210 AND 6.0 PSID CABIN DIFFERENTIAL THE CARGO DOOR UNSAFE LIGHT INDICATION ILLUMINATED. AIR	CRAFT DUMPED FUEL AND RETURNED TO STATION, DURING APPROACH THE CARGO DOOR UNSAFE LIGHT EXTINGUISHED. UPON INSPECTION MAI	NTENANCE FOUND DOOR CLOSE MICRO SWITCH OUT OF RIG. SWITCH ADJUSTED IAW AEI MM CHAPTER 24 PAGE 26. CONTRIBUTING FACTORS: 	PRIOR TO DEPARTURE THE AIRCRAFT WAS UNDERGOING THE INCORPERATION OF SB AEI 04-02 REV 1R. CLARIFICATION OF RIGGING PROCED	URES WAS REQUESTED FROM AEI. (TC NR 20060728002)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006092600187	20060926	00187	SW  	2006	9	26	CA060728003      	1	20060714	G	6510	2040406009	BEARING         	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL ROTOR DRIVE	FAILED          	W				C				ABORTED TAKEOFF         				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		TO	TAKEOFF        	1			CA						A2079238					(CAN) THE TAIL ROTOR DRIVESHAFT HANGER HAD BEEN INSTALLED THE NIGHT BEFORE THE FAILURE. WE SUSPECT AN INNER COUPLING FAI	LURE. THE SUSPECT COUPLING HAD BEEN RECOATED JUST BEFORE INSTALLATION BY USING AN AMS2451/4 PROCESS. (TC NR 20060728003)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006080800095	20060808	00095	NE  	2006	8	8	CA060728004      	2	20060727	G	7230		FAN BLADE       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	DISAPPEARED     	W				E	F	A		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA			10896					873549			(CAN) DURING CLIMB OUT AT 18,000FT, THE COCKPIT CREW HEARD A LOUD BANG, FOLLOWED BY HIGH VIBES ON THE NR 1 ENGINE. FIRE 	WARNING CAME UP, PILOT DISCHARGED THE FIRE BOTTLES AND SHUTDOWN THE ENGINE. EMERGENCY WAS DECLARED AND AIRCRAFT RETURNED	 TO BARCELONA, WHERE IT PERFORMED AN UNEVENTFULL SINGLE-ENGINE LANDING. INITIAL REPORT SAYS ONE FAN BLADES DISAPPEARED, 	JET PIPE IS BURNED AND CRACKED.  FURTHER INFORMATION WILL BE PROVIDED ONCE THE ENGINE STRIP REPORT IS AVAIALBLE. (TC NR 	20060728004)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006092600188	20060926	00188		2006	9	26	CA060728005      	4	20060721	G	2312	8992125014	CONTROL PANEL   			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					VHF	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			24101	24101		4520					(CAN) DURING FLIGHT, LIGHT SMOKE CAME FROM THE NR 1 VHF CONTROL PANEL. THE CIRCUIT BREAKER WAS PULLED AND THE FLIGHT PRO	CEEDED WITHOUT ANY FURTHER PROBLEM. THE PANEL WAS REPLACED AT THE ARRIVAL STATION AND WAS SYSTEM CHECKED SERVICEABLE. PA	NEL WAS ROUTED TO THE VENDOR FOR INVESTIGATION.  (TC NR 20060728005)				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006080800096	20060808	00096	NE  	2006	8	8	CA060728006      	2	20060722	G	7261		ENGINE          			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	OIL CONSUMPTION 	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAD TO SHUTDOWN THE RT ENGINE DURING FLIGHT, DUE TO LOW OIL PRESSURE. APPROX 3 HOURS INTO THE FLIGHT, THE	 PILOT REPORTED THE OIL PRESSURE WAS FLUCUTATING BETWEEN 45 AND 65 PSI, THEN DROPPED AGAIN TO 35 AND 55 PSI, AND FINALLY	 GOT A STEADY LOW OIL PRESSURE LIGHT. THIS IS WHEN THE PILOT SHUTDOWN THE RT ENGINE, AND DIVERTED.  AN INSPECTION REVEAL	ED THE RT ENGINE WAS 4 QTS LOW ON OIL. THE PILOTS HAD ALREADY SERVICED THIS ENGINE WITH 2 QTS, PRIOR TO  LEAVING.  APPEA	RS THE AIRCRAFT USED 4 QTS OF OIL IN THAT 3 HOUR PERIOD. AN OIL CONSUMPTION CHECK WAS PERFORMED,  AND WAS FOUND TO BE WI	THIN LIMITS. THE AIRCRAFT IS UNDERGOING FURTHER TROUBLESHOOTING. (TC NR 20060728006)	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006080800097	20060808	00097	WP  	2006	8	8	CA060728007      	2	20060727	G	7200		ENGINE          			DHAV  	DHC3  	DHC3        	2800202	EA  	GARRTT	TPE331	TPE33110R   	0517	WP  	HARTZL	HCB4T	HCB4TN5     	GL  		VIBRATES        	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) DURING DESCENT FOR FLOAT LANDING ON WATER,  PILOT NOTICED VIBRATION IN ENGINE . ENGINE SHUTDOWN, PROP FEATHERED. A	IRCRAFT LANDED WITHOUT INCIDENT. ENGINE REMOVED SENT TO REPAIR FACILITY. (TC NR 20060728007)					1	H	7	1 	3R	4	T		A815    	E4WE	6	C	P40EA	 
2006080800098	20060808	00098	EA  	2006	8	8	CA060729001      	1	20060724	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			8565 								(CAN) DESENDING THROUGH 13000 FT - F/O SIDE WINDOW CRACKED. TAXING TO GATE WINDOW (F/O SIDE WINDOW) CRACKED MORE. WINDOW	 WAS REPLACED IAW AMM. SIDE WINDOW IS PRE SB NP139322-001 (TC NR 20060729001)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006080800099	20060808	00099	CE  	2006	8	8	CA060731001      	1	20060727	G	2720	656530129	GUARD           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RUDDER CONTROL	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7217 								(CAN) WHEN MOVING THE RUDDER WITH HAND PRESSURE OF APPROXIMATELY 10 DEGREES EITHER SIDE OF CENTER A NOISE ALONG WITH A R	OUGH SNAGGING FEEL NOTICED.  TRACING THE NOISE DOWN THROUGH THE TAIL INTO THE CABIN BETWEEN FLIGHT STATION 166 TO 180.  	THE CABLE GUARD PN 6565301-29 FOUND TO BE DISPLACED FORWARD OUT OF REAR CLAMP AND CABLE END CONTACTING THE END OF THE CA	BLE GUARD.  THE CABLE GUARD WAS REMOVED AND INSPECTED, FOUND INNER LAMINATE OF THE PHENOLIC DELAMINATED WITH WHAT LOOKED	 LIKE A CONTACT POINT FROM CONTACT WITH THE CABLE END OR TURN BARREL NEAR THE FWD END AND THE GUARD WAS DAMAGED ON THE A	FT END FROM CONTACT WITH THE CABLE END. (TC NR 20060731001)	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006092600191	20060926	00191	EA  	2006	9	26	CA060731002      	2	20060713	G	7210	310152501	PLANETARY GEAR  			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				184  				PCE41483			(CAN) METAL CONTAMINATION WAS FOUND ON THE CHIP DETECTOR.  METAL ORIGINATED FROM RGB AND WAS THE RESULT OF SIGNIFICANT M	ATERIAL LOSS BETWEEN THE 1ST STAGE SUN GEAR AND THE 1ST STAGE PLANETARY GEARS. THIS IS OUR 2ND SUCH CASE WITH TIME CONTI	NUED GEARS. (TC NR 20060731002)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2006080800100	20060808	00100	EA  	2006	8	8	CA060731003      	2	20060728	G	8520	13828	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				517  				L57468A			(CAN) DURING A ROUTINE INSPECTION AN AME VISUALLY DISCOVERED A CRACK 2-3 INCHES IN LENGTH. THE CRACK IS LOCATED BETWEEN 	CYLINDERS 3 AND 5 IN THE VICINITY OF THE LOWER RIB. PREVIOUSLY NO DISCREPANCIES HAD BEEN NOTED. THE ENGINE WAS SUBSEQUEN	TLY REMOVED FOR REPAIR AT AN APPROVED ENGINE OVERHAUL SHOP. THE TTSN FOR THIS CASE COULD NOT BE OBTAINED. THIS CASE WAS 	INSTALLED 516.8 HRS EARLIER BECAUSE OF ANOTHER INCIDENT OF CRACKED CASE.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006092600195	20060926	00195	CE  	2006	9	26	CA060731005      	1	20060728	G	7714	991214736	INDICATOR       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					N2 SPEED	SHORTED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING OF A POSSIBLE N2 OVERSPEED OF BOTH ENGINES, THE N2 GAGE WAS TESTED BY SIMULATING SPEEDS WIT	H VOLTAGE AT SEVERAL FREQUENCIES. WHEN VALUES WERE BROUGHT AT LEVELS TO ILLUMINATE THE RED OVERSPEED WARNING LIGHT, IT W	AS NOTED THAT THE INDICATION WAS CROSSED MEANING THAT FOR A READING OF 96 PERCNET N2 AND ABOVE ON LT ENGINE THE RT WARNI	NG LIGHT IN THE GAGE ILLUMINATES.  THE REVERSE CONDITION HAPPENS WHEN THE RT ENGINE INDICATION IS TESTED (N2 READING), M	EANING THAT THE LT INDICATION (RED WARNING LIGHT) ILLUMINATES. THE SUSPECT GAUGE WAS REPLACED AND THE SYSTEM GROUND CHEC	KED SERVICEABLE. (TC NR 20060731005)	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006081400110	20060814	00110	NE  	2006	8	14	CA060731006      	2	20060628	G	7320	3031829	LINE            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	P3 AIR TUBE	FRACTURED       	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE ENGINE WAS REPORTED TO FLAME OUT DURING APPROACH RESULTING IN THE AIRCRAFT LANDING SHORT OF THE RUNWAY.  SUBSE	QUENT INSPECTION REVEALED A FRACTURED P3 PNEUMATIC LINE TO THE FUEL CONTROL.  MFG WILL MONITOR INVESTIGATION AND ADVISE 	OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731006)				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2006081400112	20060814	00112	EA  	2006	8	14	CA060731007      	2	20060629	G	7261		OIL SYSTEM      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA								41601			(CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE FOLLOWED BY A LOSS IN OIL PRESSURE. THE ENGINE WAS SHU	TDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED INTERNAL OIL LEAKAGE.  	MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731007)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006081400113	20060814	00113	NE  	2006	8	14	CA060731008      	2	20060705	G	7321		FUEL CONTROL    			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE ENGINE WAS REPORTED TO FLAME OUT ON APPROACH.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.  MFG WILL INVE	STIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731008)					1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2006081400114	20060814	00114	NE  	2006	8	14	CA060731009      	2	20060704	G	7250		TURBINE BLADES  			AYRES 	S2T   	STRT34      	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  					ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PH0243			(CAN) THE ENGINE WAS REPORTED TO LOSE ALL POWER IN CRUISE. A DEAD-STICK LANDING WAS PERFORMED IN A  FIELD RESULTING IN A	IRFRAME DAMAGE.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL INVESTIGATE AND ADVISE OF ROOT	 CAUSE ONCE DETERMINED. (TC NR 20060731009)				1	L	7	1 	3T	4	T		A3SW    	E4EA				 
2006081400066	20060814	00066	EA  	2006	8	14	CA060731010      	2	20060705	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						MAKING METAL    	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) THE ENGINE WAS REPORTED TO LOSE POWER IN HOVER ACCOMPANIED BY A CHIP DETECTOR INDICATION.  SUBSEQUENT INSPECTION R	EVEALLED LOSS OF DRIVE TO THE ACCESSORY GEARBOX.  MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINE	D. (TC NR 20060731010)				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2006081400067	20060814	00067	EA  	2006	8	14	CA060731011      	2	20060704	G	7200		ENGINE          			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  		MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA								86312			(CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE AND SMOKE WAS SEEN EMERGING FROM THE EXHAUST.  TAKEOFF WAS ABORTED	 AND THE ENGINE SECURED. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC 	NR 20060731011)				2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006080900196	20060809	00196	NE  	2006	8	9	CA060731012      	2	20060710	G	7230		DIFFUSER        			AEROSP	ATR72 	ATR72212A   	8680902	EU  	PWA   	PW120 	PW127       	 	NE  					LOW COMPRESSOR	FRACTURED       	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL, ENGINE TEMPERATURE WAS SEEN EXCEEDING LIMITS AND THE TAKE-OFF WAS ABORTED.  SUBSEQUENT INSPEC	TION REVEALED A FRACTURED LOW PRESSURE DIFFUSER TUBE.  THE TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC N	R 20060731012)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006080900197	20060809	00197	EA  	2006	8	9	CA060731013      	2	20060712	G	7230		COMPRESSOR      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	SEIZED          	W				E				ENGINE SHUTDOWN         				B	X	J	SMOKE/FUMES/ODORS/SPARKS  	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING FLIGHT AN OIL SMELL WAS REPORTED IN THE COCKPIT.  THE ENGINE SUBSEQUENTLY SURGED ACCOMPANIED BY A LOW OIL P	RESSURE WARNING AND WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE AND A PARTIALLY SEIZED HIGH PRES	SURE COMPRESSOR.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731013)				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006080900198	20060809	00198	EA  	2006	8	9	CA060731014      	2	20060714	G	7320	312241908	METERING UNIT   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE AIRCRAFT YAWED ACCOMPANIED BY A LOSS IN ENGINE TORQUE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE	 FUEL METERING UNIT WAS SUBSEQUENTLY DETERMINED TO BE UNSERVICEABLE AND WAS REPLACED. (TC NR 20060731014)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006080900199	20060809	00199	EU  	2006	8	9	CA060731015      	1	20060716	G	7712	311629401A	LIMITER         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TORQUE	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) IN DESCENT THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. THE MANUAL FUEL CONTROL OVER-RIDE WAS ENGAGED, AN EMERG	ENCY DECLARED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  THE ENGINE TORQUE LIMITER WAS SUBSEQUENTLY DETERMINED TO BE FAU	LTY AND WAS REPLACED. (TC NR 20060731015)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006081000020	20060810	00020	NE  	2006	8	10	CA060731016      	2	20060525	G	7250		TURBINE BLADES  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PC0951			(CAN) DURING CRUISE THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE AIRCRAFT DIVERTED 	TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A FRACTURED POWER TURBINE BLADE.  MFG WILL INVESTIGATE THE EVENT 	AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731016)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006081000021	20060810	00021	NE  	2006	8	10	CA060731017      	2	20060719	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								63196			(CAN) THE ENGINE EMITTED A NOISE IN FLIGHT ACCOMPANIED BY A RISE IN ITT TEMPERATURE. THE ENGINE WAS SHUTDOWN AND AN UNSC	HEDULED LANDING CARRIED OUT.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST. MFG WILL MONITOR THE INVESTIGA	TION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731017)				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006081000022	20060810	00022	NE  	2006	8	10	CA060731018      	2	20060711	G	7200		ENGINE          			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  						VIBRATES        	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA								PH0054			(CAN) DURING FLIGHT THE ENGINE WAS REPORTED TO LOSE POWER ACCOMPANIED BY HEAVY VIBRATIONS.  A FORCED LANDING WAS CARRIED	 OUT RESULTING IN AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC N	R 20060731018)				1	L	7	1 	3T	4	T		A3SW    	E4EA				 
2006081000023	20060810	00023	NE  	2006	8	10	CA060731019      	2	20060722	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FOLLOWING TAKE-OFF THE ENGINE EMITTED A NOISE AND FLAMED OUT.  SUBSEQUENT GROUND INSPECTION REVEALED EXERNAL OIL L	EAKAGE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731019)	.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006081400068	20060814	00068	NE  	2006	8	14	CA060731020      	2	20060722	G	7320		HMU             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					ENGIEN	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								120282			(CAN) DURING TAKE-OFF ROLL THE ENGINE MASTER CAUTION WARNING ANNUNCIATED. IN CLIMB, ENGINE TORQUE REDUCED UNCOMMANDED AN	D THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE ELECTRONIC AND HYDROMECHANICAL F	UEL CONTROLS WERE SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE	 OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731020)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006081000024	20060810	00024	NE  	2006	8	10	CA060731021      	2	20060727	G	7200		ROTOR           			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	SEIZED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								BB0122			(CAN) DURING CLIMB THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND THE PILOT ELECTED TO LAND.  ON DESCENT THE AIRCR	AFT BEGAN TO VIBRATE AND THE PILOT AUTOROTATED.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO ENGINE REAR MOUNT AND ROTOR SE	IZURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731021)				1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2006081000025	20060810	00025	EA  	2006	8	10	CA060731022      	2	20060720	G	7250		TURBINE BLADES  			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								3200832167			(CAN) FOLLOWING TAKEOFF THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SHUT	 DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE	 BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731022)				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006081000026	20060810	00026	NE  	2006	8	10	CA060801001      	2	20060604	G	7250		TURBINE BLADES  			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				M	T		OVER TEMP                 	ENGINE CASE PENETRATION   		TO	TAKEOFF        	1			CA								13266			(CAN) ON INITIAL TAKEOFF ROLL, ENGINE 13266ON A/C 477-1 SURGED AND EXPERIENCED A BRIEF OVER TEMPERATURE. MAX TGT WAS 903	 DEG C FOR LESS THAN A FEW SECONDS. METAL IN TAIL PIPE WAS FOUND AS WELL AS A HOLE IN THE HP T CASE. ENGINE IS UNDER INV	ESTIGATION AT RRC. FURTHER DETAIL WILL BE SUBMITTED WHEN AVAILABLE. (TC NR 20060801001)				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2006092600196	20060926	00196	EA  	2006	9	26	CA060801003      	1	20060713	G	3320	BR90002	BALLAST         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CABIN LIGHTS	ODOR            	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING PASSENGER BOARDING AND UPON ENTRY TO FLIGHT DECK A STRONG ELECTRICAL SMELL WAS APPARENT AND PROGRESSIVELY G	OT WORSE. PASSENGERS WERE DE-PLANED. LINE MAINTENANCE CREW FOUND FORWARD BOARDING LIGHT BALLAST P/N BR9000-2 BURNED. THE	 BURNED BALLAST WAS REPLACED, GROUND CHECKS PERFORMED AND AIRCRAFT RETURNED TO SERVICE. AIRFRAME HOURS WERE 25426:25 AND	 CYCLES WERE: 20767. (TC NR 20060801003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006101800077	20061018	00077	SW  	2006	10	18	CA060801004      	1	20060722	G	5302	206031329103S	FITTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16806								(CAN) A CRACK WAS FOUND FROM THE AFT TOP RIVET HOLE. THE CRACK STARTS AT THE TOP OF THE FITTING AND TRAVELS DOWNWARD THR	OUGH THE RIVET HOLE AND APPROXIMATELY .2500 FURTHER. (TC NR 20060801004)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006092600198	20060926	00198	NM  	2006	9	26	CA060801005      	1	20060412	G	2910	82950010141	LINE            	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			36205								(CAN) AFTER TAKEOFF NR 1 RUDDER FULL PRESSURE AND ROLL SPOILER IB HYDRAULIC CAUTION LIGHT ILLUMINATED. CREW DECLARED EME	RGENCY RETURNED TO AIRFIELD. MAINTENANCE REMOVED FLAP WELL PANEL 532AB AND FOUND AREA UNDER PANEL WAS CHARRED FROM FIRE.	 FIRE WAS HOT ENOUGH TO RUPTURE TWO HYDRAULIC LINES, MELTED SPACER BLOCKS AND MELTED PLASTIC ON WIRE BUNDLE. (TC NR 2006	0801005)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006092600200	20060926	00200	EU  	2006	9	26	CA060801007      	1	20060731	G	2197		WIRE            			AIRBUS	A340  	A340*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					CARGO FAN	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) (FWD CARGO VENT FAULT) DISPLAYED ON ECAM. TROUBLESHOOTING IDENTIFIED BURNED WIRING UNDER FWD CARGO FLOOR, APPROX 2	 IN FROM ELECTRICAL CONNECTOR 285HN-A ON FWD CARGO EXTRACTION FAN. BURNED WIRES WERE LOCATED BETWEEN SUPPORT STANDOFFS W	ITH NO EVIDENCE OF CHAFFING. WIRING REPAIRED IAW ESPM, REPLACED FWD CARGO EXTRACT FAN. (TC NR 20060801007)				2	L	7	4 	4F	4	F	RT	A197    	A12EU				 
2006092600202	20060926	00202	NM  	2006	9	26	CA060801008      	1	20060708	G	5753	734187B	TORQUE TUBE     			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A LINE MAINTENANCE WALK-AROUND CHECK, AN ENGINEER FOUND THAT THE LT WING FLAP IB (SECTION BETWEEN NACELLE A	ND FUSELAGE) TORQUE TUBE HAS BEEN CHAFED THROUGH IN ONE SPOT BY ITS RETAINING BRACKET. TORQUE TUBE ASSY PN REPLACED WITH	 SERVICEABLE ASSY FUNCTIONAL TEST COMPLETED ON FLAP SYSTEM AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060801008)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006092600203	20060926	00203	NM  	2006	9	26	CA060801009      	1	20060528	G	2910	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SERVO	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			40236								(CAN) AFTER NR 2 ENGINE START CREW OBSERVED THAT THE NR 2 HYDRAULIC SYSTEM QUANTITY HAD DECREASED TO 1 QUART. ENGINES SH	UTDOWN AND PASSENGERS DISEMBARKED FOR DEFECT INVESTIGATION.  ENGINEERING DETERMINED SYSTEM FLUID LOSS TO BE FROM THE RT 	OB SERVO ACTUATOR HOUSING. THE SERVO ACTUATOR WAS REPLACED AND HYDRAULIC SYSTEM REPLENISHED IAW THE AMM. (TC NR 20060801	009)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006092600204	20060926	00204	EU  	2006	9	26	CA060802001      	1	20060725	G	6310	35013001	FREEWHEEL UNIT  			SNIAS 	350   	AS350BA     	8680817	EU  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	MAKING METAL    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			5074 	61   							(CAN) AFTER INSTALLING A OVERHAULED FREEWHEEL, METAL WAS FOUND (4) SEPARATE TIMES IN 61.1 HOURS, SILVER FLAKES FOUND ON 	CHIP PLUG. (TC NR 20060802001)					1	G	7	1 	3U	3	U	NC	H9EU    	E1GL				 
2006081000027	20060810	00027	NE  	2006	8	10	CA060802002      	2	20060711	G	7250	2292253850	TURBINE BLADES  			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					GAS GENERATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			254  	254  							(CAN) THE PILOT SHUTDOWN THE AIRCRAFT TO HOOK UP HIS WATER BUCKET, AFTER A SHORT TIME PERIOD OF APPROXIMATELY 8 TO 10 MI	NUTES HE ATTEMPT TO RESTART THE AIRCRAFT. THE STARTER WOULD NOT TURN THE ENGINE. A BORESCOPE WAS USED TO LOOK INSIDE THE	 ENGINE AND FOUND THAT THE 1ST STAGE TURBINE BLADE HAD RUBBED. THE M03 WAS THEN REPLACED AND THE AIRCRAFT RETURN TO SERV	ICE. (TC NR 20060802002)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006092600205	20060926	00205	NM  	2006	9	26	CA060802003      	1	20060722	G	6120	7898426009	CONTROL UNIT    			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA				198  							(CAN) DURING THE TAKEOFF ROLL, THE FIRST OFFICER NOTED ILLUMINATION OF THE NR 1 ENGINE MANUAL CAUTION AND THE CAPTAIN EL	ECTED TO CONTINUE THE TAKE OFF. SHORTLY AFTER GEAR RETRACTION, THE NR 1 PROPELLER FEATHERED. THE ENGINE WAS SECURED AFTE	R COMPLETION OF PLATEAU HEIGHT DRILLS AND THE AIRCRAFT MANOEUVRED FOR A RETURN TO LAND.  NR 1 ELECTRONIC CONTROL UNIT RE	PLACED.  (TC NR 20060802003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006092600206	20060926	00206	EA  	2006	9	26	CA060802004      	1	20060801	G	2752		WARNING MESSAGE 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	ILLUMINATED     	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) 0 FLAP LANDING DUE TO FLAP FAIL EICAS MESSAGE. ON APPROACH, CREW SELECTED FLAPS AND NOTICED THEY WERE STUCK AT ZER	O.   CREW COMPLETED CHECKLIST, THEN CONTACTED DISPATCH/ MTC.   AFTER TALKING TO MTC THE FLIGHT LANDED WITH ZERO FLAP.   	AIRPORT FIRE FIGHTING WAS CONTACTED AS A PRECAUTION.   FLIGHT LANDED WITHOUT INCIDENT.  MAINT RESET SYSTEM AND CARRIED O	UT INSPECTION IAW TIB CRJ-27-04. SYTEM RESET OK. DMI APPILED TO HAVE FAULT CODES READ AND INTERPRETTED. (801574 8/1/2006	 21:01) (TC NR 20060802004)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006092600207	20060926	00207	NE  	2006	9	26	CA060802005      	2	20060427	G	7320	311496001	COUPLING        			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	RT ENGINE	WORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			18287	7506 							(CAN) DURING CRUISE, NUMBER 2 ENGINE EXPERIENCED EXTREME TORQUE FLUCTUATIONS OF UP TO 50 PRESENT WITH ASSOCIATED FUEL FL	OW AND NH RPM INDICATIONS. AS A RESULT OF A SUBSEQUENT TORQUE DROP THE CREW ELECTED TO CARRY OUT A PRECAUTIONARY ENGINE 	SHUT DOWN IN FLIGHT.  THE NO.2 PROPELLER ASSEMBLY WAS REPLACED DUE TO THE OVERTORQUE AND SENT FOR MAJOR INSPECTION. THE 	MECHANICAL FUEL CONTROL UNIT (MFCU) AND FUEL PUMP WERE REPLACED DURING WHICH IT WAS DISCOVERED THAT THE INTERCONNECTING 	COUPLING WAS STRIPPED POSSIBLY DUE TO AN INTERNAL FAILURE OF THE MFCU. (TC NR 20060802005)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006092600208	20060926	00208	NE  	2006	9	26	CA060802007      	2	20060419	G	7320	311717503	FUEL CONTROL    			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1 ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA			20271								(CAN) DURING APPROACH NR 1 ENGINE TORQUE AND RPM SURGING 10 PERCENT WITH POWER ABOVE 80 PERCENT. ENGINE SHUTDOWN AT 5000	 FEET ON DOWNWIND. MAINTENANCE REPLACED NR 1 ENGINE FUEL PUMP AND FUEL CONTROL. OPERATIONAL CHECK GOOD. AIRCRAFT RETURNE	D TO SERVICE. (TC NR 20060802007)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006092600209	20060926	00209	NE  	2006	9	26	CA060802008      	2	20060726	G	7497		WIRE            	CONT        		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	CHAFED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			DE	DESCENT        	1			CA			400  								(CAN) WHEN THE COLLECTIVE LEVER WAS LOWERED DURING DESCENT FOR A LANDING AT THE HELICOPTER BASE THE ENGINE TACHOMETER BE	CAME ERRATIC, THE ENGINE OVERSPED ABOVE 116 PERCENT AND THE THROTTLE GOVERNOR WAS NOT WORKING. THE ROTOR TACH ALSO INDIC	ATED AN OVERSPEED ABOVE 114 PERCENT. INSPECTION OF THE RT MAGNETO FOUND THAT THE INSULATION ON THE WIRE CARRYING THE SPE	ED SIGNAL FROM THE SECONDARY POINTS TO THE TACHOMETER AND SPEED GOVERNOR HAD BEEN CUT THROUGH AND SHORTED TO GROUND. THE	 INTERMITTENT LOSS OF SIGNAL RESULTED IN ERRATIC TACH INDICATION AND THE AIRFRAME MANUFACTURER CONFIRMED THAT WITH THAT 	CONDITION THE GOVERNOR COULD BE EXPECTED TO GO OFF LINE. THE MOST LIKELY CAUSE OF THE DAMAGE WAS PINCHING OF THE WIRE BE	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006091300046	20060913	00046	NM  	2006	9	13	CA060802009      	1	20060405	G	3240	DSC252A40230	HOSE            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	BRAKES	LEAKING         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PRE TAKE-OFF CHECKS FOR THE FIRST FLIGHT OF THE DAY (PARK BRAKE ON), THE FLIGHT CREW NOTICED THAT THE NR 2 	HYDRAULIC SYSTEM HAD LOST MOST OF ITS FLUID. AIRCRAFT GROUND RETURN AND DURING THE TAXI BACK TO THE GATE, THE NR 1 HYDRA	ULIC SYSTEM QUANTITY WAS ALSO OBSERVED TO BE GOING DOWN.  MAINTENANCE INSPECTION REVEALED THAT THE LT OB (NR 1) BRAKE HY	DRAULIC FLEX HOSE TO BE LEAKING FLUID.  A NEW  FLEXIBLE BRAKE HOSE ASSEMBLY P/N: DSC252A4-0230 INSTALLED, BOTH HYDRAULIC	 SYSTEMS SERVICED AND BLEED IAW AMM (TC NR 20060802009).		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300050	20060913	00050	WP  	2006	9	13	CA060802010      	2	20060801	G	7261		ENGINE          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LEFT	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			4828 					P70275			(CAN) ON CLIMB, THE LT LOW OIL PRESSURE LIGHT ILLUMINATED, ALONG WITH A OIL PRESSURE GAUGE DECREASE. THE LT ENGINE WAS S	HUTDOWN IN FLIGHT AND RETURNED TO BASE. ON INSPECTION IT APPEARS THAT THE OIL EXITED OUT THE EXHAUST. ENGINE REMOVED AND	 SENT FOR REPAIR AND INSPECTION. (TC NR 20060802010)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2006091300051	20060913	00051	EU  	2006	9	13	CA060803001      	1	20060614	G	5210	852G10	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					PAX DOOR	PEELING         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			HO	HOVERING       	1			CA											(CAN) THE PILOT WAS LONG LINING WITH THE PILOT SIDE DOORS OFF, THE WEATHER STRIPPING PEELED OFF THE DOOR FRAME. THE LAST	 3 INCHES CAUGHT ON THE POCKET DOOR STOP. THE PILOT SLOWED DOWN AND LANDED TO REMOVE THE REST OF THE DOOR SEAL. THE DOOR	 SEAL IS 4 METERS LONG,AND ALTERNATE P/N 704A39821031.  (TC NR 20060803001)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006091300054	20060913	00054	NM  	2006	9	13	CA060803003      	1	20060803	G	2611	656020916	CONTROLLER      			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D*       	 	NE  					FIRE DETECTION	MALFUNCTIONED   	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) JUST AFTER ENGINE, ALL 3 ENGINES WERE STARTED AND THE FLIGHT CREW WERE CARRYING OUT THE AFTER START CHECKLIST, THE	 NR 2 ENGINE (FIRE WARNING) ILLUMINATED AND THE (FIRE BELL RANG). THE FIRE HAND WAS PULLED AND THE FIRE BOTTLE DISCHARGE	D LIGHT WENT OUT. MAINTENANCE CONFIRMED THAT THERE WAS NO FIRE AND THAT THE FIRE DETECTION UNIT HAD FAILED. THIS UNIT IS	 A ON CONDITION SOLID STATE PART. AIRCRAFT IS CURRENTLY ON THE GROUND AWAITING PARTS. (TC NR 20060803003)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006091300055	20060913	00055	SW  	2006	9	13	CA060803004      	1	20060728	G	2910	70061H000T13	HOSE            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) UPON LANDING AND SHUTDOWN ON LAST UNEVENTFULL FLIGHT OF THE DAY. PILOT REPORTED HYD FLUID ON SIDE OF A/C. A/C GROU	NDED UNTIL INSP, UPON INSP. HYD PRESSURE FEED LINE FOUND LEAKING. LINE REPLACED WITH SEVICEABLE UNIT. RECOMMEND OPERATOR	S AND MAINT FACILITIES INSPECT O/C HYD LINES FREQUENTLY AND REPLACE. (TC NR 20060803004)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006091300058	20060913	00058	NM  	2006	9	13	CA060804001      	1	20060503	G	7603	87620136055057	CONTROL ROD     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	POWER LEVER	MISINSTALLED    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB NR 2 ENGINE WAS MAKING ONLY 78 PERCENT POWER AND THE ENGINE POWER LEVER WAS JAMMED 1.5 INCH FROM FULL	 TRAVEL.  AIRCRAFT RETURN ON GROUND SAFELY SHORTLY AFTER TAKEOFF.  MAINTENANCE FOUND NR 2 CONTROL AND CONDITION LEVER RO	DS HARDWARE (BOLT AND NUT) INCORRECTLY INSTALLED. PROPER HARDWARE INSTALLATION AND ENGINE RIGGING WERE PERFORMED. AN INT	ERNAL SAFETY ALERT WAS ISSUED ON JULY 14, 2006 IN RESPECT TO THIS EVENT. AIRFRAME HOURS: 37405:43. CYCLES:48382 (TC IN 2	0060804001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300059	20060913	00059	EA  	2006	9	13	CA060804002      	1	20060729	G	3320	BR95005	BALLAST         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CABIN LIGHTS	FAULTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE AN ELECTRICAL SMELL WAS APPARENT IN THE FRONT HALF OF THE CABIN.  EIGHT (8) CABIN LIGHT BALLAST	S WERE FOUND AT FAULT.  ALL 8 WERE REPLACED AND AIRCRAFT WAS MONITORED FOR TWO HOURS FOR SNAG RE-OCCURENCE WITH NO FAULT	 FOUND.  AIRFRAME HOURS: 3602:31. CYCLES: 2780. (TC NR 20060804002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006091300061	20060913	00061	NM  	2006	9	13	CA060804003      	1	20060602	G	2910	AN81510D	FITTING         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1 HYD SYS	FRACTURED       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			310  								(CAN) DURING THE FLIGHT, OPERATOR LOST ALL HYDRAULIC QUANTITY AND PRESSURE FROM THE SYSTEM NR 1 AND ALL ASSOCIATED LIGHT	S. CREW COMPLETED THE RESPECTIVE CHECKLIST AND LANDED WITH FLAPS 0 AND WITHOUT NORMAL BRAKING,  INVESTIGATION REVEALED 	THAT THE NR 1 PRESSURE MANIFOLD INLET UNION HAD FRACTURED. (TC NR 20060804003)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300063	20060913	00063		2006	9	13	CA060804004      	4	20060410	G	3442	707700301	INDICATOR       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	WEATHER RADAR	MALFUNCTIONED   	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA			9667 	1105 							(CAN) DURING DESCENT, CREW DETECTED A STRONG BURNING SMELL ON THE FLIGHT DECK. FLIGHT CREW DONNED OXYGEN MASKS AND LANDE	D WITHOUT FURTHER INCIDENT.  FLIGHT CREW HAD REPORTED TO ENGINEERING THAT THE WEATHER RADAR WAS INOPERATIVE FROM TOP OF 	DESCENT. UPON INVESTIGATION BY ENGINEERING THE WEATHER RADAR INDICATOR WAS FOUND TO HAVE A STRONG BURNING SMELL. WEATHER	 RADAR INDICATOR REPLACED AND FUNCTIONALLY TESTED SERVICEABLE.  (TC NR 20060804004)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300084	20060913	00084	NE  	2006	9	13	CA060804005      	3	20060329	G	6111	73030SOCN8173881	SEAL            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER BLADE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			135  			200504062525					(CAN) DURING FLIGHT, NR 1 PROP LOST APPROXIMATELY 7 QUARTS OF OIL FROM THE HUB.  UPON ARRIVAL AIRCRAFT WAS COVERED IN OI	L (LT). THERE WAS NOT AN INFLIGHT SHUTDOWN AND NO EMERGENCY MEASURES WERE REQUIRED OR TAKEN. THE AIRCRAFT RESPONDED NORM	ALLY.  THE PROP SEAL WAS FOUND TORN AND THE GARTER SPRING WAS DISTORTED WHERE THE TWO ENDS OF THE SPRING ARE WELDED. (TC	 NR 20060804005)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300105	20060913	00105		2006	9	13	CA060804006      	4	20060728	G	6122	5337050	IDLER GEAR      	WOODWARD    							PWA   	PT6   	PT6A67B     	52043	NE  					PROPELLER GOVER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1584 			13313260					(CAN) ENGINE PCE-PR0055 WAS SUBMITTED FOR A SCHEDULED FIRST TIME OVERHAUL (TSN 3621.0 HRS).  THE PROPELLER GOVERNOR S/N 	13313260 (TSN 1583.6 HOURS) WAS DISMANTLED FOR CLEANING BEFORE OVERHAUL INSPECTION.  IT WAS DISCOVERED THAT THE IDLER GE	AR BUSHING WAS SEVERELY WORN AWAY RESULTING IN AN ELLIPTICAL ROTATION OF THE GEAR THAT CAUSED THE GEAR POCKET TO WEAR IN	 AN OVAL MANNER ON THE PRESSURE SIDE.   A NORMAL IDLER GEAR BUSHING MEASURES APPROXIMATELY 0.100 IN.  THE WORN IDLER GEA	R BUSHING MEASURED 0.0175 IN., I.E. IT HAD WORN AWAY 0.0825 IN.  IT IS NOT KNOWN WHAT CAUSED THE EXCESSIVE WEAR. THE PER	IODIC OIL ANALYSIS PROGRAM (SOAP) DID NOT INDICATE A PROBLEM. AFTER DISCOVERING THIS CONDITION, WE TRIED TO ROTATE THE G						4	T			E26NE				 
2006121300137	20061213	00137	EU  	2006	12	13	CA060804007      	1	20060803	G	2913	S40	COUPLING        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	LEAKING         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						40652121					(CAN) PILOT FELT STIFFNESS IN FLIGHT CONTROLS AND LANDED. INVESTIGATION REVEALED THAT THE SLEEVE COUPLING INTERNAL SPLIN	ES HAD WORN EXCESSIVELY SO THAT THE FLIGHT CONTROL HYDRAULIC PUMP WAS NO LONGER DRIVEN BY THE DRIVE BELT FROM THE MAIN G	REAR BOX.  THE FAILED COUPLING SHOWS SIGNS OF MILD CORROSION IN THE INTERNAL SPLINES.  THE COUPLING WAS LUBRIATED DURING	 THE LAST SCHEDULED INSPECTION 30 HOURS PREVIOUSLY.  THE SLEEVE COUPLING WAS REPLACED AND THE AIRCARFT WAS RETURNED TO S	ERVICE.   DISCUSSION WITH OTHER OPERATORS INDICATE AN INCREASE IN THE SLEEVE COUPLING FAILURE RATE SINCE THE INTRODUCTIO	N OF THE POLY V DRIVE BELT AS REQUIRED BY AD CF-2004-10 ( SB 63.00.08) ISSUED 4 JUNE 2004.    (TC NR 20060804007)	1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006091300113	20060913	00113	EA  	2006	9	13	CA060804008      	2	20060801	G	8530	SLC36005F	CYLINDER HEAD   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1640 								(CAN) ALL 4 CYLINDERS HAVE CRACKS THAT BEGIN AT THE INNER MOST EXHAUST FLANGE STUD AND MOVING TO THE EXHAUST VALVE SEAT,	 THEN 180 DEGREES ACROSS THE EXHAUST VALVE SEAT TO THE UPPER SPARK PLUG HOLE.  SN. E36-10511 E36-10244 E36-10426 E36-104	96  NOTE: THIS MAKES 10 OF THESE CYLINDERS FROM 3 DIFFERENT AIRCRAFT IN 6 WEEKS TO HAVE THE SAME CRACKS. TIME ON THESE V	ARY FROM 1600 TO 2100 HOURS. ALL ON AN (ON CONDITION PROGRAM) REQUIRING AN EXTERNAL SOAPY/WATER LEAK CHECK AND BORESCOPE	 INSPECTION WHICH IS HOW THE DEFECT IS DISCOVERED. A CYLINDER DPI DOES NOT REVEAL AND A PARTIAL ENGINE TEARDOWN ID REQUI	RED FOR VISUAL DETECTION. (TC NR 20060804008)	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2008013100013	20080131	00013	CE  	2008	1	31	CA060804009      	1	20060802	G	5330	50420066281	DOUBLER         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12559				1129				(CAN)  DURING PHASE 2 INSPECTION AND WHILE PERFORMING SPECIAL INSPECTION ON NR 25 (INSPECTION OF UPPER AND LOWER WINDSHI	ELD CORNERS), DAMAGE TO THE DOUBLER BELOW THE WINDSCREEN WAS FOUND. THE PN OF THE DOUBLER IS 50-420066-281 LOCATED BETWE	EN  FS 94.00AND FS 100.50. THE DAMAGE WAS CAUSED FROM THE ITT HARNESSES CHAFFING INTO THE DOUBLER. THE DAMAGE IS LOCATED	 BETWEEN 1.5 TO 5.5 LT OF THE WINDSCREEN CENTER POST, THE DOUBLER THICKNESS IS .100, THE CHAFFING DAMAGE RANGES FROM .01	0 TO .069 IN DEPTH. THE DAMAGED AREA HAS BEEN MAPPED, AND THE INFORMATION SENT TO MFG REPAIR DESIGN OFFICE FOR ASSESSMEN	T.  A FOLLOW UP REPORT SHALL BE SUBMITTED.     (TC NR 20060804009)	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006091300115	20060913	00115	WP  	2006	9	13	CA060804010      	1	20060731	G	6320	369D25146	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R TRANSMISSION	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				574  		1265					(CAN) 369D25146 ROLLER BEARING INNER RACE CRACKED, THIS RACE IS PRESSED ONTO TRANSMISSION T/R O/P PINION WITH AN INTERFE	RENCE FIT.  CRACKED INNER RACE CAUSED THE RACE TO SPALL AND CAUSED A CHIP LIGHT.  SEVERE METAL CONTAMINATION WAS FOUND (	TC NR 20060804010)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006091300116	20060913	00116	CE  	2006	9	13	CA060806001      	1	20060727	G	3246	RA105002	RIVET           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	BRAKE LINING	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON LANDING THE PILOT EXPERIENCE A SEVERE PROBLEM WITH THE LT MAIN WHEEL BRAKE SYSTEM. DURING THE DISASSEMBLY OF 	THE LT BRAKE SYSTEM IT WAS DISCOVERED THAT THE BRAKE LINING RIVETS (RA105-002) HAD BOTH SHEARED AND THE LINING WAS NO LO	NGER ATTACHED TO THE BACKING PLATE.  THE RIVETS THAT SHEARED WERE MADE FROM BRASS (RA105-002) UNLIKE THE CLEVELAND RIVET	S (105-002 WHICH ARE BRASS PLATED STEEL. THE AIRCRAFT WAS RETURNED TO SERVICE WITH NEW BRAKE LININGS AND NEW CLEVELAND R	IVETS. (TC NR 20060806001)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006091300118	20060913	00118	CE  	2006	9	13	CA060807001      	1	20060804	G	3246	16211800	WHEEL           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) APPROX 1.5 INCH CRACK AROUND CIRCUMFERENCE OF BEARING RACE, INSIDE OF WHEEL HALF, SUSPECT MIS-ALIGNMENT OF WHEEL H	ALF SPACER DURING BUILD-UP (TC NR 20060807001)					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006091300119	20060913	00119	EU  	2006	9	13	CA060807002      	1	20060806	G	6420	704A33651190	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			200  								(CAN) FOUND DURING 500 HOUR INSPECTION.  ABNORMAL BEARING NOISE, AXIAL WEAR BEYOND LIMITS. (TC NR 20060807002)						1	G	7	1 	3U			NC	H9EU    					 
2006091300121	20060913	00121	EU  	2006	9	13	CA060808001      	1	20060731	G	2910	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			3988 	3988 							(CAN) LANDING GEAR SELECTED DOWN ON FINAL. NO GEEN DOWN LOCK INDICATION FOR THE NOSE GEAR. PILOT DID AN EMERGENCY GEAR E	XTENSION AND GOT THE LANDING GEAR DOWN AND LOCKED INDICATION FOR ALL THREE GEAR. THE SYSTEM WAS TROUBLESHOT AND FOUND TO	 HAVE A MALFUNCTIONING HYD PWR RELAY K601. THE RELAY WAS REPLACED AND A FUNCTIONAL CHECK OF THE LANDING GEAR SYSTEM WAS 	CARRIED OUT WITH NO FURTHER PROBLEMS. (TC NR 20060808001)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006091300122	20060913	00122	EA  	2006	9	13	CA060808004      	2	20060703	G	8520	LW13521	BEARING         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CONNECTING ROD	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2183 	2183 							(CAN) CONNECTING ROD BEARINGS ON NR 1,3, AND 5 RODS HAD SIGNIFICANT SURFACE DELAMINATION.  BROKEN PIECES .5 INCH L X .12	50 INCH W FOUND IN BETWEEN CONNECTING ROD BEARING AND CRANKSHAFT. (TC INCH 20060808004)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006091300123	20060913	00123	GL  	2006	9	13	CA060808005      	2	20060719	G	7230	23056109	SCROLL          	ALLSN       		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					COMPRESSOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			6983 			CAC70614					(CAN) HIGH TOT WAS NOTICED IN CRUISE. ON RETURNING A POWER CHECK WAS CARRIED OUT AND LOW POWER WAS DETECTED. A HAIT LINE	 CRACK WAS IDENTIFIED BY VISUAL INSPECTION  IN THE ELBOW AREA OF SCROLL. COMPRESSOR CHANGED. (TC NR 20060808005)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006091300125	20060913	00125	CE  	2006	9	13	CA060808006      	1	20060804	G	5343	12116011	FITTING         			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MLG OUTBOARD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9713 								(CAN) DURING A 100 HOUR INSPECTION LOOSE RIVETS WERE NOTICED AROUND THE LT MAIN GEAR.  ONCE THE FLOOR WAS LIFTED TO PERF	ORM THE REPAIRS, THE LT MAIN GEAR OB FITTING WAS FOUND TO BE CRACKED PROPOGATING FROM THE AFT END OF THE GEAR LEG OPENIN	G TOWARDS THE AFT END OF THE FITTING. (TC NR 20060808006)				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
2006091300126	20060913	00126	WP  	2006	9	13	CA060808009      	1	20060703	G	3213	369H600151	STRUT           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE YEARLY INSPECTION, THE LT AFT LANDING GEAR STRUT WAS INSPECTED AND FOUND TO BE CRACKED, FROM THE LOWER 	DRAG BRACE ATTACH HOLE.  THE CRACK WAS APPROX. 1.250 INCH LONG, AND EXTENDED LENGTHWISE TOWARDS THE BEND IN THE STRUT (T	C NR  20060808009)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006091300132	20060913	00132	EA  	2006	9	13	CA060808010      	1	20060710	G	5610	601R3303317	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			3949 								(CAN) (ENROUTE, CREW SENT ACARS MESSAGE TO DISPATCH THAT THEY HAD A BROKEN CAPTAINS WINDSHIELD, AND WERE DIVERTING) MX D	ISPATCHED WITH WINDSHIELD.  WINDSHIELD REPLACED. (TC NR 20060808010)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006091300147	20060913	00147	NE  	2006	9	13	CA060808011      	2	20060204	G	7200	CF343A1	ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) EXPERIENCED THE RT ENGINE IFSD, JUST AFTER THE LIGHTNING STRIKE TODAY.   PIC DID NOT TRY TO RESTART THE ENGINE DUR	ING THE FLIGHT, BUT AFTER THE LANDING WE COULD START THE ENGINE.  THERE IS NO VISIBLE DAMAGE ON THE OUTSIDE OF THE ENGIN	E, WE WILL DO THE BSI.  WE WOULD LIKE TO KNOW THE MOST PROBABLE ROOT CAUSE OF THE IFSD.  IF YOU HAVE A SIMILAR EXPERIENC	E IN OTHER OPERATORS, PLEASE PROVIDE YOUR INFORMATION. THE CIRCUMSTANCES IS AS FOLLOWS, OCCURRED DATE : APRIL 02, 10:37J	ST  ASN: 7052 ESN : 807222 FLT PHASE : DURING THE DESCENDING TO DESTINATION ALT : 13,000 FT IGNITION : CONTINUOUS IGNITI	ON WEATHER CONDITION : IN-CLOUD, LIGHT RAIN) AFTER THE EVENT THE OPERATOR SUPPLIED THE DFDR TO MFG.  MFG ANALYSIS CONCLU	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006091300148	20060913	00148	SW  	2006	9	13	CA060809001      	1	20060809	G	2910	2781006019	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FOUND HYD LEAK IN LT WHEEL WELL.  GEAR UP LINE FOUND CRACKED.  LINE REPLACED, GEAR SWINGS CARRIED OUT.  AIRCRAFT R	ETURNED TO SERVICE (TC NR 20060809001)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006091300149	20060913	00149	SO  	2006	9	13	CA060809002      	1	20060528	G	7810	LW121127	EXHAUST DUCT    			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1599 								(CAN) EXHAUST TRANSITION BETWEEN TURBO AND EXHAUST STACKS FROM CYLINDERS HAD CRACKED AND STARTED TO BLOW A HOLE BELOW TH	E EGT PROBE HOLE. THE DEFECT WAS NOTICED BY AN EXHAUST STAIN ON THE INSIDE OF THE COWL ON A MAINTENANCE DAILY INSPECTION	. THE AIRCRAFT WAS 39 HOURS OUT OF INSPECTION. (TC NR 20060809002)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006101800078	20061018	00078	NM  	2006	10	18	CA060810001      	1	20060810	G	5220	MS2764639	ROD END         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	EMERGENCY EXIT	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A C-CHECK INSPECTION THE TASK WAS CALL UP TO INSPECT THE FWD EMERGENCY EXIT. UPON INSPECTION IT WAS DETERMI	NED THAT IT WAS EXTREMELY STIFF AND DIFFICULT TO OPERATE. UPON REMOVAL AND TROUBLESHOOTING IT WAS DETERMINED THAT THE CO	NNECTING ROD END (X10) REF IPC 52-20-00 FIG. 20 ITEM 180 WERE FOUND SEIZED INTERNALLY. THE FAILURE APPEARS TO BE DUE THE	 PHENOLIC BALL WIPER NOT ALLOWING THE BEARING TO ROLL FREELY. IT WAS ALSO DETERMINED THAT THE LAYSHAFT BEARINGS (X4) EXH	IBITED ABNORMAL WEAR AND CORROSION ASSOCIATED WITH HIGH TIME BEARINGS REF IPC 52-20-00 FIG. 20 ITEM 590. 2 OF THE 4 HAVE	 FAILED DUE TO INTERNAL SEIZING. ALL PART ARE CURRENTLY BEING REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300150	20060913	00150	CE  	2006	9	13	CA060810004      	1	20060731	G	5712	052303018	RIB             			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19931								(CAN) DURING NR 3 INSPECTION CRACK LOCATED IN (D) RIB JUST OB OF WING STRUT. LT WING. (TC NR 20060810004)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006091300151	20060913	00151	CE  	2006	9	13	CA060810005      	1	20060806	G	7712	1013890053	TRANSMITTER     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TORQUE	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF RT TORQUE TRANSMITTER WAS READING HIGH AIRCRAFT RETURNED AIRPORT. AIRCRAFT ELECTRICAL POWER TURNED OFF 	AND TORQUE INDICATOR WENT TO ZERO. A GROUND RUN WAS ACCOMPLISHED AND TORQUE INDICATION WAS NORMAL AT HIGH AND LOW POWER 	SETTINGS. AIRCRAFT RETURNED TO DESTINATION WITHOUT FURTHER INCIDENT.  MAINTENANCE REPLACED RT ENGINE TORQUE TRANSMITTER 	P/N 101-390005-3 AS A PRECAUTIONARY. (TC NR 20060810005)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006091300152	20060913	00152	SO  	2006	9	13	CA060810006      	1	20060726	G	5523	11030120115	SUPPORT         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BALANCE WEIGHT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING AN INSPECTION OF THE LTO ELEVATOR AND ITS ASSOCIATED PARTS A CRACK WAS FOUND IN THE ELEVATOR BALANCE W	EIGHT SUPPORT. THE CRACK MEASURED   2.3750 OF AN INCH IN LENGTH AND STARTED APPROXIMATELY 2 INCHES BELOW THE LOWER THROU	GH-TUBE FOR THE BALANCE SUPPORT TO ELEVATOR TORQUE TUBE ATTACH POINTS. THE SUPPORT WAS REPLACED WITH A NEW ONE. (TC NR 2	0060810006)			1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2006091300153	20060913	00153	EU  	2006	9	13	CA060810007      	1	20060726	G	2740	HC273H0344	ARM             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LEVER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			36261	14   							(CAN) RESTRICTED MOVEMENT OF CONTROL COLUMN IN THE AFT DIRECTION. SEE CA1673 14 NR CTS/06/001 ATTACHED (TC NR 2006081000	7)					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
2006091300154	20060913	00154	SO  	2006	9	13	CA060811001      	1	20060807	G	2400		PANEL           			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  	HARTZL	HCC3Y	HCC3YN      	GL  	CIRCUIT BREAKER	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CIRCUIT BREAKER PANEL STARTED TO SMOKE AND SPARK DURING CRUISE AT 14000 FT. ELECTRICAL FIRE CHECKLIST WAS INITIATE	D AND DESCENDED TO 7500 FT. UPON COMPLETION OF ELECTRICAL FIRE CHECKLIST SMOKE AND SPARK NO LONGER PRESENT.  (TC NR 2006	0811001)				1	L	7	2 	3O	3	O		A8EA    	E19EA	5	C	P25EA	 
2006091300155	20060913	00155	WP  	2006	9	13	CA060811002      	1	20060810	G	7921	369D25623	BELT            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					BLOWER OIL COOL	WORN            	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			816  								(CAN) ON APPROACH TO LAND THE PILOT HEARD A NOISE TO THE REAR OF THE AIRCRAFT FOLLOWED BY A VIBRATION.  UPON INSPECTION 	THE ENGINEER NOTICED THE OIL COOLER BLOWER BELT TENSION WAS LOOSE AND THE TEETH OF THE BELT WERE WORN. (TC NR 2006081100	2)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2006101800079	20061018	00079	NM  	2006	10	18	CA060811003      	1	20060810	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG WOW	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LANDING GEAR DID NOT RETRACT AFTER TAKE OFF, RETURN TO FIELD. FOUND FAULTY NLG WOW 2/ CENTERING HARNESS. HARNESS R	EPLACED. AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006121300138	20061213	00138	SW  	2006	12	13	CA060814002      	1	20060717	G	6220	412010190105	SPINDLE         	BELL        		BELL  	412   	412         	1182202	SW  										MAIN ROTOR HUB	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2396 			A2713					(CAN) ON A MAIN ROTOR HUB ASSY 2500 HOUR INSPECTION THE RED BLADE SPINDLE ASSY WAS FOUND WITH DAMPER BEARING DEBONDED. (	TC NR 20060814002)					1	G	7	2 	4U				H4SW    					 
2006101800080	20061018	00080	GL  	2006	10	18	CA060814003      	3	20060729	G	6110	6505656	BRUSH BLOCK     			LKHEED	188   	188LKHEED*  	       	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	NR 2 PROPELLER	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF CREW NOTICED NR 2 BETA LIGHT ILLUMINATED AND PROP RPM ERRATIC THE CREW ELECTED TO SHUT-DOWN NR 2 ENG	. AND RETURN TO BASE FOR MAINTENANCE. BRUSH BLOCK WAS CHANGED ENG. WAS GROUND RUN  AND FOUND SERVICABLE. (TC NR 20060814	003)				2	L	7	4 	4T	4	T		4A22    	E282	6	C	P898	 
2006091300166	20060913	00166	SW  	2006	9	13	CA060815001      	1	20060807	G	2910	2781032167	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FLUID NOTICED BY MAINTENANCE ON BELLY AREA OF AIRCRAFT.  GEAR UP LINE FOUND CRACKED.  LINE REPLACED AND 	GEAR SWINGS CHECKED SERVICIBLE. (TC NR 20060815001)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006101800081	20061018	00081	NM  	2006	10	18	CA060815002      	1	20060814	G	5220	85220270001	MECHANISM       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	EMERGENCY EXIT	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37863	37863							(CAN) DURING INTERNALLY GENERATED MAINTENANCE FLEET CAMPAIGN TO CHECK FOR EMERGENCY DOOR OPERATING FORCE. MAINTENANCE UN	ABLE TO OPEN FORWARD EMERGENCY EXIT DOOR USING INTERNAL OR EXTERNAL HANDLE ( TASK 5220/07). REQUIRED DISASSEMBLY OF DOOR	 OUTER SHAFT MECHANISM TO ALLOW DOOR TO BE REMOVED. DISASSEMBLY OF OUTER SHAFT HANDLE FOUND BURR OF METAL ON SHAFT. DOOR	 REPAIRED AND MECHANISM LUBRICATED. AIRCRAFT HAD ACCUMULATED 1023HR/1823CY SINCE LAST SCHEDULED ACCOMPLISHMENT OF TASK 5	220/07 IN JAN2006.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300168	20060913	00168	SW  	2006	9	13	CA060815003      	1	20060815	G	7931	2090620031	PRESSURE SWITCH 			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE OIL	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			296  								(CAN) FLUID LEAK AT UNION OF SWITCH BODY.  THE BODY NORMALY HAS A RIVET TO KEEP THE UNIT FROM BEING TAKEN APART, BUT THI	S RIVET WAS FOUND TO BE MISSING.  THE THREADS HAD DAMAGE WHERE THE RIVET HOLE WAS.  A HOLE IS PROVIDED IN THE THREADS TO	 INSTALL A RIVET.  THIS DID NOT LINE UP. (TC NR 20060815003)				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006091300172	20060913	00172	WP  	2006	9	13	CA060815004      	1	20060815	G	8011	31B22111	STARTER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			25   								(CAN) PILOT WENT TO START THE AIRCRAFT.  HE COULD HEAR THE MOTOR TURNING, HOWEVER THE ENGINE WAS NOT TURNING OVER.  THE 	AME FOUND THE DRIVE TO BE ENGAGED TO THE RING GEAR.  WHEN THE STARTER WAS REMOVED, THE DRIVE COULD BE TURNED FREELY BY H	AND.  THE DRIVE FAILED INTERNALLY.  NO REPORT OF ANY BACKFIRE OR KICKBACK DURING START. THE AME BELIEVES THAT AN INTERRU	PTION OF THE POWER TO THE STARTER MAY HAVE CAUSED THE STARTER TO DISENGAGE AND REENGAGE, DAMAGING THE STARTER PINION.  H	E BELIEVES THE FAULT TO BE IN THE AIRCRAFT WIRING, NOT IN THE STARTER.  (TC NR 20060815004)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007051600165	20070516	00165	NE  	2007	5	16	CA060816001      	2	20060815	G	7261		OIL SYSTEM      			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					ENGINE	LOW PRESSURE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			4595 								(CAN) ENGINE INFLIGHT SHUTDOWN DO TO OIL PRESSURE AND QUANTITY LOSS, ENROUTE, DIVERTED, SUSPECT NR 4 BEARING. (TC NR 200	60816001)					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2006101800082	20061018	00082	NM  	2006	10	18	CA060816002      	1	20060707	G	5280	83231044005	GUARD           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	RT NACELLE	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, AFTER GEAR UP SELECTION AMBER AND RED LIGHTS ILLUMINATED IN GEAR HANDLE, ALONG WITH 3 AMBER LANDING 	GEAR DOOR LIGHTS. A LOUD GRINDING NOISE WAS HEARD IN THE COCKPIT. AIRCRAFT RETURNED AND LANDED SAFELY TO THE ORIGINATING	 AIRPORT. MAINTENANCE FOUND RT NACELLE`S WHEEL WELL DEBRIS GUARD DAMAGED AND WAS REPLACED. NO MAINTENANCE WAS PREVIOUSLY	 PERFORMED IN THAT AREA. MAINTENANCE FEED-BACK REVEALED THAT THE DEBRIS GUARD GETS LOOSE QUITE OFTEN, DUE TO THE FASTENI	NG SYSTEM USED. AIRFRAME HOURS WERE: 36610:07. CYCLES WERE: 40842. (TC NR 20060816002)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091300173	20060913	00173	EA  	2006	9	13	CA060816003      	1	20060809	G	4920	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						SMOKE           	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA			15928	15928							(CAN) AT THE GATE, CREW TURNED ON BOTH AIR CONDITIONING PACKS AND SMOKE/AND OR HAZE ACCOMPANIED BY ODOR BEGAN TO FILL TH	E COCKPIT AND CABIN. CREW IMMEDIATELY OPENED THE MAIN CABIN DOOR TO VENT THE AREA, AND SMOKE/HAZE BEGAN TO DISSIPATE. MA	INTENANCE FOUND A MAJOR OIL LEAK FROM THE COMPRESSOR SECTION OF THE APU. OIL WAS INJESTED IN TO ONE OR BOTH PACKS. NEW A	PU INSTALLED. BOTH CONDENSOR BAGS REPLACED AND DUCTS CLEANED OF OIL. INFORMATION WILL BE UPDATED WHEN ROOT CAUSE OF LEAK	 IS AVAILABLE. (TC NR 20060816003)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006091300191	20060913	00191	NE  	2006	9	13	CA060816004      	2	20060701	G	7230		COMPRESSOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			3745 	1396 							(CAN) PILOT STARTED THE AIRCRAFT IN THE FIELD AND NOTICED THE THE START WAS VERY SLOW, HE RETURNED FROM A FLIGHT AND NOT	IFIED THE MAINTENANCE STAFF OF THE PROBLEM. THEY HAD THE PILOT START THE AIRCRAFT AND NOTICED THAT THE ENGINE WAS VIBRAT	ING, THEY MADE THE PILOT ABORT THE START. UPON FURTHER INVESTIGATION THEY MOTORED OVER THE ENGINE WITHOUT STARTING IT AN	D THERE WAS A SCREACHING GRINDING NOISE COMING FROM THE ENGINE. THEY INSPECTED THE STARTER GENERATOR AND CHECKED THE ENG	INE AND DRIVE SHAFT FOR CONDITION BUT DIDN`T FIND ANYTHING. THEY HAND ROTATED THE POWER TURBINE BLADES AND THERE WASN`T 	ANY NOISE. THEY ROTATED THE COMPRESSOR AND DISCOVERED THAT THERE WAS RUBBING NOISE COMING FROM THE M03. THE ENGINE WAS R	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007051600166	20070516	00166	NM  	2007	5	16	CA060816005      	1	20060815	G	7600		BEARING         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CONDITION CABLE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37331	37331							(CAN) DURING ROUTINE MAINTENANCE INSPECTION OF MFG TASK 422 (A CHECK 500 HR REPETITIVE TASK) ZONAL  INSPECTION OF RT ENG	INE COMPARTMENT. FOUND POWER AND CONDITION CABLE PULLEYS (2 EACH SYSTEM, TOTAL 4 PULLEYS) IN THE UPPER AFT NACELLE/FRONT	 OF WING SPAR, TO ALL HAVE SEIZED BEARINGS (1 PULLEY WITH BRG ASSY FALLING OUT OF PHENOLIC PULLEY). PULLEYS REPLACED AND	 ENGINE CONTROLS RE-RIGGED. AIRCRAFT HAD ACCUMULATED 492 HOURS SINCE LAST ACCOMPLISHMENT OF TASK 422, AND 2465 HOURS SIN	CE LAST ACCOMPLISHMENT OF TASK 7610/05 (C-CHECK 5500 HR TASK) VISUAL INSPECTION OF ENGINE POWER AND CONDITION CONTROL CA	BLES AND PULLEYS. (TC NR 20060816005)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006101800084	20061018	00084	SO  	2006	10	18	CA060816006      	1	20060815	G	5330		SKIN            			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											(CAN) WHILE DOING A MOD TO THE AIRCRAFT THE ELT ANTENNA HAD TO BE REMOVED. THE AIRCRAFT SKIN WAS FOUND TO BE CRACKED ON 	2 SIDES OF THE ANTENNA. THE ANTENNA HAD NOT BEEN MOUNTED PROPERLY. (TC NR 20060816006)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006091300192	20060913	00192	GL  	2006	9	13	CA060817001      	2	20060710	G	7320	AN4H12A	BOLT            			CVAC  	STC   	STC3405800  	       	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	NR 2 FUEL	WORN            	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) THIS REPORT IS A FOLLOW-UP TO THE ORIGINAL VERBAL REPORT MADE IMMEDIATELY AFTER THE INCIDENT. THE AC LOST CONTROL 	OF THE NR 2 FUEL COORDINATOR AT THE TOP OF THE DECENT INTO YVR.  THE (E) HANDLE WAS PULLED ON THE NR 2 ENGINE 5 MILES BA	CK FROM THE YVR APPROACH AND THE AIRCRAFT LANDED SAFELY. ON EXAMINATION WE DISCOVERED THAT THE PINCH BOLT THAT HOLDS THE	 FUEL COORDINATOR ONTO THE NOTCH IN A SPLINED SHAFT HAD WORN TO A POINT THAT THE COORDINATOR ARM CAME ADRIFT FROM THE FU	EL COORDINATOR. WE HAVE CARRIED OUT A FLEET WIDE CAMPAIGN DIRECTIVE CHECKING ALL OUR IN-SERVICE CONVAIRS FOR BOLT CONDIT	ION AND THREAD DAMAGE. WE REPLACED 9 OUT OF 14 BOLTS DUE TO SLIGHT WEAR, AS A PRECAUTION. (TC NR 20060817001)	2	L	7	2 	4T	4	T	RT	6A6     	E282	6	C	P898	 
2006091300194	20060913	00194	CE  	2006	9	13	CA060817002      	1	20060328	G	2432	S35979	SENSOR          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					BATTERY	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			573  								(CAN)  INTERMITTENT FAILURE OF TEMPERATURE SENSOR CAUSING INDICATED OVERTEMP OF AIRCRAFT MAIN BATTERY FOR SEVERAL SECOND	S AT A TIME IN FLIGHT CAUSING MASTER CAUTION WARNING LIGHT ALSO.  REPLACED TEMPERATURE SENSOR, SYSTEM CHECKED OK.  NOTE 	THIS IS SECOND SENSOR TO FAIL IN 1284 HOURS. (TC NR 20060817002)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006091300197	20060913	00197	CE  	2006	9	13	CA060817003      	1	20060501	G	7830	25630005	SEAL            	PARKERHANFIN		CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					T/R ACTUATOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			1385 			1559					(CAN) IB THRUST REVRSER ACTUATOR LEAKING HYDRAULIC FLUID, GETTING PROGRESSIVELY WORSE, LEAKING FLUID TRAIL ON TR STANG. 	  IB STANG CANNOT BE REMOVED MAKING DIAGNOSIS OF PROBEM DIFFICULT.   REPLACED IB T/R ACTUATOR WITH OVERHAULED UNIT WHICH	 REQUIRED ENGINE TO BE REMOVED FROM THE AIRCRAFT.   (TC NR 20060817003)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006091300198	20060913	00198	NE  	2006	9	13	CA060817004      	2	20060518	G	7532	305265501	GASKET          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					BLEED VALVE	BROKEN          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			1390 								(CAN) ENGINE AT TAKEOFF AND CRUISE AT 40,000 FT AND ABOVE REQUIRED N2 TO BE HIGHER BY 1 - 1.5 PERCENT HIGHER THAN NORMAL	 FOR A SPECIFIC N1.   PROBELEM FOUND TO BE A COMPRESSOR BLEED VALVE NOT CLOSING COMPLETELY.  PROBLEM CAUSED BY LEAKING (	BROKEN) GASKET BETWEEN COMPRESSOR BLEED VALVE AND BLEED VALVE SERVO (TORK MOTOR).  (TC NR 20060817004)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006091300200	20060913	00200	CE  	2006	9	13	CA060817005      	1	20060619	G	2510	01073370	INERTIA REEL    	PACIFICSCIEN		CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					SEAT BELT	BROKEN          	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) COPILOT SHOULDER HARNESS (JAMS) WHEN EXTENDING:  FOUND PLASTIC END COVER OF INERTIA REEL BROKEN LOOSE, CAUSING INT	ERIM REEL TO MALFUNCTION. CAUSED BY COPILOT PUTTING FLIGHT MANUALS ETC BEHIND SEAT AND PUSHING SEAT AFT ON SEAT RAILS WH	ICH PUSHED SEAT BOTTOM SKIRT INTO INERTIA REEL.  - THIS IS TO BE CORRECTED BY EDUCATING THE (PILOTS) TO THE CAUSE OF THE	 PROBLEM AND THE REPLACEMENT OF THE INERTIA REEL.  (TC NR 20060817005)			2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006091300240	20060913	00240	EA  	2006	9	13	CA060817006      	2	20060804	G	8530	ST203	RING            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	CYLINDER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			506  	506  		104593					(CAN) THE TECHNICIANS OBSERVED AN ABNORMAL LOSS OF COMPRESSION ON SOME CYLINDERS FOLLOWING A ROUTINE INSPECTION. THEY RE	MOVED THE CYLINDERS AND SENT THEM TO OUR SHOP FOR INVESTIGATION. WE OBSERVED A DELAMINATION OF CHROME PLATING ON THE CYL	INDER RINGS. WE REPAIRED THE CYLINDERS BY REPLACING THE DEFECTIVE PARTS WITH A NEW PARTS. THE MANUFACTURER HAS BEEN ADVI	SED ABOUT THE DEFECTIVE RINGS.  (TC NR 20060817006)			1	L	7	2 	3O	3	O		1A10    	E14EA	5	C	P9EA	 
2006091300253	20060913	00253	EA  	2006	9	13	CA060817007      	2	20060817	G	8520		BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CRANKSHAFT	DAMAGED         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA				2209 				L793261A			(CAN) PILOTS NOTICED SMOKE COMING FROM THE LT ENGINE AFTER SHUTDOWN. THEY ALSO NOTICED AN OIL LEAK. FURTHER INVESTIGATIO	N REVEALED THAT ONE CRANKSHAFT BEARING HAD BEEN MOVED FROM ITS ORIGINAL PLACE AND WAS NOW LOOSE. THE ENGINE IS BEING REM	OVED FOR REPLACEMENT. A TEARDOWN REPORT WILL BE REQUESTED. (TC NR 20060817007)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006101800085	20061018	00085	NM  	2006	10	18	CA060818001      	1	20060803	G	2910	2890410115	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					HYD SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			33559								(CAN) HYD LINE IN UPPER FORWARD AREA OF NR 1 NACELLE CHAFED THROUGH AT ADJACENT ADELE CLAMP,  LEAKAGE LOCATED AND LINE A	SSY P/N 82970410-115 REPLACED, SYSTEM BLED AND REPRESSURIZED WITH NO FURTHER FAULTS. GOING THROUGH THE LAST 1 MONTH PERI	OD THERE HAVE BEEN NO RELATED DEFECTS IN REGARDS TO ATA 29 ON THIS A/C. THIS WAS AN ISOLATED INCIDENT NOT A RECURRING DE	FECT.  NO SDR IS REQUIRED OR SUBMITTED. LAST SCHEDULED INSP WAS THE DAILY INSP OF AUG 3 /06 AT TTAF 33549.3 HRS CURRENT 	TTAF ON A/C 33559.7 HRS. NEXT INSP, DAILY INSP DUE AUG 4 2006 L CHECK AUG 8 2006. (TC NR 20060818001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006101800086	20061018	00086	SW  	2006	10	18	CA060818002      	1	20060817	G	5300	S3526EC4	WASHER          			BELL  	407   	407         	1182206	SW  										ECU	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  THE -4 WASHER IS NOT CUT TO FIT THE BOLT AT THE SHANK, CAUSING FRETTING AND CORROSION ON THE SHANK RADIUS UNDER T	HE BOLT HEAD.   (TC NR 20060818002)					1	G	7	1 	3U			O	H2SW    					 
2006091300254	20060913	00254	SW  	2006	9	13	CA060818003      	1	20060803	G	5302	407530014101	SKIN            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1700 								(CAN) DURING SCHEDULED 150 HOUR TAILBOOM INSPECTION A CRACK MEASURING .7500 OF AN INCH LONG WAS DISCOVERED ON THE UPPER 	LT SIDE OF THE TAILBOOM AT STATION 98.89. AIRCRAFT WAS GROUNDED AND A NEW TAILBOOM WAS ORDERED (200 SERIES). (TC NR 2006	0818003)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006101800087	20061018	00087	SW  	2006	10	18	CA060818004      	1	20060814	G	6720	UK	BOLT            			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					TAIL ROTOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONT	ROL ROD.  INVESTIGATION REVEALED AN UNDERSIZED BOLT , IE SMALLER DIAMETER,  WAS INSTALLED.  THE CORREECT BOLT, P/N AN175	-20 WAS INSTALLED AND A FUNCTION CKECK CARRIED OUT, WITH NO FAULT FOUND.  AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060	818004)			1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2006091300255	20060913	00255	GL  	2006	9	13	CA060818005      	2	20060816	G	7230	6887167	CASE            	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1677 		CAC33790					(CAN) AIRCRAFT WAS IN FOR AN INSPECTION. THE COMPRESSOR CASE HALVES HAD 23 HOURS LT TO A 1750 INSPECTION. MFG REQUESTED 	THAT WE CARRY OUT THE INSPECTION. IT WAS FOUND THAT THE 2ND AND 3RD STAGE STATOR BLADES WERE SO UNDER CUT FROM EROSION (	NEAR THE ROOT OF THE BLADES) THAT A COMPRESSOR BLADE FAILURE WAS GOING TO OCCUR. IN SOME SPOTS THE PLASTIC LINEAR WAS ER	ODED TO THE BARE METAL. THE AIRCRAFT DOES HAVE A INTAKE PARTICLE SEPARATOR KIT INSTALLED. ANOTHER COMPRESSOR WAS INSTALL	ED. (TC NR 20060818005)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006101800088	20061018	00088	NE  	2006	10	18	CA060818006      	1	20060817	G	2913	66WBL200	BOLT            	NYAIRBRAKE  		SKRSKY	S61   	S61L        	8142102	NE  	GE    	CT58  	CT581401    	30011	NE  					HYD PUMP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				234  		A0259					(CAN) THE HYDRAULIC PUMP WAS BEING REMOVED FOR MAINTENANCE PLANNING, WHEN 2 BOLT HEADS WERE FOUND TO BE SHEARED OFF, AND	 HELD IN PLACE BY THE LOCK WIRE. PUMP WILL BE SENT TO VENDOR FOR INVESTIGATION. PUMP WAS OPERATING NORMALLY. (TC NR 2006	0818006)				2	G	7	2 	4U	4	U		1H15    	1E3				 
2006091300256	20060913	00256	CE  	2006	9	13	CA060821001      	1	20060812	G	3242	075302781	PLATE           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	LT BRAKE SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4000 								(CAN) TORQUE PLATE TOP GUIDE FOR BRAKE CALIPER CRACKED AND BROKE OFF LEAVING CALIPER ATTACHED BY BOTTOM GUIDE HOLE ONLY.	   PART REPLACED WITH NEW.  (TC NR 20060821001)					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2006091300257	20060913	00257	CE  	2006	9	13	CA060821002      	1	20060815	G	6123	C1650130604	WIRE HARNESS    	MCAULY      	3AF32C88    	CESSNA	310   	310Q        	2074242	CE  	CONT  	O520  	TSIO520B    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			CA						739222					(CAN) HARNESS TOO SHORT WOULD NOT ALLOW PROPELLER TO FEATHER. PILOT COULD NOT FEATHER LT OR RT PROPELLERS DURING TRAININ	G FLIGHT. WRONG PROPELLER DEICE WIRING HARNESSES FOUND INSTALLED AND REPLACED WITH CORRECT P/N D5855-1. (TC NR 200608210	02)				1	L	7	2 	3O	3	O		3A10    	E8CE	5	C	P22EA	 
2006091300259	20060913	00259	EA  	2006	9	13	CA060821003      	1	20060812	G	2810	21564002	FUEL CELL       			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14RF	14RF19      	NE  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1361 								(CAN) UPON INSPECTION IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE RT FUEL CELLS. ALL 8 FUEL CELLS WERE REMO	VED AND INSPECTED AND FUEL CELLS NRS 3 AND 4 AND 6 AND 8 WERE LEAKING  P/N AND S/N AND POSITION OF LEAKING CELLS. 215-64	002-4 S/N 74730 NR 3 CELL 215-64002 S/N 74770 NR 4 CELL 215-64002 S/N 74586 NR 6 CELL 215-64075-1 S/N 72476 NR 8 CELL. (	TC NR 20060821003)			2	H	7	2 	4R	4	T	RT	A14EA   	E20NE	6	C	P11NE	 
2007051600167	20070516	00167	EA  	2007	5	16	CA060821004      	2	20060808	G	7321	32447531917	FCU             			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 1 ENGINE	FAILED          	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER INSTALLING THE FRESHLY OVERHAULED ENGINE IN THE NR 1 POSITION, THE ENGINE WAS STARTED TO PERFORM THE BETA RI	GGING; THE PROPELLER WAS UNFEATHERED, THE POWER LEVEL MOVED UP TO THE FWD BETA STOP TO RECORD NUMBERS, ALL THE PARAMETER	S STABILIZED.  THE NUMBERS WERE ABOUT TO BE RECORDED WHEN THE FCU. FAILED, ALL ENGINE PARAMETERS ACCELERATED.  THE POWER	 LEVER WAS PULLED BACK AND THE ENGINE KEPT ACCELERATING. THE T-HANDLE WAS USED TO SHUTDOWN THE ENGINE. NO ENGINE LIMITS 	WERE EXCEEDED. THE FCU WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE FCU WAS FRESHLY OVERHAULED AND IT HAS BEEN	 RETURNED TO THE OVERHAUL FACILITY FOR REPAIR.  (TC NR 20060821004)	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006101800089	20061018	00089	CE  	2006	10	18	CA060821005      	1	20060812	G	7921	723747	BYPASS VALVE    	RAYTHN      		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	OIL COOLER	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1168 	1168 		6176					(CAN) RT OIL TEMPERATURE REACHED THE REDLINE WHEN CLIMBING THROUGH 25000 FT.  POWER REDUCED AND A/C DESENDED TO 20000 FT	. OIL TEMP RETURNED TO NORMAL.  ENG POWER SETTING RETURNED TO NORMAL, NO FURTHER FAULT.  NR 2 ENGINE OIL COOLER THRMOSTA	TIC BYPASS VALVE REPLACED IAW MM CH 79-00-00 P 9. GROUND/LEAK CHECKS PERFORMED. SYSTEM CHECKS SERVICEABLE.  (TC NR 20060	821005)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006091300260	20060913	00260	NE  	2006	9	13	CA060821006      	2	20060726	G	7230	4029T16P13P15	RETAINER        	GE          							GE    	CF34  	CF343B1     	 	NE  					FAN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						VARIOUS		807315C			(CAN) DURING ROUTINE SCHEDULED ENGINE MAINTENANCE, AFTER VISUAL, DIMENSIONAL, AND NON-DESTRUCTIVE INSPECTION, A HIGH NR 	OF FAN BLADE RETAINING PINS WERE REJECTED FOR CRACKING, DETAILS AS FOLLOWS:  ESN 807315C QTY 28 OF 28 P/N 4029T16P15 PIN	S CRACKED. ESN 872933 - QTY 18 OF 28 P/N 4029T16P13 PINS CRACKED. ESN 872934 - QTY 11 OF 28 P/N 4029T16P13 PINS CRACKED.	  FURTHER INVESTIGATION AND REVIEW  INDICATES THAT THE REJECT RATE FOR THESE COMPONENTS MAY BE UNUSUALLY HIGH ON THE SUB	JECT ENGINES.  DUE TO THE CRITICAL NATURE OF THE COMPONENT, HAVE INITIATED COMPONENT FAILURE INVESTIGATIONS.   PRODUCT S	UPPORT ENGINEERING HAS REPORTED THIS CONDITION TO THE FAA, REF. FM&D REPORT CF34-3/06-02. (TC NR 20060821006)						4	F			E15NE				 
2006091300261	20060913	00261	CE  	2006	9	13	CA060822001      	1	20060805	G	3246		BOLT            	BFGOODRICH  		CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					MLG WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6248 			1841					(CAN) ON DAILY INSPECTION, FOUND (1) BOLT BROKEN ON NR 4 MAIN WHEEL ASSY. (TC NR 20060822001)						2	L	7	2 	4F	4	F		A9NM    	E6WE				 
2006101800090	20061018	00090	EU  	2006	10	18	CA060822002      	1	20060818	G	3246	C201950001	WHEEL           			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2*    	 	GL  					MLG	CRACKED         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING THE AIRCRAFT PUSHBACK, IT WAS NOTED ON THE ECAM THAT NR 8 MAIN WHEEL WAS LOOSING PRESSURE. AFTER RETURNING 	TO THE GATE, IT WAS CONFIRMED USING A REGULAR TIRE PRESSURE GAUGE THAT THE PRESSURE WAS DROPPING. USING LEAK DETECTOR FL	UID, IT WAS DETERMINED TO BE LEAKING FROM A CRACK BETWEEN TWO TIE BOLTS IN THE OUTER HUB SECTION. WHEEL WAS REPLACED AND	 ROUTED TO THE REPAIR SHOP FOR INVESTIGATION.  (TC NR  20060822002)			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006101800091	20061018	00091	EU  	2006	10	18	CA060822003      	1	20060816	G	2910	A29181081000	LINE            			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2*    	 	GL  					HYDRAULIC SYS	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE INSPECTION, FOUND NR 1 ENGINE DRIVEN PUMP OUTLET PRESSURE TUBE OF GREEN HYDRAULIC SYSTE	M CHAFED BY THE AILERON TRIM INPUT CABLE AT REAR SPAR OB OF RIB 5A. HYDRAULIC TUBE REPLACED. CAMPAIGN INITIALIZED TO VER	IFY THE REST OF THE FLEET AND ALL FINDING WILL BE REPORTED TO MFG FOR EVALUATION.  (TC NR 20060822003)				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006091300263	20060913	00263	NM  	2006	9	13	CA060822004      	1	20060727	G	7160	001A716E1000010	INTAKE          			DORNER	DO32  	DO328100    	2996000	NM  										NR 1 ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4393 								(CAN) OUR AC WAS ABOUT TO DEPART WHEN DEFECT WAS SPOTTED.  DURING A NORMAL PRE-FLIGHT PILOT WALK AROUND OUR PILOT NOTICE	D A GAP/ ABNORMAL SPACE BETWEEN THE LOWER ENGINE INLET AND THE UPPER MATING COWL.  WE GROUNDED THE A/C TO AOG STATUS AND	 SENT AME`S TO RESCUE.  AME`S DISCOVERED QTY. 3 MISSING MOUNTING HARDWARE BOLTS, NUTS AND WASHERS, WHICH ARE STILL MIA. 	 ALSO QTY. 1 MOUNTING BOLT WAS FOUND STILL IN PLACE BUT WAS SHEARED OFF COMPLETELY AND THE APPARENT STRESS CAUSED THE EN	GINE METAL MATING FLANGE TO BREAK A 1 INCH DIA. APPROX SECTION OFF AT THE FWD. OB AREA.  AME REPLACED THE LOWER INLET AS	SY. WITH SAME P/N AND S/N AND ADDED THE WIDER WASHERS MINOR REPAIR IAW MM 72-20-00-300-801-A01-001.  A (SPR)  SERVICE PR	2	H	7	2 	4T			RT	A45NM   					 
2006091300264	20060913	00264	NM  	2006	9	13	CA060822005      	1	20060822	G	2710	BACP30F9	PULLEY          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					RT AILERON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE CHECK, A GRINDING NOISE WAS HEARD WHEN THE AILERON WAS MOVED BY HAND TO CHECK FOR FREEDOM OF MOVEME	NT. UPON FURTHER INVESTIGATION,THE BOLT HOLDING THE PULLEY IN PLACE WAS REMOVED AND THE BEARING FELL APART.  BEARING WAS	 SEVERELY CORRODED AND BUSHING FOUND TO BE GOUGED.  PULLEY AND BUSHING REPLACED.  TIMES:  36,972.52  CYCLES: 23,427 (TC 	NR 20060822005)			2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006101800092	20061018	00092	CE  	2006	10	18	CA060822006      	1	20060822	G	5311	504200285758	FRAME           			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BS 176	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22986								(CAN) LT SIDE OF FUSELAGE, DISCOVERED 4 LOOSE RIVETS AT FS 176.5. MAINTENANCE DEPT REMOVED INTERIOR TO INVESTIGATE DEFEC	T.  IT WAS DISCOVERED THAT FRAME MEMBER P/N  50-420028-57 WAS CRACKED IN SEVEN SPOTS.  MAINTENANCE DECIDED TO INVESTIGAT	E THE RIGHT HAND OF FUSELAGE EVEN THOUGH NO INDICATION FROM OUTSIDE OF AIRCRAFT.  ONLY THREE CRACKS WERE DISCOVERED THER	E TO FRAME P/N  50-420028-58.  TOTAL CYCLES SINCE LAST DETAILED FUSELAGE INSPECTION OF THESE AREAS IN 1859.  REPETITIVE 	EVERY 3000 CYCLES.  NO PREVIOUS DAMAGE NOTED. (TC NR 20060822006)		1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
2006101800093	20061018	00093	GL  	2006	10	18	CA060822008      	1	20060814	G	2820	C2P2009	LINE            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION, NOTICED FUEL PIPE FROM PUMP TO SHUT-OFF VALVE (BEHIND ENGINE) STAINED GREEN, FOUND CLEARANCE BETWEE	N PIPE AND RUDDER PEDAL TQ TUBE INSUFICIENT CAUSING FRETTING/DISSIMILAR CORROSION PITTING ON TUBE CAUSING FUEL LEAK (TC 	NR 20060822008)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006101800094	20061018	00094	NM  	2006	10	18	CA060823001      	1	20060823	G	2710	BACP30F9	PULLEY          			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					LT AILERON	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE CHECK THE LT AILERON CABLE PULLEY WAS FOUND TO HAVE A SEIZED BEARING AND A WORN PULLEY.  PULLEY AND	 BEARING REPLACED.  A FLEET CAMPAIGN WILL BE INIATED TO CHECK ALL AILERON PULLEYS FOR FREEDOM OF MOVEMENT AND BEARING CH	ECK.  TIMES:  36,972.52  CYCLES:  23,427 (TC NR 20060823001)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006101800095	20061018	00095	GL  	2006	10	18	CA060823002      	3	20060822	G	6114		HUB             			LKHEED	188   	188LKHEED*  	       	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	PROPELLER	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA				659  					HC2555		(CAN) RPM DROOPED TO 13,400 RPM. ENGINE SHUTDOWN AND LANDING IAW SOP. PROP OIL LEAKING OUT OF VENT HOLE IN PROPELLER HUB	. (TC NR 20060823002)					2	L	7	4 	4T	4	T		4A22    	E282	6	C	P898	 
2006121300139	20061213	00139		2006	12	13	CA060824002      	1	20060821	G	3246	50140251	RETAINING RING  																	MAIN WHEEL	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING SHOP VISIT AND UPON DISASSEMBLY FOR TIRE REPLACEMENT, RETAINING RING FOR THE OUTER WHEEL HALF FOUND SPLIT A	XIAL APPROXIMATELY 60 PERCENT OF ITS CIRCUMFERENCE. (TC NR 20060824002)																		 
2006091300268	20060913	00268	WP  	2006	9	13	CA060824003      	2	20060818	G	7322	8978017	FUEL CONTROL    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA				2552 							(CAN) UPON LANDING, CREW APPLIED REVERSE THRUST.  BELOW 70 KIAS, THE RPM LEVER WAS SELECTED TO (LOW).  ON THE TAXIWAY, T	HE CREW NOTED VERY LOW ENGINE RPM, LOW OIL PRESSURE LIGHT, AND LOW EGT.  THEY DETERMINED THE ENGINE HAD FLAMED OUT AND P	ARTIALLY RESTARTED.  A NORMAL SHUTDOWN WAS CARRIED OUT.  A SUBSEQUENT MAINTENANCE GROUND RUN WAS ABLE TO DUPLICATE THE F	AILURE, WHEN THE SPEED LEVER WAS RAPIDLY MOVED FROM HIGH TO LOW.  THE FUEL CONTROL AND FUEL PUMP WERE REPLACED WITH SERV	ICEABLE UNITS. (TC NR 20060824003)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2006091300269	20060913	00269	SW  	2006	9	13	CA060824004      	1	20060822	G	2910	2781006495	LINE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS IN CRUISE, CREW NOTED HYDRAULIC LEAKAGE ON THE COCKPIT FLOOR.  CONDUCTED A NORMAL LANDING, NOSE GEAR 	UP LINE IN COKPIT WAS LEAKING. REPLACED LINE, ON NEXT LEG, A LINE FAILED IN THE LH GEAR WELL, CREW ACTIVATED EMERGENCY E	XTENSION AND NORMAL LANDING CARRIED OUT.  THE FOLLOWING DAY ANOTHER LINE CRACKED IN THE WHEEL WELL.  MAINTENANCE SERVICE	D THE ACCUMULATOR AFTER THE SECOND OCCURENCE AND NOTED THE PRESSURE WAS LOW.  AFTER THE THIRD OCCURENCE, THE ACCUMULATOR	 WAS REPLACED AS A PRECAUTION. NO OTHER OCCURENCES THAT WEEK.  ON THE WEEKEND, MAINTENANCE PLACED THE AIRCRAFT ON JACKS,	 AND FOUND SMALL PRESSURE FLUCTUATIONS DUE TO A FAILED MAIN GEAR UPLOCK POWER PACK SWITCH.  THE SWITCH WAS REPLACED, THE	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2006101800096	20061018	00096	NM  	2006	10	18	CA060825001      	1	20060822	G	2997	W44000118	WIRE            			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					HYD PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50063								(CAN) LT ELECTRIC HYDRAULIC PUMP PRESSUE SWITCH S27 WIRING FOUND CHAFED 6 INCHES FROM CONNECTOR D56, WIRING TEMPORARILY 	REPAIRED IAW AMM FAULT WAS INTERMITTENT AND 4 S27 PRESSURE SWITCHS HAD BEEN REPLACED OVER THE LAST FEW MONTHS. (TC NR 20	060825001)				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2006091300270	20060913	00270	CE  	2006	9	13	CA060825002      	1	20060823	G	5520	07321008	HINGE           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3522 								(CAN) HINGE ASSEMBLY FOR STABILIZER OB BEARING WAS FOUND CRACKED FOR BOTH ELEVATORS.  ELEVATORS REMOVED.  SEVERAL CRACKS	 WERE FOUND ON EACH HINGE ASSEMBLY.  HINGE ASSEMBLIES REPLACED ON STABILIZER. ALL PARTS INSTALLED USING NEW (AN) HARDWAR	E.  INDEPENDENT CONTROL CHECK CARRIED OUT. (TC NR 20060825002)				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2006091300271	20060913	00271	CE  	2006	9	13	CA060825003      	1	20060513	G	5511	053200198	SPAR            			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175*      	GL  	STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14693								(CAN) P/N 0532001-97 SPAR REINFORCEMENT AND P/N 0532001-98 FRONT SPAR ASSEMBLY WAS REPALCED DUE TO CRACKED CENTER SECTIO	N OF MAIN SPAR.  PARTS WERE INSTALLED USING EXISTING RIVET SIZE AND PATTERN ACCORDING TO SPECIFIED APPROVED METHODS IN M	FG SRM. (TC NR 20060825003)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2006091300272	20060913	00272	CE  	2006	9	13	CA060825004      	1	20060820	G	7830	183238001	SOLENOID        			CESSNA	750   	750         	2076810	CE  										THRUST REVERSER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND THAT THE SOLINOID SHAFT HAD BEEN GROUND DOWN TO ACCOMIDATE A CLEVIS PIN THAT WAS NOT LONG ENOUGH. HALF THE M	ATERIAL ON THE SHAFT HAD BEEN REMOVED. THIS WAS FOUND ON INSPECTION OF THE TR SYSTEM FOR STICKY TR LEVERS. AT THIS TIME 	WE DO NOT THINKING THAT IT HAD ANY THING TO DO WITH THE ORIGINAL SNAG. (TC NR 20060825004)				2	L	7	2 	4J			RT	T00007WI					 
2006091300274	20060913	00274	NE  	2006	9	13	CA060828001      	2	20060828	G	7314	6052T06P05	PUMP            			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					ENGINE FUEL	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			5621 	2673 							(CAN) LT MAIN AND SCAVENGE EJECTOR FAILURE (MOTIVE FLOW FAILURE). FUEL PUMP SHAFT  FOUND BROKEN. FUEL PUMP REPLACED AND 	AIRCRAFT RETURNED TO SERVICE.  A/C HOURS;  25194:25 CYCLES; 29896  (TC NR 20060828001)					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006101800097	20061018	00097	CE  	2006	10	18	CA060828002      	1	20060828	G	3230	25800	SELECTOR VALVE  			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE SCHEDULED TASK TO LEAK CHECK THE LANDING GEAR SYSTEM (LANDING GEAR MM M-8101, ROUTINE MAINTENANCE) IT W	AS NOT POSSIBLE TO BUILD PRESSURE IN THE LANDING GEAR HYDRAULIC SYSTEM WITH THE MANUAL PUMP INSTALLED. UPON INVESTIGATIO	N IT WAS FOUND THAT FLUID WAS BEING ROUTED TO THE DOWN PORT AND THE RETURN PORT AT THE SAME TIME. ELECTRICAL POWER WAS O	N THE AIRCRAFT AND THE LANDING GEAR SELECTED TO THE DOWN POSITION. THIS VALVE HAD BEEN PREVIOUSLY REMOVED FROM ANOTHER S	IMILAR TYPE AIRCRAFT FOR THE SAME PROBLEM AND WAS REPAIRED. REF NR ASR-6188-011605. WHEN CYCLED USING THE AIRFRAME SYSTE	M HYDRAULIC PUMP THE LANDING GEAR OPERATED CORRECTLY AND APPEARED TO NOT HAVE AN FAULTS. (TC NR 20060828002)	1	L	7	2 	3T	3	T		3A20    	E4EA	6	C	P15EA	 
2006101800098	20061018	00098	CE  	2006	10	18	CA060828003      	1	20060828	G	3230	25800	SELECTOR VALVE  			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON SCHEDULED  MAINTENANCE 1000 HRS HYD. SYSTEM 3000 PSI LEAK TEST  (LANDING GEAR MM M-8101, ROUTINE MAINTENANCE) H	YD. SELECTOR FOUND LEAKING TO RETURN ON GEAR DOWN SECTION. WAS UNABLE TO BUILD UP PRESSURE TO OPERATE GEAR WITH MANUAL E	XTERNAL PUMP. NEW HYD. SELECTOR INSTALLED AND IT WAS FOUND LEAKING TO RETURN ON GEAR UP SELECTION. WHEN LANDING GEAR CYC	LED WITH AIRCRAFT HYD.PUMP SYSTEM OPERATES NORMALLY. SUSPECT  NOT TESTING HYD. SELECTOR VALVES BOTH OLD AND NEW VALVES O	VERHAULED BY THEM. (TC NR 20060828003)		1	L	7	2 	3T	3	T		3A20    	E4EA	6	C	P15EA	 
2006101800099	20061018	00099	WP  	2006	10	18	CA060828004      	1	20060827	G	6420		BEARING         	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					T/R PITCH LINK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			53   								(CAN) PITCH LINKS WERE FOUND TO BE CONTACTING THEIR SPACERS, CAUSING THEM TO WEAR INTO THE STAKING AROUND THE BEARING ON	 THE PITCH LINKS.  TAFT 53.1 HOURS.  ALL HARDWARE WAS PROPERLY INSTALLED. (TC NR 20060828004)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006101800100	20061018	00100	WP  	2006	10	18	CA060828005      	1	20060826	G	6420		BEARING         	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					T/R PITCH LINK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			162  								(CAN) PITCH LINKS WERE FOUND TO BE CONTACTING THEIR SPACERS, CAUSING THEM TO WEAR INTO THE STAKING AROUND THE BEARING ON	 THE PITCH LINKS.  TAFT 161.6 HOURS.  ALL HARDWARE WAS PROPERLY INSTALLED.  THIS WAS THE SECOND OCCURENCE OF THIS ON OUR	 FLEET IN 2 DAYS.  THE MFG HAS RECENTLY CHANGED THE PART FROM B345-2 TO B345-4.  THE INSTALLATION IS THE SAME.  THIS WAS	 NEVER A PROBLEM WITH THE -2 PART. (TC NR 20060828005)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006101800101	20061018	00101	SW  	2006	10	18	CA060829001      	1	20060829	G	2910	AN937D6	FITTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYD SYSTEM	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, A LEAK WAS DISCOVERED IN THE HYDRAULIC SYSTEM PRESSURE SIDE CROSS FITTING (AN 937-D6). DISASSEM	BLY REVEALED CORROSION AT MATING SURFACE OF O-RING AND CROSS. PART REPLACED WITH NEW.  O-RINGS AND RETAINING RING REPLAC	ED. SYSTEM SERVICED WITH HYDR OIL. (TC NR 20060829001)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006091300277	20060913	00277	EA  	2006	9	13	CA060829002      	2	20060828	G	8550	982C9HE2	ENGINE          			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	NR 2	OVERTEMP        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA				341  							(CAN) AIRCRAFT DEPARTED ENROUTE TO A FIRE. PILOT NOTED THE OIL TEMP ON NR 2 ENGINE WAS VERY HIGH. THE ENGINE WAS SHUTDOW	N AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED AND LANDED. UPON INVESTIGATION BY MAINTENANCE STAFF, THE MAIN O	IL SCREEN WAS FOUND TO BE CONTAMINATED WITH BRONZE MATERIAL. IT APPEARS THAT THE MAIN BEARING FAILED. THE ENGINE IS BEIN	G REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20060829002)			2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2006101800102	20061018	00102	EU  	2006	10	18	CA060829003      	1	20060825	G	3244	308419030	TIRE            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON DEPARTURE A PIECE OF TIRE WAS FOUND ON THE RUNWAY. THE AIRCRAFT CARRIED OUT A NORMAL LANDING WITHOUT FURTHER IN	CIDENT. MAINTENANCE REPLACED NR 1 AND 2 MAIN WHEEL ASSYS, AND THE LT MAIN GEAR DOOR DUE TO DAMAGE FROM THE DEPARTED TREA	D SEGMENT (APPROX. 12 INCH X 3 INCH) BEFORE RETURNING THE AIRCRAFT TO SERVICE. (TC NR 20060829003)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006091300280	20060913	00280	NM  	2006	9	13	CA060829004      	1	20060805	G	2730	69403483	BEARING         			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					ELEVATOR CONTROL	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			64027								(CAN)  AIRCRAFT ENCOUNTERED INTERMITTENT REPEAT SNAGS FOR STIFF ELEVATOR MOVEMENT.  FINAL RECTIFICATION CAME ON AUGUST 5	 2006 WHEN THE REFERENCED BEARING AND RETAINER WERE REPLACED.  REFERENCED BEARING WAS FOUND SEIZED.  CURRENT MAINTENANCE	 PROGRAM WAS REVIEWED TOWARDS THIS FINDING.  INSP TASKS ARE CONDUCTED EVERY C CHECK.  HAS MFG HAD OTHER REPORTS OF STIFF	 ELEVATORS DUE TO THE REFERENCED BEARING.  2) IF SO, DOES MFG HAVE THE TOTAL TIME OF THE AIRCRAFT WITH THOSE REPORTS. (I	E TO DETERMINE IF A LIFE LIMIT EXISTS)  3) MAINTENANCE C CHECK TASKS UTILIZE AMM 27-31-0.  AMM D6-12010 IS USED FOR THE 	AIRCRAFT INVOLVED.  AMM 27-31-0 PAGE 535 2.B CONTAINS SPRING SCALE LIMITS FOR DIFFERENT ELEVATOR DEFLECTIONS (HYDRAULICS	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006101800103	20061018	00103		2006	10	18	CA060829005      	4	20060811	G	2565	GOODRICH	SLIDE           			BOEING	767   	767*        	       	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  						NO TEST         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTION OF OFF-WING SLIDE COMPARTMENT DOOR LATCHES AND DISCONNECT HOUSING IAW SB 767-25A0260, 	BOTH OFF-WING SLIDES WERE INFLATED WITHOUT THE ASSOCIATED SLIDE COMPARTMENT DOOR BEING COMMANDED OPEN.   AS A RESULT THE	 COMPARTMENT DOORS, LATCHES, SLIDES AND IB FLIGHT CONTROLS WERE DAMAGED BY THE FORCE OF THE CONFINED SLIDES. ZOOM AIRLIN	ES HAS HAD 2 PREVIOUS SIMILAR UNCOMMANDED OFF-WING SLIDE DEPLOYMENTS (JULY 29, 2005 AND SEPTEMBER 2, 2005) DURING ROUTIN	E MAINTENANCE.   IN BOTH PREVIOUS INCIDENTS ZOOM HAS INVESTIGATED AND TAKEN MITIGATING ACTIONS. MFG IS WELL AWARE OF THE	 SERVICE RELATED PROBLEMS. REF  767-FTD-25-00004, 767-FTD-25-03003,  767-FTD-25-06001.  ZOOM`S TCCA PMI HAS ASKED THAT T	2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2006091300281	20060913	00281	EU  	2006	9	13	CA060830001      	1	20060828	G	2750	9787320016	WARNING SYSTEM  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				159  							(CAN) 1 HR INTO CRUISE AT FL 220 PILOT EXPERIENCED INSTANTANEOUS AURAL AND VISUAL WARNINGS OF MULTIPLE SYSTEMS FAILURE. 	CAUTION ADVISORY PANEL DISPLAYED PUSHER INOP, FLAPS INOP, AUTO PILOT FAIL; FLAP POSITION INDICATOR JUMPED FROM 0 DEG TO 	40 DEG.ALSO INDICATING RED OVERSPEED, EADI FAILED TO RAW DATA ONLY ,GEAR INDICATOR LIGHTS WENT TO THREE RED/ UNSAFE,GEAR	 AND FLAP WARNING TONES AUDIBLE. AFTER APPX. 20 MIN. ALL SYSTEMS SUDDENLY REVERTED TO NORMAL EXCEPT FOR THE FLAPS WHICH 	REQUIRED A FLAP RESET BY MAINTENANCE FLAPS THEN FUNCTION NORMALLY.PILOT COMPLETED FLIGHT AT ZERO FLAP.MAINTENACE TROUBLE	SHOOTING IDENTIFIED ONE FAULT CODE ON A/C COMPUTER INDICATING A POSSIBLE FLAP CONTROL WARNING UNIT  ERROR.THE FCWU WAS R	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006091300282	20060913	00282	EA  	2006	9	13	CA060830002      	1	20060817	G	7810		NOZZLE          			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT ENG EXHAUST	DETACHED        	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			4032 								(CAN) DURING ENGINE START-UP, AN OVERHEAT CONDITION WAS DETECTED IN THE RT ENGINE EXHAUST AREA. THE ENGINE WAS SHUTDOWN 	AND CAUSE OF OVERHEAT INVESTIGATED. THE INVESTIGATION REVEALED THAT A SECTION OF PRIMARY EXHAUST NOZZLE WAS COMPLETLY MI	SSING AND WAS EXPELLED THROUGH THE SECONDARY DUCT. THERE WERE NO OTHER DAMAGES FOUND. AN INVESTIGATION AS TO CAUSE OF TH	E PROBLEM WILL BE MADE BY MFG.  (TC NR 20060830002)			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006101800133	20061018	00133	SO  	2006	10	18	CA060830003      	1	20060829	G	2750	486597	DRIVE ASSY      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT FLAP	SHEARED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) DURING APPROACH AND FLAP EXTENSION TO 5 DEGREES CREW NOTICED AIRCRAFT ROLL TO THE RT AND OBSERVED THAT THE RT FLAP	 HAD NOT EXTENDED. THE LANDING WAS UNEVENTFUL. MAINTENANCE INVESTIGATION REVEALED THE RT FLAP DRIVE CABLE SPLINES AT THE	 MOTOR END WERE WORN AWAY. THE RT FLAP DRIVE CABLE ASSY WAS REPLACED AND OPERATION CHECKED NORMAL. (TC NR 20060830003)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006091300283	20060913	00283	NM  	2006	9	13	CA060831002      	1	20060827	G	3220	8800121	STRUT           			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	CRACKED         	W				J				DUMP FUEL               				O			OTHER                     			IN	INSP/MAINT     	1			CA			39456	15435							(CAN) DURING A SCHEDULED MAINTENANCE CHECK, TASK CARD 3220/01 AND 02 VISUAL INSPECTION AND LUBRICATION OF NLG ASSY, A CR	ACK WAS DISCOVERED IN THE NLG SHOCK STRUT HOUSING. THE NLG ASSEMBLY WAS IMMEDIATELY REPLACED.  TSN=39456.7HRS / CSN=4672	3CYC TSO=15435.7HRS / CSO=13147CYC TSI=799.0HRS / CSI=590CYC (TC NR 20060831002)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006101800138	20061018	00138	GL  	2006	10	18	CA060831004      	2	20060828	G	7200		ENGINE          			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  						POWER LOSS      	W				R				AUTOROTATION            				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AIRCRAFT LOST POWER RESULTING IN A HARD LANDING. DATE OF OCCURRENCE, JUNE 26, 2006.  ROTORCRAFT LOST ENGINE POWER 	AT APPROX 400 FEET AND AUTOROTATED. AIRCRAFT IS CONSIDERED A TOTAL WRITE-OFF. TSB CURRENTLY INVESTIGATION ROOT CAUSE OF 	THIS EVENT.   (TC NR 20060831004)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006091300336	20060913	00336	NM  	2006	9	13	CA060831006      	1	20060707	G	6123	D59901	HYDRAULIC SYSTEM	HARTZL      		DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	PROPELLER	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			4293 			HL316					(CAN) AIRCRAFT READIED AND RT ENGINE START PARAMETERS NORMAL.  RT CONDITION LEVER ADVANCED TO MIN.  RT PROP DOES NOT UNF	EATHER.  RT CONDITION LEVER RETARDED TO FEATHER.  RT CONDITION LEVER ADVANCED TO MIN.  RT PROP DOES NOT UNFEATHER.  MAIN	TENANCE CALLED TO SIGHT FOR  INVESTIGATION AND TROUBLESHOOTING.  PASSENGERS CHARTERED.  AIRCRAFT GROUNDED FOR 3 DAYS.  R	T HYDRAULIC UNIT D-5990-1 SN S296 UNSERVICEABLE.  SN S296 TSN 4293.1.  RT HYDRAULIC UNIT D-5990-1 REPLACED WITH OVERHAUL	ED UNIT SN S53.  HYDRAULIC UNIT SN S53 TSN 12735.5. (TC NR 20060831006)		2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2006101800139	20061018	00139	NM  	2006	10	18	CA060901002      	1	20060831	G	2920		PRESSURE SWITCH 			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					FLT CONTROL MODU	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY ONE FLIGHT HOUR ENROUTE THE (B) SYSTEM FLIGHT CONTROL MODULE LOW PRESSURE LIGHT ILLUMINATED. AIRCRAF	T TURNED BACK.  (B) SYSTEM FLIGHT CONTROL MODULE REPLACED DUE TO LOW PRESSURE SWITCH UNSERVICEABLE.  TIMES- 37968:59   C	YCLES: 23555 (TC NR 20060901002)				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006091300344	20060913	00344	GL  	2006	9	13	CA060901003      	2	20060823	G	7320	76715	FADEC           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RT ENGINE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			424  								(CAN) THE RT ENGINE FADEC CHANNEL A FAULT LIGHT ILLUMINATED. MAINTENANCE ACCESSED FADEC DATA AND DOWNLOADED FAULT CODES.	 FAULT CODES FORWARDED TO MFG, DURING TELEPHONE CONVERSATION WITH MFG OF AC AND ENG, IT WAS DETERMINED THAT THE FADEC HA	D AN INTERNAL FAULT. AC MFG SENT A FIELD SERVICE TECHNICIAN WHO REPLACED THE FADEC AND AFTER GROUND RUNS THE SYSTEM WAS 	SERVICEABLE. (TC NR 20060901003)			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006091300345	20060913	00345	NE  	2006	9	13	CA060901004      	2	20060823	G	8530	399359CR	CYLINDER HEAD   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	NR 2 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1174 				2P103622			(CAN) FOUND CRACK ON NR 2 CYLINDER HEAD AT EXHAUST ROCKER HOUSING WHILE CHECKING OIL LEAK AT OTHER POSITIONS. CRACK WAS 	NOT DETECTED AT THE LAST 100 HOUR INSPECTION. 33.5 HOURS PAST. (TC NR 20060901004)					1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2006101800140	20061018	00140	SW  	2006	10	18	CA060901005      	1	20060818	G	6340		BEARING         			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	TACH GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			450  			86342					(CAN) A NOISE WAS DETECTED AND THE TACH GENERATOR WAS REMOVED AND FOUND THAT THE LOWER SHAFT BEARING WAS BADLY WORN. (TC	 NR 20060901005)					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2006091300346	20060913	00346	WP  	2006	9	13	CA060901006      	2	20060831	G	7320	3055383	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					COCKPIT	ODOR            	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA				78   							(CAN) CREW NOTED BEFORE TAKEOFF A BURNING SMELL IN THE COCKPIT PRIOR TO TAKEOFF.  NO SYSTEM FAULTS WERE NOTED OR BREAKER	S POPPED AND THE SMELL WENT AWAY, SO THE FLIGHT CONTINUED IT`S LAST LEG.  NO FAULTS NOTED IN FLIGHT.  IT WAS LATER DISCO	VERED A SPEED SWITCH HAD FAILED.  THIS WAS DETERMINED TO BE THE CAUSE OF THE ELECTRICAL SMELL.  THIS UNIT HAD 77.5 HOURS	 TSO HOURS AND IS ONE OF A NUMBER OF FAILED SWITCHES FROM THIS VENDOR. (TC NR 20060901006)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2006091300347	20060913	00347	SO  	2006	9	13	CA060901007      	2	20060822	G	8530	T1ST712ACA	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	CYL NR 5	SCORED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1019 	1019 		69166EAB					(CAN) THE PILOT REPORTED AN IMPORTANT OIL LEAK TO THE AMO. AFTER INVESTIGATION, THE TECHNICIAN DISCOVERED THE SOURCE TO 	BE FROM  NR 5 CYLINDER BARREL O-RING. THE PISTON WAS FOUND DAMAGED, SCORED, PROBABLY CAUSED BY EXCESSIVE HEAT. PARTS REP	LACED. (TC NR 20060901007)				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006091300348	20060913	00348	NM  	2006	9	13	CA060901008      	1	20060818	G	3231		SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG DOOR	SHORTED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE LANDING GEAR STARTED TO CYCLE BY ITSELF AND SEVERAL GEAR DOOR AND GEAR UNSAFE ADVISORY LIGHTS WE	RE ILLUMINATED. ACCORDING QRH ALTERNATE GEAR EXTENSION PERFORMED. NORMAL LANDING PERFORMED. A/C HANDED OVER TO MAINTENAN	CE FOR FURTHER INVESTIGATION. INVESTIGATION FOUND THE NLGDCL SENSOR SHORTED. REPLACED NLG DOOR CLOSED SENSOR (S19) IAW F	IM TASK AND PERF RIGGING OF PROXIMITY SENSOR. ALL READINGS WITHIN LIMIT. THE DAMAGE OF THE NLG DOOR CLOSED SENSOR HARNES	S WAS CAUSED BY A BOLT WHICH IS INSTALLED IN THE WRONG DIRECTION. BOLT REPLACED AND DIRECTION INVERTED IAW MODSUM ISQ320	0003.  BOLT INSTALLATION IS CORRECTLY SHOWN IN IPC/AMM. (TC NR 20060901008)	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006101900111	20061019	00111	SW  	2006	10	19	CA060901009      	1	20060901	G	7797	MS3451L10SL4P	CONNECTOR       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	CORRODED        	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) EGT INDICATION WAS ERRATIC ON LANDING. ALL OTHER PARAMETERS WERE NORMAL. THERE WAS HEAVY PRECIPITATION PRIOR TO TH	E ERATIC INDICATION.  THE CONNECTOR PLUG WAS CLEANED AND RETURNED TO SERVICIBLE CONDITION.  EGT INDICATION WAS NOT ERATI	C AND AIRCRAFT RETURNED TO SERVICE. (TC 20060901009)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007012900317	20070129	00317	CE  	2007	1	29	CA060903001      	1	20060624	G	2497		WIRE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELECTRICAL SYS	IMPROPER        	W				D				RETURN TO BLOCK         				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) OVERVOLTAGE LIGHT FOUND WIRED TO SYSTEM WITH UNAPPROVED AUTOMOTIVE WIRING. THIS WIRING DISCONNECTED, AND CAUSED A 	DEAD SHORT TO THE SYSTEM. (TC NR 20060903001)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006101900112	20061019	00112	NE  	2006	10	19	CA060905001      	2	20060905	G	7414	1052947	SHAFT           	CONT        		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1005 		B140011ER					(CAN) DURING A 500 HOUR INSPECTION, THE LOWER BEARING INNER RACE WAS FOUND LOOSE ON THE SHAFT.  THE BEARING INNER RACE H	AD BEEN SPINNING ON THE SHAFT CAUSING SHAFT JOURNAL TO WEAR. (TC NR 20060905001)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006101900113	20061019	00113	SO  	2006	10	19	CA060905002      	1	20060830	G	3210	AN626	BOLT            	PIPER       	1003306     	PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE FORWARD LT LANDING GEAR ATTACH BOLT WAS LO	OSENED IN THE FUSELAGE ATTACH FITTING. CLOSER EXAMINATION FOUND THE BOLT TO BE SHEARED ABOUT HALF WAY DOWN THE SHANK OF 	THE BOLT. ALL FOUR LANDING GEAR ATTACHMENT BOLTS WERE REMOVED AND REPLACED WITH NEW BOLTS. THE OTHER 3 BOLTS SHOWED SIGN	S OF WEAR BUT ONLY THE ONE HAD SEPARATED. (TC NR 20060905002)			1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
2006091300349	20060913	00349	CE  	2006	9	13	CA060905003      	1	20060831	G	2121	99101133	FAN BLADE       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COOLING FAN	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN PILOTS WERE USING FLOOD COOLING  ON THE GROUND THEY HEARED A NOISE AND HAD A VIBRATION THEY SHUT THE SYSTEM D	OWN . AFTER MAINTENANCE REMOVED THE FLOOD COOLING FAN MOTOR ASSY THEY FOUND A BROKEN FAN BLADE . THEY REPLACED FLOOD COO	LING FAN MOTOR ASSY P/N OFF/ON 9910113-3 S/N ON 0019  GROUND CHECKED SERVICEABLE  AND RETURNED AIRCRAFT TO SERVICE.  (TC	 NR 20060905003)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006091400005	20060914	00005	EU  	2006	9	14	CA060905004      	1	20060902	G	5554	555401203	RIB             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RUDDER	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A WALK AROUND ON THE AIRCRAFT, THERE WAS LOTS OF PLAY FOUND AT THE UPPER ATTACHMENT BOLT ON THE RUDDER	.  THE BOLT HAD ELONGATED THE HOLE AND DAMAGED THE NOSE RIB.  WHEN TRYING TO TAKE THE BOLT OUT, THE NUT PLATE BROKE AWAY	 AND A PIECE OF THE NOSE RIB THAT IT WAS RIVETED TO WAS ALREADY CRACKED FROM SO MUCH PLAY IN THE UPPER ATTACHMENT THAT I	T WAS WHAT ACTUALLY BROKE AWAY WITH THE NUT PLATE.  THE UPPER BEARING WAS ALSO DAMAGED.  THE BOLT HEAD HAD TO BE CUT OFF	 TO GET BOLT OUT. THE RUDDER WAS REMOVED AND ANOTHER INSTALLED TO MAKE THE AIRCRAFT AIRWORTHY AGAIN.  THE DAMAGED RUDDER	 IS NOW AWAITING PARTS TO FACILITATE A REPAIR. (TC NR 20060905004)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006091400006	20060914	00006	EU  	2006	9	14	CA060905005      	1	20060902	G	5340	5531012326	BRACKET         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD ACTUATIOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A WALKAROUND ON THE AIRCRAFT THERE WAS A CRACK FOUND ON THE UPPER ATTACHMENT BRACKET IN THE NOSE GEAR 	BAY THAT THE NOSE GEAR HYDRAULIC ACTUATOR ATTACHES TO.  BRACKET REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 200609	05005)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006091400007	20060914	00007	NE  	2006	9	14	CA060905006      	3	20060819	G	6112	7849141	BULKHEAD        	HAMSTD      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						880512					(CAN) THE FLIGHT CREW SNAGGED THE PORT PROP DEICE AS U/S NO LIGHTS OR INDICATION ON AC LOAD GAUGE.  UPON FURTHER INVESTI	GATION, MAINTENANCE FOUND THAT ALL 3 OF THE PROP DEICE BRUSH BLOCK SLIP RINGS HAD COME OFF OF THE PROPELLER BULKHEAD AND	 WERE WRAPPED AROUND THE PROPELLER SHAFT. THE SURROUNDING AREA OF THE ENGINE COMPARTMENT WAS INSPECTED FOR FURTHER DAMAG	E, WITH NO OTHER DAMAGE FOUND. THE PROPELLER BULKHEAD AND DEICE BRUSH BLOCK WERE REPLACED AND THE AIRCRAFT RETURNED TO S	ERVICE. THE BULKHEAD HAS BEEN SENT OUT FOR REPAIR AND A STRIP REPORT. (TC NR 20060905006)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006091400008	20060914	00008	SW  	2006	9	14	CA060905007      	1	20060831	G	2497		WIRE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	ROTOL	R321	R321482F8   	GL  	BATTERY/CHARGER	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAD EXPERIENCED PROBLEMS WITH BATTERY DISCONNECTING INTERMITTENTLY.  FIRST TIME WAS CIRCUIT BREAKER POPPE	D. NEXT TIME FOUND CORROSION ON BATTERY RELAY, REPLACED RELAY.  THIS IS A COMMON DEFECT WITH THESE TYPE OF RELAYS.  THIR	D INSTANCE WAS ON NEXT LEG AFTER BATTERY RELAY WAS REPLACED.  CREW EXPERIENCED A BATTERY FAULTY ENUNCIATOR AND BOTH DISC	ONNECT LIGHTS INDICATED.  ONCE ON THE GROUND, THEY WERE UNABLE TO GET EITHER BATTERY ON LINE.  MAINTENANCE DISCOVERED TH	E 4 GAUGE FEEDER WIRES FROM THE RAH BATTERY TO THE SERIES-PARALLEL RELAY CHAFED INSIDE THE WING.  THE WIRES WERE PROTECT	ED WITH FIRE SLEEVE AND HAD CHAFED THROUGH.  THERE WAS ASSOCIATED DAMAGE TO THE BLEED AIR LINE THAT THE WIRES RUBBED AGA	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2006091400009	20060914	00009	EA  	2006	9	14	CA060905008      	2	20060729	G	7230		BLADES          			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					COMPRESSOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								20529			(CAN) PROBLEMS WERE REPORTED WITH THE ENGINE SHORTLY AFTER TAKE-OFF.  THE AIRCRAFT SUBSEQUENTLY CRASHED.  PRELIMINARY IN	VESTIGATION EVIDENSED COMPRESSOR BLADE DISTRESS.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINE	D. (TC NR 20060905008)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006091400029	20060914	00029	NE  	2006	9	14	CA060905009      	2	20060727	G	7261		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  						LEAKING         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA								121400			(CAN) DURING CLIMB SMOKE AND ODORS BECAME EVIDENT IN THE CABIN.  ENGINE BLEEDS WERE CLOSED AND THE AIRCRAFT DIVERTED TO 	POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE AT THE ENGINE INLET AND EXTERNALS.  MFG WILL MONITOR INV	ESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20060905009)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006091400037	20060914	00037	NE  	2006	9	14	CA060905010      	2	20060731	G	7250		BEARING         			GULSTM	200   	200         	4500308	NM  	PWA   	306   	PW306B      	 	NE  					TURBINE SECTION	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN INCREEASE IN INTER-TURBINE TEMPERATURE AND VIBRATI	ONS AND A CHIP DETECTOR INDICATION.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND AN UNSCHEDULED LANDING CARRIED OUT.  SUBSEQUE	NT INSPECTION REVEALED DAMAGE TO THE LOW PRESSURE TURBINE NR4 BEARING. (TC NR 20060905010)				2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2006101900114	20061019	00114	NE  	2006	10	19	CA060905011      	2	20060731	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW121 	PW121       	52124	NE  						FAILED          	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA								120363			(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POI	NT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST AND SEIZURE OF THE PROPELLER.  MFG WILL MONI	TOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060905011)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2006101900115	20061019	00115	EA  	2006	10	19	CA060905012      	2	20060730	G	7200		ENGINE          								PWA   	PT6   	PT6A45R     	52043	EA  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								84317			(CAN) THE ENGINE FLAMED OUT IN CRUISE.  A SUBSEQUENT IN-FLIGHT RELIGHT ATTEMPT WAS UNSUCCESSFUL. INVESTIGATION REVEALED 	DAMAGE TO THE COMPRESSOR AND POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE	 ONCE DETERMINED. (TC NR 20060905012)									4	T			E4EA				 
2006101900116	20061019	00116	NE  	2006	10	19	CA060905013      	2	20060729	G	7321		FUEL CONTROL    			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE FLAMED OUT DURING DESCENT.  SUBSEQUENT INSPECTION REVEALED METAL PARTICLES IN THE FUEL SYSTEM DOWNSTREA	M OF THE FUEL CONTROL UNIT. THE FUEL SYSTEM COMPONENTS WERE REPLACED. MFG WILL MONITOR INVESTIGATION OF THE FCU AND ADVI	SE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905013)				1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2006101900117	20061019	00117	NE  	2006	10	19	CA060905014      	2	20060804	G	7200		ENGINE          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  						SMOKE           	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE CAUSED SMOKE IN THE CABIN AIR, REQUIRING THE DEPLOYMENT OF OXYGEN MASKS.  MFG WILL	 INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20060905014)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2006101900118	20061019	00118	EU  	2006	10	19	CA060905015      	1	20060618	G	7500	311221801	SWITCH          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					P2 AIR	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, SMOKE WAS REPORTED IN THE CABIN AIR AND ENGINE CABIN BLEED WAS SELECTED OFF.  SUBSEQUENT INSPECTI	ON REVEALED DAMAGED P2.5 AIR SWITCHING VALVE COMPONENTS ON BOTH ENGINES (124335 AND 124297). (TC NR 20060905015)					2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2006091400038	20060914	00038	EA  	2006	9	14	CA060906001      	1	20060811	G	5610	NP139322001	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) CREW NOTED DURING DESCENT CAPT LT SIDE WINDOW SHATTERED THE MIDDLE PANE AND NO PRESSURE PROBLEMS. THEY LANDED WITH	 NO PROBLEMS. (TC NR 20060906001)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006091400039	20060914	00039	EA  	2006	9	14	CA060906002      	1	20060817	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			9833 								(CAN) RT SIDE WINDOW CRACK. RT SIDE WINDOW IAW AMM CHANGED, WINDOW HEAT TEST PERF. OK.PLEASE PERFORM CABIN PRESS TEST. C	ABIN PRESS TEST PERF. FOUND OK. (TC NR 20060906002)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006091400040	20060914	00040	EA  	2006	9	14	CA060906003      	1	20060822	G	5610	NP15932211	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			CR	CRUISE         	1			CA			3947 								(CAN) LT SIDE WINDOW SHATTERED IN FLIGHT AT FL300 CABIN DIFF 8.2, REDUCE PRESS TO 6.2. QRH INITIATED. MAINTENANCE REPLAC	ED THE LT SIDE WINDOW. (TC NR 20060906003)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006091400041	20060914	00041	EA  	2006	9	14	CA060906004      	1	20060826	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			10052								(CAN) LT WINDOW CRACKED. LT SIDE WINDOW IAW AMM 56-12-01 REPLACED. (TC NR 20060906004)						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006091400042	20060914	00042	EA  	2006	9	14	CA060906005      	1	20060828	G	2150	GG67065009	ACM             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					LEFT	SMOKE           	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			9784 								(CAN) DISC- BURN/SMOKE ODOR IN COCKPIT, SMOKE ODOR TEMPORARY LT PACK AUTO FAIL ISSUED MEL 2112. C/A - RAI LT ACM IAW CRJ	 700 AMM 21-51-08 OPS CK, LEAK CHECK GOOD MEL RESTORED. (TC NR 20060906005)					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006101900119	20061019	00119	EU  	2006	10	19	CA060906006      	1	20060903	G	3150		WARNING SYSTEM  			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  						MULTIPLE IND    	W				C				ABORTED TAKEOFF         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AT 50 KNOTS, FLIGHT CREW REJECTED TAKE OFF DUE TO NAV ADC, GPS DISAGREE WARNING. DURING TAXI TO THE GATE, FAULT CL	EARED IT`S SELF. FMS WAS RESET IAW MM, GPS, IRS AND FM POSITIONAL FOUND MATCHING. AUTO FLIGHT SYSTEMS TESTED AND FOUND S	ERVICEABLE. AIRCRAFT WAS DISPATCHED WITH NO FURTHER PROBLEM.  (TC NR 20060906006)				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2006091400043	20060914	00043	GL  	2006	9	14	CA060906007      	2	20060905	G	7250	23076977	TURBINE BLADES  			EMB   	145   	EMB145LR    	3260212	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								A710015			(CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PN CONFIGURATION.  THE HP1 TURBINE BLADES INSTALLED AR	E POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION.  	THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060	906007)			2	L	7	2 	4T	4	F	RT	T00011AT	TE6CH				 
2006091400044	20060914	00044	GL  	2006	9	14	CA060906008      	2	20060905	G	7250	23076977	TURBINE BLADES  			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  						MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								A71843			(CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PN CONFIGURATION.  THE HP1 TURBINE BLADES INSTALLED AR	E POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION.  	THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060	906008)			2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2006091400045	20060914	00045	GL  	2006	9	14	CA060906009      	2	20060905	G	7250	23079436	TURBINE BLADES  			EMB   	135   	EMB135ER    	3260203	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								A71332			(CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PART NUMBER CONFIGURATION.  THE HP1 TURBINE BLADES INS	TALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGU	RATION.  THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC	 NR  20060906009)			2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2006101900120	20061019	00120	EU  	2006	10	19	CA060906011      	1	20060906	G	5280		SKIN            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9668 								(CAN) DURING REMOVAL FOR ACCESS, A GENERAL VISUAL INSPECTION OF THE RT MAIN GEAR DOOR REVEALED A LARGE CRACK IN THE INNE	R SKIN PANEL AS WELL AS SEVERAL PULLED RIVETS ADJACENT TO THE GEAR DOOR JACK ATTACH BRACKET.  SB 32-192-2845 (TO PREVENT	 CRACKING OF THE BRACKET ITSELF) HAD BEEN PREVIOUSLY EMBODIED AT 4608.6 HOURS TSN AND 3015 CYCLES.  THE CRACK HAD PROPAG	ATED TO 6 INCHES IN LENGTH ALONG THE FORWARD IB EDGE OF THE STRENGTHENED (POST MOD) BRACKET IN THE STRUCTURE THE BRACKET	 IS ATTACHED TO: THE INNER DOOR PAN.  A SOFT (TC NR 20060906011)		2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2006101900122	20061019	00122	NE  	2006	10	19	CA060906012      	2	20060904	G	7230	2292152810	COMPRESSOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2236 	2236 				9922			(CAN) DURING ROUTINE INSPECTION IT WAS NOTED THAT THE AXIAL COMPRESSOR WHEEL HAD SUFFERED FOD, WHICH WAS BEYOND LIMITS. 	THERE WAS NO EVIDENCE THAT THE INTAKE COWL HAD LOST ANY HARDWARE WHICH MAY HAVE CAUSED THIS. NOR WAS THERE ANY RESIDUAL 	PARTICLES/OBJECTS FOUND IN THE INTAKE SCOOP. THE AXIAL COMPRESSOR WHEEL WAS CHANGED AND THE AIRCRAFT WAS RETURNED TO SER	VICE. (TC NR 20060906012)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006101900129	20061019	00129	NE  	2006	10	19	CA060906013      	2	20060907	G	7200		ENGINE          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  						FLAMED OUT      	W				G				O2 MASK DEPLOYED        				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								JA0626			(CAN) THE AIRCRAFT ENTERED RAIN AND TURBULENCE AT 40K FEET AND THE ENGINE FLAMED OUT.  ENGINE ANTI-ICE AND CONTINUOUS IG	NITION HAD NOT BEEN SELECTED.  THE ENGINE WAS SUCCESSFULLY RE-STARTED AT 28K FEET.  MFG WILL MONITOR THE INVESTIGATION O	F THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906013)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2006101900130	20061019	00130	SW  	2006	10	19	CA060906014      	1	20060906	G	2897	MS3456W14S5S	CONNECTOR       	BELL        		BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL VALVE	SHORTED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						T71706					(CAN) FLASHING LIGHT OF ENGINE FUEL VALVE NR 2 ON STARTING PROCEDURE. CONNECTOR 1B14P1 SHORTED TOGETHER BETWEEN PINS A A	ND B AND WATER CONTAMINATION FOUND INSIDE BACK SHELL. INTERNAL LEAKAGE MEASURED ON THE CONNECTOR BETWEEN PINS A AND B CA	USING ON-OFF SIMULTANEOUS COMMANDS AND DAMAGES TO THE VALVE (205-060-612-003). CONNECTOR AND VALVE REPLACED AND A/C RETU	RNED TO SERVICE.  A/C HOURS 1754:16 A/C CYCLES  1904  (TC NR 20060906014)			1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2006101900131	20061019	00131	NE  	2006	10	19	CA060906015      	2	20060815	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								19374			(CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD BANG IN FLIGHT FOLLOWED BY A FLAMEOUT.  A DEAD-STICK LANDING WAS ACCOMPLISH	ED.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL FILTER AND SEIZURE OF THE COMPRESSOR.  MFG WILL INVESTIGATE	 THE EVENT AND ADVSE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906015)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006101900132	20061019	00132	EA  	2006	10	19	CA060906016      	2	20060818	G	7314	3031709	PUMP            								PWA   	PT6   	PT6A27      	52043	EA  					FUEL SYSTEM	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			5439 								(CAN) THE ENGINE FLAMED OUT DURING TAKE-OFF ROLL AND THE TAKE-OFF WAS ABORTED. METAL DEBRIS WAS FOUND IN THE FUEL PUMP O	UTLET FILTER. (TC NR 20060906016)										4	T			E4EA				 
2006101900133	20061019	00133	CE  	2006	10	19	CA060906017      	1	20060818	G	7712		ENGINE          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		AP	APPROACH       	1			CA								PJ0711			(CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE ON APPROACH AND THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT.  THE ENGINE WA	S SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906017)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006101900134	20061019	00134	NE  	2006	10	19	CA060906018      	2	20060717	G	7250		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						DAMAGED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								PC0472			(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD BANG ACCOMPANIED BY A LOSS IN POWER AND AN AGB CHIP DETECTOR INDICATION.  T	HE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ACCESSORY AND REDUCTION GEARBOXES AND PO	WER TURBINE ROTOR DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 2006090	6018)			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006101900135	20061019	00135	NM  	2006	10	19	CA060906019      	1	20060703	G	7931		SEAL            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENG OIL PUMP	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE IN FLIGHT AND THE ENGINE WAS SHUT DOWN. SUBSEQUENT INSPECTION REVEAL	ED A LEAKING HYDRAULIC PUMP PAD OIL SEAL. (TC NR 20060906019)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006102300075	20061023	00075	NE  	2006	10	23	CA060906020      	2	20060826	G	7230		FAN BLADE       								PWA   	306   	PW306B      	 	NE  					COMPRESSOR	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								CD0046			(CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE E	NGINE WAS SHUT DOWN, AN EMERGENCY DECLARED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEA	LED METAL DEBRIS IN THE ENGINE EXHAUST AND A HEAVY FAN BLADE RUB.  PWC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAU	SE ONCE ESTABLISHED.								4	F			E35NE				 
2006101900136	20061019	00136	NE  	2006	10	19	CA060906021      	2	20060828	G	7321	305964401	FUEL CONTROL    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					PNEUMATIC	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE DURING CLIMB.  DURING DESCENT ENGINE TORQUE INCREASE UNCOMMANDED AND THE ENGIN	E WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED CONTAMINATION OF THE PNEUMATIC SECTION OF THE FUEL CONTROL 	UNIT. (TC NR 20060906021)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2006101900137	20061019	00137	NE  	2006	10	19	CA060906022      	2	20060907	G	7261		SEAL            			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  					ALTERNATOR DRIVE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FOLLOWING TAKEOFF ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND DECAY TO ZERO.  THE ENGINE WAS SHUTDOWN IN FLIGHT 	AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A LEAKING ALTERNATOR DRIVE SEAL. (TC NR	 20060906022)				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE				 
2006101900138	20061019	00138		2006	10	19	CA060906023      	1	20060824	G	7931		TRANSDUCER      								PWA   	PW120 	PW127       	 	NE  					OIL PRESSURE	DIRTY           	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) DURING DESCENT THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE ENGINE OI	L PRESSURE TRANSDUCER WAS SUBSEQUENTLY REMOVED, CLEANED AND RE-INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20	060906023)									4	T			E20NE				 
2006101900139	20061019	00139	CE  	2006	10	19	CA060906024      	1	20060829	G	2750	1005240731	MOTOR           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAP	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA				3851 							(CAN) SHORTLY AFTER TAKEOFF, AT APPROXIMATELY 1000 FEET ALTITUDE A LIGHT SMOKE APPEARED IN THE CABIN ACCOMPANIED WITH A 	BURNING SMELL. THE AIRCRAFT IMMEDIATELY RETURNED TO THE DEPARTURE AIRPORT. FURTHER INVESTIGATION BY MAINTENANCE REVEALED	 THAT THE FLAP MOTOR WAS BURNED OUT AND WAS THE CAUSE OF THE SMOKE AND BURNING SMELL. THE FLAP MOTOR AND GEARBOX WERE RE	PLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060906024)			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006101900140	20061019	00140	EU  	2006	10	19	CA060906025      	1	20060802	G	6123	311809101	AUTOFEATHER SYS 			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					PROPELLER	FAULTY          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4265 								(CAN) ON APPROACH THE PROPELLER FEATHERED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION R	EVEALED A FAULTY AUTO FEATHER UNIT. (TC NR 20060906025)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007050400127	20070504	00127	CE  	2007	5	4	CA060906026      	1	20060831	G	5610	991438012	WINDSHIELD      			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					COCKPIT	FAILED          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			542  								(CAN) IN CRUISE AT 41000 FEET A SOUND LIKE A SHOTGUN WAS HEARD AND THE RT WINDSHIELD OUTER PANE SHATTERED.  AFTER AN UNS	CHEDULED LANDING AND INSPECTION BY AN AME IT WAS DETERMINED TO BE EITHER A LIGHTNING STRIKE OR A SHORT OF THE HEATING EL	EMENT.  THE WINDOW WAS THEN REPLACED AND A LIGHTNING STRIKE INSPECTION WAS COMPLIED WITH. THE AIRCRAFT WAS THEN RETURNED	 TO SERVICE. (TC NR 20060906026)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2006101900141	20061019	00141	CE  	2006	10	19	CA060907002      	1	20060901	G	3240	4500SA1	VALVE           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	PARK BRAKE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			10221								(CAN) RT BRAKE WOULD NOT RELEASE AFTER TOUCHDOWN, AIRCRAFT STOPPED ON RUNWAY, BRAKE PRESSURE HAD TO BE RELEASED BEFORE A	IRCRAFT REMOVED FROM RUNWAY. RT BRAKE MASTER CYLINDER REPLACED WITH USED SERVICEABLE UNIT. OPERATION CHECK CARRIED OUT O	KAY. DURING TAKEOFF THE CREW FELT A LUNGE FORWARD AFTER ROTATION. THEY FELT THE BRAKE WAS STILL DRAGGING SO THEY DECIDED	 TO DIVERT FROM  AIRPORT . REQUESTED ERS STANDBY, ANTICIPATING POSSIBLE DIRECTIONAL CONTROL PROBLEMS AFTER TOUCHDOWN. AI	RCRAFT LANDED WITHOUT INCIDENT. FURTHER INVESTIGATION REVEALED PROBLEMS WITH THE RT PARK BRAKE VALVE P/N 4500SA1. WHEN T	HE RT BRAKE PEDAL WAS DEPRESSED, THE PARK BRAKE VALVE HELD PRESSURE, AND WOULD NOT RELEASE THE RT BRAKE. THE PARK BRAKE 	1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006101900142	20061019	00142	EA  	2006	10	19	CA060907003      	2	20060905	G	7421		SPARK PLUG      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	FOULED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								L411961A			(CAN) AIRCRAFT (CARGO FLIGHT, NO PASSENGERS, 2 CREW ON BOARD) RETURNED AFTER TAKEOFF WITH REPORT OF LT ENGINE RUNNING VE	RY ROUGH AND PARTIAL POWER LOSS AS INDICATED BY SLIGHT YAW OF THE AIRCRAFT AND LT ENGINE RPM FLUCTUATION OF APPROX. 200 	RPM. MAINTENANCE INVESTIGATION REVEALED NR3 CYLINDER SPARK PLUGS FOULED; REPLACED WITH NEW FINE-WIRE TYPE PLUGS AND GROU	ND RUN CHECKED SERVICEABLE. SNAG REOCCURRED NEXT FLIGHT AND AIRCRAFT TAKEN OUT OF SERVICE FOR MAINTENANCE. ALL LT ENGINE	 FUEL INJECTOR NOZZLES CLEANED, ALL FUEL INJECTOR LINES CLEANED AND GROUND RUN CHECKED SERVICEABLE. AIRCRAFT TEST FLIGHT	 AND SUBSEQUENT FLIGHTS WITH LH ENGINE OPERATION NOW NORMAL. (TC NR 20060907003)	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006101900143	20061019	00143	SW  	2006	10	19	CA060907004      	1	20060629	G	7170		O-RING          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					DRAIN VALVE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						NA					(CAN) STARTED NR 2 ENGINE FIRST.  SECOND START OF THE DAY.  STARTED NR 1 AND BROUGHT IT UP TO IDLE.  THE AME CAME RUNNIN	G TO THE COCKPIT AND GAVE THE SIGNAL TO SHUTDOWN THE ENGINE.  ENGINE WAS SHUT DOWN AND BOOST PUMP TURNED OFF.  HE SAID F	UEL WAS STILL LEAKING FROM THE DRAIN AND TO TURN NR 2 BOOST PUMP OFF.   NR 2 BOOST PUMP WAS TURNED OFF.  SHORTLY THERE A	FTER NR 2 ENGINE FLAMED OUT AND QUIT.  ALL BOOST PUMPS AND FUEL VALVES CLOSED.  ENGINES SECURED AND PASSENGERS EVACUATED	. INVESTIGATION REVEALED THAT THE NR 1 FUEL FILTER DRAIN VALVE WAS DEFECTIVE AND ALLOWED THE BOOST PUMP PRESSURED FUEL T	O LEAK OUT THROUGH THE DRAIN.   NR 2 ENGINE FLAMED OUT BECAUSE WHEN NR 1 BOOST PUMP WAS SHUTOFF THE CROSSFEED VALVE OPEN	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006101900144	20061019	00144	SW  	2006	10	19	CA060907005      	1	20060830	G	6730	205076031003	ACTUATOR        			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					TAIL ROTOR SERVO	FAILED          	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			CA				180  							(CAN) DURING LONG LINE SLINGING OPERATIONS, UPON APPROACHING A DROP ZONE WITH A LOAD. THE COLLECTIVE WAS RAISED TO CUSHI	ON LANDING OF THE LOAD, THEN LOWERED TO TAKE TENSION OFF OF THE LINE. THE HELICOPTER TURNED TO THE LT AND THE RT TAIL RO	TOR PEDAL WAS FOUND TO BE STUCK. THE LOAD WAS ALREADY ON THE GROUND AND SUBSEQUENTLY RELEASED. THE COLLECTIVE WAS THEN A	GAIN RAISED UNTIL THE AIRCRAFT STOPPED ROTATING AND FWD FLIGHT COULD BE ACHIEVED. THE HELICOPTER MAINTAINED FWD FLIGHT W	HILE THE P/C CONTINUED OPERATING THE COLLECTIVE AND TAIL ROTOR CONTROLS. THE LT PEDAL INPUT WAS FINE BUT THE RT PEDAL IN	PUT WAS AT FIRST JAMMED, THEN BEGAN TO OPERATE WITH RESISTANCE LIKE A HYDRAULIC FAILURE. THE HYDRAULIC ON/OFF SWITCH WAS	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2006101900145	20061019	00145	EU  	2006	10	19	CA060907006      	1	20060125	G	7931		TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENG OIL PRESSURE	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			292  								(CAN) PILOT INDICATED THE PRESSURE INDICATOR WAS FLUCTUATING.  TROUBLESHOOTING DETERMINED IT WAS PRESSURE TRANSMITTER.  	(TC NR 20060907006)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006101900147	20061019	00147	CE  	2006	10	19	CA060907007      	1	20060829	G	2910	1013880167	LINE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) PILOT REPORTED THAT LANDING GEAR DID NOT RETRACT. 2.5 QUARTS OF HYDRAULIC FLUID WERE LOST AND HYDRAULIC PUMP CIRCU	IT BREAKER POPPED AND LOW FLUID LEVEL CAUTION LIGHT ILLUMINATED. MANUAL EXTENSION WAS CARRIED OUT AND AIRCRAFT LANDED SA	FELY. INVESTIGATION REVEALED RT MAIN LANDING GEAR HYDRAULIC RETRACT LINE WAS LEAKING. THE LINE WAS REPLACED, HYDRAULIC S	YSTEM REPLENISHED, GEAR SWINGS CARRIED OUT AND LEAK CHECKED SERVICEABLE. HYDRAULIC LINE P/N 101-388016-7 WAS PRESSURE TE	STED ON BENCH AND FOUND TO HAVE A HOLE ONE INCH FROM SWAGED FITTING. THE MFG RECOMMENDED INSPECTION CRITERIA FOR TEFLON 	COATED HYDRAULIC LINES CALL FOR A VISUAL INSPECTION FOR DETERIORATION AND LEAKS; HOWEVER THE OUTER  SHEATHING PREVENTS S	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006101900150	20061019	00150	EA  	2006	10	19	CA060907008      	1	20060826	G	5250		LOCK            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT DOOR	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 10 MINUTES PRIOR TO DESCENT, CALLED THE FLT ATTENDANT TO ENTER AND STAY IN THE FLIGHT DECK AS I WENT	 TO THE LAV. AFTER RETURNING AND ACTIVATING THE DOOR LOCK CODE THE FLIGHT ATTENDANT HAD PROBLEM UNLOCKING THE DOOR. THE 	FIRST OFFICER NOW HELPED AND ALSO NOT ABLE TO UNLOCK THE DOOR. I ALSO VERIFIED AND DISCUSSED ALL POSSIBLE OPTIONS VIA TH	E INTERPHONE. IT WAS DECIDED TO PULL THE DOOR PINS TO OPEN THE DOOR. AFTER RETURNING TO OUR POSITIONS, RESECURED THE DOO	R IN POSITION WITHOUT PINS AS NOT TO TRAP OURSELVES IN THE FLIGHT DECK IN THE EVENT OF AN EVACUATION. THE FLIGHT ATTENDA	NT JUMP SEAT WAS PUT INTO PLACE AS TO CREATE A BARRIER. AFTER LANDING MAINTENANCE WAS CALLED WHO RESECURED THE DOOR AND 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006101900151	20061019	00151	CE  	2006	10	19	CA060908001      	1	20060908	G	3010	29S7D517515	BOOT            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	DEICE SYS	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			135  								(CAN) THE CARGO POD DEICER BOOT EXHIBITS DETERIORATION DUE TO OIL/FUEL CONTAMINATION. SUSPECTED CAUSE IS LEAKING OR OPEN	 STOP COCKS ON THE ENGINE DRAINS. (TC NR 20060908001)					1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2006101900153	20061019	00153	CE  	2006	10	19	CA060908002      	1	20060907	G	3243	MS28775011	O-RING          	BEECH       		BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CHECK VALVE	CUT             	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			10222								(CAN) REF. SDR NR 20060907002  RT BRAKE LOCKED-UP PREVIOUS SDR SUBMITTED MENTIONED THE PARK BRAKE VALVE AS THE UNSERVICE	ABLE PART, HOWEVER THE NEXT FLIGHT THE BRAKES ON THE RT SIDE LOCKED-UP AGAIN, BRAKES INSPECTED, PRESSURE RELIEVED AND AI	RCRAFT RETURNED TO BASE FOR TROUBLSHOOTING, FOUND CO-PILOT RT BRAKE MASTER CYLINDER TRAPPING PRESSURE IN THE SYSTEM, BRA	KE CYLINDER REMOVED AND EXAMINED, FOUND O-RING ON CHECK VALVE CUT, O-RINGS IN MASTER CYLINDER REPLACED WITH NEW, FUNCTIO	N TEST CARRIED-OUT, BRAKES OPERATED NORMALLY  (O-RING P/N MS28775-011) (TC NR 20060908002)		1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2006101900155	20061019	00155	EU  	2006	10	19	CA060909001      	1	20060906	G	5610	NAS1581C3T11	SCREW           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSCREEN	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS.  ATTACHMENT SCR	EWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE.  ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPP	ENING MORE AND MORE.  2 MORE SDRS WILL BE ENTERED FOR SIMILAR ISSUES.   NO OTHER PROBLEMS WERE ENCOUNTERED AND THE AIRCR	AFT WAS RETURNED TO SERVICE. (TC NR 20060909001)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006101900156	20061019	00156	EU  	2006	10	19	CA060909002      	1	20060908	G	5610	NAS1581C3T11	SCREW           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSCREEN	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS.  ATTACHMENT SCR	EWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE.  ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPP	ENING MORE AND MORE.  2 MORE SDRS WILL BE ENTERED FOR SIMILAR ISSUES.   NO OTHER PROBLEMS WERE ENCOUNTERED AND THE AIRCR	AFT WAS RETURNED TO SERVICE. (TC NR 20060909002)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006101900159	20061019	00159	EU  	2006	10	19	CA060909003      	1	20060823	G	5610	NAS1581C3T11	SCREW           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSCREEN	BACKED OUT      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A WALKAROUND SEVERAL WINDSCREEN ATTACHMENT SCREWS WERE NOTED AS BEING PARTIALLY BACKED OUT.  ALL ATTACHMENT SCR	EWS RE-TORQUED AND SEVERAL MORE WERE FOUND TO BE LOOSE.   SCREWS RETORQUED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 2006	0909003)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006121300140	20061213	00140	CE  	2006	12	13	CA060911001      	1	20060909	G	3260		INDICATOR       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) DURING FLIGHT TRAINING GEAR WAS EXTENDED. THERE WAS NO RT MAIN GEAR DOWN AND LOCKED LIGHT. AN EMERGENCY GEAR EXTEN	SION WAS CARRIED OUT. RT MAIN GEAR LIGHT STILL NOT ILLUMINATED. LAMP TEST CARRIED OUT WITH GEAR HANDLE RED INTRANSIT LIG	HT ILLUMINATED. PILOTS WERE UNABLE TO REMOVE LIGHT HOLDER TO INSPECT BULBS.  EMERGENCY LANDING DECLARED. LANDING GEAR VI	SUALLY CHECKED DURING A CIRCUIT BY MAINTENANCE PERSONNEL. GEAR APPEARED DOWN AND LOCKED. AIRCRAFT LANDED WITHOUT EVENT. 	MAINTENANCE PERSONNEL INSTALLED GEAR PINS AND TOWED AIRCRAFT BACK TO HANGER. FAULTY BULB REPLACED AND SEVERAL GEAR SWING	S CARRIED OUT. NO FAULTS FOUND. THIS PROBLEM COULD HAVE BEEN LESS EVENTFUL IF THE PILOTS WERE MORE EASILY ABLE TO REMOVE	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007050700181	20070507	00181	WP  	2007	5	7	CA060911002      	1	20060724	G	2810		FUEL FILTER     			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE 100 HOUR INSPECTION, A LARGE AMOUNT OF PARTICLES WERE FOUND IN THE MAIN FUEL FILTERS AND THE FUEL	 PUMP INLET FILTERS. THE PARTICLES WERE SENT TO A LAB AND IT WAS DETERMINED THAT IT WAS ORGANIC MATERIAL SIMILAR TO THE 	EXPLOSION SUPPRESSANT FOAM USED IN THE PYLON FUEL TANKS. THE FOAM HAS BEEN REMOVED, SYSTEM FLUSHED AND NEW FOAM INSTALLE	D. THE REMAINDER OF THE FLEET (9 AIRCRAFT TOTAL) WILL HAVE THE FOAM REPLACED DURING WINTER MAINTENANCE. (TC NR 200609110	02)		2	H	7	2 	4R	4	T		A25WE   	E26NE	6	C	P44GL	 
2006101900164	20061019	00164	NM  	2006	10	19	CA060911006      	1	20060908	G	3320	AL845T279	LAMP            			AMD   	FALC50	FALCON2000  	2730170	NM  										LAVATORY	MELTED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING THE POST FLIGHT INSPECTION, A ELECTRICAL BURNING ODOR WAS DETECTED IN THE AFT AREA OF THE CABIN. 	APON FURTHER INSPECTION ONE OF THE LAVATORY MIRROR VANITY LIGHTS WAS FOUND TO BE INOP. WHEN THE BULB WAS REMOVED TO BE R	EPLACED IT WAS NOTICED THAT ONE END OF THE LAMP ASSEMBLY HAD STARTED TO MELT. WITH THE DEFECTIVE LAMP ASSEMBLY REMOVED I	T WAS ALSO NOTED THAT THE DEFECTIVE PN WAS WRONG. INSTALLED WAS A AL-845-T-279 BUT IAW THE FALCON IPC THE LAMP ASSEMBLY 	SHOULD HAVE BEEN A AL-845-T-279-F. AFTER THE DEFECTIVE LAMP ASSEMBLY WAS REMOVED THE ELECTRICAL BURNING SMELL IN THE CAB	IN WAS NOT DETECTED ANYMORE. THE CORRECT LAMP ASSEMBLY WAS ORDERED AND THE AIRCRAFT HAS BEEN RETURNED TO SERVICE. (TC NR	2	K	7	2 	4F			RT	A50NM   					 
2006101900165	20061019	00165	NE  	2006	10	19	CA060912001      	2	20060912	G	7250	BRH20351	TURBINE BLADES  			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	FRACTURED       	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			13801					13322			(CAN) IN CLIMB AT 11000 FT PILOT REPORTED LOUD BANG. TGT ROSE  TO 1194 DEG.  PILOT SHUT DOWN ENGINE. AND TURNED BACK. FO	UND HEAVY METAL CONTAMINATION IN THE TAIL PIPE.  EMERGENCY LANDING CONDUCTED WITHOUT INCIDENT. ENGINE PRESENTLY AT RRC F	OR REPAIR, STRIP OF ENGINE REVEALED HP1 TURBINE BLADES FAILURE BELOW INNER PLATFORM AND SEVERE SECONDARY DAMAGE IN LP TU	RBINE MODULE. ENGINE IS HIGH TIME TSN;13801 HOURS, CSN; 9396 AND THIS IS FIRST SHOP VISIT. FAILED BLADES HAVE BEEN SHIPP	ED TO THE OEM (GERMANY) FOR INVESTIGATION.  (TC NR 20060912001)		2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2006101900166	20061019	00166		2006	10	19	CA060913001      	4	20060816	G	6113	05522311	BULKHEAD        	CESSNA      		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			492  								(CAN) DURING CHANGEOVER FROM FLOATS TO WHEELS, AND DURING THE CHANGE FROM SEAPLANE PROP TO WHEELPLANE PROP , CLOSER INSP	ECTION OF THE FORWARD PROP SPINNER BULKHEAD REVEALED NUMEROUS CRACKS. THESE CRACKS WERE RADIATING FROM THE PROP ATTACHME	NT BOLT HOLES, TO THE BEND RADIUS OF THE BULKHEAD (P/N 0552231-1). CRACKS WERE ALSO AROUND THE RADIUS WHERE THE PROP BOL	T WASHERS MEET AGAINST THE SPINNER PLATE. AIRCRAFT HAD FLOWN 157.1 HRS ON FLOATS WITH NUMEROUS TAKEOFFS AND LANDINGS DUR	ING FLOAT FLIGHT TRAINING. THIS SPINNER PLATE WAS LAST CHANGED 492.0 HRS AGO AFTER IT HAD AGAIN BEEN CHANGED OVER FROM F	LOATS TO WHEELS. AT THAT TIME, THE PLANE HAD LOGGED 222.1 HRS OF FLOAT FLIGHT TRAINING, AND CRACKS WERE ALSO APPARENT AT	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006101900167	20061019	00167	CE  	2006	10	19	CA060913002      	1	20060816	G	3220	05412024	BUSHING         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	NLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2578 								(CAN) THE MAIN GEAR LEG BUSHINGS ARE A STEEL OUTER TUBE, WITH A THICK INNER URETHANE CENTER.  DURING PROGRESSIVE CARE OP	ERATION NR 1, INSPECTION OF THE RT MAIN GEAR LEG REVEALED THAT THE URETHANE INNER BUSHING MATERIAL HAD DEPARTED FROM THE	 OUTER STEEL BUSHING (P/N 0541202-4).  IT HAD MOVED LOOSELY ALONG THE TUBULAR GEAR LEG TOWARDS THE CENTER OF THE AIRCRAF	T. THIS ALLOWED THE TUBULAR GEAR LEG TO RATTLE ON THE INSIDE OF THE STEEL OUTER BUSHING. THE STEEL OUTER BUSHING IS HELD	 IN PLACE WITH 2 (C) CLIPS, HOWEVER THE URETHANE INNER PART OF THE BUSHING LOOKS TO BE ONLY A PRESS FIT. THE AIRCRAFT WA	S JACKED UP, THE LEG WAS REMOVED, AND A NEW BUSHING WAS INSTALLED. THE OTHER 3 MODEL AIRCRAFT IN THE FLEET HAVE BEEN INS	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007050700086	20070507	00086	SW  	2007	5	7	CA060913003      	1	20060912	G	5302	80011P12F20	SKIN            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15442								(CAN) WHILE CARRYING OUT ASB 206-06-107, FIN WAS REMOVED AND A FIN ATTACHMENT INSERT P/N 80-011-P12F2-0 WAS FOUND CRACKE	D. AFTER REMOVAL OF THE CRACKED INSERT, THE IB SKIN BELOW WAS FOUND TO HAVE SEVERAL CRACKS PROPAGATING UNDERNEATH THE DO	UBLER. THE IB DOUBLER WAS REMOVED AND A TOTAL OF APPROXIMATELY 6 CRACKS WAS FOUND, ONE OF WHICH WAS 3 INCHES IN LENGTH. 	THE FIN WAS REPLACED. (TC NR 20060913003)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006101900168	20061019	00168	EA  	2006	10	19	CA060913004      	1	20060906	G	2810	215640015	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1414 								(CAN) A/C DEVELOPED A FUEL LEAK. LEAK WAS MEASURED AND FOUND TO BE THE DRIP TYPE AND COMING FROM THE WING TIP AREA.UPON 	INSPECTION IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE RT FUEL CELLS. DUE TO PREVIOUS REPLACEMENT OF CELLS 	NR 3 THROUGH NR 8 IT WAS DETERMINED TO TEST CELLS NR 1 AND 2.  BOTH CELLS WERE FOUND LEAKING AND SUBSEQUENTLY REPLACED. 	A/C GROUND CHECKED OK. P/N 215-64001-5 SERIAL NR 72672 NR 1 CELL P/N 215-64002-8 SN 72872 NR 2 CELL (TC NR 20060913004)			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007050700087	20070507	00087	SW  	2007	5	7	CA060913005      	1	20060911	G	7921	212030041233	SUPPORT         			BELL  	412   	412         	1182202	SW  										OIL COOLER	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SUPPORT 212-030-041-233 FOULS WITH TRANSMISSON OIL LINE 212-040-229-001. (TC NR 20060913005)						1	G	7	2 	4U				H4SW    					 
2006101900169	20061019	00169	EU  	2006	10	19	CA060913006      	1	20060913	G	3246	40424	WHEEL           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6024 								(CAN) DURING AN INSPECTION WHEEL ASSY WAS REMOVED, GREASE COVER FOR THE BEARING AND BEARINGS REMOVED FOR INSPECTION/ REP	ACKING. THE WHEEL WAS THEN CLEANED AND INSPECTED FOR WEAR.  AT THAT POINT IT WAS NOTICED THAT THE WHEEL HOUSING HAD SEVE	RAL DEEP GROOVES WHERE THE GREASE COVER SITS.  WE HAVE NOTICED THIS PROBLEM ON OTHER WHEEL ASSY BUT TO A LESSER DEGREE. 	WE HAVE SENT AN E-MAIL TO MFG AND INFORMED THEM OF THIS PROBLEM. (TC NR 20060913006)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006101900170	20061019	00170	EU  	2006	10	19	CA060914001      	1	20060911	G	3150		WARNING MESSAGE 			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  		MULTIPLE IND    	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AFTER DEPARTING THE CREW OBSERVED NR 1 ADC, NR 1 ENGINE ANTI-ICE AND NR 1 PROP DEICE FAULTS. THE AIRCRAFT RETURNED	 TO POINT OF DEPARTURE WITHOUT INCIDENT. MAINTENANCE TROUBLE SHOOTING  WAS UNABLE TO DUPLICATE THE FAULT. AFTER SATISFAC	TORY OPERATIONAL TESTING OF THE AFFECTED SYSTEMS THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060914001)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007050700090	20070507	00090	SW  	2007	5	7	CA060914002      	1	20060906	G	5302		STRUCTURE       	BELL        		BELL  	407   	407         	1182206	SW  										TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9257 			53247					(CAN) APPROX. 8 IN. CRACK FOUND IN TAILBOOM NEAR THE 5TH HANGER BEARING  APPROX. 270 HRS REMAINING OUT OF THE 5000 HRS R	ETIREMENT LIFE. (TC NR 20060914002)					1	G	7	1 	3U			O	H2SW    					 
2006101900171	20061019	00171	CE  	2006	10	19	CA060914003      	1	20060808	G	2497		CONNECTOR       	FORD        		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ALTERNATOR	BROKEN          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			H	P		ELECT. POWER LOSS-50 PC   	NO WARNING INDICATION     		CR	CRUISE         	1			CA			4075 			R204620					(CAN) ALTERNATOR FAILURE WHILE ON ROUTE TO DESTINATION WAS CAUSED BY AN AMP CONECTOR LOOP END BREAKING OFF AND CAUSING L	OSS OF ELECTRICAL POWER AND A SHORT IN THE SYSTEM. (TC NR 20060914003)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2006101900172	20061019	00172	CE  	2006	10	19	CA060914004      	1	20060914	G	2510	07190131	SEAT BACK       			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	COCKPIT SEAT	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			4089 								(CAN) CO PILOTS SEAT BACK WAS FOUND BROKEN ABOUT 2 INCHES ABOVE THE WELDED JOINT ON THE LT SIDE OF THE SEAT BACK. BROKEN	 PART REMOVED NEW SEAT BACK FRAME ON ORDER WITH CESSNA. (TC NR 20060914004)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2007050700091	20070507	00091	WP  	2007	5	7	CA060915001      	1	20060914	G	7820	C1963	MUFFLER         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1939 								(CAN) WHILE PERFORMING CF90-3R2 ON THE MUFFLER ASSEMBLY THE EXHAUST SHROUD WAS REMOVED AND A (2) INCH CRACK WAS FOUND WH	ERE THE EXHAUST PIPE JOINS THE MUFFLER. (TC NR 20060915001)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2006101900173	20061019	00173	NE  	2006	10	19	CA060915002      	2	20060914	G	7314	2043M12P03	SHAFT           			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					FUEL PUMP	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			159  					994203			(CAN) DURING CRUISE AT FL360, THE NR 1 ENGINE FAILED.  THE CREW DECLARED AN EMERGENCY AND BEGAN DESCENT.  DURING THE DES	CENT A RE-START WAS ATTEMPTED BUT WAS UNSUCCESSFUL.  THE FLIGHT DIVERTED AND LANDED APPROX 400 KG OVERWEIGHT. (TC NR 200	60915002)				2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2006101900174	20061019	00174	EA  	2006	10	19	CA060918001      	1	20060918	G	2750		FLAP SYSTEM     			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					TE FLAPS	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) FLAP FAILED ON TAKEOFF, A/C RETURNED AND LANDED SAFELY AT QB MAIN BASE, BREAKER WAS RESET IAW OPERATING MANUAL, CO	ULDN`T DUPLICATED THE SNAG. A/C DID ONE FLIGHT AND RETURN TO BASE WITHOUT ANY SNAG.					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006101900176	20061019	00176		2006	10	19	CA060918002      	4	20060912	G	3100	285T003117	CIRCUIT CARD    			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2*    	 	GL  					COCKPIT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) CAPTAIN REJECTED TAKEOFF ROLL AT 155KTS BECAUSE OF A (TAKEOFF CONFIGURATION SAFETY WARNING) MESSAGE, 4 MAIN LANDIN	G GEAR TIRES REPLACED DUE TO HIGH ENERGY BRAKING AND FUSE PLUGS MELTING. NEW LANDING CONFIGURATION CARD INSTALLED AND TE	STED. (TC NR 20060918002)				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2006121300141	20061213	00141	GL  	2006	12	13	CA060918003      	1	20060829	G	5210	2256136100	HOOK            	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	CANOPY	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			2175 								(CAN) PILOT NOTICED CANOPY LIGHT ON IN FLIGHT AND RETURNED FOR LANDING. INSPECTION REVEALED THAT THE CANOPY LATCH PLATE 	( P/N 22-5613-61-00) ON THE LT SIDE WAS BROKEN ALLOWING THE CANOPY LIGHT TO BE ILLUMINATED. 2 MICRO SWITCHES ARE USED TO	 TURN THE WANING LIGHT OFF ONLY WHEN BOTH LATCHES ARE FULLY CLOSED. THE SYSTEM WORKED PROPERLY WHEN ONE LATCH FAILED. SE	RVICEABLE LATCH INSTALLED AND SYSTEM CHECKED AND ADJUSTED IAW  MM (DMM) AS REQUIRED. AIRCRAFT RELEASED. THE SYSTEM IS IN	SPECTED EVERY 100 HR, WHICH REQUIRES A PULL TEST TO BE CARRIED OUT FOR FRICTION VERIFICATION AND ADJUSTMENT AS REQUIRED.	 STRESS CAN BE APPLIED TO THE LATCH HOOK IF THE CANOPY IS ACCIDENTALLY CLOSE WITH THE LATCH IN THE CLOSED POSITION OR IF	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006101900177	20061019	00177	SO  	2006	10	19	CA060918004      	1	20060909	G	7120	LW38275	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE MOUNT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1446 							(CAN) DURING ROUTING INSPECTION IT WAS NOTED THAT ONE OF THE BOLTS SECURING THE RT BOTTOM ENGINE MOUNT BRACKET ONTO THE 	CRANKCASE OF THE RT ENGINE WAS BROKEN AND THE OTHER BOLT WAS LOOSE. BROKEN TREADED BOLT PIECE WAS REMOVED FROM CRANKCASE	 AND A SERVICEABLE BRACKET INSTALLED DUE TO ELONGATED HOLES IN OLD UNIT. TOP RT BRACKET WAS ALSO FOUND LOOSE, BRACKET RE	MOVED AND VISUALLY INSPECTED, NO DAMAGE FOUND. BRACKET REINSTALLED. ALL 6 ENGINE MOUNTING BRACKET BOLTS REPLACED AND TOR	QUED. BOLT TORQUE TO BE RECHECKED NEXT INSPECTION.  ALTHOUGH THE ENGINE HAD 1445.6 HRS SINCE LAST OVERHAUL IT IS NOT MAN	DATORY ACCORDING TO MFG SB 240T TO REPLACE THESE BOLTS. (TC NR 20060918004)	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006101900178	20061019	00178	GL  	2006	10	19	CA060918005      	1	20060908	G	8011	656762	GEAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	STARTER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28   					650199			(CAN) DURING THE FIRST 25/100 HR INSPECTION ON THIS AIRCRAFT, INSPECTION OF THE OIL SYSTEM REVEALED CONTAMINATION ON THE	 DRAIN PLUG MAGNET AND OIL FILTER. SUBSEQUENTLY, THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STAR	TER AND CLUSTER GEARS WERE FOUND DAMAGED IN THE AREA OF INITIAL STARTER ENGAGEMENT. THE DAMAGE EXCEEDED THE NORMAL WEAR 	DESCRIBED IN SB04-07. BOTH STARTER AND CLUSTER GEARS WERE REPLACED. (TC NR 20060918005)			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006101900179	20061019	00179	GL  	2006	10	19	CA060918006      	1	20060915	G	8011	656762	GEAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	STARTER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37   					650197			(CAN) DURING TROUBLESHOOTING OF THE FUEL SYSTEM DUE TO ENGINE QUITTING ON ROLL OUT FROM LANDING, THE ENGINE FUEL SYSTEM 	WAS BEING CHECKED IAW SID97-3C, AT WHICH TIME DURING A GROUND RUN IT WAS NOTICED THAT OIL PRESSURE HAD DROPPED TO ALMOST	 (0). THE ENGINE WAS SHUTDOWN IMMEDIATELY.  FURTHER INSPECTION OF THE LOSS OF OIL PRESSURE REVEALED METAL CONTAMINATION 	ON THE OIL PRESSURE RELIEF VALVE. FURTHER INSPECTION OF THE OIL SYSTEM REVEALED MORE CONTAMINATION ON THE DRAIN PLUG MAG	NET AND OIL FILTER. SUBSEQUENTLY THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STARTER AND CLUSTER 	GEARS WERE FOUND DAMAGED IN THE AREA OF INITIAL STARTER ENGAGEMENT. THE DAMAGE EXCEEDED THE NORMAL WEAR DESCRIBED IN SB0	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006101900180	20061019	00180	SO  	2006	10	19	CA060918007      	2	20060915	G	7314	64936849A1	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					FUEL SYS	OUT OF ADJUST   	W				D				RETURN TO BLOCK         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			37   					650197			(CAN) PILOT REPORTED ENGINE QUIT ON TOUCH DOWN, ABLE TO RESTART. FUEL INJECTION SYSTEM CHECKED IAW SID97-3C AND ADJUSTED	. BOTH INLINE FUEL FILTERS INSPECTED FOR CONTAMINANTS, CLEANED AND RE-INSTALLED. SMALL AMOUNT OF CONTAMINANTS FOUND IN I	NLINE FILTER AFTER THE MECHANICAL FILTER. AIRCRAFT RELEASED CONDITIONAL TO SATISFACTORY TEST FLIGHT. AIRCRAFT TEST FLIGH	T CARRIED OUT SATISFACTORY. A SISTER AIRCRAFT HAS REPORTED A SIMILAR DEFECT. AN SDR WILL BE SUBMITTED AFTER TROUBLESHOOT	ING IS COMPLETED. TROUBLESHOOTING IS BEING CARRIED OUT BY DIAMOND AIRCRAFT. THESE 2 AC EQUIPED WITH NEW ALTITUDE COMPENS	ATION FUEL PUMPS. (TC NR 20060918007)	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2006101900181	20061019	00181	EA  	2006	10	19	CA060918009      	1	20060916	G	7830	22850809119	TRACK           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					THRUST REVERSER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24451								(CAN) NR 2 ENGINE LT LOWER THRUST REVERSER TRACK FOUND CRACKED DURING A C-CHECK INSPECTION. PART REPLACED AS A MAIN TRAC	K ASSEMBLY P/N 228-50809-801.   REFERENCE :MFG CSP A-006 IPC CHAP 78-34-11 FIGURE 1 , ITEM 75A AND 95A. (TC NR 200609180	09)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006101900182	20061019	00182	NM  	2006	10	19	CA060918010      	1	20060913	G	8012	97907021	START VALVE     			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9       	52048	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) THE NR 3 ENGINE START VALVE OPEN LIGHT ILLUMINATED DURING CLIMB OUT.  A/C RETURNED TO BASE.   A/C INSPECTED AND TH	E START VALVE REPLACED DUE CRACKED.  A/C RETURNED TO SERVICE. FAULT REOCCURRED DURING CLIMB.  A/C RETURNED TO BASE.   TH	E FUEL HEAT DUCT WAS FOUND CRACKED CAUSING WIRING DAMAGE (HEAT) AND THE START VALVE INDICATION. DETAILED ENGINE INSPECTI	ON CARRIED OUT. THE FUEL HEAT DUCT WAS REPLACED AND AIRCRAFT WIRING REPAIRED AS REQUIRED.  A/C RETURNED TO SERVICE.  (TC	 NR 20060918010)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006101900183	20061019	00183	EA  	2006	10	19	CA060918011      	1	20060906	G	3246	L312111	BEARING         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG WHEEL	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			8944 								(CAN) AT TIRE CHANGE, DURING WHEEL AND BEARING INSPECTION FOUND THE OUTER WHEEL OUTER BEARING CUP, WITH A PLATING SURFAC	E MISSING (.3750 INCH X .2500 INCH) AND ROLLER BEARING P/N L81214 * 2-629 THAT MATCH THIS CUP WITH LITTLE MARK ON ROLLER	. WHEEL AFT VISUALLY INSPECTED AND FOUND OK. (TC NR 20060918011)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006101900184	20061019	00184	NE  	2006	10	19	CA060919001      	2	20060916	G	7200		SHUTOFF VALVE   			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 3 ENGINE	LEAKING         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DEPARTING THE CREW OBSERVED A STRUT OVERHEAT CONDITION ON NR 3 ENGINE. THE AIRCRAFT DIVERTED WHERE MAINTENANCE DET	ECTED A LEAK AT THE WING ANTI ICE SHUT-OFF VALVE (SOV). GASKETS WERE REPLACED AND NO FURTHER FAULT APPEARED EVIDENT AT G	ROUND RUN. DURING THE SUBSEQUENT DEPARTURE THE OVER TEMP CONDITION AT APPLICATION OF TAKE-OFF POWER, THE CREW REJECTED T	HE TAKE-OFF. MAINTENANCE DETECTED A LEAK AT THE PRE-COOLER WHICH WAS CORRECTED AND CARRIED OUT MULTIPLE TAKE-OFF POWER T	ESTS WITH NO FAULT INDICATION. THE SUCCEEDING DEPARTURE WAS AGAIN REJECTED AT 60KNOTS DUE TO AN OVERTEMP CONDITION ON NR	 3 STRUT. MAINTENANCE REPLACED THE FIRE WIRE LOOP AND CORRECTED AN ADDITIONAL LEAK AT THE PRECOOLER BEFORE RETURNING THE	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006101900185	20061019	00185	CE  	2006	10	19	CA060919002      	1	20060918	G	2435	30728692	SPLINE          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					STARTER GEN	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								P116176C			(CAN) ENGINE FAILED TO START.  AFTER INSPECTION FOUND THAT STARTER/GEN SPLINE INSERT HAD CRACKED CAUSING THE SPLINE TEET	H TO BREAK OFF.  UNABLE TO DETERMINE IF CRACK HAD OF OCCURRED BEFORE OR AFTER GEAR TEETH HAD BROKEN OFF.  REPLACE SPLINE	 AND AIRCRAFT STARTED NORMALLY. FLEET INSPECTION TO BE C/O. (TC NR 20060919002)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006101900186	20061019	00186	NM  	2006	10	19	CA060919003      	1	20060918	G	3320	BV33001215	SOCKET          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	CABIN LIGHTS	BURNED          	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) AFTER BOARDING WAS COMPLETED AND DOORS CLOSED, CA1 REPORTED A STRONG SMELL OF SMOKE COMBINED WITH LIGHT SMOKE DEVE	LOPMENT IN THE CABIN. CONTROLLED DISEMBARKATION WAS ORDERED, MAYDAY CALL PERFORMED AND ON GROUND EMERGENCY ITEMS COMPLET	ED ON THE FLIGHT DECK. AFTER PAX DISEMBARKATION COCKPIT CREW DISCHARGED ONE FIRE EXTINGUISHER INTO THE AREA OF SMOKE DEV	ELOPMENT AND THEN DISEMBARKED THE A/C. REASON FOR THE SMOKE DEVELOPMENT WAS A SHORT IN THE OVERHEAD LIGHTING SYSTEM. THE	 FAULT OCCURED ON THE FIRST LT OVERHEAD LAMP HOLDER. HOLDER FOUND BURNED.  (TC NR 20060919003)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006101900187	20061019	00187	EA  	2006	10	19	CA060919004      	1	20060917	G	5512	60021134434	VISOR           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24451								(CAN) BOTH THE LT AND RT LOWER VISOR ASSEMBLIES WERE FOUND DAMAGED  FROM CRACKING AT THE AFT TOP END. THIS MAY HAVE BEEN	 DUE TO FLUTTER AT THE AFT END OF THE FAIRING DURING FLIGHT. SINCE IT IS ATTACHED TO THE MOVABLE HORIZONTAL STABILIZER, 	THERE IS NO FASTENERS AT THAT AFT END OF THE FAIRING. THERE WERE NO VIBRATIONS OR DEFECTS OF THAT THAT NATURE REPORTED O	N THIS AIRCRAFT BEFORE IT CAME IN FOR A HEAVY  CHECK DURING  WHICH TIME THIS DAMAGED FAIRINGS WERE FOUND.  HOWEVER THIS 	DAMAGE IS OFTEN NOTED ON OTHER AIRCRAFT AS WELL AND MAY OR MAY NOT HAVE CAUSED AIRFRAME VIBRATION OR INTERFERENCE WITH  	THE MOVING HORIZONTAL STABILIZER. (TC NR 20060919004)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006101900188	20061019	00188	EU  	2006	10	19	CA060919005      	1	20060910	G	2760	233009	ACTUATOR        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					SPEED BRAKE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				O			OTHER                     			LD	LANDING        	1			CA											(CAN) FLIGHT CREW REPORTED THAT THE SPEED BRAKE WOULD NOT RETRACT UPON SELECTION TO DO SO. FOLLOWING LANDING.  BOTH PADD	LES CONFIRMED OPEN. AIRCRAFT WAS FERRIED TO BASE, WHERE THE SPEED BRAKE ACTUATOR WAS REPLACED. SYSTEM TESTED SERVICEABLE	 AFTER REPLACEMENT.  SPEED BRAKE ACTUATOR PN 23300-9 SN MC-046 WAS REPLACED MFG SERVICES HAVE REQUESTED THIS ACTUATOR FO	R ANALYSIS DUE TO SIMILAR REPORTS FROM OTHER OPERATORS.  ITEM OPEN TO MONITOR THE FOLLOW UP VIA THE QUARTERLY RELIABILIT	Y MEETING.  (TC NR 20060919005)		2	L	7	2 	4F	4	F	RT	        	E25NE				 
2006101900189	20061019	00189	EA  	2006	10	19	CA060919006      	1	20060916	G	5610	601R3303311	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			8346 								(CAN) LT SIDE-WINDOW REPLACED IAW AMM.   AERODYNAMIC SEAL INSTALLED AND SEALING PERFORMED. CABIN PRESSURE TEST AND LEAK 	CHECK PERF, OK. WINDOW HEATING CHECKED, OK. (TC NR 20060919006)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006101900190	20061019	00190	GL  	2006	10	19	CA060920001      	2	20060917	G	7210		GEARBOX         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2 RGB	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DEPARTING THE CREW OBSERVED A CHIP LIGHT INDICATION ON NR 2 RGB. THE ENGINE WAS SHUT-DOWN AND THE AIRCRAFT RETURNE	D TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND  CONTAMINATION ON THE RGB PLUG BELIEVED TO BE FROM T	HE STARTER SEAL. THE SEAL WAS REPLACED AND THE AIRCRAFT RUN AT HIGH POWER SETTING FOR 30 MINUTES WITH NO FURTHER INDICAT	ION. (TC NR 20060920001)			2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2006101900191	20061019	00191	EU  	2006	10	19	CA060920002      	1	20060920	G	2820	416113004	LINE            			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					FCU	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) GOVERNOR FAIL TO RESPONSE ON TAKE OFF, VISUAL CHECK OF ENGINE COMPARTMENT FOUND CRACKED LINE ON GOVERNOR TO FCU LI	NE NP TO PR TO PG LINE . LINE REPLACED WITH NEW A/C BACK TO SERVICE. (TC NR 20060920002)					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2006101900192	20061019	00192	EU  	2006	10	19	CA060920003      	1	20060920	G	2435	150SG116Q	STARTER GEN     			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				350  							(CAN) GENERATOR LIGHT CAME ON IN FLIGHT, LANDED AND SHOTDOWN, STARTER FOUND BROKEN. STARTER REPLACED AND SENT FOR OVERHA	UL. (TC NR 20060920003)					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2006101900193	20061019	00193		2006	10	19	CA060920004      	4	20060918	G	3422		AHRS            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2	FAILED          	W				A				UNSCHED LANDING         				I			FLT. ATTITUDE INST.       			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE THE NR 2 AHRS UNIT FAILED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. CURRENTLY AWAITING PARTS.	 (TC NR 20060920004)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006101900194	20061019	00194	CE  	2006	10	19	CA060920005      	1	20060814	G	2133	52771338	OUTFLOW VALVE   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					CABIN PRESSURE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			1545 								(CAN) UNCOMMANDED PRESSURIZATION DURING DESCENT OF CABIN AT APPROX 10,000 FEET WHILE IN AUTO MODE - PREVENTING TO  MANUA	L MODE WOULD NOT DECREASE RATE OF CABIN DIVE - CREW CONTROLLED CABIN PRESSURIZATION BY CONTROLLING ENGINE BLEED AIR SOUR	CE VALVES SUPPLYING CABIN AIR. THIS PROBLEM IS CAUSED BY A STICKING OPEN DIVE SOLENOID VALVE IN THE PRIMARY OUTFLOW VALV	E ASSEMBLY.  MFG HAS INCORPORATED SB 560-21-27 TO INSTALL A PARTICULATE TRAP IN THE PNEUMATIC LINE TO PREVENT THIS PROBL	EM. (TC NR 20060920005)		2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006101900195	20061019	00195	EA  	2006	10	19	CA060920006      	1	20060912	G	5510		BOLT            			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	HORIZONTAL STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			600  								(CAN) UPON REMOVAL OF THE LT FINLET THE REAR ATTACH BOLT (P/N AN3-4A) BROKE. WHEN INSTALLING 4 NEW BOLTS IT WAS NOTICED 	THAT THE WASHER RODE UP ON THE RADIUS OF THE ATTACH BRACKET CAUSING STRESS ON THE BOLT. WHEN HOLE LOCATION WAS CHECKED A	GAINST THE RT FINLET THERE WAS .100 OF AN INCH DIFFERENCE. A SMALL FLAT WAS GROUND IN THE WASHER SO IT WOULD NOT RIDE UP	 IN THE RADIUS WHEN BOLT INSTALLED. (TC NR 20060920006)			1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA	 
2006101900121	20061019	00121	EA  	2006	10	19	CA060920007      	1	20060413	G	2434		GENERATOR       			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					NR 2	SHORTED         	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) IN CLIMB BOTH GENERATORS TRIPPED OFF LINE AND WOULD NOT RESET. TROUBLE SHOOTING REVEALED AN INTERNAL SHORT IN THE 	NR 2 GENERATOR THAT CAUSED BOTH GENERATORS TO TRIP THROUGH THE BUSTIE.  SUBMITTER FILE IS ADR 150. (TC NR 20060920007)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006101100129	20061011	00129	SW  	2006	10	11	CA060920008      	1	20060918	G	7714	AG44AF	TACH GENERATOR  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT ENGINE	SLIPPED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED AIRPORT AND UPON CLIMBOUT THE RT ENGINE RPM INDICATION BEGAN TO FLUCTUATE.  ALL OTHER PARAMETERS	 REMAINED NORMAL.  AIRCRAFT RETURNED AND UPON INVESTIGATION FOUND DRIVE SHAFT INTACT YET SLIPPING INTERNALLY.  TACH GENE	RATOR REPLACED, RUNUP COMPLETED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060920008)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006101100133	20061011	00133	EA  	2006	10	11	CA060920009      	1	20060906	G	3213	C6UF10151	STRUT           			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FRONT FLOAT	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF IN ROUGH WATER THE LT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920009)						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006101100134	20061011	00134	EA  	2006	10	11	CA060920010      	1	20060906	G	3213	C6UF10151	STRUT           			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FRONT FLOAT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING IN ROUGH WATER THE RT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920010)						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006101100135	20061011	00135		2006	10	11	CA060920011      	4	20060918	G	2565		SLIDE           			AIRBUS	320   	A320214     	3930316	EU  	CFMINT	CFM56 	CFM565B4P   	 	NE  					L2 DOOR	UNWANTED DEPLOY 	W				H				DEACTIVATE SYST/CIRCUITS				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA											(CAN) ACCIDENTLY FLIGHT ATTENDANT DEPLOYED THE SLIDE AT L-2 DOOR. INITIALLY SHE WENT TO DEACTIVATE THE DOOR BUT WAS DIST	RACTED THEN USED THE OPEN LEVER INSTEAD OF THE DISARM LEVER CAUSING THE INCIDENT. SLIDE WAS DEPLOYED BUT NOT INFLATED, D	UE TO THE ACTUATION CABLE FOUND WRAPPED AROUND THE TOP OF CYLINDER WHICH PREVENT THE INFLATION. (TC NR 20060920011)				2	L	7	2 	4F	4	F	RT	A28NM   	E38NE				 
2006101100136	20061011	00136	SO  	2006	10	11	CA060920013      	2	20060916	G	8520	649134	CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	BROKEN          	W				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			1835 	1835 				293447R			(CAN) AT APPROXIMATLY 300 FEET AGL ON TAKE OFF THE PILOT REDUCED POWER FOR FULL POWER TO CLIMB POWER. A BANG WAS HEARD A	ND THE ENGINE LOST POWER. THE AIRCRAFT WAS OPERATING ON FLOATS AND WAS LANDED STRAIGHT AHEAD BACK ON TO THE LAKE IT HAD 	DEPARTED FROM.  INVESTIGATION DETERMINED THAT THE CRANKSHAFT HAD BROKEN BETWEEN CYLINDERS 1-2 /3-4. POSSIBLE CAUSE MAY H	AD BEEN MAIN CRANKSHAFT BEARING FAILURE.   THE AIRCRAFT HAD A 50 HR INSPECTION CARRIED OUT 11.1 HRS PRIOR TO THE ENGINE 	FAILURE. AT THAT TIME THE OIL AND OIL FILTER WERE CHANGED. THE REMOVED OIL FILTER WAS OPENED AND INSPECTED. AT THE TIME 	OF THE INSPECTION NO METAL OR OTHER CONTAMINANTS WERE DISCOVERED IN THE OIL FILTER. (TC NR 20060920013)	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006101100137	20061011	00137		2006	10	11	CA060921001      	4	20060827	G	8300	70BM011030	GEARBOX         			SNIAS 	350   	AS350*      	       	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ACCESSORY	DAMAGED         	W				B				EMER. DESCENT           				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			5400 	1384 							(CAN) OIL PRESSURE LINE FITTING AT ACCESSORY GEARBOX (FELL OUT) OF GEARCASE AND SUBSEQUENT COMPLETE LOSS OF OIL IN FLIGH	T.  THREADS IN GEARCASE STRIPPED 90 PERCENT; NO PREVIOUS INDICATION OF DISCREPANCY, IE: OIL LEAK OR LOOSENESS. (TC NR 20	060921001)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006101100138	20061011	00138	NM  	2006	10	11	CA060921002      	1	20060823	G	2910	AN81510D	UNION           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 HYD SYST	SHEARED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			1300 								(CAN) CREW REPORTED NR 2 ENG HYD PUMP CAUTION ILLUMINATED, PRESS AND QTY DEPLETED. FOLLOWING GEAR EXTENSION ON APPROACH.	 NO EMERGENCY DECLARED. MAINTENANCE FOUND THE HYD FITTING FROM THE EDP TO THE PRESS MANIFOLD SHEARED.  SYD 8-29-002, REP	LACEMENT OF ALUMINIUM UNION WITH STEEL UNION COMPLETED. (TC NR 20060921002)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006121300142	20061213	00142	SW  	2006	12	13	CA060921003      	1	20060916	G	6220	222011114103	PENDULUM        			BELL  	222   	222         	1182122	SW  										MAIN ROTOR	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			2006 								(CAN) A/C WAS IN CRUISE FLIGHT AT 700 FT, AGL WHEN A SUDDEN VIBRATION BEGAN. THE CREW MADE AN IMMEDIATE LANDING IN A FI	ELD AND SHUTDOWN. INSPECTION FOUND THAT ONE M/R PENDULUM WEIGHT HAD SEPARATED  AND STRUCK A M/R BLADE. THE DAMAGED AREA	 IS 3 INCHES LONG BY .1250-.2500 INCH WIDE AND A MAX DEPTH OF 0.0025 INCH. THE DAMAGE BLADE 222-015-500-105 S/N AMR06030	 TT4840.7 (TC NR 20060921003)			1	G	7	2 	3U				H9SW    					 
2006101100139	20061011	00139	NE  	2006	10	11	CA060921004      	2	20060911	G	7250	3044700	ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  		LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			14810	6715 				PS0145			(CAN) THE CREW REPORTED A LOW OIL PRESSURE INDICATION WHILE TAXING, SOME OIL WAS NOTED ON THE FUSELAGE SO AN AME WAS DIS	PATCHED. THEY COULD FIND NO AREA OF LEAKAGE DURING INSPECTION AND THE AIRCRAFT WAS REPLENISHED AND NUMEROUS GROUND RUNS 	DID NOT REVEAL ANYTHING FURTHER. THE AIRCRAFT WAS RETURNING TO A MAINTENANCE BASE WHEN THE AME NOTICED OIL COMING FROM T	HE BREATHER AREA OF THE ENGINE. THE CREW SHUT THE ENGINE DOWN AND RETURNED TO PLACE OF DEPARTURE WHERE THEY HAD AN UNEVE	NTFULL LANDING. FURTHER INSPECTION HEARD GRINDING NOISES COMING FROM THE POWER SECTION AREA WHICH INDICATES BEARING DAMA	GE IN THAT AREA. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE HAS BEEN RETURNED TO THE MAIN 	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006121300143	20061213	00143	CE  	2006	12	13	CA060921005      	1	20060919	G	2697		WIRE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NACELLE	CONTAMINATED    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA			14827								(CAN) CREW HAD A FIRE WARNING LIGHT COME ON IN FLIGHT, CREW FOLLOWED PROCEDURES AND TURNED THE AIRCRAFT 90 DEGREES TO RU	LE OUT LIGHT POSSIBLY TRIPPING DETECTORS AND LIGHT REMAINED ON. NO SIGN OF FIRE WAS NOTED VISUALLY ON WING NOR ON THE GL	ANCE OF INSTRUMENTATION. CREW THEN CARRIED ON AND THE LIGHT WHEN OFF PRIOR TO APPROACH. MAINTENANCE NOTIFIED AND INSPECT	ED,  FUNCTION CHECKED SYSTEM. SYSTEM FUNCTIONED NORMALLY. WIRING IN NACELLE FOUND  WET DUE TO THE WEATHER CONDITION ENRO	UTE WHICH WE HAVE DETERMINED A CAUSE FOR AN INTERMITTENT WARNING IN THE PAST. MAINTENANCE SEALED WIRING AS  REQUIRED TO 	REDUCE THE CHANCE OF THIS HAPPENING WHILE FLYING IN PRECIP. (TC NR 20060921005)	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2006101100140	20061011	00140	CE  	2006	10	11	CA060921006      	1	20060905	G	7500		LINE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	BLEED AIR	CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 10 MIN. INTO THE FLIGHT AT 5500 FT ALTITUDE AND IN CRUISE, THE PILOT NOTICED LIGHT SMOKE COMING FROM	 THE GENERAL LOCATION OF THE CIRCUIT BREAKER PANEL, AND A DISCOLORING OF THE LT CREW DOOR FWD POST PANEL, LOCATED JUST A	BOVE THE CB PANEL. THE PILOT FOLLOWED PROCEDURES FOR CABIN FIRE AND ELECTRICAL FIRE, AND RETURNED SAFELY TO THE AIRPORT 	OF DEPARTURE. AME`S WERE DISPATCHED TO THE A/C AND UPON INSPECTION FOUND THE CAUSE TO BE THAT THE LT CREW DOOR FWD POST 	TRIM PANEL WAS TOO CLOSE TO THE BLEED AIR LINE THAT RUNS UP THE DOOR POST FROM THE FIREWALL TO THE WING FOR DE-ICE PURPO	SES. THE METAL FLANGE THAT HELD THE PANEL IN PLACE HAD BEEN BENT, POSSIBLY FROM PILOTS REACHING UP AND GRIPPING THE DOOR	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006121300144	20061213	00144	CE  	2006	12	13	CA060922001      	1	20060922	G	3246	21401400	BEARING         	CLEVELAND   		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT MAIN GEAR	DESTROYED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			267  			DOT6849					(CAN) MAINTENANCE NOTICED FLUID LEAKING FROM THE RT MLG BRAKE ASSY. INVESTIGATION REVEALED THAT THE BRAKE ASSY. PISTON R	ETENTION BOLT WAS THE SOURCE OF THE LEAK. A MORE DETAILED INSPECTION DISCOVERED THAT THE RT MAIN WHEEL INNER WHEEL HALF 	CONE AND BEARING HAD BEEN DESTROYED. WHEEL REMOVAL SHOWED THAT THE WHEEL ASSY, AXLE, FORWARD AND AFT BRAKE CALIPERS AND 	LOWER TORQUE LINK HAD BEEN DAMAGED. THE WHEEL DID NOT DEPART THE AIRCRAFT AS THE OUTER WHEEL HALF BEARING ASSY. REMAINED	 IN TACT AND RETAINED THE WHEEL. ON THE DAY OF DISCOVERY THE AIRCRAFT HAD RECEIVED A PRE-DISPATCH INSPECTION AND FLEW FO	R A TOTAL OF 1.8 HOURS AIRTIME AND COMPLETED 5 LANDINGS. THERE WERE NO DEFECTS RECORDED IN THE JOURNEY LOG BOOK POST FLI	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2006121300145	20061213	00145	EU  	2006	12	13	CA060922002      	1	20060921	G	6220	350A37116200	STOP            	SNIAS       		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAST YOKE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5739 			M4979					(CAN) DAILY INSPECTION REVEALED YOKE ASSEMBLY STOP WAS BROKEN BELOW THE ATTACHMENT POINT. THE CABLE CLIP LOWER EDGE WOUL	D FOLLOW THE CRACK LINE. THE CABLE CLIP WOULD NOT CONTAIN THE BROKEN COMPONENT AND COULD CREATE FURTHER PROBLEMS IF UNIT	 BECOMES DISLODGED FROM THE RING. THE GRANULAR COMPOSITION OF THE BREAK MAY INDICATE A METALLURGICAL PROBLEM. THIS PART 	WAS NOT TESTED BUT IS BEING RETAINED IF MORE INVESTIGATION IS REQUIRED. (TC NR 20060922002)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006101100141	20061011	00141	CE  	2006	10	11	CA060925001      	1	20060925	G	3201	264101828	FAIRING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	RT MAIN GEAR	LOOSE           	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA			5509 	5509 							(CAN) DURING LANDING A SLIGHT THUMP AND A VIBRATION WAS FELT. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED TH	E AIRCRAFT AND FOUND THE RT MAIN LANDING GEAR FAIRING (GEAR TO FUSELAGE FAIRING) WAS MISSING THE LOWER PORTION. THIS FAI	RING IS A ONE PIECE FAIRING.THE LOWER PORTION OF THE FAIRING HAD BROKEN FREE. FURTHER INSPECTION FOUND MINOR DAMAGE TO T	HE RT HORIZONTAL STAB. LEADING EDGE. REPAIRS ARE CURRENLY BEEN CARRIED AND A NEW FAIRING ORDERED TO BE REPLACED. (TC NR 	20060925001)		1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006101100142	20061011	00142	NE  	2006	10	11	CA060925002      	2	20060819	G	7322	AKM621RA	CARBURETOR      			DHAV  	DHC3  	DHC3        	2800202	EA  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  					ENGINE	LEAKING         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA			311  								(CAN) ACCORDING TO THE PILOT WHILE IN FLT THE ENGINE STARTED TO RUN ROUGH AND SPUTTERED A FEW TIMES, THE PILOT CHECKED L	T AND RT MAGNETOS, CARB HEAT, BOOST PUMP, GAUGES-OIL TEMPERATURE AND PRESSURE, FUEL PRESSURE AND CYLINDER HEAD TEMPERATU	RE. ALL GAUGES WERE INDICATING NORMAL RANGES. SWITCHED FUEL TANKS AND THE PROBLEM THEN WENT AWAY. A FEW MINUTES LATER TH	E PROBLEM OCCURRED AGAIN. THE PILOT THEN NOTIFIED A COMPANY AIRCRAFT AND PROCEEDED WITH UNSCHEDULED LANDING FOR PURPOSE 	OF INVESTIGATING PROBLEM. THE ENGINE PROBLEM WAS NOT EVIDENT ON THE APPROACH AND LANDING. ONCE ON THE WATER THE PILOT TH	EN WENT TO SHORE AND DRAINED THE FUEL SUMPS AND CHECKED THE CARB HEAT FUNCTION. THE PILOT THEN DID MULTIPLE RUN UPS AT D	1	H	7	1 	3R	3	R		A815    	E10NE				 
2006121300146	20061213	00146	SO  	2006	12	13	CA060925003      	1	20060830	G	2797	6345703	CONNECTOR       	PIPER       		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	RUDER TRIM ARM	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			3676 								(CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED THE RUDDER FAILED TO RESPOND. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CO	NNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD. THE COMPLET	E RUDDER TRIM ARM ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW UNIT. METAL FATIGUE IS SUSPECTED. (TC NR 20060925003)				1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2006101100155	20061011	00155	NE  	2006	10	11	CA060925004      	2	20060912	G	8520	27056CAI	PISTON          			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985*       	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				946  							(CAN) DURING REGULAR INSPECTION LOW COMPRESSION WAS NOTED ON NR 1 CYL. CYLINDER WAS REMOVED AND PISTON WAS CRACKED. CYLI	NDER ASSY WAS REPLACED. AIRCRAFT GROUND RUN WAS CARRIED OUT SATISFACTORY. (TC NR 20060925004)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006121300112	20061213	00112	EA  	2006	12	13	CA060925005      	1	20060922	G	7931		SCREEN          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					OIL SCAVENGE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ABOUT 50 NM EAST AND AT FL330 THE CREW REPORTED LT ENG OIL PRESSURE WARNING LIGHT WITH FLUCTUATING LOW OIL PRESSUR	E READINGS (20-46PSI) AT IDLE POWER LT OIL TEMP WAS INCREASING. THE CREW ELECTED TO SHUT DOWN THE LT ENGINE.  LINE MAINT	ENANCE REMOVED LT ENGINE OIL PUMP AND INSPECTED ALL SCAVENGE SCREENS IAW SB 79-001200 OIL. FOUND SCAVENGE SCREEN PLUGGED	 WITH COKED OIL. REPLACED OIL PUMP AND PUMP SCREENS IAW AMM 79-21-01 ENGINE RUNS CARRIED OUT AND THE AIRCRAFT WAS RELEAS	ED INTO SERVICE. THE OIL FILTER AND SAMPLE HAVE BEEN SENT FOR ANALYSIS. (TC NR 20060925005)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120800006	20061208	00006	SW  	2006	12	8	CA060925007      	1	20060923	G	2435		SHAFT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER GEN	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				461  							(CAN) PILOT REPORTED THAT THE STARTER WOULD NOT TURN THE ENGINE, IT WOULD JUST SPIN.  MAINTENANCE FOUND THAT THE SHAFT O	N THE STARTER HAD BEEN SHEARED. STARTER HAD BEEN REPLACED AND AIRCRAFT RETURN TO SERVICE. (TC NR 20060925007)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006101100160	20061011	00160	CE  	2006	10	11	CA060925008      	1	20060919	G	3213	45325400018	STRUT           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					NLG	UNDERSERVICED   	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA			2707 								(CAN) AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND ALL LANDING GEAR NOT-UP AND LOCKED LIGHTS DID NOT EXTINGUISH. AIRCR	AFT DIVERTED AND AFTER LANDING IT WAS DISCOVERED THE NOSE STRUT WAS COMPLETELY COLLAPSED. THE NOSE STRUT WAS RE-SERVICED	 WITH NITROGEN AND GEAR SWINGS ACCOMPLISHED WITH NO PROBLEMS. ON RETURN TO OUR BASE, THE NOSE STRUT WAS MODIFIED TO NEW 	PN 4532230001-804 (MODIFICATION OF UPPER STRUT SEAL ASSY. INSTALLATION) (TC NR 20060925008)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2006101100161	20061011	00161	NM  	2006	10	11	CA060925009      	1	20060923	G	3297	D4668	CONNECTOR       			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ANTI-SKID SYS	FAULTED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING, THE NR 1 AND NR 4 TIRES SKIDDED UNTIL THEY BLEW OUT. THE A/C HAD TO BE TOWED FROM THE RUNWAY. AVIONICS	 PERSONELL DISCOVERED AN INTERMITTENT FAULT IN AN ANTI-SKID CONNECTOR (D4668) ABOVE THE RT GEAR LEG. ALL 4 TIRES AND THE	 CONNECTOR WERE REPLACED AND THE A/C RETURNED TO SERVICE. (TC NR 20060925009)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006120800007	20061208	00007	CE  	2006	12	8	CA060926003      	1	20060921	G	5610	10138402524	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			1354 								(CAN) IN HOLDING PATTERN  AT 9,000 FT/-2C/WINDSHIELD HEAT ON LOW; OUTER PANE OF WINDSHIELD CRACKED FOR NO APPARENT REASO	N. FLIGHT CONTINUED  AND LANDED WITHOUT INCIDENT.  NO EVIDENCE OF BIRD STRIKE OR FOREIGN OBJECT DAMAGE NOTED.  (TC NR 20	060926003)				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007050700093	20070507	00093	CE  	2007	5	7	CA060926004      	1	20060923	G	2731	11452403725	CONTROL CABLE   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ELEVATOR TRIM	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			22576								(CAN) CREW REPORTED DIFFICULTY WITH CHANGING THE ELEVATOR TRIM ON APPROACH.  MAINTENANCE FOUND THAT THE ELEVATOR TRIM CA	BLE HAS BROKEN AT THE TRIM SERVO/CAPSTAN LOCATION. THIS SERVO/CAPSTAN COMPONENT IS ONLY INSTALLED ON AUTOPILOT EQUIPPED 	1900D`S OF WHICH THERE ONLY VERY FEW. THE CAPSTAN REQUIRES ROUTING OF THE .0625 CABLE. (TC NR 20060926004)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006101100162	20061011	00162	GL  	2006	10	11	CA060926005      	3	20060913	G	6111	M10876ANS	BLADE           	HARTZL      		STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3341 		EVA2469			EVA2469		(CAN) UPON VISUAL INSPECTION , CORROSION WAS FOUND ON THE BLADE SHANK. AFTER REWORK TO MINIMUM DIMENSION DAMAGE STILL RE	MAINS. BLADE WIDTH AND THICKNESS IS WELL ABOVE MINIMUM DIMENSION. ALL 5 BLADES ARE U/S.  (TC NR 20060926005)					2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL	 
2006101100163	20061011	00163	GL  	2006	10	11	CA060927001      	2	20060919	G	7230	23053990	SCROLL          	RROYCE      		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6362 	5265 		CAC90168					(CAN) DURING SCHEDULED 100/300 HR INSPECTION COMPRESSOR SCROLL FOUND CRACKED ON VISUAL INSPECTION. A/C GROUNDED AND COMP	RESSOR REPLACED. RECOMMEND BETTER DAILY INSPECTIONS BEFORE FIRST FLIGHT. (TC NR 20060927001)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2006120800020	20061208	00020	SW  	2006	12	8	CA060927003      	1	20060927	G	5730		SKIN            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	WINS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28657								(CAN) PERIMETER WAS INFORMED FROM ANOTHER OPERATOR OF THE SAME AIRCRAFT OF POTENTIAL WING SKIN CRACKS EMINATING FROM THE	 LT AND RT BATTERY VENT SCOOPS INSTALLED IN THE LOWER WING SKIN BETWEEN THE NACELLE AND FUSELAGE. INITIAL VISUAL INSPECT	ION REVEALED NO CRACKS BUT WITH THE USE OF EDDY CURRENT THE CRACKS WERE DISCOVERED AND FOUND PROGRESSING FROM 3 OF THE 4	 CORNERS OF THE BATTERY VENT SCOOP AT THE WING SKIN. THE 4 AC OF THIS TYPE INSPECTED, 3 HAD CRACKS FOUND ON THE LOWER WI	NG BATTERY VENT SCOOPS. THEY WERE INSPECTED AND ALL FOUND WITH EDDY CURRENT INSPECTION METHOD. REPAIR DESIGN CERTIFICATE	 RDC C-RA06-235/D HAS BEEN APPROVED FOR THE REPAIR OF THIS DEFECT. (TC NR 20060927003)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006101100164	20061011	00164	NM  	2006	10	11	CA060928001      	1	20060928	G	7312	S2L354	O-RING          			DHAV  	DHC8  	DHC8301     	1386003	NM  										FUEL HEATER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ACCOMPLISHMENT OF THE TASK 2150/05 (HEAT EXCHANGER CORE CLEANNING) WE FOUND A NEW O-RING DAMAGED IN THE	 ORIGINAL PACKAGE. THE O-RING COME FROM NATIONNAL O-RING  MFGR. COMPD. NR V-14  MFG BATCH NR: 58978  CURE DATE: 4088  EX	P. DATE: OCT 01,2009 THE O-RING WAS DAMAGE ALL AROUND. A OTHER O-RING WITH THE SAME BATCH AND PN USE ON THE SAME JOB WAS	 FOUND OK FOR THE INSTALLATION. (TC NR 20060928001)			2	H	7	2 	4T			RT	A13NM   					 
2006101100165	20061011	00165	NE  	2006	10	11	CA060928002      	2	20060916	G	7200		ENGINE          			AIRBUS	320   	A320211     	3930320	EU  	GE    	CFM56 	CFM565A     	13802	NE  					NR 2	VIBRATION       	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA								731250			(CAN) T/O REJECTED AT APPROX 110 KTS DUE SERIOUS VIBRATIONS (SUSPECT RT MAIN GEAR).  AUTO BRAKE USED MAX BRAKE TEMP IND 	480 DEG FOR NR 2, OTHERS WERE 450-480. ON STARTING NR 2 ENGINE, FELT HIGH VIBRATION AND HIGH EGT, ABORTED ENGINE START. 	WHEN TURNING NR 2 FAN BY HAND, COULD HEAR N2 TURNING AS WELL. FOUND RT GEAR FIXED DOOR ASSY WITH 2 ATTACH STUDS SHEARED.	  SB A320-52-1100 ALREADY AVAILABLE TO INSTALL IMPROVED ATTACH STUDS.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007050700094	20070507	00094	SW  	2007	5	7	CA060928003      	1	20060909	G	5521	222182	STRINGER        			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235K2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	FUSELAGE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			3626 								(CAN) AFTER RECOVERING FROM AN AEROBATIC MANEUVER, THE PILOT FOUND THAT FULL DOWN ELEVATOR TRAVEL COULD NOT BE OBTAINED.	 A UNEVENTFUL RETURN TO THE AIRPORT AND LANDING WAS CARRIED OUT.  ONCE THE ELEVATOR BELLCRANK COVER WAS REMOVED, THE LT 	GUSSET FROM THE AFT STRINGER SUPPORT FELL OUT AND FULL ELEVATOR TRAVEL WAS OBTAINED. EXAMINATION OF THE GUSSET, SUPPORT 	AND RIVETS INDICATED THAT VIBRATION OF THE FABRIC IN FLIGHT HAD LOOSENED THE SOFT ALUMINUM POP RIVETS THAT THE MFG HAD U	SED IN ATTACHING THE GUSSET HAD WORKED LOOSE AND EVENTUALLY BROKEN, ALLOWING THE GUSSET TO FALL INTO THE BELLY AND WORK 	ITS WAY BACK INTO THE TAIL WHERE IT BECAME LODGED IN THE NARROW CLEARANCES AROUND THE ELEVATOR BELLCRANK.  THE SUBMITTER	1	H	7	1 	3O	3	O		A759    	E223	5	N	P9045	 
2006120800021	20061208	00021	CE  	2006	12	8	CA060928004      	1	20060817	G	3210	1158100325	TORQUE KNEE     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION THE LT UPPER TORQUE KNEE WAS FOUND CRACKED. THE TORQUE KNEE WAS REPLACED AND THE AIRCR	AFT RETURNED TO SERVICE. SEE ATTACHED PICTURES. (TC NR 20060928004)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2006121100154	20061211	00154	GL  	2006	12	11	CA060928005      	3	20060925	G	6111	R1015255	BLADE           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2015 						AH4		(CAN) PROPELLER RECEIVED FOR O/H. UPON DISMANTLING DISCOLORATION ON THE BLADE SHANKS WAS NOTED. SHANKS WERE LIGHTLY MEDI	A BLASTED AND THE DAMAGE IS MORE SEVERE THAN AT FIRST INSPECTION. BLADE SHANK RADIUS IS AT 4.194 INCHES MINIMUM FOR REPA	IR IS 4.187 INCHES. THESE 3 BLADES ARE UNSERVICEABLE DUE TO THIS CORROSION. (TC NR 20060928005)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2006120800022	20061208	00022	GL  	2006	12	8	CA060928006      	3	20060915	G	6114	C3054	FERRULE         	MCAULY      		CESSNA	185   	185         	2072802	CE  	CONT  	O470  	IO470F      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				69   		778082					(CAN) PROP RECEIVED FOR 10 YR. O/H. UPON DISMANTLING DISCOVERED CORROSION DAMAGE TO FERRULE. PART IS U/S (TC NR 20060928	006)					1	H	7	1 	3O	3	O	NC	3A24    	3E1	5	C	P3EA	 
2006101100166	20061011	00166	EA  	2006	10	11	CA060929001      	1	20060918	G	5751	DSC5108	BEARING         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE DEFECT WAS FOUND DURING A REPAIR OF WING TIP LIGHTNING STRIKE ON SEPTEMBER 18, 2006 AT A/C TCSN 35,548 CYCLES.	 AT THE OUTER AILERON THE HINGE FITTING ASSY SHOWED A PREMATURE BEARING WEAR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006101100167	20061011	00167	NM  	2006	10	11	CA060929002      	1	20060926	G	2781	10608197	INDICATOR       			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					KRUEGER FLAPS	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DEPARTING THE CREW OBSERVED A L/E FLAP UNRETRACTED INDICATION AT THE NR 1 POSITION.THE AIRCRAFT RETURNED TO POINT 	WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE POSITION INDICATION SWITCH HAD FAIL AT THE NR 1 KRUEGER FLAP LOCATION. T	HE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060929002)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007010400001	20070104	00001		2007	1	4	CA060929003      	4	20060920	G	6122	941521	SCREW           			AMBLP 	A150  	A150        	3850110	NM  	ROTAX 	914   	ROTAX914    	 	EU  					GEARBOX	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			2077 	577  							(CAN) PROP WOULD NOT CHANGE PITCH DURING RUN-UP. GEARBOX WAS REMOVED AND THE SCREW HOLDING THE GOVENOR DRIVE COUPLING TO	 THE DRIVE GEAR WAS FOUND BROKEN. THE SCREW APPEARED TO HAVE FAILED FROM TORQUE OVERLOAD. THE SCREW, DRIVE COUPLING AND 	GEAR WERE REPLACED AND ENGINE RETURNED TO SERVICE. NO FOD NOTED. THE ENGINE HAS 577 HRS SINCE OVERHAUL. (TC NR 200609290	03)			1	B	7	2 	3O	3	O	0	SOOOO2SE	EXPE3I				 
2006120800029	20061208	00029	EU  	2006	12	8	CA060929004      	1	20060928	G	3246	50104882A	WHEEL           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	MLG	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ARRIVAL, THE CAPTAIN WAS NOTIFIED THAT THE AIRCRAFT NR 3 MAINWHEEL WAS MISSING.  MAINTENANCE INSPECTION REVE	ALED THAT ALTHOUGH THE WHEEL NUT AND LOCKING BOLT WERE IN PLACE THE WHEEL ITSELF WAS MISSING. (TC NR 20060929004)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2006120800030	20061208	00030	EA  	2006	12	8	CA060929005      	2	20060928	G	7313	310926302	DUCT            								PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3035 					RB0207			(CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE L	ARGE EXIT DUCT.  THE (LED) WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THROUGH	 ONE LAYER OF THE DUCT AND CRACKS HAD FORMED IN THE SECOND LAYER.  THE ENGINE HAD  OF 3034.6 TSN HOURS AND 6819 CYCLES. 	 THIS WAS THE THIRD (LED) THAT THIS OPERATOR HAS HAD PROBLEMS WITH.  IT IS SUSPECTED THAT EITHER A BAD FUEL NOZZLE (NOZZ	LES HAVE BEEN SENT OUT FOR TESTING) OR MATERIAL DEFECT CAUSED THE FAILURE. (TC NR 20060929005)							4	T			E4EA				 
2006120800031	20061208	00031	NE  	2006	12	8	CA061002001      	2	20061002	G	7200	AS21040	BOLT            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAYMK6118   	 	NE  					ENGINE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7000 					16230			(CAN) NON APPROVED AS21040 BOLT WAS FOUND. BOLT HEAD WAS MACHINED TO ADD PN AS21040.  BOLT END ALSO MACHINED WITH A CENT	ER HOLE, THREAD LENGTH SHORTER AND DIAMETER OF BOLT IS UNDERSIZE. BOLT LOCATIONS ON ENGINE; CLIPPING POINT FOR P3 AIR TU	BE TO FFR UNION P3 LIMITER,  IP BLEED VALVE CLAMPING SEAL/RETAINING SEAL AND LP FUEL FILTER MOUNTING BOLT.  (TC NR 20061	002001)			2	L	7	2 	4F	4	F	RT	A12EA   	A25NE				 
2006120800050	20061208	00050	NE  	2006	12	8	CA061002002      	2	20060909	G	7200	3066T90G02	ENGINE          			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TP 	CT79B       	30030	NE  					NR 1	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE FOLLOWING REPORT REFERS TO FLT OCCURRENCE REPORT NR 06-00894. THE AIRCRAFT WAS OPERATING FOR CUSTOMER ON AN OF	FSHORE FLIGHT. AT APPROX 09.58 WHILE ON SHORT FINAL APPROACH (IN VMC), 2 POPS WERE HEARD BY THE CREW. A MISSED APPROACH 	WAS INITIATED, AND DURING THE CLIMB OUT IT WAS APPARENT THE NR 1 ENGINE HAD HIGH TGT AND LOWER TORQUE THAN THE NR 2 ENGI	NE. DURING THE CLIMB SEVERAL MORE POPS WERE HEARD. AFTER REACHING A SAFE HEIGHT, THE EMERGENCY CHECKLIST WAS FOLLOWED FO	R (COMPRESSOR STALLING) ON THE NR 1 ENGINE.  IAW THE CHECKLIST, THE NR 1 ENGINE WAS BROUGHT BACK TO IDLE, AND THE COMPRE	SSOR STALLING CEASED. THE CREW THEN ELECTED TO RETURN TO DEPARTURE, WITH NR 1 ENGINE AT IDLE, IAW THE EMERGENCY CHECKLIS	2	G	7	2 	4U	4	T		R00024BO	E8NE				 
2006120800051	20061208	00051		2006	12	8	CA061002003      	4	20060824	G	3442		DIODE           	HONEYWELL   		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	WX RADAR SYSTEM	BURNED          	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA			26789	26789		1643					(CAN) ON DECENT THROUGH 10,000 FEET, F/O NOTICED A HAZY SMOKE IN THE COCKPIT. BOTH THE CAPTAIN AND THE F/O BEGAN TO FEEL	 A BURNING SENSATION IN THEIR THROATS. THEY DONNED THEIR OXYGEN MASKS AND REQUESTED A VISUAL DIRECT APPROACH.  THERE WAS	 A DEFINITE ELECTRICAL SMELL IN THE COCKPIT. THE CABIN HAD A SLIGHT ODOR BUT NOT RECOGNIZABLE. PASSENGERS WERE UNAWARE O	F THE SITUATION, NO PASSENGER REACTION. CREW DID NOT DECLARE AN EMERGENCY AND LANDED SAFELY WITHOUT FURTHER INCIDENT. MA	INTENANCE DISCOVERED WEATHER RADAR INDICATOR TO BE AT FAULT. WEATHER RADAR INDICATOR AND TRANSMITTER/RECEIVER REPLACED A	ND TESTED SERVICEABLE. AIRCRAFT SUCCESSFULLY TEST FLOWN PRIOR TO RETURN TO SERVICE. INDICATOR HAD 865:02 HOURS AND 830 L	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120800052	20061208	00052	WP  	2006	12	8	CA061002004      	1	20060805	G	5411	C04618	FRAME           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			350  	350  							(CAN) AFT TAB WAS FOUND TO BE CRACKED UPON ROUTINE SCHEDULED INSPECTION. NEW FRAME ORDERED AND HELICOPTER WAS NOTIFIED O	F THE PROBLEM.  THEY HAVE SINCE RELEASED A NEW BULLETIN ADDING A CLAMP TO THE FRAME.  THIS AIRCRAFT IS REGISTERED WITH M	FG FOR WHEN THE CORRECTIVE PARTS BECOME AVAILABLE. (TC NR 20061002004)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006120800053	20061208	00053	SW  	2006	12	8	CA061002005      	1	20060831	G	2711		CABLE           			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2B     	41508	EA  	MCAULY	1A175	1A175GMA    	GL  	AILERON TAB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48   								(CAN) IAW AD 2005-24-10 AND MFG SERVICE LETTER NR 427, THE FLIGHT CONTROL CABLE INCLUDED IN THE WING RETROFIT KIT WAS IN	SPECTED FOR PROPER SWAGING. AILERON CABLES REQUIRED PROPER SWAGING.  (TC NR 20061002005)					1	H	7	1 	3O	3	O	NC	A759    	E274	5	N	P857	 
2006120800054	20061208	00054	SO  	2006	12	8	CA061002006      	1	20060928	G	3230		LANDING GEAR    			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  	HARTZL	HCC3Y	HCC3YN      	GL  	RIGHT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DEFECT: UNABLE TO PUT DOWN GEAR AND GET 3 GREEN LIGHTS. UPON 4TH TRY WHILE IN A HARD RT TURN, FINALLY GOT RT MAIN 	GEAR DOWN AND LOCKED. AIRCRAFT RETURNED TO BASE WITH LANDING GEAR IN DOWN/LOCKED POSITION UNDER FERRY FLIGHT PERMIT.  RE	CTIFICATION: LANDING GEAR INSPECTED, SYSTEM FLUSHED AND BLED IAW MFG MM. LANDING SWUNG 50 FAULT FREE TIMES. UNABLE TO DU	PLICATE FAULT. AIRCRAFT RETURNED TO SERVICE.  (TC NR 20061002006)			1	L	7	2 	3O	3	O		A8EA    	E19EA	5	C	P25EA	 
2006120800055	20061208	00055	EA  	2006	12	8	CA061002007      	2	20060928	G	7321	25245019	FUEL CONTROL    			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  	HARTZL	HCC3Y	HCC3YN      	GL  	ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) UNCONTROLLABLE POWER FLUCTUATIONS AT HIGH POWER SETTINGS ON LT ENGINE.  FOUND FUEL CONTROL UNIT P/N 2524501-9 S/N 	70084801 TO BE UNSERVICEABLE. REPLACED WITH REBUILT UNIT P/N 2524501-9 S/N 70157810. SYSTEM GROUND RUN SERVICEABLE. (TC 	NR 20061002007)				1	L	7	2 	3O	3	O		A8EA    	E19EA	5	C	P25EA	 
2006120800066	20061208	00066	WP  	2006	12	8	CA061002009      	1	20060926	G	6797	1520	WIRE            	ROBSIN      	C0581       	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CYCLIC GRIP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2196 								(CAN) GRIP ASSEMBLY OPENED TO INSTALL CARGO HOOK SWITCH AND FOUND STARTER BUTTON WIRE CHAFED UP AGAINST A GRIP MOUNTING 	SCREW.  THE INSULATION WAS SPLIT OPEN 0.25 INCH AND 2 WIRE STRANDS REMAINED UNBROKEN. (TC NR 20061002009)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006120800067	20061208	00067	EU  	2006	12	8	CA061002010      	1	20060928	G	2497	E0052R22B55SNE	CONNECTOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	ELECTRICAL PWR	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA											(CAN) CONNECTOR WAS SHORTING ACROSS INSULATING MATERIAL. PROBLEM WAS BETWEEN ADJACENT PIN CONTACTS. MATING CONNECTOR 704	VC WAS UNHARMED. BURNED CONTACTS HAD LOTS OF BLACK CARBON ON THEM. (TC NR 20061002010)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006120800069	20061208	00069	GL  	2006	12	8	CA061002011      	3	20060929	G	6197	5038912131	CONNECTOR       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	NR 2 PROPELLER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FAULT - LT SIDE AUTOFEATHER LIGHT DOES NOT ARM.   NR 2 HIGH PRESS FEATHER SWITCH CONNECTOR, CONNECTOR PIN LETTER B	 REPLACED. SWITCH CONNECTORS CLEANED. PROBLEM SEEMED TO BE CAUSED BY CONTAMINATION. (TC NR 20061002011)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006120800070	20061208	00070	EU  	2006	12	8	CA061003001      	1	20060924	G	3240	AC13794	PRESSURE VALVE  			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	BRAKE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				11340							(CAN) DURING TAXI TO POSITION THE THE MAIN HYDRAULIC SYSTEM WAS CYCLING EVERY 30 SECONDS. THE CREW RETURNED TO COMPANY R	AMP. THE IB BRAKE PRESSURE REDUCING VALVE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061003001)					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2006120800071	20061208	00071	EU  	2006	12	8	CA061003003      	1	20060928	G	3060		BRUSH BLOCK     			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	PROPELLER	UNKNOWN         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AFTER DEPARTURE THE CREW OBSERVED AN ANTI-ICE FAULT ON NR 1 POSITION.  THE AIRCRAFT RETURNED TO POINT	 OF DEPARTURE. MAINTENANCE REPLACED THE BRUSHES ON NR 1 BRUSH BLOCK AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 200	61003003)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006120800072	20061208	00072	CE  	2006	12	8	CA061003004      	1	20060926	G	5740	114430002179	ANGLE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	BS 288	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9184 								(CAN) WHILE COMPLETING A PRESSURIZATION CHECK OF THE CABIN, AIR WAS FOUND TO BE LEAKING OUT AROUND SPAR/ FUSE JOINT AREA	. CRACKS WERE FOUND ON THE LT AND RT WING-FUSELAGE CLOSING ANGLES AT FS 288  IN THE SAME SPOTS MEASURING 1.7500 INCHES E	ACH.  LT ANGLE IS P/N 114-430002-179 AND THE RT IS114-430002-180.  CRACKS REPAIRED IAW SRM 53-90-23. (TC NR 20061003004)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006120800073	20061208	00073	GL  	2006	12	8	CA061003005      	1	20061001	G	2910		HYDRAULIC SYSTEM			BOMBDR	BD100 	BD1001A10   	1390044	GL  										NR 2	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE VERIFYING A NOSE WHEEL STEERING SNAG DURING TAXI TEST, A LOSS OF HYDRAULIC FLUID FROM NR 2 SYSTEM OCCURED.  	LT AND RT ENGINES WERE SHUTDOWN AND AREA WAS INSPECTED.  HYDRAULIC FLUID WAS FOUND TO HAVE SPRAYED IN AFT FUSELAGE AND O	N THE RT SIDE. (TC NR 20061003005)				2	L	7	2 	4F			RT	T00005NY					 
2006120800074	20061208	00074	SO  	2006	12	8	CA061004001      	2	20060924	G	7314	64936849A1	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE	OUT OF ADJUST   	W				O				OTHER                   				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			CA			88   					650201			(CAN) AIRCRAFT ENGINE FAILED IMMEDIATELY AFTER SPIN RECOVERY.  INSTRUCTOR CONFIRMED FUEL PUMP ON AND MIXTURE FULL RICH. 	 INSTRUCTOR ESTABLISHED BEST GLIDE ATTITUDE AND RESTARTED ENGINE IAW AFM (ENGAGING STARTER).  UPON LANDING AND TAXI, INS	TRUCTOR KEPT POWER ABOVE 1000 RPM, SO THERE IS NO FURTHER INFO ON LOW POWER BEHAVIOR DURING THIS FLIGHT.  IMMEDIATELY PU	T TEST GAUGES ON, AND RAN UP AIRCRAFT.  UNMETERED PRESSURE WAS APPROXIMATELY 1.6 PSI LOW AND METERED PRESSURE WAS APPROX	 2 PSI LOW.  IDLE MIXTURE RISE OF 10 TO 20 RPM.  IT IS WORTH NOTING THAT I FELT THE ENGINE DID NOT (SOUND) AS IF IT WAS 	FUNCTIONING PROPERLY.  WE HAVE CURRENTLY REMOVED ALL FUEL SCREENS, INSPECTED AND CLEANED.  MODERATE CONTAMINATION FOUND 	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006120800076	20061208	00076	NM  	2006	12	8	CA061004003      	1	20061002	G	3233	65446604	ACTUATOR        			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	BYPASSING       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THE NOSE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHO	UT INCIDENT. MAINTENANCE DETERMINED THAT THE NOSE LANDING GEAR GRAVEL DEFLECTOR ACTUATOR HAD FAILED. THE ACTUATOR WAS RE	PLACED AND THE AIRCEAFT WAS RETURNED TO SERVICE. (TC NR 20061004003)				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006120800078	20061208	00078	EA  	2006	12	8	CA061004004      	1	20061002	G	2722	82960010147	TUBE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	RUDDER ACTUATOR	CRACKED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) CREW NOTICED FLUID STAINS AND ACCUMULATION ON RT SIDE OF RUDDER AND TAIL CONE.  MAINTENANCE FOUND CRACK AT FIRST E	LBOW FROM TOP FITTING OF  NO. 1 HYDRAULIC SYSTEM PRESSURE LINE TO THE RUDDER ACTUATOR. LINE REPLACED AND SYSTEM LEAK CHE	CKED SERVICEABLE. IPC REF CH 27-21-00 FIG. 20 ITEM 120. AFTT 34,145:10 HOURS, AFTC 38202. (TC NR 20061004004)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120800079	20061208	00079	EU  	2006	12	8	CA061004005      	1	20060926	G	3250	114068003	ACTUATOR        			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	NLG STEERING	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			136  	136  							(CAN) PILOTS REPORTED NOSE GEAR STEERING FAILURE.  NOSE GEAR ACTUATOR REPLACED.  SYSTEM TESTED AND AIRCRAFT RETURNED TO 	SERVICE (TC NR 20061004005)					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
2006120800082	20061208	00082	EA  	2006	12	8	CA061004006      	2	20061001	G	8520		BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					CRANKSHAFT	BROKEN          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			8542 	1341 				L251768A			(CAN) THE AIRCRAFT DEPARTED THE RUNWAY FOR A 1 HOUR TRIP. APPROXIMATELY 17 MINUTES INTO THE CRUISE PORTION OF FLIGHT THE	 PILOT NOTICED A LOSS IN OIL PRESSURE FOLLOWED BY NOISE FROM THE RT ENGINE. THE PILOT IMMEDIATELY FEATHERED THE PROP AND	 SHUTDOWN THE ENGINE. THE WEATHER WAS OK AND ELECTED TO RETURN TO THE DEPARTURE RUN-WAY AND LANDED WITHOUT INCIDENT. AN 	INVESTIGATION REVEALED THAT THE CRANKSHAFT BROKE AT THE NR 2 BEARING JOURNAL. (TC NR 20061004006)			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006120800083	20061208	00083	SW  	2006	12	8	CA061004007      	1	20061002	G	5302	206020113	INSERT          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13000								(CAN) IN COMPLIANCE WITH CF-2006-12 THE VERTICAL FIN WAS INSPECTED WITH 10X MAGNAFLYING GLASS AND THEN WAS LPI INSPECTED	 AND A CRACK WAS FOUND ON ONE OF THE INSERTS. THE FIN WAS SENT OUT FOR REPAIR. (TC NR 20061004007)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120800084	20061208	00084	EA  	2006	12	8	CA061004008      	2	20060930	G	7240	310926302	DUCT            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1677 							(CAN) DURING A REGULARLY SCHEDULED HOT SECTION INSPECTION A CRACK WAS NOTICED IN THE LARGE EXIT DUCT (LED) BEING REMOVED	 FROM THE ENGINE.  THE CRACK WAS LOCATED ON THE DOME AT THE DOUBLE WALL SEAM.  THE LED HAD BEEN RECENTLY OVERHAULED AND 	HAD A TSO OF 1676.9.  THIS WAS THE 4TH LED DUCT THAT THIS OPERATOR HAS HAD A PROBLEMS WITH. (TC NR 20061004008)				1	H	7	1 	3R	4	T		A815    	E4EA				 
2006120800086	20061208	00086	EA  	2006	12	8	CA061004009      	1	20061004	G	3200		WASHER          			DHAV  	DHC6  	DHC6        	2802606	EA  										MLG	MISMANUFACTURED 	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) WE HAVE FOUND 2 BATCHES OF C6U1156-27 MAIN LANDING GEAR WASHERS MADE FROM ALUMINUM LAMINATED SHIM MATERIAL, BUT SH	OULD HAVE BEEN MADE FROM STAINLESS STEEL SHIM MATERIAL.  DUE TO THE APPLICATION OF THE WASHER, THERE IS NO STRENGTH REQU	IREMENT, HOWEVER, THERE IS A POTENTIAL FOR GALVANIC CORROSION. THE AFFECTED BATCHES OF WASHERS ARE WO-25363/1 AND PO4314	1/69.  (TC NR 20061004009)			1	H	7	2 	3T			RT	A9EA    					 
2006120800088	20061208	00088		2006	12	8	CA061005001      	1	20061005	G	3000		LINE            								PWA   	JT15  	JT15D4      	52112	NE  					ANTI ICE SYS	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			7161 	858  							(CAN) SEE REPORT ATTACHED  GAS GENERATOR DISPLAYED VISIBLE SIGNS OF COKED OIL ON THE EXTERNAL CASING. ENGINE OIL LEAK WA	S CAUSED BY ANTI-ICING STEEL TUBE DEBONDING FROM THE INTERMEDIATE CASE CASTING AT THE STEEL TAB USED TO LOCATE THE TUBE 	DURING THE CASTING PROCESS. THE TAB PROTRUDES INTO THE OIL TANK AND IF DEBONDED CAN CAUSE OIL LEAKAGE.  ENGINEERING REPO	RT ATTACHED TO THIS SDR. (TC NR 20061005001)								4	F			E1NE				 
2006120800091	20061208	00091	CE  	2006	12	8	CA061005002      	1	20061005	G	5740	0513006142	RIVET           			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FITTING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7171 								(CAN) THE AIRCRAFT WAS DISASSEMBLED. IT WAS NOTED THAT THERE WERE SEVERAL LOOSE AND SMOKING FASTENERS THROUGH RT AFT WIN	G FITTING BRACKET IN FUSELAGE. REFERENCED MFG PART MANUAL P527-12 FIGURE 30 INDEX NR 99.  (TC NR 20061005002)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2006120800093	20061208	00093	NE  	2006	12	8	CA061005003      	2	20061005	G	8530		INTAKE DUCT     			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 5 OF THE 9 INTAKE TUBES WERE FOUND CRACKED AT THE CYLINDER FLANGE. (TC NR 20061005003)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006120800095	20061208	00095	NE  	2006	12	8	CA061005005      	2	20060925	G	7300	1851M43P08	ECU             			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					NR 2 ENGINE	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			J			WARNING INDICATION        			CR	CRUISE         	1			CA			33115					741568			(CAN) DEPARTURE AND ENROUTE TO DESTINATION, NR 2 ENGINE PARAMETERS ERRATIC, THEN INDICATE THAT NR 2 EGT OVER LIMITS, THE	N VIBRATION.  ENGINE SHUTDOWN AND BOTTLE DISCHARGED. REPLACED ECU IAW MM, RT VSV ACTUATOR REPLACED.  FADEC MOTORING CHK 	ACCOMPLISHED IAW MM, MIN IDLE LEAK CHK ACCOMPLISHED IAW MM, PWR ASSURANCE CHK ACCOMPLISHED IAW MM, VIBE SURVEY CHK ACCOM	PLISHED IAW MM,  CHK ACCOMPLISHED IAW MM.  ALL CHECKS OK, ENGINE OPS WITHIN NORMAL PARAMETERS. (TC NR 20061005005)			2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2006120800097	20061208	00097	NM  	2006	12	8	CA061005006      	1	20061004	G	2435	23088002A	STARTER GEN     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				413  							(CAN) THE FLIGHT CREW SNAGGED THAT THE NR 2 GENERATOR FAILED. UPON FURTHER INVESTIGATION MAINTENANCE DISCOVERED THAT STA	RTER-GENERATOR HAD FAILED INTERNALLY. WHEN THE STARTER-GENERATOR IS COOLING DUCT AND WINDOW STRAP WERE REMOVED LOSE PIEC	ES OF BRUSH MATERIAL FELL OUT OF THE STARTER-GENERATOR. ONE OF THE COMMUTATOR SEGMENTS WAS ALSO PARTIALLY MISSING AND MA	NY BRUSHES WERE CRACKED OR BROKEN. ONE OF THE DC CURRENT LIMITERS IN THE DC CONTACTOR BOX WAS ALSO FOUND TO BE OPEN. THE	 STARTER-GENERATOR, GENERATOR CONTROL UNIT, AND THE ASSOCIATED CURRENT LIMITER WERE REPLACED AND THE AIRCRAFT WAS RETURN	ED TO SERVICE. (TC NR 20061005006)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120800101	20061208	00101	EA  	2006	12	8	CA061005007      	1	20061004	G	3244	900012001	TIRE            			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF348C1     		NE  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			455  								(CAN) THE CREW REPORTED THAT DURING THE TAKEOFF ROLL THE FLIGHT ATTENDANT REPORT A LOUD BANG. AFTER CONFERENCING WITH MA	INTENANCE CONTROL, THE AIRCRAFT WAS ASKED TO CONTINUE TO DESTINATION. UPON ARRIVAL, IT WAS DETERMINED THAT THE NR 4 MAIN	 WHEEL WAS RAGGED AND APPEARED DEFLATED. THIS IS THE SECOND (WILKERSON RETREAD) FOR THE CRJ 700/900 AS DOCUMENTED IN SDR	 20060110004. (TC NR 20061005007)			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006120800107	20061208	00107	EU  	2006	12	8	CA061005009      	1	20061004	G	5280		BOLT            			EMB   	ERJ190	ERJ190100IGW	3260408	EU  										LT MLG DOOR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT MLG STAY AND DOOR BRACKET BOLTS SHEARED.  OLD BOLTS HAVE P/N 2821-8041, AND THE NEW BOLTS HAVE P/N NAS6605D28 (	BETTER QUALITY).  THEY ARE BEING INSTALLED THROUGH SB 190-32-0010. (TC NR 20061005009)					2	L	7	2 	4F			RT	A57NM   					 
2006120800110	20061208	00110	EA  	2006	12	8	CA061005010      	2	20060909	G	7321		SHAFT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 FMU	SHEARED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA			5602 			F48358					(CAN) DURING DESCENT INTO BASE, NR 2 ENGINE SUDDENLY SHUTDOWN. CREW GOT THE INDICATION BY A YAW AND DISCOVERED AFTERWARD	S THE PROP TQ WAS ZERO.  EMERGENCY DECLARED. POWERPLANT MESSAGE ON ED QRH ACTIONS WERE CARRIED OUT.  PAX BRIEFED ON DESC	ENT AND IN TERMINAL AFTERWARDS. UNEVENTFUL APPROACH/LANDING AND TAXI. MAINT REPORT: FAULT CODES: 360/907/935/970. FMU RE	MOVED AND FOUND SHAFT SHEARED. FMU REPLACED EGR CARRIED OUT NORMAL. (TC NR 20061005010)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006120800111	20061208	00111		2006	12	8	CA061005011      	4	20060914	G	6122		GOVERNOR        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROPELLER	SEIZED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA									051411		(CAN) THE A/C WAS IN NORMAL FLIGHT AND NOTED AN OVERSPEED CONDITION FROM CRUISE RPM TO FULL POWER.  CYCLING THE PROP PIT	CH CONTROL DID NOTHING; THE PILOT EXECUTED A FORCED LANDING.  AME REMOVED THE PROP GOVERNOR AND NOTICED IT WAS SEIZED AN	D CONTAMINATED. REMOVED THE OIL FILTER AND NOTICED IT WAS CONTAMINATED WITH METAL PARTICLES. DRAINED THE OIL PAN WITH FR	ESH VARSOL AND FLUSHED THE PAN TO CLEAN ANY CONTAMINATES.  INSTALLED FRESH NEW OIL AND INSTALLED NEW GOVERNOR.  GROUND R	UN UP WAS SATISFACTORY FOR FERRY FLIGHT TO REQUIRED BASE. PROP AND ENGINE REMOVED DUE TO OVERSPEED AND SENT TO REPAIR ST	ATION FOR INSPECTION. (TC NR 20061005011)	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2008022000003	20080220	00003	EU  	2008	2	20	CA061005012      	1	20061005	G	6200	355A27008200	LEVER           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					LOAD COMPENSATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2315 								(CAN) LOAD COMPENSATOR ARM WAS FOUND TO HAVE ELONGATED ATTACHMENT HOLES. NEW LEVER INSTALLED. THE OLD LEVER HAS BEEN SEN	T TO MFG FOR EVALUATION AS TO WHAT MAY BE THE CAUSE OF THIS. SUSPECT EXCESSIVE FORCE APPLIED BY THE ACCUMULATOR. (TC NR 	20061005012)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006121100156	20061211	00156	SW  	2006	12	11	CA061006002      	1	20061001	G	3250	2719087007	ACTUATOR        			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NOSE STEERING	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) MAINTENANCE WAS COMPLETING AN ENGINE CHANGE.  AN AME TAXI`D THE AIRCRAFT FROM THE HANGER TO THE DESIGNATED RUNUP A	REA.  ON THE TAXI WAY, THE AIRCRAFT ABRUPTLY VEERED TO THE RT, AND THE RT PROPELLER STRUCK A TAXIWAY MARKER.  THE ENGINE	 WAS SHUTDOWN AND DAMAGE WAS EVIDENT TO THE PROPELLER.  THE ENGINE AND PROPELLER WERE REPLACED.  THE NWS SYSTEM WAS TROU	BLESHOT, NO ELECTRICAL CONTROL FAULTS WERE EVIDENT.  THE NWS DID FAIL ON A SUBSEQUENT GROUND RUN WITH ANOTHER AME.  ALL 	NWS COMPONENTS AT THE NOSE GEAR WERE REPLACED WITH SERVICEABLE PARTS - ACTUATOR, MANIFOLD, PRESSURE SWITCH, SERVO VALVE.	  NO FAULTS WERE NOTED ON TAXI TESTS OR TEST FLIGHTS. (TC NR 20061006002)	2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P15EA	 
2006121100158	20061211	00158	EA  	2006	12	11	CA061006003      	2	20060901	G	7321		DRIVE SHAFT     	HAMSTD      		BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					FMU	FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA						F48358					(CAN) ON DESCENT, THE ENGINE FLAMED OUT.  GROUND INSPECTION REVEALED A FRACTURED FUEL METERING UNIT DRIVE SHAFT. (TC NR 	20061006003)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006121100159	20061211	00159	NE  	2006	12	11	CA061006004      	2	20060904	G	7230		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  						FIRE            	W				F				ACTIVATE FIRE EXT.      				A	J		FLAME/FIRE                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								61956			(CAN) DURING FLIGHT THE FIRE WARNING ACTIVATED. THE FIRE BOTTLES WERE DISCHARGED AND THE AIRCRAFT DIVERTED TO POINT OF D	EPARTURE.  SUBSEQUENT INSPECTION REVEALED A PUNCTURED GAS GENERATOR CASE AND FIRE DAMAGE TO THE ENGINE.  MFG WILL INVEST	IGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006121100161	20061211	00161	EA  	2006	12	11	CA061006005      	2	20060831	G	7314		COUPLING        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A6       	52043	EA  					PUMP	FRACTURED       	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			2254 								(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION IN FLIGHT.  THE ENGINE WAS SHUTDOWN AND SUCCESSFULLY RE-LIT AND	 THE UNCOMMANDED ACCELERATION REPEATED.  THE ENGINE WAS AGAIN SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FRAC	TURED FUEL CONTROL / FUEL PUMP COUPLING. (TC NR 20061006005)				1	L	7	1 	3T	3	T	RT	A78EU   	E4EA				 
2006121100163	20061211	00163	EA  	2006	12	11	CA061006006      	2	20060719	G	7321		DRIVE SHAFT     			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUEL CONTROL	FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			2254 			A75829					(CAN) THE FUEL CONTROL DRIVE SHAFT WAS FOUND FRACTURED.  THE FUEL CONTROL MID LIFE INSPECTION WAS DETERMINED NOT TO HAVE	 BEEN PERFORMED. (TC NR 20061006006)					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2006121100164	20061211	00164	NE  	2006	12	11	CA061006007      	2	20060824	G	7261		PRECOOLER       			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					ENGINE	UNKNOWN         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								124481			(CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED DURING A FLIGHT TEST.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE FUEL-	COOLED-OIL-COOLER AND FUEL HEATER WERE SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUS	E ONCE ESTABLISHED. (TC NR 20061006007)				2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2006121100165	20061211	00165	NE  	2006	12	11	CA061006008      	2	20060811	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2	UNKNOWN         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA								62572			(CAN) ON TRANSITION FROM HOVER, NR 2 POWER SECTION TORQUE DECREASED UNCOMMANDED.  AN EMERGENCY LANDING FOLLOWED RESULTIN	G IN AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006008)					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006121100167	20061211	00167	NE  	2006	12	11	CA061006009      	2	20060908	G	7200		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								CA0090			(CAN) THE ENGINE FLAMED OUT ON DESCENT.  AN INFLIGHT RELIGHT WAS SUCCESSFULLY ACCOMPLISHED.  MFG WILL INVESTIGATE THE EV	ENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006009)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006121100168	20061211	00168	NE  	2006	12	11	CA061006010      	2	20060913	G	7310		MANIFOLD        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					FUEL SYSTEM	LEAKING         	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			K	A		FLUID LOSS                	FLAME/FIRE                		DE	DESCENT        	1			CA											(CAN) A LOUD NOISE AND A FLASH FROM THE ENGINE WERE REPORTED ON DESCENT ACCOMPANIED BY A FIRE DETECTOR WARNING.  THE ENG	INE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED SEPARATION OF THE NACELLE COWLS WITH RESULTANT AIRFRAME IMPA	CT DAMAGE.  THE ENGINE FUEL MANIFOLD AND EXTERNALS WERE FOUND TO BE FIRE DAMAGED.  MFG WILL INVESTIGATE THE EVENT AND WI	LL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006010)			2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006121100205	20061211	00205	NE  	2006	12	11	CA061006012      	2	20060918	G	7261		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								114348			(CAN) DURING TAKE-OFF CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND OIL PRESSURE DECREASED TO ZERO.  THE ENGI	NE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  INSPECTION REVEALED OIL IN THE ENGINE EXHAUS	T DUCT.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006012)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006121100206	20061211	00206	NE  	2006	12	11	CA061006013      	2	20060815	G	7230		COMPRESSOR      			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	SEIZED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								19374			(CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE AND SUBSEQUENTLY FLAMED OUT IN FLIGHT.  POST-FLIGHT INSPECTION REVEAL	ED METAL DEBRIS IN THE OIL, RUBBING NOISES FROM THE POWER SECTION AND A SEIZED COMPRESSOR.  MFG WILL INVESTIGATE THE EVE	NT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006013)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007010800144	20070108	00144	NE  	2007	1	8	CA061006014      	2	20060919	G	7200		BLADE           			AMTR  	ALPHA 	ALPHA       	05613GU	GL  	PWA   	306   	PW306B      	 	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								CD0130			(CAN) ON CLIMB, THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  SUBSEQUENT INSPECTION REVEALED HPT1 BLADE DAMAGE.  P&WC	 WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006014)					1	D	7	1 	3I	4	F	RT	EXPA1D71	E35NE				 
2006121100207	20061211	00207	NE  	2006	12	11	CA061006015      	2	20060920	G	7261		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								DB0238			(CAN) IN CRUISE, ENGINE OIL PRESSURE WAS SEEN TO DECREASE AND THE LOW OIL PRESSURE WARNING ACTIVATED.  THE ENGINE WAS SH	UTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF RO	OT CAUSE ONCE ESTABLISHED. (TC NR 20061006015)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006121100208	20061211	00208	EA  	2006	12	11	CA061006016      	2	20060615	G	7210		PLANETARY GEAR  			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	RGB	WORN            	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, ENGINE POWER FLUCTUATED ACCOMPANIED BY AN INCREASE IN ITT TEMPERATURE AND LOW OIL PRESSURE.  THE ENG	INE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED FIRST STAGE PLANETARY GEAR DISTRESS. (TC NR 20061006016)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006121100209	20061211	00209	NE  	2006	12	11	CA061006017      	2	20060909	G	7261		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  		LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								PS0145			(CAN) IN FLIGHT THE ENGINE LOST OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT-OF-D	EPARTURE.  POST-FLIGHT INSPECTION REVEALED A LOW ENGINE OIL LEVEL AND NOISES FROM THE ENGINE POWER SECTION ON ROTATION. 	 MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006017)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006121100210	20061211	00210	NE  	2006	12	11	CA061006018      	2	20060927	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FIRE            	W				D				RETURN TO BLOCK         				A	J		FLAME/FIRE                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI FOLLOWING LANDING, FLAMES WERE SEEN COMING FROM THE ENGINE EXHAUST.  MFG WILL INVESTIGATE THE INCIDENT AND	 ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006018)					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006121100211	20061211	00211	NE  	2006	12	11	CA061006019      	2	20060927	G	7321		BEARING CAGE    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					FUEL CONTROL	FRACTURED       	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA						C65140					(CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE IN CRUISE, REDUCING TO ZERO UNCOMMANDED DURING DESCENT. POWER WAS RECOVERED US	ING THE FUEL CONTROL MANUAL OVER-RIDE SYSTEM.  ON A SUBSEQUENT START THE ENGINE ACCELERATED UNCOMMANDED.  SUBSEQUENT INS	PECTION REVEALED A PRE-SB1561 FCU BEARING CAGE FRACTURE. (TC NR 20061006019)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006121100212	20061211	00212	EA  	2006	12	11	CA061006020      	2	20060925	G	7200		ENGINE          			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  						SEIZED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								111106			(CAN) ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE IN FLIGHT ACCOMPANIED BY A LOSS OF OIL PRESSURE.  THE ENGINE WAS SHUTD	OWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED OIL IN THE ENGINE DRAINS AND SEIZURE OF THE POWER SECTION.  MFG WILL INVE	STIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006020)				1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2006121100213	20061211	00213	SW  	2006	12	11	CA061006021      	1	20061004	G	6320		SHAFT           	BELL        	206040004101	BELL  	206   	206L        	1181522	SW  										TRANSMISSION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4049 	4049 		BMC00615					(CAN) EXCESSIVE CORROSION ON SHAFT. (TC NR 20061006021)						1	G	7	1 	3U				H2SW    					 
2006121100214	20061211	00214	CE  	2006	12	11	CA061010001      	1	20061003	G	5712	0513006142	BULKHEAD        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  		DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3535 								(CAN) AT INSPECTION, SMOKING FASTENERS AT THE LT WING AFT FITTING WERE FOUND.  FASTENERS WERE REPLACED AS REQUIRED. (TC 	NR 20061010001)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2006121100215	20061211	00215	EU  	2006	12	11	CA061010002      	1	20061010	G	3250	5325012044	BEARING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG FORK	TWISTED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) AFTER LANDING, CREW REPORTED TO MAINTENANCE THAT THEY HAD A HARD SHIMMY IN THE RUDDER PEDALS.  UPON INSPECTION WE 	FOUND THE NOSE STEERING BRACKETS BENT AND THE SPRING STRUT UNABLE TO MOVE.  THE STEERING STRUT CONNECTED TO THE STEERING	 HAD FAILED CAUSING THE FORK BEARING TO TWIST.  THE BENT BRACKET WAS REPLACED AND THE SPRING STRUT WAS SERVICED.  THE SY	STEM WAS FUNCTION CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061010002)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006121100216	20061211	00216	CE  	2006	12	11	CA061010003      	1	20061010	G	3040	26106731	LINE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	DE ICE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WIRE BUNDLE SECURED INCORRECTLY LEADING TO CHAFING ON/THRU PNEUMATIC DEICE AIR SUPPLY LINES. DURING THE INITIAL CO	MPLETION OF THE DEICE SYSTEM TEST AND SERVICE IT WAS FOUND THAT THE WIRING BUNDLE FOR THE DEICE SOLENOIDS AND PRESSURE S	WITCHES HAD BEEN SECURED IN A POSITION WHICH ALLOWED THEM TO CONTACT SUPPLY LINE P/N 261067-31, WEARING A HOLE IN THE LI	NE AND DAMAGING SEVERAL WIRES. DEICE PIPES P/N 2601067-31 AND -32 WERE REPLACED.  WIRING WAS REPAIRED, REROUTED AND PROT	ECTED TO PREVENT FURTHER CONTACT WITH DEICE PIPES.  THE AIRCRAFT WAS RETURNED TO SERVICE. OTHER AIRCRAFT IN THE FLEET WE	RE INSPECTED WITH NO FAULTS FOUND.    (TC NR 20061010003)	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2006121100217	20061211	00217	NM  	2006	12	11	CA061010004      	1	20060927	G	5512	184T10071	SKIN            	BOEING      		BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					HORIZONTAL STAB	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			73006								(CAN) LT HORIZONTAL STAB LEADING EDGE PANEL 332CL INNER SKIN COMPLETELY DELAMINATED. DELAMINATED SKIN WEARING INTO VERTI	CAL STIFFENERS LOCATED ALONG FRONT SPAR. (TC NR 20061010004)					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2006121100218	20061211	00218	EA  	2006	12	11	CA061010005      	1	20061009	G	2750		FLAP SYSTEM     			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) FLAP FAIL BETWEEN 20 DEGREES TO 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF , FLAPS RESET ON GROUND IAW OPE	RATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P3-4.  A/C RETURN TO SERVICE. NO SNAG.  FLAP FAIL BETWEEN 20 DEGREES TO	 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF, FLAPS RESET ON GROUND IAW OPERATING MANUAL NR 1 ABNORMAL PROCEDURE 	SECTION 10 P3-4. A/C RETURN TO SERVICE. NO SNAG.  (TC NR 20061010005)			2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2006121100219	20061211	00219	NE  	2006	12	11	CA061010006      	2	20060913	G	7310	305262701	MANIFOLD        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					FUEL SYSTEM	FAILED          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA			2117 					DC0045			(CAN) THE PILOTS HEARD A LOUD NOISE FOLLOWED BY A MOMENTARY FIRE WARNING LIGHT.  THE PILOTS SHUT THE ENGINE DOWN AND RET	URNED TO BASE.  AFTER LANDING THE COWLING FOR THE RT ENGINE WAS FOUND TO BE MISSING THE ENGINE DAMAGED BY FIRE AND THE T	AIL DAMAGED. (TC NR 20061010006)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006121100220	20061211	00220	GL  	2006	12	11	CA061010007      	1	20061010	G	5511	C2TP1A	SPAR            	DHAV        		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3180 			SA387					(CAN) DURING THE CF-91-42 INSPECTION THE FORWARD SPAR WAS FOUND CRACKED AT THE TOP OF THE TOP ATTACH HOLE FOR THE FORWAR	D ATTACH BRACKETS PN C2TP159/160.  (TC NR 20061010007)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2006121100221	20061211	00221	WP  	2006	12	11	CA061011001      	2	20060829	G	7200	31030351	BEARING         			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			5858 					P38328C			(CAN) AN IN-FLIGHT SHUTDOWN WAS CARRIED OUT WHEN THE ENGINE STARTED TO SURGE AND THE NEGATIVE TORQUE SYSTEM (NTS) PULSE.	 UPON DISASSEMBLY AT AN ENGINE REPAIR FACILITY, IT WAS NOTED THAT THE CAUSE WAS PREMATURE WEAR AND SUBSEQUENT FAILURE OF	 THE DUAL P/N: 3103035-1 BEARINGS. FAILURE OF THIS BEARING SET CAUSED LOSS OF ENGAGEMENT BETWEEN THE SPUR GEAR P/N: 8968	04-2 AND THE MATING GEAR IN THE TORQUE SENSOR. THE INTEGRITY OF THE FCU DRIVE TRAIN WAS LOST AND THE ENGINE FAILED WHEN 	THE FUEL CONTROL STOPPED BEING DRIVEN. THE ENGINE IS BEING OVERHAULED AT THIS TIME.  IT IS TO BE NOTED THAT AN OIL SAMPL	E WAS TAKEN 9.7 HOURS PRIOR TO THE FAILURE. THE SAMPLE CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) ONE WEEK AFTER THE EN	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2006121100222	20061211	00222	SO  	2006	12	11	CA061011002      	1	20060830	G	5543	6345703	CONNECTOR       	PIPER       		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	RUDDER TRIM ARM	BROKEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			3675 								(CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED IN CLIMB THERE WAS NO RESPONSE. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT 	CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD.  THE COMP	LETE RUDDER TRIM ARM ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW UNIT SUPPLIED FROM MFG.  METAL FATIGUE IS SUSPECTED.  	(TC NR 20061011002)			1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2006121100223	20061211	00223	EA  	2006	12	11	CA061011003      	2	20060927	G	7200	4708849004	CONTROLLER      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	DEFECTIVE       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA				686  							(CAN) DURING A FLIGHT, THERE WAS A LOSS OF LT ENGINE OIL PRESSURE. THE AFFECTED ENGINE WAS SHUTDOWN AND AN UNSCHEDULED L	ANDING ACCOMPLISHED. AFTER INVESTIGATION, THE DENSITY CONTROLLER WAS FOUND DEFECTIVE. THE SEAL WAS RUPTURED ON THE (INTA	KE) SIDE AND OIL WAS LEAKING INTO THE ENGINE AIR INTAKE. (TC NR 20061011003)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006121100224	20061211	00224	EU  	2006	12	11	CA061011004      	1	20061001	G	2530	72067002M	OVEN            			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211*      	54555	NE  					GALLEY	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) BURNING SMELL WAS NOTICED IN THE FWD GALLEY BY THE FLIGHT ATTENDANT WITH AN ASSOCIATE ECAM SMOKE WARNING OF THE FW	D LAVATORY. F/A NOTICED SMELL COMING FROM NR 3 OVEN TIMER. OVEN WAS SWITCHED OFF FOR THE REMAINING OF THE FLIGHT WITH NO	 FURTHER PROBLEM. AIRCRAFT WAS INSPECTED AT THE ARRIVAL STATION AND THE OVEN WAS DEACTIVATED.  OVEN WAS REPLACED ON ARRI	VAL AT MAIN BASE. DURING SHOP INSPECTION THE OVEN OPERATION WAS NORMAL BUT A SMALL PIECE OF MELTED PLASTIC WAS FOUND AT 	THE FWD BOTTOM CORNER OF THE OVEN. OVEN WAS TESTED AND RETURNED TO SERVICE.  (TC NR 20061011004)		2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2006121100225	20061211	00225	EU  	2006	12	11	CA061011005      	1	20060929	G	5300	A5247017100200	ACCESS PANEL    			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	MISSING         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON AIRCRAFT ARRIVAL, DURING WALK AROUND INSPECTION, FOUND THE FWD CARGO DOOR LOWER FWD ACCESS PANEL, FIN811AR, M	ISSING. MOUNTING HARDWARE, FASTENERS AND LANYARDS WERE STILL ATTACHED TO THE CARGO DOOR. DOOR WAS INSPECTED AND NO FURTH	ER DAMAGE WAS NOTICED. AIRCRAFT WAS DISPATCH UNDER CDL. NEW PANEL INSTALLED OCT5/06. (TC NR 20061011005)				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006121100251	20061211	00251	NM  	2006	12	11	CA061011007      	1	20060721	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			1576 			K0294					(CAN) DURING CRUISE AT 18000 FT, (NR 2 HYD ISO VLV, NR2 ENG HYD PUMP) AND (ROLL SPLR OB HYD) CAUTION LIGHT WERE ILLUMINA	TED, AND THEN, NR 2 HYD PRESS DROPPED TO 0 PSI AND QUANTITY ALSO DROPPED TO 0. EMERGENCY LANDING CONDUCTED WITH ALTERNAT	E LDG EXTENSION. THE AIRCRAFT WAS TOWED TO PARKING SPOT. THE GROUND INSPECTION REVEALED THAT NR 2 EDP WAS CRACKED AND HA	D A (1.5 X 1.0 CM) HOLE. METAL DEBRIS WAS FOUND IN ALL FILTERS (PRESS, RETURN AND CASE DRAIN), AND DPI FOR NR 2 CASE DRA	IN FILTER WAS POPPED OUT. EDP REPLACED, HYDRAULIC SYSTEM FLUSHED. (TC NR 20061011007)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006121100254	20061211	00254	NM  	2006	12	11	CA061011008      	1	20061004	G	2611	473925	CONTROL UNIT    			BOEING	737   	7372L9      	1384497	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SMOKE DETECTION	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI FOR DEPARTURE THE CREW OBSERVED A NR 2 CARGO PIT CAUTION INDICATION. THE AIRCRAFT RETURNED TO COMPANY RAMP	 WHERE MAINTENANACE DETERMINED THE SMOKE DETECTOR SYSTEM CONTROL ELECTRONICS UNIT IN THE NR 2 PIT WAS AT FAULT. THE UNIT	 WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061011008)				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006121100256	20061211	00256	NM  	2006	12	11	CA061011009      	1	20061004	G	3246	65446604	ACTUATOR        			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	BYPASSING       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE THE NOSE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURT	HER INCIDENT. MAINTENANCE FOUND THE NOSE LANDING GEAR GRAVEL DEFLECTOR ACTUATOR WAS BYPASSING. THE UNIT WAS REPLACED AND	 THE AIRCRAFT REURNED TO SERVICE. THE ACTUATOR REMOVED HAD BEEN REPLACED THE PREVIOUS DAY AND THE VENDOR HAS BEEN CONTAC	TED TO PROVIDE AN IMMEDIATE TEARDOWN REPORT. (TC NR 20061011009)			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006121100258	20061211	00258	SW  	2006	12	11	CA061011010      	1	20061004	G	6310	CL422501	CLUTCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FREEWHEEL UNIT	CRACKED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1927 								(CAN) 2 SPRAG RETAINER WERE CRACKED, THEREFORE ALLOWING MISALIGNMENT AND CAUSING A NOISE. (TC NR 20061011010)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006121100262	20061211	00262	GL  	2006	12	11	CA061011011      	3	20061004	G	6110	M5150021	FITTING         	HARTZL      		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROPELLER	OPEN            	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			1483 			FP1078A			FP1078A		(CAN) PILOT EXPERIENCED EXCESSIVE GREASE LEAKAGE ON WINDSCREEN DURING TAKEOFF AND CLIMB, RETURNED TO MAINTENANCE BASE IM	MEDIATELY. ON INSPECTION ONE GREASE FITTING WAS FOUND DEFECTIVE. GREASE FITTING WAS REPLACED. PROP RE-GREASED IAW PROP O	WNERS MANUAL, PN115N, CHAP6-6. A/C GROUND RUN + PROP LEAK CHECKED. NO FAULTS FOUND. A/C TEST FLOWN TO ENSURE NO LEAKAGE 	AT HIGH POWER SETTINGS AND FOR PROPER PROPELLER FUNCTION. CHECKED SERVICEABLE - 100HR PROPELLER INSPECTION AND LUBRICATI	ON WAS C/O PRIOR TO FLIGHT ON OCT.3/06 (TC NR 20061011011)		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2006121100264	20061211	00264	SW  	2006	12	11	CA061011012      	1	20061010	G	6730	C4264278	GLAND NUT       	TACTAIR     		BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SERVO ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3581 			RH4576A					(CAN) DURING THE FIRST OVERHAUL OF THREE SERVO ACTUATORS 2 WERE FOUND TO HAVE CRACKS ON THE GLAND THAT RETAINS THE PISTO	N SEAL. BOTH SERVO ACTUATOR GLAND ASSEMBLIES WERE CRACKED IN THE SAME AREA.  (TC NR 20061011012)					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2006121100266	20061211	00266	NE  	2006	12	11	CA061011013      	2	20061007	G	7250	597602A	TURBINE BLADES  			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			CA			2947 					672488			(CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS, ON A SHORT FINAL APPROACH TO THE LOG LANDING THE AIRCRAFT 	DEVELOPED A VERY NOTICEABLE HIGH FREQUENCY VIBRATION THAT WAS FELT BY THE FLIGHT CREW THROUGHOUT THE AIRCRAFT INCLUDING 	THE FLIGHT CONTROLS. THE VIBRATION WAS ALSO ACCOMPANIED BY A VERY LOUD GROWLING NOISE. A SCAN OF THE AIRCRAFT INSTRUMENT	S REVEALED NOTHING ABNORMAL. THE PILOT ELECTED TO CONTINUE THE APPROACH TO DROP OFF THE LOAD AT THE LOG LANDING AND THEN	 MADE A PRECAUTIONARY LANDING AT A NEAR BY LOCATION ON THE BEACH OF THE LAKE. AFTER SHUTDOWN, AN EXTENSIVE INSPECTION OF	 THE ENTIRE AIRCRAFT CARRIED OUT BY MAINTENANCE PERSONNEL REVEALED A LARGE AMOUNT OF METAL PARTICLES FUSED TO THE INSIDE	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006121100268	20061211	00268	NE  	2006	12	11	CA061011014      	2	20061005	G	7322	1D1	FUEL CONTROL    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  						LEAKING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FUEL SMELL WAS REPORTED IN THE CABIN WHEN THE HEATER WAS TURNED ON.  FCU WAS REMOVED AND FUEL WAS FOUND IN THE P2 	AIR CHAMBER WHEN THE FCU WAS INVERTED. FCU WAS REMOVED AND RETURNED TO MFG FOR REPAIRS.  FCU RAN 712.6 HRS SINCE LAST RE	PAIR. FCU P/N 2915145338508 S/N A969B (TC NR 20061011014)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006121100269	20061211	00269	EU  	2006	12	11	CA061012001      	1	20061012	G	2740	200031800	CLUTCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITCH SERVO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE PHASE INSPECTION, THE AREA AROUND THE PITCH SERVO IS INSPECTED.  DURING THIS, THE FRICTION PLATE 	WAS DISCOVERED TO BE CRACKED IN HALF.  THE PITCH SERVO CLUTCH WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC	 NR 20061012001)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006121100270	20061211	00270		2006	12	11	CA061012002      	4	20060526	G	3160	C19190AB04	DISPLAY         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			1670 								(CAN) DURING FLIGHT, THE FLIGHT CREW REPORTED THAT THE COPILOT`S PFD WENT BLANK, THEN CAME BACK ON IN POST MODE (GREEN T	) THEN WENT BLANK AGAIN PERMANENTLY, FOLLOWED BY A BURNING ODOR (NO VISIBLE SMOKE OR FLAMES). THE ODOR WAS CARRIED BY TH	E RECIRC FAN THROUGHOUT THE CABIN AND DETECTED BY THE FLIGHT ATTENDANTS. MECHANICS FOUND EVIDENCE OF SOOT AROUND THE COO	LING HOLES OF THE REMOVED PFD. (TC NR 20061012002)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006121100271	20061211	00271	EA  	2006	12	11	CA061012003      	1	20061011	G	2730	6229815704	CIRCUIT CARD    			CNDAIR	CL600 	CL6002B19   	1900309	EA  										ELEVATOR CONTROL	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, ENROUTE, CREW EXPERIENCED PITCH TRIM, MACH TRIM AND STAB TRIM CAUTION INDICATIONS. CREW THOUGHT 	THEY EXPERIENCED FLIGHT CONTROL ISSUES. AFTER SOURCING THE QUICK REFERENCE HANDBOOK, CREW ELECTED TO DIVERT, BEING THE C	LOSEST SUITABLE AIRPORT. CREW DID CONTACT MAINTENANCE TO RESET SOME CIRCUIT BREAKERS AND ALSO DID HOLD WEST OF YFC FOR F	UEL BURN OFF. CREW DID DECLARE AN EMERGENCY AND DID HAVE EMERGENCY VEHICLES STANDING BY. PASSENGER ANNOUNCEMENT WAS MADE	 TO THE EFFECT THAT AIRCRAFT WAS HAVING  A FLIGHT CONTROL PROBLEM HOWEVER EVERYTHING WAS UNDER CONTROL. PASSENGERS WERE 	ADVISED TO BRACE FOR LANDING. PASSENGER REACTION WAS NIL. FLIGHT LANDED SAFELY AND PASSENGERS DEPLANED. (TC NR 200610120	2	L	7	2 	4F			RT	A21EA   					 
2006121100272	20061211	00272	NE  	2006	12	11	CA061012004      	2	20061012	G	7510	3039936	GASKET          	PWC         		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) GASKET PN 3007342 AND SUBSEQUENT SUPERCEDURE TO 3039936 ARE THE ONLY GASKETS SPECIFIED FOR USE ON THE CABIN BLEED 	AIR PORT. THE 3039936 GASKETS ARE MADE OF A FIBER OR OTHER MATERIAL NOT WELL SUITED TO THIS HOT AND HIGH PRESSURE AREA. 	OTHER ENGINES LIST A METAL GASKET OPTION PN 3029677 AS APPROVED FOR INSTALLATION AT THIS PORT. MFG HAS BEEN NOTIFIED OF 	THIS ISSUE IN THE -42 IPC. (TC NR 20061012004)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2006121100274	20061211	00274	NM  	2006	12	11	CA061012005      	1	20061008	G	3260	858601	PSEU            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PRXY SENSOR	WARNING LIGHT   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			30189	9400 							(CAN) AFTER TAKEOFF GEAR SELECTED UP , VISUALLY CONFIRMED GEAR WAS UP , INDICATION STILL SHOWED GEAR DOWN AND LOCKED (3 	GREEN LIGHTS) , NORMAL GEAR EXTENSION AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT FOR NORMAL LANDING. MAINTENANCE INSPECT	ION FOUND PSEU INTERNAL HISTORY SHOWING CARD FAULT . PSEU REPLACED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061012005)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006121100275	20061211	00275	EU  	2006	12	11	CA061013001      	1	20061010	G	7500	690200	DUCT SEAL       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	BLEED AIR SYS	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENROUTE THE CREW OBSERVED A BLEED AIR LEAK WARNING. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITH NO	 FURTHER PROBLEM. MAINTENANCE DETERMINED THAT A BLEED AIR SYSTEM DUCT SEAL HAD FAILED. THE AIRCRAFT IS AWAITING PARTS. (	TC NR 20061013001)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006121100278	20061211	00278	EA  	2006	12	11	CA061013003      	1	20061011	G	5730		SKIN            			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED	 TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND A	N NDT REPORT FOR DELAMINATION OF BONDED UPPER SKINS THEREFORE THE MAINTENANCE FACILITY PROVIDED AN INDEPENDENT NDT SPECI	ALIST TO INSPECT THE WINGS. THE PICTURES REVEAL WHERE THE SKINS WERE FOUND DELAMINATED (COLORED SPOTS).  THE DELAMINATIO	N IS MAINLY ON THE OB SKIN, WITH THE EXCEPTION OF 2 LOCATIONS: RT WING IB OF RIB WS 297.50 AND LT WING IB OF RIB WS 272.	  (TC NR 20061013003)	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006121100279	20061211	00279	EA  	2006	12	11	CA061013004      	1	20061011	G	5730		SKIN            			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED 	TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN	 NDT REPORT FOR DELAMINATION OF BONDED UPPER SKINS THEREFORE THE MAINTENANCE FACILITY PROVIDED AN INDEPENDENT NDT SPECIA	LIST TO INSPECT THE WINGS. THE PICTURES REVEAL WHERE THE SKINS WERE FOUND DELAMINATED (COLORED SPOTS).  THE DELAMINATION	 IS MAINLY ON THE OB SKIN, WITH THE EXCEPTION OF 2 LOCATIONS: RT WING IB OF RIB WS 297.50 AND LT WING IB OF RIB WS 272. 	 (TC NR 20061013004)	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2006121100280	20061211	00280	NE  	2006	12	11	CA061013005      	2	20061008	G	7310	J1175D0244AA	FUEL LINE       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 ENGINE	LEAKING         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			10439	10439							(CAN) RAMP CREW SERVICING AIRCRAFT REPORTED FUEL LEAKING FROM NR 1 ENGINE ON TAXI OUT. SHUTDOWN NR 1 ENGINE. FUEL DRIPPI	NG FROM LOWER COWL. MAINTENANCE INSPECTION FOUND VARIABLE GUIDE VANE FUEL LINE LEAKING. LINE P/N J1175D0244AA REPLACED. 	LEAK CHECKED AND AIRCRAFT RETURNED TO SERVICE. NOTE: THIS PART IS NOT TRACKED AS A ROTABLE COMPONENT , TIMES PROVIDED AR	E THE ENGINE INSTALLED TIMES . NR 1 ENGINE S/N 873093 , NR 1 ENGINE P/N 6089T11G01 (TC NR 20061013005)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006121100304	20061211	00304	EA  	2006	12	11	CA061013006      	1	20061011	G	2750	855D100	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					INTERNAL	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4796 	4796 							(CAN) ON SELECTING FLAPS FOR APPROACH (FLAP FAIL) MESSAGE DISPLAYED. DUE TO WEATHER CONDITION AIRCRAFT PROCEEDED WITH MI	SSED APPROACH. UNABLE TO RETRACT FLAPS.  AIRCRAFT DIVERTED TO NEAREST ALTERNATE AIRPORT WITH IMPROVED WEATHER , WITH FLA	PS REMAINING EXTENDED AT 30 DEG.  IN-FLIGHT RESET PROCEDURE FOR FLAPS UNSUCCESSFUL. AFTER ARRIVAL AT ALTERNATE AIRPORT F	LAP RESET PROCEDURE CARRIED OUT , FLAPS RETRACTED TO 8 DEG AND AIRCRAFT FERRIED TO MAINTENANCE BASE. MAINTENANCE REPLACE	D LT BRAKE AND POSITION SENSING UNIT. RIGGING AND FUNCTION CHECKS COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 200610	13006)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006121100307	20061211	00307	NM  	2006	12	11	CA061014001      	1	20061011	G	2150	39854021	VALVE           			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					A/C PACK	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, CREW DISCOVERED THAT THE A/C WOULD NOT PRESSURIZE. A/C RETURNED TO BASE WHERE A PACK VALVE WAS FO	UND FAILED IN THE CLOSED POSITION. VALVE WAS REPLACED AND A/C RETURNED TO SERVICE. (TC NR 20061014001)					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2006121100308	20061211	00308	NM  	2006	12	11	CA061016001      	1	20060821	G	2497		WIRE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	AC POWER	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			7115 								(CAN) AN OPERATOR EXPERIENCED AN EXTERNAL AC POWER PROBLEM THAT WAS TRACED TO SEVERAL BURNED WIRES AND A BLOWN (F4) FUSE	.  IT IS DETERMINED THAT THE MOST PROBABLE CAUSE FOR THIS EVENT WAS THE (12 GAUGE) FEEDER CABLES CHAFING TOGETHER ON THE	 ADJACENT STRUCTURE. (TC NR 20061016001)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500305	20061205	00305	GL  	2006	12	5	CA061016002      	1	20061014	G	3213	58S9241	STRUT           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					FLOATS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION, THE L/H MIDDLE FLOAT STRUT WAS FOUND TO HAVE A 4" STRESS CRACK EXTENDING DOWN THE LEAD	ING EDGE FROM THE TOP OF THE STRUT.  THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT IN GENERA	LLY ADVERSE LANDING CONDITIONS.  TSN UNKNOWN. (TC# 20061016002)				1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006121100310	20061211	00310	NE  	2006	12	11	CA061016003      	2	20061006	G	7200	M8505237	CLAMP           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE CONTROL CLAMP FOUND CRACKED ON ENGINE INSPECTION. REFERENCE AIRCRAFT IPC 71-00-02 FIG 15, ITEM NR 6 THE PAR	T WAS NOT IDENTIFIED BY A SPECIFIC PN MARKED ON THE CLAMP.  SUSPECT POSSIBLE UNAPPROVED PART PREVIOUSLY INSTALLED. (TC N	R 20061016003)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2006120500303	20061205	00303	GL  	2006	12	5	CA061016004      	1	20061014	G	3213	58S9242	STRUT           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION THE RT REAR FLOAT STRUT WAS FOUND TO HAVE A 6` STRESS CRACK ORIGINATING AT THE TOP FORW	ARD SIDE OF THE STRUT. TIME IN SERVICE IS UNKNOWN.  TAT 22,057 HOURS.  THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN	 A CORROSIVE ENVIRONMENT AND GENERALLY ADVERSE LANDING CONDITIONS. (TC# 20061016004)				1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2006121100312	20061211	00312		2006	12	11	CA061016005      	4	20061012	G	3421	79266941	GYRO            			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	COCKPIT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT THE CREW OBSERVED A GYRO FLAG AND THE A/P DISENGAGED. THE COMPASS BEGAN TO OSCILLATE WITH A COMPARA	TOR FAIL LIGHT INDICATION.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT.  MAINTENANCE REPLAC	ED THE NR 1 VG AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER SATISFACTORY GROUND TEST. (TC NR 20061016005)				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2006121100313	20061211	00313	NE  	2006	12	11	CA061016006      	2	20061011	G	7230		CASE            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	GAS GENERATOR	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			23187	14478				120775			(CAN) SHORTLY AFTER TAKE-OFF AT 500FT AGL THE CREW REDUCED POWER TO CLIMB POWER AND REALIZED THAT THE LT ENGINE ITT ROSE	 RAPIDLY TO APPROXIMATELY 850-900 DEGREES CELSIUS. THE OVER-TEMPERATURE LIGHT ILLUMINATED AND THE ENGINE OIL TEMPERATURE	 WAS ALSO RISING. THE ENGINE POWER WAS REDUCED TO STAY WITHIN LIMITS AND THE AIRCRAFT TURNED BACK TO LAND SAFELY WITHOUT	 INCIDENT. MAINTENANCE FOUND THAT THE ENGINE HAD DEVELOPED 2 SUBSTANTIAL CRACKS ON THE GAS-GENERATOR CASE.  THE CRACKS M	EASURED APPROXIMATELY 3.5 INCHES IN LENGTH EACH AND WERE LOCATED AT APPROXIMATELY THE 11:30  AND 10 OCLOCK POSITIONS. I	T SHOULD ALSO BE NOTED THAT THIS PORTION OF THE GAS GENERATOR CASE IS NORMALLY COVERED WITH AN INSULATION BLANKET. THE E	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500304	20061205	00304	CE  	2006	12	5	CA061016007      	1	20061014	G	5534	04310093	ATTACH BRACKET  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21277								(CAN) ONE OF THE TWO VERTICAL TAIL ATTACH BRACKETS WAS DISCOVERED CRACKED APPROXIMATELY 90% OF ITS LENGTH DURING A SCHE	DULED INSPECTION. THE CRACK LOCATION IS IN THE RADIUS WHERE THE VERTICAL LEG INTERSECTS THE HORIZONTAL LEG.   THERE IS A	 SERVICE LETTER WHICH DEALS WITH THIS, HOWEVER IT DOESNT APPLY TO THIS SERIAL NUMBER AIRCRAFT.  WE ARE REPLACING THE TW	O ON THIS AIRCRAFT AS WELL AS ON THE OTHER C152 IN THE FLEET. (TC# 20061016007)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007012900325	20070129	00325	EU  	2007	1	29	CA061017004      	1	20061016	G	2910	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYDRAULIC SYS	BURNED          	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			CA			5042 								(CAN) FOLLOWING LANDING OF AIRCRAFT AMBER (HYD).  ANNUNCIATOR ILLUMINATED. INSPECTION OF HYDRAULIC MOTOR POWER RELAY MAI	N CONTACTS INDICATED THE CONTACTS WERE SEVERLY BURNED. NEW RELAY INSTALLED ,FUNCTION TEST OF LANDING GEAR SYSTEM PERFORM	ED SATISFACTORY. (TC NR 20061017004)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006120500293	20061205	00293	SO  	2006	12	5	CA061017005      	1	20061016	G	3260		DOWNLOCK SWITCH 			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	MLG	OUT OF ADJUST   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE THE NOSE LANDING GEAR FAILED TO RETRACT ON TAKE-OFF. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE 	WITHOUT FURTHER PROBLEM. MAINTENANCE ADJUSTED THE DOWNLOCK SWITCH AND CARRIED OUT A GEAR SWING BEFORE THE AIRCRAFT WAS R	ETURNED TO SERVICE.  (TC# 20061017005)				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2006120500306	20061205	00306		2006	12	5	CA061017006      	4	20061013	G	8300	6014T81G26	GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT ENGINE	FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			CA											(CAN) LEFT ENGINE IN-FLIGHT SHUTDOWN DUE TO ACCESORIES GEARBOX (AGB)FAILURE. AGB BORESCOPE INSPECTION REVEALED A BROKEN 	GEAR. AIRFRAME HOURS=25499:54. CYCLES=21133. (TC# 20061017006)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900326	20070129	00326		2007	1	29	CA061017007      	4	20061017	G	6113	04500391791	BULKHEAD        			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3509 								(CAN) ON PILOT WALK AROUND THE SPINNER ASSY WAS NOTED TO BE LOOSE. UPON INSPECTION IT WAS OBSERVED THAT THE FWD SPINNER 	BULKHEAD WAS CRACKED. THIS WAS MOST LIKELY CAUSED BY PILOTS PUSHING ON THE SPINNER WHEN GROUND HANDLING THE AIRCRAFT. (T	C NR 20061017007)				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2006120500307	20061205	00307	CE  	2006	12	5	CA061018001      	1	20061013	G	7800	1754001	EXHAUST RISER   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NR 3	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			150  								(CAN) THE (EXHAUST) FLANGE WAS CRACKED THROUGH AND INTO THE UPPER END OF THE (EXHAUST) PIPE ITSELF, WITH THE CRACK TRAVE	LLING ALMOST HALFWAY AROUND THE PIPE.   SUBMITTER REGULARLY FINDS THESE RISERS CRACKED AND SUSPECTS THAT A SHARP/ROUGH E	DGE ON THE FLANGE CONTRIBUTES TO ITS FAILURE.    THOROUGH INSPECTION OF THIS TYPE OF EXHAUST SYSTEM AT EVERY 50-HOUR INT	ERVAL IS RECOMMENDED BY THE SUBMITTER. EXHAUST STAINING AROUND THE TOP OF THE PIPE IS USUALLY APPARENT. PRESSURE-TESTING	 OF THE WHOLE SYSTEM WHILE CARRYING OUT A.D. CF90-03R2 WILL ALSO FIND THESE DEFECTS. (TC# 20061018001)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006120500302	20061205	00302	SW  	2006	12	5	CA061018002      	1	20061014	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3940 								(CAN) UPON POST FLIGHT INSPECTION, A TEAR AND PROTRUTION OF THE LOWER SKIN, JUST AFT OF THE LEADING EDGE OUTBOARD ERROSI	ON STRIP WAS DISCOVERED APPROXIMATELY 4 INCHES INBOARD FROM THE TIP OF THE BLADE AT STATION 206. (TC# 20061018002)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006121100314	20061211	00314	NE  	2006	12	11	CA061018003      	1	20061010	G	6220	641026005104	ROD             	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					DAMPER PISTON	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3464 	827  		106					(CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS AND HAD JUST SHUT DOWN FOR ITS MIDDAY MAINTENANCE. THIS MA	INTENANCE INVOLVES A FLUID LEVELS CHECK, SERVICING AND INSPECTION OF CRITICAL AREAS ON THE AIRCRAFT. ON THIS PARTICULAR 	DAY THE MAIN ROTOR DAMPERS WERE BEING CHECKED FOR PROPER OPERATION AND ASSOCIATED LINKAGE WEAR. THIS IS ACCOMPLISHED BY 	SWEEPING THE CORRESPONDING MAIN ROTOR BLADE BACK AND FORTH AT THE TIP END TO EXTEND AND RETRACT THE DAMPER PISTON AND RO	D. WHEN THE AME CAME TO CHECK THE SUBJECT DAMPER HE DISCOVERED THE BLADE MOVED BACK AND FORTH FREELY WITH NO RESISTANCE 	FROM THE DAMPER. A CLOSER INSPECTION OF THE DAMPER BY A SECOND AME WHILE THE BLADE WAS BEING MOVED REVEALED THE DAMPER P	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2006121100316	20061211	00316	EA  	2006	12	11	CA061018004      	2	20061007	G	8530	RBLW12967EC	CYLINDER HEAD   			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	K		PARTIAL RPM/PWR LOSS      	FLUID LOSS                		CL	CLIMB          	1			CA				428  				RL352361A			(CAN) AFTER CLIMB OUT THE LT ENGINE LOST POWER AND A LOUD BANG WAS HEARD. THE ENGINE (PROPELLER) WAS FEATHERED AND THE A	IRCRAFT RETURNED TO THE AIRPORT WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT THE NR 2 CYLINDER ASSEMBLY WAS CRACK	ED/BROKEN BETWEEN THE HEAD AND BARREL. THIS ALLOWED THE HEAD TO MISALIGN AND ALLOWED THE PUSH ROD TUBES TO LEAK OIL ONTO	 THE TOP COWL. THE CYLINDER WAS REMOVED AND AN OVERHAUL ASSEMBLY INSTALLED. THE ADJACENT CYLINDER WAS INSPECTED AND FOUN	D SERVICEABLE, OIL AND SCREWS WERE INSPECTED SERVICEABLE. THE ENGINE WAS GROUND RUN AND CHECKED SERVICEABLE.  (TC NR 200	61018004)	1	L	7	2 	3O	3	O		A12SW   	E14EA	5	C	P33EA	 
2006121100318	20061211	00318	NM  	2006	12	11	CA061018005      	1	20060919	G	3213	MS2877A344	SEAL            			BOEING	737   	737*        	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					STRUT	TORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				1732 							(CAN) ON CLIMB OUT, NOSE GEAR RED WARNING LIGHT STAYED ON; GEAR CYCLED TWICE, NIL CURE. AIRCRAFT PROCEEDED TO AIRPORT, L	ANDING WAS NORMAL. ON GROUND, NOSE GEAR SERVICED, SUBSEQUENT TAKEOFF NORMAL. ON RETURN TO BASE, ONE SEAL FOUND TORN, ALL	 SEALS REPLACED, FULL NOSE GEAR SERVICING CARRIED OUT.  (TC NR 20061018005)				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006121100319	20061211	00319	    	2006	12	11	CA061018006      	1	20061006	G	5711		SPAR            			ARONCA	7A    	LSA7AC      	       	    	CONT  	A65   	A658        	17003	SO  	SNSNCH	72C	72CK        	EA  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2452 								(CAN) CRACKING AT REINFORCING PLATES.  PREVIOUS DAMAGE AT TIP. HAD PREVIOUS REPAIR. REPLACED BOTH FRONT AND REAR SPARS. 	(TC NR 20061018006)					1	H	7	1 	3O	3	O		A759    	E205	5	N	P9045	 
2007010800187	20070108	00187	SO  	2007	1	8	CA061018007      	2	20061011	G	8520		PISTON          			AMTR  	CUBY  	CUBYACROTNER	05624DP	GL  	CONT  	O200  	O200*       	17020	SO  					NR1 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1100 								(CAN) ENGINE WAS TORN DOWN FOR INSPECTION DUE TO SMALL AMOUNT NON FERROS METAL IN FILTER.  ENGINE TIME 2,707 HOUR. FRONT	 BEARING SLIGHT WEAR AND FLAKING (NORMAL FOR HIGH TIME ENGINE).   NR 1 PISTON SKIRT CRACKED AT 1,100 HOURS.   NOTE: THIS	 IS THE 4TH PISTON THAT I HAVE SEEN. RANGING FROM 1,100 HOURS TO 2,100 HOURS.  ACTION ON ENGINE - PISTON REPLACED NEW MA	IN BEARINGS INSTALLED.  (TC NR 20061018007)			1	H	7	1 	3O	3	O	NC	EXPA1H71	E252				 
2007061300122	20070613	00122		2007	6	13	CA061018008      	4	20061011	G	6113	SB10401	SPINNER         			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT PROPELLER	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GOOSE HIT THE OB SIDE OF THE LT PROP SPINNER.  DAMAGE WAS MINIMAL TO THE SPINNER WHERE THE BLADE CUT OUT IS.  THER	E WAS ALSO MINIMAL DAMAGE TO THE CHIN COWL PN 27-63026-053.  DAMAGE ON BOTH UNITS WERE COVERED BY THE SRM LIMITS OF .375	0 DEGREES 4. (TC NR 20061018008)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007050700095	20070507	00095	SW  	2007	5	7	CA061018009      	1	20061005	G	2910	2781032005	LINE            			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYD FLUID WAS DISCOVERED FROM GEAR UP LINE WHEN SYSTEM PRESSURE WAS APPLIED.  LINE WOULD ONLY LEAK AFTER 1200 PSI 	WAS APPLIED, SYSTEM PRESSURE WAS 2000 PSI.  PIN HOLE WAS IN RADIUS OF LINE. (TC NR 20061018009)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007050700096	20070507	00096	SW  	2007	5	7	CA061018010      	1	20060920	G	2913	PV304426	PUMP            			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON ROUTINE SPLINE REPLACEMENT IT WAS NOTICED THAT A CASTING DEFECT HAD BEEN FOUND AT THE BASE OF THE PUMP BELOW 	A FITTING.  THE NATURE OF THE CASTING DEFECT IS WHAT IS TERMED AS A COLD SHUNT.  A FLOURSECENT PENETRANT INSPECTION WAS 	CARRIED OUT AND THE COLD SHUNT WAS NOT FUSED CREATING A FATIQUE CRACK SINCE THE PUMP HAD BEEN IN SERVICE FOR SOME TIME. 	 PUMP WAS REJECTED. (TC NR 20061018010)			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007080800117	20070808	00117	SW  	2007	8	8	CA061018011      	1	20061018	G	7603	3219012123	CABLE           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	POWER LEVER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT POWER LEVER CABLE WAS DISCOVERED BROKEN 1 FOOT FROM POWER LEVER ATTACH POINT (TC NR 20061018011).						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007080800118	20070808	00118	SW  	2007	8	8	CA061018012      	1	20061015	G	5610	92063H0421	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) AIRCRAFT WAS IN CRUISE FLIGHT WHEN THE RT WINDSHIELD SHATTERED, OUTER PANE.  THE ELT WENT OFF AND HAD TO BE RESET 	AT THE SAME TIME.  REPORTS OF ARCING ON INSIDE OF WINDSHIELD FROM (P) STATIC BEFORE OUTER PANE CRACKED. (TC NR 200610180	12)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006120500260	20061205	00260	NM  	2006	12	5	CA061018013      	1	20061018	G	5315	147A550412	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS 947	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOORBEAM CORRODED AT BS 947.						2	L	7	2 	4F			RT	A16WE   					 
2006121100320	20061211	00320		2006	12	11	CA061018014      	4	20060915	G	6122		GOVERNOR        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								1686209F			(CAN) PROPELLER GOVERNOR FAILED IN FLIGHT CAUSING SEVERE OVERSPEED OF ENGINE. UPON LANDING, THE ENGINE OIL SCREEN WAS FO	UND TO BE METAL CONTAMINATED. PROPELLER GOVERNOR WAS REMOVED AND METAL WAS DISCOVERED AT GOVERNOR PAD. NO SCREEN WAS PRE	SENT BETWEEN GOVERNOR AND ENGINE. ENGINE DISMANTLED AND OIL TRANSFER COLLAR FOUND SEVERELY WORN, THE OIL PUMP WAS DAMAGE	D BEYOND REPAIR, THE CRANKSHAFT WAS WORN IN THE TRANSFER COLLAR AREA AND THE CRANKCASE WAS BADLY FRETTED. ONE CAMSHAFT L	OBE AND ONE LIFTER FACE WERE ALSO SEVERELY WORN. INSPECTION WAS LIMITED TO VISUAL AND MEASURING. NO NON-DESTRUCTIVE TEST	ING WAS CARRIED OUT. (TC NR 20061018014)	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2006120500313	20061205	00313	CE  	2006	12	5	CA061019002      	1	20061013	G	5311	1014300263	FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					BS 207	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16144								(CAN)  SPECIAL INSPECTION  50 WAS COMPLETED AS PER RAYTHEON MM 5-20-05, WHICH INVOLVES THE FOLLOWING: FRAME WEB FS 179 T	HROUGH FS 271  INSPECT THE FRAME WEBS FOR CRACKS FROM THE LIGHTNING HOLES AND STRINGER CUTOUTS. THE FRAMES SHOULD BE INS	PECTED FROM THE LOWER CENTERLINE TO STRINGER 4. EXAMINE THE CROSSTIES CLOSELY AT STRINGER 7 POSITION. THE INSPECTION INT	ERVAL IS INITIALLY 10,000 CYCLES AND AT 1000 CYCLES THERE AFTER.  DURING THIS INSPECTION THE RT FUSELAGE FRAME  207.0 (P	/N:101-430026-3) WAS FOUND CRACKED IN TWO LOCATIONS. THE FIRST CRACK WAS LOCATED AT THE UPPER EDGE OF THE FRAME LIGHTNIN	G HOLE MIDPOINT OF RT STRINGER 9 AND RT STRINGER 10 (WL 103.0). THE CRACK MEASURED .900 IN LENGTH. THE SECOND CRACK WAS 	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007012900327	20070129	00327	CE  	2007	1	29	CA061019003      	1	20061018	G	3220	AN517A	BOLT            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C*     	GL  	NLG	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING THE MAIN GEAR CAME DOWN AND LOCKED BUT THE NOSE GEAR STAYED UNLOCKED. THE AN5-17A BOLT CONNECTING THE D	RAG LINK ASSY TO THE DRAG BRACE TRUSS ASSY. HAD FAILED CAUSING THE NOSE GEAR STRUT ASSY TO JAM AGAINST THE TRUSS ASSY HO	LDING THE GEAR FROM COLLAPSING ON LANDING. (TC NR 20061019003)				1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2006121100321	20061211	00321	SW  	2006	12	11	CA061019004      	1	20061003	G	2844		INDICATOR       			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FUEL PRESSURE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						210D					(CAN) FUEL PRESSURE OVER-READING. PEGS AT 30 PSI WITH BOTH PUMPS AND GENERATOR ON. REMOVED FOR REPAIR AT INSTRUMENT SHOP	. (TC NR 20061019004)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006121100323	20061211	00323	SW  	2006	12	11	CA061019005      	1	20061003	G	7712	2060751853	INDICATOR       			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TORQUE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OIL IN GAUGE GLASS. REMOVED FOR REPAIR AT INSTRUMENT SHOP. (TC NR 20061019005)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120500268	20061205	00268	EA  	2006	12	5	CA061019007      	1	20061018	G	6123	8190026	PRESSURE SWITCH 			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AUTOFEATHER SYS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				1439 							(CAN) AFTER TAKE OFF WHILE REDUCING POWER FROM TAKE OFF POWER TO CLIMB, THE L/H PROP AUTOFEATHERED. AUTO FEATHER CIRCUIT	 BREAKER PULLED AND PROP RETURNED TO NORMAL. MAINTENANCE CONFIRMED SNAG AND REPLACED THE AUTOFEATHER PRESSURE SWITCH, CA	RRIED OUT GROUND RUNS AND RETURNED THE AIRCRFAT TO SERVICE. (TC# 20061019007)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2006120500276	20061205	00276	NM  	2006	12	5	CA061019008      	1	20061017	G	5220	85220281007	SEAL            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	EMERGENCY EXIT	LEAKING         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			4982 	4982 							(CAN) DURING CRUISE, FLIGHT CREW REPORTED R SIDE EMERG EXIT DOOR SEAL FAILED (LEAKING) RESULTING IN PRESSURIZATION LOSS 	. AIRCRAFT REQUESTED AND WAS CLEARED TO A LOWER ALTITUDE. AFTER NORMAL LANDING, MAINTENANCE INSPECTED AND REPLACED EMERG	ENCY EXIT DOOR SEAL. (TC# 20061019008)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500273	20061205	00273	SO  	2006	12	5	CA061019009      	2	20061018	G	7414	1051324	SPRING          			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	MAGNETO	BROKEN          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA						217469R					(CAN) NOTE THE SERIAL NUMBER ON THE ENGINE ON THIS FORM IS INCORRECT IT IS 217469-R.  THE IMPULSE COUPLING SPRING WAS FO	UND BROKEN. CUSTOMER HAD COMPLAINED OF ROUGH RUNNING CHECK MAG DROP, REMOVED MAGS AND INSPECTED.  THE SPRINGS WERE BROKE	N IN BOTH MAGNETOS,				1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL	 
2006121100324	20061211	00324	EA  	2006	12	11	CA061019011      	1	20060806	G	2897	CC670582071	CONDUIT         			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF348C1     		NE  					WIRING COVER	INTERFERENCE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2551 	2551 							(CAN) DURING GROUND INSPECTION NOTICED FUEL LEAK NEAR FRONT SPAR AREA IN BELLY PANEL. INSPECTION FOUND ELECTRICAL CONDUI	T FOR LT FUEL BOOST PUMP, WIRE COVERING INTERFERING WITH FLARE AT BULKHEAD FITTING. THIS ALLOWED FUEL TO PASS INTO THE C	ONDUIT AND OUT OF BELLY. WIRING COVERING TRIMMED BACK AND CONDUIT RESECURED. (TC NR 20061019011)				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006121100325	20061211	00325	EA  	2006	12	11	CA061019012      	2	20060821	G	7322	30804	FLOAT           	PREAIR      							LYC   	O320  	O320*       	41508	EA  					CARBURETOR	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				3    		A1211973					(CAN) THE CARBURETOR WAS DISASSEMBLED INSPECTED AND THE FLOAT ASSY HAD GAS IN .5 OF THE FLOAT.  FLOAT HAD NO APPARENT HO	LES OR CRACKS AS FLUID WAS INSIDE AND WOULD NOT DRAIN OUT. (TC NR 20061019012)										3	O			E274				 
2007012900328	20070129	00328	EU  	2007	1	29	CA061020001      	1	20061018	G	2750	527521213	FLAP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WING	OBSTRUCTED      	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) ICE BUILD UP INTO THE IB FLAP COVER CAUSED THE FLAPS TO NOT GO FULL UP.  IT TRIPPED THE FLAP CIRCUIT BREAKER.  THE	 ICE CAUSED THE ROD TO BEND FROM THE STRESS OF TRYING TO MOVE THE FLAP UP.  IT WAS NOTICE BY SEEING A 50 AMP DRAW FROM T	HE FLAP MOTOR.  ROD REPLACED, ICE MELTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061020001)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006120500301	20061205	00301	EU  	2006	12	5	CA061020004      	1	20061014	G	7334	1379287L405	LINE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  					LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) P3 LINE FLANGE FOUND WITH SMALL CRACK DURING ROUTINE ENGINE CHANGE. LINE REPLACED WITH NEW UNIT. (TC# 20061020004)						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE				 
2006121100327	20061211	00327	NM  	2006	12	11	CA061020005      	1	20060815	G	3230	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER GEAR WAS SELECTED UP IN CLIMB OUT, NOSE GEAR DOOR CAUTION WAS ON TOGETHER WITH NOISE OF SPINNING WHEEL. QRH 	LANDING GEAR DOOR MALFUNCTION PERFORMED. AFTER GEAR WAS SELECTED DOWN DOOR CAUTION DISAPPEARED BUT WE NOW HAD AN INDICAT	ION OF UNSAFE NOSE GEAR ( RED ). QRH ALTERNATE LANDING GEAR EXTENSION PERFORMED AND GREEN LIGHT FOR NOSE GEAR RECEIVED. 	NORMAL LANDING PERFORMED AND TAXIED TO PARKING. PASSENGERS AND CREW WAS BRIEFED SEVERAL TIMES DURING THE FLIGHT.  NLG SO	LENOID SEQUENCE VALVE REPLACED IAW 32-31-71-400-801 (TC NR 20061020005)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006121100329	20061211	00329	NM  	2006	12	11	CA061020006      	1	20060824	G	3220	471515	SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT. INDICATION SHOWED 3 GREENS AND 3 REDS. AFTER EMERGENCY CHECKLIST WAS 	COMPLETED THE DECISION FOR RE-LANDING WAS MADE. CABIN PAX AND STATION WERE INFORMED AND SUCCESSFUL RELANDING PERFORMED. 	FOUND NOSE WHEEL CENTER SENSOR FAULT AND SENSOR REPLACED. (TC NR 20061020006)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2006120500281	20061205	00281	EA  	2006	12	5	CA061020007      	1	20061017	G	5700		UNKNOWN         			DHAV  	DHC6  	DHC6300     	2802606	EA  											UNKNOWN         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) TYPE CERTIFICATE HOLDER (TCH) RECEIVED CALL INDICATING THIS AIRCRAFT WAS IN LEVEL FLIGHT WITH AN INDICATED AIRSPEE	D OF 120 KNOTS. THE PILOT FELT A VIBRATION IN THE AIRFRAME, LOOKED OUT THE LT WINDOW AND SAW THAT THE LT WING WAS FLUTTE	RING UP AND DOWN. THE PILOT REDUCED POWER AND IMMEDIATELY RETURNED TO BASE. (TC# 20061020007)				1	H	7	2 	3T			RT	A9EA    					 
2006120500295	20061205	00295	EA  	2006	12	5	CA061022009      	1	20061015	G	5610	NP13932211	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) LEFT SIDE WINDOW CRACKED (NOT SHATTERED) AT FL 350 (TC# 20061022009)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500257	20061205	00257	NE  	2006	12	5	CA061023002      	1	20061019	G	5210	9220902411043	HINGE FITTING   			SKRSKY	S92   	S92A        	       	NE  										PAX DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			103  								(CAN) THE FOLLOWING INFORMATION REFERS TO CHC HELICOPTERS INTERNATIONAL GROUND OCCURRENCE REPORT ,WHICH WAS SUBMITTED BY	 OUR BASE IN MALAYSIA: "ON CARRYING OUT 50 HOUR INSPECTION ON PASSENGER DOOR AND HINGES, FOUND FORWARD UPPER HINGE CRACK	ED. CRACK WAS RUNNING FROM UPPER AFT BOLT HOLE AND DOWN ALONG HINGE FITTING". PLEASE NOTE THAT THIS PARTICULAR HINGE FIT	TING HAS ONLY BEEN INSTALLED SINCE AUGUST 2006. . THE PREVIOUSLY INSTALLED HINGE FITTING WAS FOUND CRACKED ON 22 AUGUST 	2006 AND HAD FLOWN A TOTAL OF 168.6 HOURS (AIRCRAFT WAS UNDERGOING 50 HOURS INSPECTION. DID NOT RESULT IN ANY OTHER FAIL	URE. INSPECTION/MAINTENANCE WAS CONTINUED AND REPORT SUBMITTED. (TC# 20061023002)	2	G	7	2 	4U				R00024BO					 
2006120500294	20061205	00294	EA  	2006	12	5	CA061023004      	1	20061016	G	3097	302114BB1	WIRE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ELECTRICAL	BURNED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			33719	33719							(CAN) DURING CRUISE , FLIGHT CREW NOTICED NR 2 ENGINE LIP HEATER INDICATION SHOWING FAILURE OF LIP HEATER, DUE TO ICING 	CONDITIONS AT DESTINATION AIRPORT CREW ELECTED TO RETURN TO ORIGINATING AIRPORT. NORMAL LANDING. DURING MAINTENANCE INVE	STIGATION FOUND NO POWER TO LIP HEATER. PROBLEM TRACED TO BURNED WIRE 30-21-14BB-18 IN WIRING BUNDLE BEHIND LAVATORY WAL	L ( AFT OF CO-PILOT SEAT). WIRING BUNDLE HAD CHAFED ON LAVATORY WALL CAUSING INSULATION TO BE WORN. WIRE ( AND 3 OTHER W	IRES IN SAME BUNDLE) REPAIRED. AIRCRAFT RETURNED TO SERVICE. (TC# 20061023004)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006121100330	20061211	00330	SO  	2006	12	11	CA061023005      	2	20061012	G	8520	643202	CASE            			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1324 				521407			(CAN) THE ENGINE HAD A SMALL OIL LEAK. AFTER REMOVING THE DIP STICK ASSEMBLY, A CRACK WAS FOUND BETWEEN NR 2 AND NR 4 CY	LINDERS. THE ENGINE WAS REMOVED FOR OVERHAUL. (TC NR 20061023005)					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2006120500248	20061205	00248	EA  	2006	12	5	CA061024001      	1	20061023	G	5610	601R3303314	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  											FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) F/O WINSHIELD BROKE WHILE AT CRUISE ALTITUDE, DIVERTED  C/A -RAR F/O WINDSHIELD IAW AMM (CRJ 700) 56-11-01 REF LGP	G2160865 ITEMS 1 AND 2 FOR FUNCTIONAL CHECK AND OPERATIONAL CHECK. OPS CHECKS AND FUNCTIONAL CHECKS OK. (TC# 20061024001	)				2	L	7	2 	4F			RT	A21EA   					 
2006120500256	20061205	00256	EA  	2006	12	5	CA061024002      	2	20061020	G	8500	TIGO541E1A	ENGINE          			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					RIGHT	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA								RL27662			(CAN) AFTER TAKEOFF, RT ENGINE STARTED MAKING POWER FLUCTUATIONS WITH A RAPID EGT RISE. RT ENGINE WAS SHUT DOWN IN DESCE	NT AND AIRCRAFT RETURNED SAFELY. A MAINTENANCE INVESTIGATION IS UNDER WAY TO DETERMINE THE CAUSE. REPORT TO FOLLOW WHEN 	CAUSE IS IDENTIFIED. (TC# 20061024002)				1	L	7	2 	3O	3	O		A8EA    	E19EA				 
2006120500245	20061205	00245	EU  	2006	12	5	CA061024003      	1	20061024	G	2120		UNKNOWN         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	COCKPIT	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT CREW COULD DETECT FUMES OF AN ELECTRICAL NATURE. AIRCRAFT RETURNED TO DEPARTURE POINT WITHOUT	 INCIDENT. A MAINTENANCE INVESTIGATION IS UNDER WAY TO DETERMINE THE CAUSE OF THE FUMES/ODOUR. A REPORT WILL FOLLOW WHEN	 CAUSE IS IDENTIFIED. (TC# 20061024003)				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2006120500247	20061205	00247	EA  	2006	12	5	CA061025002      	1	20061024	G	3520	13740003	SWITCH          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					OXYGEN CONTROL	INOPERATIVE     	W				O				OTHER                   				G			MULTIPLE FAILURE          			NR	NOT REPORTED   	1			CA			1656 								(CAN) WHILE CARRYING OUT A 12 MONTH CABIN OXYGEN FUNCTIONAL TEST, FOUND THE OXYGEN CONTROL PANEL SEMI-FUNCTIONAL. THE RO	TARY KNOB WOULD NOT GO TO THE "CLOSED" POSITION WITHOUT EXCESSIVE FORCE. ROTATING TO THE "OVERRIDE" POSITION FUNCTIONED 	PROPERLY BUT OXYGEN FLOW TO THE CABIN MASKS SEEMED RESTRICTED. SELECTING THE "THERAPEUTIC" SWITCH "ON" WAS EXTREMELY STI	FF AND WOULD NOT TURN OFF WHEN SELECTED. FOUND PANEL TO BE CONTAMINATED. MOST LIKELY COFFEE AND/OR SOFT DRINK RESIDUE. N	EW PANEL INSTALLED, FLOW TO CABIN OXYGEN MASKS SEEMED TO INCREASE TO DOUBLE THE FLOW RATE OF THE ORIGINAL. THERAPEUTIC S	WITCH OPERATED AS NORMAL.412 SQUADRON OPS WILL BE CONTACTED TO APPRISE PILOTS OF THE FINDINGS. (TC# 20061025002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500255	20061205	00255	NM  	2006	12	5	CA061025003      	1	20061020	G	2710	82700567001	CABLE           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT AILERON	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			16203								(CAN) FINDINGS DURING C-CHECK INSPECTION IN AREA WING STA 171, AFT SPAR, LT AND RT REVEALED HEAVILY CHAFED AILERON CABLE	S IN PULLEY AREA AT WING BS 171. ON RT SIDE THE CABLE WAS SEVERELY DAMAGED AND ONLY A PART OF ONE STRAND WAS LEFT INTACT	. THE CABLE IS OF TYPE 19X7 (7 STRANDS AND WITH 19 WIRES). LAST INSPECTION PERFORMED IN 2001 (TASK 2C INTERVAL) - NO FIN	DINGS. ON LT SIDE APPROX 40% OF THE STRANDS/WIRES WAS BROKEN. THE PULLEYS ARE MADE OF STEEL WITH A ROLLER BEARING AND UN	DERNEATH THE PULLEYS IS A CABLE GUARD. CABLE TENSION APPROX 52 LBS (AMM) INSPECTION OF A NUMBER OF PULLEYS, AILERON AND 	SPOILER, REVEALED HEAVY WEAR/INDENTATION AT ONE SPOT AS IF THE PULLEY HAD BEEN. (TC# 20061025003)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500253	20061205	00253	GL  	2006	12	5	CA061025004      	3	20061022	G	6110		STUD            	MCAULY      		CESSNA	185   	185F        	2072820	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	PROPELLER	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				306  		7710359					(CAN) WHILE INSTALLING THE MCCAULEY MODEL D3A34C403-B PROPELLER ONTO A CESSNA 185, THE ENGINEER WAS TIGHTENING THE FIBER	 LOCK NUTS ONTO THE PROPELLER MOUNTING STUDS, WHEN ONE OF THE NUTS KEPT ON TURNING AND DID NOT SEEM TO BE GETTING ANY TI	GHTER. HE TRIED ANOTHER NEW LOCK NUT BUT THE SAME THING HAPPENED AND THEN NOTICED THAT THE MOUNTING STUD WAS BEING PULLE	D OUT FROM THE PROP HUB. THE LOCK NUT HAD NOT BEEN TIGHTENED UP TO THE RECOMMENDED TORQUE VALUE FOR MOUNTING THE PROP BE	FORE THIS STARTED TO HAPPEN. THE PROPELLER BEING INSTALLED HAD ONLY 305.7 TSO. IT WAS SENT BACK TO THE SHOP THAT OVERHAU	LED IT. (TC# 20061025004)	1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2006121100333	20061211	00333	SW  	2006	12	11	CA061025005      	1	20060907	G	2822	1C27	CARTRIDGE       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					BOOST PUMP	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ABOVE 7000 FEET BOOST PUMP LIGHT WOULD COME ON. BELOW 7000 FEET WARNING LIGHT WOULS EXTINGUISH. BOOST PUMP CARTRID	GE P/N 1C27 REPLACED. (TC NR 20061025005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006121100335	20061211	00335	CE  	2006	12	11	CA061025006      	1	20060502	G	5711		SPAR            			BEECH 	95    	E95         	1153410	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7004 								(CAN) DUING INSPECTION IAW FAA AD 90-08-14 AND SB53-2269 REV 2 SHORT CRACKS WERE VISUALLY FOUND EMINATING FROM 2 HUCK BO	LT LOCATIONS ON THE LT FORWARD WING SPAR CARRY THROUGH WEB FACE. CRACKS WERE CONFIRMED BY LPI. REPAIRED IAW MFG FAA APPR	OVED DRAWING 58-40009 AND 58-4008 REV C FORWARD LT FACE ONLY. (TC NR 20061025006)				1	L	7	2 	3O	3	O		3A16    	1E10	5	C	P920	 
2007012900329	20070129	00329	CE  	2007	1	29	CA061025007      	1	20060930	G	6123		CONTROL CABLE   			BEECH 	95    	E95         	1153410	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RT PROP	DEFECTIVE       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AFTER A ROUTINE TRAINING FLIGHT THE PILOT REPORTED THAT THE RT PROP CONTROL WAS VERY STIFF AND SPRINGY AND THE PRO	P WAS SLOW TO FEATHER. THE CONTROL WAS DISCONNECTED FROM THE GOVERNOR AND THE DEFECT WAS CONFIRMED TO BE THE CONTROL CAB	LE. THE TTSN FOR THE ENGINE CONTROL CABLES WERE UNKNOWN. ALL LT AND RT ENGINE CONTROL CABLES WERE REPLACED WITH NEW CONT	ROLS. (TC NR 20061025007)			1	L	7	2 	3O	3	O		3A16    	1E10	5	C	P920	 
2006120500241	20061205	00241	NM  	2006	12	5	CA061026001      	1	20061025	G	4910	4503067A	APU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						MALFUNCTIONED   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) APU ENCLOSURE SUFFERED STRUCTURAL DAMAGE AFTER FUEL VAPOR IGNITED.  CREW HAD TRIED TO START APU AFTER LANDING MINI	MUM TWICE, UNABLE TO START. NOT POSSIBLE TO GET FAULT CODES SO MECHANIC CALLED. MECH STARTED APU AND THEN IT AUTO SHUTDO	WN. MECH STARTED APU AGAIN AND SAME RESULT. MECH OBSERVED FUEL VAPOR FROM EXHAUST BUT NOT FROM FUEL DRAIN. MECH PULLED C	IRCUIT BREAKER FOR FUEL SOLENOID IN ORDER TO PERFORM DRY CRANK TO VENT APU. WHEN PUSHING POWER SWITCH THERE WAS AN EXPLO	SION IN THE APU BAY.  DAMAGE TO THE APU ENCLOSURE AND DOORS OCCURRED. TAIL CONE TO BE REPLACED. (TC# 20061026001)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006120500231	20061205	00231	NM  	2006	12	5	CA061026002      	1	20061026	G	2710	FL4C62	BEARING         			DHAV  	DHC8  	DHC8102     	2809003	NM  										AILERON CONTROL	JAMMED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE C CHECK INSPECTION, NR 5 BEARING ON 8 IN A WING AILERONS SYSTEME CABLE FAIRLEADS WAS FOUND JAMMED AND F	LAT SPOTTED. ALL CABLES PASSING THRU THE FAIRLEAD HAVE TO BE REPLACE DUE TO THE CHAFFING IN THE BEARING, THE WORSE ONE W	AS THE CABLE P/N:82700519-001. THE PART NUMBER IN THE IPC WAS FL4C6-2 BUT THE NUMBER ON THE BEARING WAS P15SP1 WITH THE 	WORD SARMA STAMP ON IT. (TC# 20061026002)			2	H	7	2 	4T			RT	A13NM   					 
2006120500240	20061205	00240	CE  	2006	12	5	CA061026003      	1	20061025	G	3246	50060285	WHEEL           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					MLG	DEPARTED        	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) PILOTS DISCOVERED NR 4 WHEEL ASSY MISSING AFTER ARRIVING AT DESTINATION. PASSENGER SAID A BANG WAS HEARD DURING TA	KE-OFF. MAINTENANCE PERSONNEL DISPATCHED TO INSPECT AIRCRAFT,  AND IF INSPECTED SERVICEABLE INSTALL NEW WHEEL ASSY AND R	ETURN TO BASE. AIRCRAFT INSPECTED SERVICEABLE, M/W INSTALLED AND AIRCRAFT FLOWN TO BASE. O/B BEARING APPEARS TO HAVE FAI	LED. (TC# 20061026003)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006120500235	20061205	00235	EU  	2006	12	5	CA061026004      	1	20061026	G	3411		INDICATOR       			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  					PITOT HEAT	BURNED          	W				O				OTHER                   				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			CA			1100 								(CAN) PILOT REPORTED MALFUNCTION OF PITOT HEAT BREAKER SWITCH, UPON INSPECTION, CIRCUIT BOARD ATTACHED TO BACK OF SWITCH	 WAS FOUND BADLY BURNT AND END OF WIRE CONNECTION FROM THE PITOT TO THE POWER SWITCH WAS FOUND OVERHEATED.  MAIN PITOT W	AS REPAIRED.  THE CIRCUIT BOARD CLAMPED BETWEEN THE BREAKER SWITCH AND THE PITOT HEAT WIRE WAS U/S DUE TO OVERHEAT.  THI	S INSTALLATION APPEARS TO BE FROM FACTORY.  2 POSSIBLE CAUSES OF THIS FAILURE: 1) FIBERGLASS CIRCUIT BOARD COULD NOT STA	ND UP TO PRESSURE OF ATTACHMENT SCREW.  DUE TO POOR CONNECTION , THE CONNECTION WOULD HAVE HEATED UP AND UPON GETTING HO	T ENOUGH, RESIN IN FIBERGLASS BOARD WOULD HAVE DISINTIGRATED CAUSING PITOT HEAT FAILURE. 2) PRINTED CIRCUIT BOARD HAS WI	1	H	7	1 	3O	3	O	NT	        	1E4				 
2006120500292	20061205	00292	WP  	2006	12	5	CA061026005      	1	20061016	G	7600		SUPPORT         			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  										ENG CONTROLS	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						NA					(CAN) IN SOME CASES, THE WELD BRAZING THAT CONNECTS THE TELEFLEX CONTROL SUPPORT BEARINGS TO THE ENGINE CONTROL QUADRANT	 ASSEMBLY HAVE BEEN FOUND TO BE CRACKED OR HAVE INSUFFICIENT BONDING TO THE BEARING SUPPORT PLATE. THIS PROBLEM, IN ADDI	TION TO INTERNAL WEAR IN THE BEARINGS, CAN CAUSE ADDITIONAL STRESS TO THE REMAINING BRAZED WELD. IN EXTREME CASES THE BE	ARING CAN SEPARATE FROM THE BEARING SUPPORT PLATE AND CAUSE UNEXPECTED POWERPLANT SETTINGS.  ORIGINALLY DISCOVERED IN AU	GUST 2002 - CASCADE AEROSPACE ISSUED A SERVICE BULLETIN (SB 3127-001) TO INSPECT THE ENTIRE FLEET WITHIN SEVEN DAYS OR 6	0 FLIGHT HOURS (WHICHEVER CAME FIRST). RECURRING NDT INSPECTIONS WERE SCHEDULED EVERY 400 HOURS TAT OR DURING AN ANNUAL 	2	H	7	2 	4R				A25WE   					 
2007012900129	20070129	00129	CE  	2007	1	29	CA061027001      	1	20061023	G	2720	0510105338	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER SYSTEM	MISROUTED       	W				K				NONE                    				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			CA			6326 	6326 							(CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION IT WAS DISCOVERED THAT WHEN TENSION WAS PLACED ON THE RT RUDDER PEDAL, IT	 WAS RUBBING AGAINST THE RT AILERON DIRECT CABLE PULLEY CLEVIS PULLEY GUARD IN THE FORWARD TUNNEL SECTION OF THE FUSELAG	E. THE RUBBING WAS SUFFICIENT ENOUGH TO CAUSE  6 WIRES TO BREAK. THE CABLE WAS IMPROPERLY ROUTED OVER THE AILERON DIRECT	 PULLEY CLEVIS PIN CABLE GUARD AND SHOULD HAVE PASSED UNDERNEATH. THE CABLE WAS FRAYED APPROXIMATELY 7 INCH AFT OF THE A	TTACHMENT TO THE AFT RUDDER BAR. THE FRAYED WIRE CAN ONLY BE SEEN BY REMOVAL OF THE PLASTIC CENTER CONSOLE AND VIEWED TH	ROUGH THE TUNNEL SECTION WITH AN INSPECTION MIRROR AND TENSION APPLIED TO THE RT RUDDER. NO RECORD OF THE CABLE EVER BEI	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006120500250	20061205	00250	SW  	2006	12	5	CA061027002      	1	20061023	G	5531	41000823	SPAR            	AEROCD      		GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8830 								(CAN) DURING ANNUAL X-RAY INSPECTION OF THE VERTICAL STABILIZER, A CRACK WAS DETECTED ON THE LEFT HAND SIDE OF THE VERTI	CAL STABILIZER CENTRE SPAR AT THE 4TH FASTENER ABOVE THE DOUBLER. THE CRACK APPEARS TO RUN INTO THE RADIUS OF THE CENTRE	 SPAR. THE AIRCRAFT WILL BE REPAIRED PRIOR TO BEING RELEASED BACK INTO SERVICE. (TC# 20061027002)				1	H	7	2 	3T	4	T		2A4     	E4WE				 
2006120500300	20061205	00300	SW  	2006	12	5	CA061027003      	1	20061014	G	7712	31017263	TORQUE SENSOR   			SWRNGN	SA226 	SA226TC     	8780404	SW  										RT ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA				4015 							(CAN) UPON TAXI INTO AIRPORT, THE RT ENGINE SHUT DOWN DUE TO THE CENTER GEAR ON THE TORQUE SENSOR SHAFT & WHERE NUT HOLD	S THE GEAR ON BROKE OFF. AT THIS TIME THE A/C WAS AT THE TERMINAL AND NO PROBLEMS AROSE DUE TO THIS INCIDENT. SUSPECT TH	E NUT ON THE SHAFT WAS OVERTORQUED AT OVERHAUL BY A APPROVED OUTSIDE FACILITY. THE R/H ENGINE WAS REPLACED AND THE ENGIN	E P-54108 WAS FORWARDED TO THE ENGINE SHOP FOR REPAIR. (TC# 20061027003)			2	L	7	2 	4T			RT	A8SW    					 
2006120500254	20061205	00254	NE  	2006	12	5	CA061027004      	2	20061021	G	7322	1897001161	SHAFT           	BEECH       		BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					AIR VALVE	WORN            	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			5598 								(CAN) PRIOR TO STARTUP, PILOTS` FOUND THE LH MANIFOLD HEAT CONTROL JAMMED.  FURTHER INVESTIGATION DISCOVERED ONE OF THE 	SCREWS SECURING THE AIR VALVE PLATE TO THE AIR VALVE SHAFT HAD DEPARTED, AND THE OTHER SCREWS WERE VERY LOOSE.  WRONG TY	PE OF NUT WAS USED ON THE SCREWS, CONTRIBUTING TO THE LOOSE HARDWARE.  PARTS MANUAL REQUIRES AN365-832 TYPE NUTS, WHILE 	PRESSED STEEL TYPE OF NUT WAS FOUND INSTALLED IN BOTH AIRBOXES.  VALVE WAS REPAIRED AND AIRCRAFT RETURNED TO SERVICE.  T	HIS HAD THE POTENTIAL TO BE AN ENGINE FAILURE. (TC# 20061027004)		1	L	7	2 	3R	3	R		A765    	5E1				 
2006120500287	20061205	00287	NM  	2006	12	5	CA061029001      	1	20061017	G	5753	654952921	BELLCRANK       			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 FLAP TRACK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 2 AFT FLAP BELLCRANK WAS FOUND BROKEN WHILE ACCOMPLISHING DAILY CHECK. INVESTIGATION FOUND EXCESSIVE WEAR ON TH	E NR 2 AFT FLAP BELLCRANK CAM TRACK WHICH RESULTED IN THE BELLCRANK POPPING OUT OF THE CAM TRACK. UPON REPLACEMENT OF TH	E CAM TRACK, IT WAS DETERMINED THE CAM TRACK WAS NOT INSTALLED IAW BOEING MAINTENANCE MANUAL. THE MM REQUIRES INSTALLATI	ON OF A TAPER SHIM TO PROPER ALIGN TRACK SO THAT THE BELLCRANK CAM ROLLER WILL RIDE PROPERLY IN THE CAM TRACK. WE BELIEV	E THE BELLCRANK BROKE AFTER IT POPPED OUT OF THE CAM TRACK AND JAMMED WHEN THE FLIGHT CREW MOVED THE FLAPS.  A FLEET CAM	PAIGN FOUND 2 OTHER CAM TRACKS WITH SIMULAR WEAR AND WERE ALSO MISSING REQUIRED TAPER SHIM. THE CAM TRACKS WERE REPLACED	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006120500208	20061205	00208	EU  	2006	12	5	CA061030001      	1	20061028	G	2910	316Q2277	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					HYDRAULIC RETURN	FRACTURED       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE EN-ROUTE THE HYDRAULIC FLOW LIGHTS ILLUMINATED AND THE HYDRAULIC PRESSURE DROPPED TO 1900PSI. THE AIRCRAFT D	IVERTED, WHERE AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE INVESTIGATION REVEALED THAT THE HYDRAULIC RETURN LINE BETWEEN	 THE HYDRAULIC CUT OUT VALVE AND THE HYDRAULIC RESERVOIR HAD FRACTURED AT THE RESERVOIR CONNECTION. THE LINE WAS REPLACE	D AND THE SYSTEM TESTED SERVICEABLE. AN OPTIONAL MOD (S/B 29/44, MOD 7297) RAISED BY BAE IN 1986 REPLACED THIS RIGID LIN	E WITH A FLEXIBLE LINE TO PRECLUDE THIS TYPE OF FAILURE. THE LINE IN QUESTION WAS A PRE-MOD ITEM. (TC# 20061030001)		2	L	7	2 	3T	4	T		A24EU   	A196				 
2006121100337	20061211	00337	WP  	2006	12	11	CA061030002      	1	20061010	G	6510	C0411	BEARING         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					DAMPER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			197  								(CAN) ABNORMAL SOUND HEARD ON SHUTDOWN.  ON FURTHER INSPECTION THE INNER RACE OF THE DAMPER BEARING ON THE TAIL ROTOR DR	IVESHAFT HAD BEEN FOUND TO HAVE SPUN.  THE INNER RACE OF THE BEARING IS NOT ALLOWED ANY MOVEMENT RELATIVE TO THE DRIVE S	HAFT.  THE TAIL ROTOR DRIVE SHAFT ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT. (TC NR 20061030002)				1	G	7	1 	3O	3	O		H11NM   	E295				 
2006121100339	20061211	00339	CE  	2006	12	11	CA061030003      	1	20060627	G	8011	631847	GEAR            	CONT        		CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					STARTER SHAFT	BROKEN          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			5    								(CAN) (1)GEAR TOOTH BROKE OFF THE STARTER SHAFT GEAR IN A NEW STARTER ADAPTER ASSEMBLY CAUSING FOREIGN MATERIAL TO ENTER	 THE ENGINE LEADING TO FURTHER DAMAGE INSIDE THE CRANKCASE. FINAL RESULT WAS LOSS OF POWER TO THE RT ENGINE AND UNSCHEDU	LED LANDING. (TC NR 20061030003)				1	L	7	2 	3O	3	O	RT	A7CE    	E7CE				 
2006121100340	20061211	00340		2006	12	11	CA061030004      	4	20061006	G	3422	568195301	SPRING          	JET         																VERTICAL GYRO	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				4681 		1367M					(CAN) AT PREVIOUS REPAIR UNIT WAS ASSEMBLED WITH A SHOP FABRICATED PRELOAD SPRING OF LARGED DIAMETER AND HIGHER PRESSURE	 RATE PRELOAD SPRING SHOULD HAVE BEEN REMOVED WHEN MOD 5 INCORPORATED (TC NR 20061030004)																		 
2007012600303	20070126	00303	CE  	2007	1	26	CA061030005      	1	20061023	G	3250	05430223	ARM             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NLG STEERING	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9448 								(CAN)   DURING INSPECTION OF STERRING SYSTEM LT STEERING ARM TUBE FOUND BENT ON THE TUBE ASSY.   NEW PART ORDERED AND IN	STALLED.  (TC NR 20061030005)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2006120500210	20061205	00210	SO  	2006	12	5	CA061030006      	1	20061027	G	7120		MOUNT           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8215 	3512 							(CAN) THE TOP ENGINE MOUNT PAD, LOCATED ON THE GAS GENERATOR CASE, HAD A CRACK ON THE WELD LINE APPROX. 1.75 INCHES LONG	. (TC# 20061030006)					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2006121100341	20061211	00341	EU  	2006	12	11	CA061030007      	1	20060518	G	6220	350A37116220	RETAINER        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					DROOP STOP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON THE DAILY CHECK BY THE ENGINEER THE MAIN ROTOR BLADE DROOP STOP RING RETAINER WAS FOUND CRACKED BELOW THE RETAI	NER CLAMP.  NO FURTHER DAMAGE.   (TC NR 20061030007)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006120500203	20061205	00203	NM  	2006	12	5	CA061031001      	1	20061030	G	3240	82920010147	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT CREW REPORTED LOSS OF HYDRAULIC FLUID (DOWN 1/2 QUART). FLIGHT RETURNED TO DEPARTING AIRPORT. ALL	 SYSTEMS WERE OPERATING NORMALLY UNTILL LANDING ROLLOUT, AT WHICH TIME CREW REPORTED NIL BRAKES. AIRCRAFT STOPPED WITH E	MERGENCY BRAKE AND WAS TOWED TO RAMP AREA WITHOUT FURTHER INCIDENT. ERS WAS REQUESTED FOR ARRIVAL BUT AN EMERGENCY WAS N	OT DECLARED. NO ADVERSE PASSENGER REACTION WAS NOTED. MAINTENANCE TROUBLESHOOTING FOUND THE NR 1 SYSTEM PRESSURE LINE (I	PC REF. 32-42-00 FIG. 5 ITEM - 160) TO THE LT BRAKE CONTROL VALVE TO HAVE A PIN HOLE AT THE LOWER FORWARD ELBOW. REPLACE	D WITH A TEMPORARY FLEX LINE. SYSTEM LEAK AND FUNCTION CHECKED SERVICEABLE. AIRCRAFT AFTT-41155:50 HOURS, CYCLES-41543.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500209	20061205	00209	GL  	2006	12	5	CA061031002      	3	20061027	G	6114	05503214	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			77   								(CAN) BULKHEAD WAS INSTALLED IAW CESSNA SK172-156A INSTRUCTIONS. BULKHEAD HAS CRACKS CURVING AROUND BOLT HOLES ABOUT HAL	F INCH AWAY FROM THE HOLE EDGE AT THE INNER BEND RADIUS.  NOTE: THIS IS THE FOURTH OR FIFTH IDENTICALLY CRACKED BULK HEA	D FOUND ON AS MANY OTHER 172 A/C IN THE PAST THREE OR SO MONTHS AT OUR FACILITY. CESSNA IS GIVING US WARRANTY FOR THE PA	RTS BUT NO CORRECTIVE ACTION HAS COME FORWARD AS YET. (TC# 20061031002)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006121100342	20061211	00342	SW  	2006	12	11	CA061031003      	1	20060920	G	6730	206076031021	SERVO           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ROTOR SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			11540	1112 							(CAN) EXCESSIVE FLUID LEAKAGE.  LEAKING BEYOND LIMITS (TC NR 20061031003)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120500290	20061205	00290	SO  	2006	12	5	CA061031004      	1	20061017	G	5344		HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABIN LOWER ENTRANCE DOOR FORWARD HINGE LOOSE, DOOR MOVES UP AND DOWN WHEN PASSENGERS STEP ON THE LOWER DOOR STEP.	 FOUND THE FORWARD DOOR HINGE ATTACHMENT FRAME CRACKED AT THE ATTACHMENTS FOR THE HINGE, ALLOWING THE DOOR SILL AND CABI	N FLOOR AT THE ENTRANCE TO MOVE UP AND DOWN WHEN A LOAD WAS APPLIED TO THE DOOR. FRAME REPLACED WITH NEW PART AND DOOR R	EINSTALLED. (TC# 20061031004)			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2006120500244	20061205	00244	EU  	2006	12	5	CA061101001      	1	20061024	G	2810	A2824004900200	VALVE           			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C      	 	GL  					FUEL SYSTEM	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE PERFORMING A GENERAL VISUAL INSPECTION INSIDE THE RIGHT HAND/OUTER FUEL TANK, THE OUTBOARD FUEL PUMP SEQUENC	E VALVE WAS FOUND BROKEN. DEBRIS OF THE SEQUENCE VALVE WHERE FOUND NEARS THE RESPECTIVE FUEL PUMP CANISTER. AREA WAS CLE	AN OUT. SEQUENCE VALVE ASSEMBLY REPLACED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2006120500199	20061205	00199	EA  	2006	12	5	CA061101002      	1	20061030	G	5730	601R1090719	CLAMP           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ACCESS DOOR	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25347								(CAN) ELECTRICAL ARC BURN MARKS FOUND ON THE REAR FACE OF NUTPLATES (QTY 17) FOR THE WING FUEL TANK ACCESS DOORS. AS PER	 THE TECHNICAL RECORDS THERE WERE TWO REPORTED LIGHTNING STRIKES ON THIS AIRCRAFT SINCE  NOVEMBER 09/2005. THE BURN MARK	S ARE A LIKELY INDICATION OF LIGHTNING STRIKE ENERGY PATH.  SOME OF THE ACCESS CUT-OUT ON THE UNDERWING WERE FOUND PAINT	ED OVER. THESE PAINT WERE REMOVED, AREA RETREATED AND NEW PANELS WERE INSTALLED. (TC# 20061101002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500202	20061205	00202	NE  	2006	12	5	CA061101003      	2	20061030	G	8530	205364205523	STUD            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					CYLINDER HOLD DO	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1124 				P36383			(CAN) DURING ANNUAL INSPECTION OF THE RT ENGINE 5 OF THE 15 CYLINDER HOLD DOWN STUDS ON CYLINDER NO. 2 WERE FOUND SHEARE	D. 3 HOLD DOWN NUTS WERE LOOSE, ALL PAL NUTS WERE INSTALLED AND TIGHT. THE PART NUMBERS FOR THE SHEARED STUDS ARE AS  FO	LLOWS: 205364 (QTY 2), 205523 (QTY 2)AND 204850 (QTY 1). ADDITIONAL INSPECTIONS OF THE ENGINE WILL BE ACCOMPLISHED. ANY 	FURTHER FINDINGS/RESULTS WILL BE REPORTED.			2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
2006120500205	20061205	00205	NE  	2006	12	5	CA061101005      	1	20061029	G	3246	5004410	WHEEL           			SKRSKY	S76   	S76A        	8143006	NE  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEEL CRACKED AND AUDIBLE AIR ESCAPING FOUND ON DAILY INSPECTION (TC# 20061101005)						1	G	7	2 	3U				H1NE    					 
2006120500206	20061205	00206	EA  	2006	12	5	CA061102001      	1	20061029	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WINDSHIELD REMOVED AND REPLACED ACC AMM TASK 56-11-01-000-801. (TC# 20061102001)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500236	20061205	00236	EA  	2006	12	5	CA061102002      	1	20061026	G	5610	601R3303314	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) WINDSHIELD CHANGED AND TESTED IAW AMM TASK 56-11-01-401-801-A01.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006120500238	20061205	00238	EA  	2006	12	5	CA061102003      	1	20061026	G	5610	NP13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAIN WINDSHIELD SHATTERED AT FL320 ENROUTE TO ORD.  DIVERTED TO BIS. (TC# 20061102003)						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007012600306	20070126	00306	CE  	2007	1	26	CA061102004      	1	20061102	G	2720	2613017202	RUDDER          			CESSNA	208   	208B        	2073701	CE  											STIFF           	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			4088 	4088 							(CAN) AIRCRAFT WAS BEING TAXIED TO THE RAMP FROM THE HANGER. THE PILOT NOTICED THAT THE RUDDER CONTROLS FELT STIFF.  THE	 PILOT DECIDED TO RETURN TO THE HANGER AND ADVISE MAINTENANCE. THE AIRCRAFT IS BEING EXAMINED AT THIS TIME AND WILL UP-D	ATE THIS SDR WHEN A CAUSE OF THIS FAULT IS FOUND. (TC NR 20061102004)				1	H	7	1 	3T				A37CE   					 
2006120500174	20061205	00174		2006	12	5	CA061102005      	1	20061102	G	5412	K6600013	FIREWALL        								GARRTT	TPE331	TPE3315251K 	 	NM  					NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS FOUND IN FIREWALL ASSEMBLY WHILE DOING SB 217. (TC# 20061102005)											4	T			E2WE				 
2006121100345	20061211	00345	NM  	2006	12	11	CA061102006      	1	20061004	G	3230		HOUSING         	TACTAIR     		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	SEQUENCE VALVE	FAILED          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			AP	APPROACH       	1			CA			13093			1769					(CAN) DURING APPROACH WHEN CREW SELECTED GEAR DOWN, NR 2 HYD ENG PUMP CAUTION LIGHT ILLUMINATED DURING EXTENSION CYCLE. 	NOSE GEAR DOORS AND RT MAIN GEAR DOORS REMAINED OPEN, LT MAIN GEAR DOOR CLOSED. QRH ITEMS FOR NR 2 HYDRAULIC SYSTEM AND 	GEAR DOORS OPEN WERE COMPLETED. INVESTIGATION BY ENGINEERING DETERMINED THAT THE LEAK WAS ORIGINATING FROM THE RT MLG DO	OR SOLENOID SEQUENCE VALVE.  (3) OF THE FOUR BOLTS SECURING THE SOLENOID TO THE VALVE BODY HAD SHEARED RESULTING IN THE 	PARTIAL SEPARATION OF THE SOLENOID FROM VALVE BODY. THIS CAUSED A LOSS OF NR 2 HYDRAULIC SYSTEM QUANTITY AND PRESSURE. N	O SECONDARY DAMAGE WAS CAUSED AS A RESULT OF THE FAILURE. THE SOLENOID SEQUENCE VALVE ASSEMBLY WAS REPLACED IAW THE AIRC	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006121100347	20061211	00347	EA  	2006	12	11	CA061102007      	1	20060926	G	5751		HINGE           	BOMBDR      		CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	AILERON	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2936 								(CAN) DURING AN ANNUEL INSPECTION WE FOUND BOTH AILERONS WITH SEVERE DAMAGE AT CENTER HINGE (TC NR 20061102007)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2006120500176	20061205	00176	NM  	2006	12	5	CA061103002      	1	20061101	G	5740	72760059101	ADAPTER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48562			1341					(CAN) A CRACK WAS DISCOVERED (C-CHECK INSPECTION) ON THE RUDDER ACTUATOR MOUNTING ADAPTOR (UPPER) TO VERTICAL STAB SPAR.	 THE CRACK IS APPROXIMATELY 2.5 INCHES AROUND THE CIRCUMFERENCE OF THE ADAPTOR TUBE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006121100349	20061211	00349	NE  	2006	12	11	CA061103003      	2	20060927	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						OVERHEATED      	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								PC1299			(CAN) DURING TAXI FOLLOWING LANDING THE ENGINE EXPERIENCED AN ITT OVER-TEMPERATURE.  SUBSEQUENT INSPECTION REVEALED DEBR	IS IN THE EXHAUST AND HEAT DISCOLORATION OF THE AIRCRAFT COWLING IN THE EXHAUST REGION.  MFG WILL INVESTIGATE THE INCIDE	NT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103003)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006121100351	20061211	00351	EA  	2006	12	11	CA061103004      	2	20060925	G	7261		OIL SYSTEM      			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  					ENGINE	OVERTEMP        	W				E				ENGINE SHUTDOWN         				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) IN FLIGHT ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE ACCOMPANIED BY A DROP IN OIL PRESSURE.  THE ENGINE WAS SHUTD	OWN IN FLIGHT.  POST FLIGHT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL SYSTEM AND EVIDENSE OF OIL LEAKAGE FROM THE ENG	INE DRAIN.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103004)				1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2006121100352	20061211	00352	NE  	2006	12	11	CA061103005      	2	20060927	G	7210		SHAFT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWA   	PW120 	PW123       	 	NE  					RGB	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE FLAMED-OUT IN CRUISE AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED M	ETAL DEBRIS ON THE ENGINE CHIP DETECTOR AND DAMAGE TO THE TOWERSHAFT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT	 CAUSE ONCE ESTABLISHED. (TC NR 20061103005)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006121100353	20061211	00353	NE  	2006	12	11	CA061103006      	2	20060810	G	7261		TUBE            			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					OIL TRANFER	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA								121355			(CAN) FOLLOWING TAKEOFF ENGINE SPEEDS REDUCED UNCOMMANDED AND AN ENGINE FIRE WARNING ACTIVATED.  THE ENGINE WAS SHUTDOWN	 IN FLIGHT. SUBSEQUENT INSPECTION FOUND THE PROPELLER DIFFICULT TO ROTATE, EVIDENCE OF OVER-HEATING ON THE GAS GENERATOR	 CASE, AND A FRACTURED OIL TRANSFER TUBE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 	(TC NR 20061103006)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006121100354	20061211	00354	NE  	2006	12	11	CA061103007      	2	20060923	G	7250		TURBINE BLADES  			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								12439			(CAN) IN FLIGHT THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY FLAMES FROM THE EXHAUST AND VIBRATION.  THE ENGINE WAS SHUTD	OWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES.  MFG WILL INVESTIGATE THE INCIDENT A	ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103007)				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA				 
2006121100356	20061211	00356	NE  	2006	12	11	CA061103008      	2	20060902	G	7321	324485718	FUEL CONTROL    			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	FAULTY          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA			3144 								(CAN) THE ENGINE FLAMEOUT IN CLIMB AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE HYDROMECHANICAL FUEL CONTROL UN	IT WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103	008)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006121100357	20061211	00357	NE  	2006	12	11	CA061103009      	2	20061005	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       	 	NE  						FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								120100			(CAN) ON TAKEOFF ENGINE POWER REDUCED UNCOMMANDED FOLLOWED BY SMOKE IN THE CABIN AIR.  THE ENGINE WAS SHUTDOWN IN FLIGHT	 AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN 	THE ENGINE CASES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103009)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006121100358	20061211	00358	NE  	2006	12	11	CA061103010      	2	20061007	G	7321		FUEL CONTROL    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF ENGINE POWER INCREASED UNCOMMANDED AND THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT.  THE ENGINE WAS 	SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT C	AUSE ONCE DETERMINED. (TC NR 20061103010)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2006120500172	20061205	00172	EA  	2006	12	5	CA061103011      	1	20061102	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF343A      	30015	NE  					TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING  TAKE OFF FLAP FAIL DURING FLAP RETRACTION, A/C RETURN TO TERMINAL .BREAKER RESET AS PER OPERATING MANUAL N	R 1 ABNORMAL PROCEDURE SECTION 10 P 3-4. A/C RETURN TO SERVICE ,NO FURTHER SNAG.TWO MORE TAKE -OFF WERE CARRIED OUT FOLL	OWING THAT INCIDENT, NO SNAG.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006121100360	20061211	00360	NE  	2006	12	11	CA061103012      	2	20061012	G	7320	1240KDC0400	EEC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE FLAMED OUT ON DESCENT.  THE PROBLEM COULD NOT BE DUPLICATED ON THE GROUND AND THE EEC WAS SUBSEQUENTLY 	REPLACED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103012)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2006121100362	20061211	00362	NE  	2006	12	11	CA061103013      	2	20061005	G	7250		TURBINE BLADES  			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PS0469			(CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER.  TAKEOFF WAS ABORTED.  SUBSEQUENT 	INSPECTION REVEALED DAMAGED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE 	ONCE ESTABLISHED. (TC NR 20061103013)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007012600307	20070126	00307	SW  	2007	1	26	CA061103014      	1	20061030	G	2910	2781006025	HYDRAULIC LINE  			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT MLG WW	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYD FLUID LEAKING FROM LT WHEEL WELL.  WHEN LT GEAR DOORS WERE OPENED TO INSPECT, ENTIRE GEAR BAY WAS COVERED WITH	 FLUID.  AFTER CLEANING, REPLACING LINE AND PUTTING AIRCRAFT ON JACKS TO CHECK FOR FURTHER LEAKS ALL CHECKED WITHIN MANU	FACTURERS LIMITATIONS.  AIRCRAFT RETURNED OT SERVICE. (TC NR 20061103014)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2006120500299	20061205	00299	NE  	2006	12	5	CA061103015      	2	20061014	G	7250		TURBINE BLADES  			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) IN CRUISE THE ENGINE EXPERIENCED VIBRATIONS FOLLOWED BY A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSP	ECTION REVEALED FRACTURED TURBINE BLADES.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.	 (TC# 20061103015)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006120500214	20061205	00214	NE  	2006	12	5	CA061103016      	2	20061027	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								71397			(CAN) THE ENGINE FLAMED OUT IN FLIGHT FOLLOWING A COMMANDED REDUCTION IN POWER TO IDLE.  PWC WILL MONITOR INVESTIGATION 	OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061103016)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006120500196	20061205	00196	GL  	2006	12	5	CA061103017      	2	20061030	G	7240	23064570B	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847206			(CAN) COMBUSTION LINER FOUND CRACKED ON REMOVAL DURING TURBINE SECTION REPLACEMENT TO COMPLY WITH ROLLS ROYCE CEB A-72-6	060. THIS PART IS FOUND TO BE CRACKED ANY TIME IT IS REMOVED AFTER ANY LENGTH OF TIME IN SERVICE. MANUFACTURERS MAINTENA	NCE MANUAL ALLOWS NO CRACKS IN THIS AREA.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006120500198	20061205	00198	GL  	2006	12	5	CA061103018      	2	20061030	G	7240	23030911K	COMBUSTION CASE 			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847206			(CAN) CRACK ALONG LEFT SIDE "ARMPIT" WELD LINE FOUND DURING UNSCHEDULED TURBINE REMOVAL FOR CEB A-72-6060. NO CRACKS ALL	OWED IN THIS AREA.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006120500177	20061205	00177	EU  	2006	12	5	CA061104001      	1	20061101	G	5510	258TF4331	PLATE           			BRAERO	DH125 	BAE125800A  	1500285	EU  										HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6160 								(CAN) UPON VISUAL INSPECTION AND CLEANING OF ATTACHMENT LUG AREA OF VERTICAL FIN TO HORIZONTAL STABILIZER, MECHANIC NOTI	CED MATERIAL FLAKING OFF OF ONE BOLT HOLE. FURTHER INSPECTION REVEALED EXFOLIATION CORROSION. SINCE THIS TYPE OF CORROSI	ON IS DIFFICULT TO DETECT VISUALLY IT WAS ONLY WHEN THE MECHANIC WAS CLEANING THE AREA THAT HE NOTICED THE DAMAGE. UPON 	CONSULTATION WITH THE MANUFACTURER (RAYTHEON) THE CORROSION WAS REMOVED TO DETERMINE THE EXTENT OF PENETRATION AND COVER	AGE (PHOTO ILLUSTRATION) WHICH WAS DETERMINED TO BE OUT-OF-TOLERANCE AND REQUIRED REPLACEMENT OF THE REINFORCEMENT PLATE	. THIS DEFECT WAS THE FIRST TIME THE MANUFACTURER HAD COME ACROSS. ESPECIALLY SIGNIFICANT WAS THE FACT THAT IT WAS EXFOL	2	L	7	2 	4F			RT	A3EU    					 
2006121100363	20061211	00363	NE  	2006	12	11	CA061106001      	2	20060821	G	7210	311196801	SHAFT           			EMB   	120   	EMB120      	3260201	SO  	PWA   	PW118 	PW118B      	 	NE  						FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			26695								(CAN) THE ENGINE SUFFERED AN IN FLIGHT SHUTDOWN AS A RESULT OF A FRACTURED TOWER SHAFT. (TC NR 20061106001)						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2006120500258	20061205	00258	NE  	2006	12	5	CA061106002      	2	20061019	G	7261		ENGINE          			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  						LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA								123308			(CAN) THE AIRCRAFT LAVATORY SMOKE DETECTOR ACTIVATED SHORTLY AFTER TAKE OFF AND OIL SMELL BECAME EVIDENT IN THE CABIN.  	A SMALL EXTERNAL ENGINE OIL LEAK WAS SUBSEQUENTLY FOUND.  &WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONC	E ESTABLISHED. (TC# 20061106002)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2006120500297	20061205	00297	NE  	2006	12	5	CA061106003      	2	20061015	G	7200		ENGINE          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  						SHUTDOWN        	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED THREE INCIDNETS OF TORQUE FLUCTUATION RESULTING IN EITHER PROPELLER FE	ATHERING OR IN-FLIGHT SHUT-DOWN BETWEEN OCTOBER 15TH AND 17TH.  THE ENGINE FUEL SYSTEM COMPONENTS WERE SUBSEQUENTLY REMO	VED FOR INVESTIGATION.  P&WC WILL MONITOR THE INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20061106003)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006120500242	20061205	00242	NE  	2006	12	5	CA061106004      	2	20061025	G	7321	8236602	HYDROMECH UNIT  			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE FLAMED-OUT IN CRUISE AND THE AIRCRAFT DIVERTED FOR A SINGLE ENGINE LANDING.  THE HYDROMECHANIAL FUEL CO	NTROL UNIT WAS SUBSEQUENTLY REPLACED.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERM	INED. (TC# 20061106004)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2006120500298	20061205	00298	EA  	2006	12	5	CA061106005      	2	20061015	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								60244			(CAN) DURING GROUND RUNS FOLLOWING EXTENSIVE MAINTENANCE THE POWER SECTION ACCELERATED UNCOMMANDED.  POWER WAS REDUCED T	O IDE AND THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED.  ON SHUT DOWN SMOKE WAS SEEN EMINATING FROM THE EXHAUST.  SUBSE	QUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND RESULTANT ENGINE DAMAGE.  PWC WILL INVESTIGATE THE EVENT AN	D ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061106005)			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2006120500180	20061205	00180	NE  	2006	12	5	CA061106006      	2	20061101	G	7200		ENGINE          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  						FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								120983			(CAN) IN CRUISE THE ENGINE EMITTED A LOUD NOISE AND ENGINE ITT TEMPERATURE WAS SEEN TO INCREASE.  POST-FLIGHT INSPECTION	 FOUND THE PROPELLER COULD NOT BE ROTATED.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED	.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2006120500243	20061205	00243	NE  	2006	12	5	CA061106007      	2	20061024	G	7320	3035381	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUEL SYSTEM	FRACTURED       	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE POWER REDUCED TO IDLE UNCOMMANDED IN CRUISE.  AN EMERGENCY WAS DECLARED AND THE ENGINE WAS SHUT DOWN IN FLI	GHT.  SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL P3 AIR SUPPLY TUBE.  THE FRACTURE HAD OCCURRED IN THE WELD	 AREA AT THE TUBE "B" NUT. (TC# 20061106007)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500096	20061205	00096	EA  	2006	12	5	CA061106008      	1	20061103	G	2497	M2750010JB3U00	WIRE HARNESS    			CNDAIR	CL600 	CL600*      	       	EA  										ADG	SHORTED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7305 								(CAN) ADG DROPPED IN FLIGHT FOR TEST, NO POWER, LANDED NORMALLY. FOUND WIRING HARNESS AND WIRES BURNED & SHORTED AT CONN	ECTOR P1XC ON ADG. BOMBARDIER PSP603A WIRING MANUAL 24-25-01 FIG. 1 SHEET1. WIRING HARNESS AND CONNECTOR REPLACED.					2	L	7	2 	4F			RT	A21EA   					 
2006120500097	20061205	00097	EU  	2006	12	5	CA061106009      	1	20061103	G	2910	137311D1431	LINE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  										HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) L/H HYDRAULIC BRAKE LINE FOUND LEAKING FLUID. LEAK FOUND AT MYCARTA CLAMPING BLOCK. NEW LINE INSTALLED. (TC# 20061	106009)					2	L	7	2 	4T			RT	BA15CAA 					 
2007012600309	20070126	00309	EU  	2007	1	26	CA061106011      	1	20061102	G	3010	FAL1007	HOSE            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					LT SLAT	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			306  								(CAN) AFTER LANDING THE PILOTS NOTICED THAT THE LT IB SLAT HAD A SMALL TRACE OF ICE FORMED.  AFTER INSPECTION IT WAS FOU	ND THAT THE LT IB SLAT ANTI-ICE HOSE INNER WALL HAD COLLAPSED.  THE HOSE WAS REPLACED AND ALL OTHER SLAT ANTI-ICE HOSES 	WERE INSPECTED AND FOUND SERVICEABLE. (TC NR 20061106011)				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2006120500314	20061205	00314	GL  	2006	12	5	CA061106012      	3	20061013	G	6111	163356	SEAL            													MCAULY	D3A36	D3A36C410   	GL  	BLADE ROOTS	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			63   								(CAN) PROPELLER WAS FACTORY ASSEMBLE WITH INCORRECT BLADE SEALS ON ALL 3 BLADES. P/N 1633-56 SHOULD HAVE BEEN INSTALL BU	T SEALS FOR A NON-OIL FILLED HUB WERE FOUND INSTALLED INSTEAD. THIS WAS A WARRANTY REPAIR.															5	C	P47GL	 
2006120500212	20061205	00212	SW  	2006	12	5	CA061106014      	1	20061027	G	3230		LANDING GEAR    			BELL  	430   	430         	1182150	SW  											MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON APPROACH TO HELIPAD, LANDING GEAR DID NOT BE DEPLOYED. PILOT NOTICE AT THE LAST MOMENT AND ALMOST LANDED ON BEL	LY. ADD NO GREEN LIGHT NOR AUDIO WARNING. USE THE EMERGENCY GEAR RELEASE. LANDING UNEVENTFUL AFTERWARD. (TC# 20061106014	)				1	G	7	2 	3U			RT	H9SW    					 
2006120500252	20061205	00252	EA  	2006	12	5	CA061106015      	2	20061022	G	7230	3023779	DIFFUSER        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ENGINE	LOOSE           	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								86199			(CAN) SHORTLY AFTER LEVELLING OFF AT 17000 FEET, THE NR 2 ENGINE BEGAN TO SURGE AFFECTING ALL ENGINE PARAMETERS.  THE PO	WER WAS REDUCED TO ALLEVIATE THE RESULTING OVER TEMPERATURE CONDITION. AT POWER SETTING ABOVE 70% NG THE ITT WOULD FLUCT	UATE WILDLY TO OVER 900 DEGREES. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. AFTER TROUBLE	SHOOTING, THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE WAS SPLIT AND THE DIFFUSER TUBE AT 6 	O-CLOCK WAS FOUND LOOSE. THIS LOOSE DIFFUSER TUBE DISRUPTED THE AIRFLOW TO THE BLEED VALVE SENSE LINE, CAUSING THE BLEED	 VALVES TO MALFUNCTION AND THE ENGINE TO SURGE. THE ENGINE WAS SENT FOR REPAIR.	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006120500085	20061205	00085	CE  	2006	12	5	CA061106016      	1	20061104	G	2750	1015210579	SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			15902								(CAN) AFTER TWO MISSED APPROACHES, THE FLAPS WOULD NOT RETRACT FROM 17 DEGREES. AIRCRAFT DIVERTED, ON THE GROUND THE FLA	P ASYMETRICAL OVERRIDE SWITCH WAS USED AND FLAPS RETRACTED. THE FLAPS WHERE THEN DEFERRED UNTIL MAINTENANCE INPECTED SYS	TEM AND FOUND FAULTY ASYMETRICAL SWITCH. SWITCH WAS REPLACED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006120500086	20061205	00086	CE  	2006	12	5	CA061106017      	1	20061104	G	7931	1013890235	TRANSDUCER      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					OIL PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			9301 								(CAN) ON CLIMB NR 2 ENGINE DISPLAYED OIL PRESSURE FLUCTUATIONS FROM 120 TO 60 PSI. NO LOW OIL PRESSURE LIGHTS ILLUMINATE	D AND NO TORQUE FLUCUATIONS. THEY ELECTED TO RETURN TO AIRPORT. MAINTENANCE REPLACED THE R/H OIL PRESSURE TRANSDUCER AND	 AIRCRAFT WAS TESTED AND RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2006120500087	20061205	00087	EA  	2006	12	5	CA061106018      	2	20061103	G	7230	3035279	LINE            			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	P3 SENSE	BROKEN          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								PCE86509			(CAN) WHILE IN CRUISE THE NR 3 ENGINE ROLLED BACK TO 60% NG.. A PRECAUTIONARY SHUT DOWN OF THE ENGINE WAS COMPLETED AND 	THE AIRCRAFT RETURNED TO BASE. ON INSPECTION OF THE ENGINE IT WAS FOUND THAT THE P3 SENSE LINE, FROM THE GAS GENERATOR C	ASE TO THE P3 FILTER, WAS BROKEN, CAUSING THE ENGINE TO ROLL BACK TO IDLE. THE SENSE LINE WAS  POST P&WC S/B-4112. THIS 	S/B INTRODUCED A BRACKET TO HELP SUPPORT THE LINE AT THE GAS GENERATOR ATTACHMENT END. THE LINE WAS REPLACED WITH A SERV	ICEABLE PART, AN ENGINE RUN-UP WAS COMPLETED AND FOUND TO BE SERVICEABLE.		2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2006120500173	20061205	00173	EA  	2006	12	5	CA061107001      	1	20061102	G	2722	AL00102	ACTUATOR        			CNDAIR	CL600 	CL6002C10   	1390015	EA  										RUDDER TRIM	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			6372 								(CAN) DISC-RUDDER TRIM MOVING ON ITS OWN WITHOUT INPUT FROM COCKPIT CONTROLS. PULLED C/B 2F2 IAW AOM VOL 1. INDICATOR ST	ILL SHOWS UNCOMMANDED MOVEMENT AND PLANE STILL FLIES SIDEWAYS, FDR DOWLNLOAD WAS REQUESTED TO CONFIRM THE TRIM MOUVEMENT	. MAINTENANCE WAS UNABLE TO DUPLICATE.  THE RUDDER TRIM ACTUATOR WAS REPLACED IAW CRJ700 AMM 27-22-01 AND PERFORMED FUNC	TIONAL TEST OF THE RUDDER TRIM SYSTEM. FOUND SYSTEM WORKING PROPERLY AT THIS TIME IAW CRJ700 AMM 27-22-00.			2	L	7	2 	4F			RT	A21EA   					 
2006120500157	20061205	00157	EA  	2006	12	5	CA061107002      	1	20061103	G	7120	ASB1810617	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE MOUNT	UNSECURE        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) AFT ENGINE MOUNT THRUST FITTING ATTACHMENT BOLTS ARE NOT SECURED (TORQUE IS UNKNOWN AND LOCKWIRE IS NOT INSTALLED)	 AT RH ENGINE. TO COMPLETE THE PROCEDURE IAW AMM 71-22-01 ENGINE TO BE REMOVED. (TC# 20061107002)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500170	20061205	00170	NM  	2006	12	5	CA061107003      	1	20061102	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA				1262 							(CAN) DURING DECENT TO THE AIRPORT PILOTS OBSERVED LOSS OF NR 2 HYD PRESSURE AND NR 2 EDP CAUTION LIGHT. THE PTU WAS SEL	ECTED ON AND THE NR 2 HYD PRESSURE RECOVERED AND FLUID QUANTITY HAD DROPPED TO 40%. CREW ELECTED TO RETURN TO BASE. NON-	EMERGENCY LANDING AND AIRCRAFT TAXIED TO RAMP UNDER ITS OWN CONTROL.  NR 2 EDP HAD INTERNAL ROTATING GROUP FAILURE, EDP 	REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006120500171	20061205	00171	SW  	2006	12	5	CA061107004      	1	20061102	G	5210	AR835OXT4619	HANDLE          			BELL  	412   	412EP       	1182205	SW  										PAX DOOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2    								(CAN) UPON TEST FLIGHT RETURN TO BASE, IT WAS NOTICED THAT THE CO-PILOT OUTSIDE DOOR HANDLE WAS MISSING, SUSPECT IT WAS 	LOST IN FLIGHT. (TC# 20061107004)					1	G	7	2 	4U				H4SW    					 
2006120500083	20061205	00083	NM  	2006	12	5	CA061107005      	1	20061105	G	5610	NP15790112	WINDSHIELD      			DHAV  	DHC8  	DHC8301     	1386003	NM  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			20816								(CAN) DURING CLIMB OUT, ALTITUDE APPROX. FL70, THE CO-PILOT NOTICED A SMALL CRACK IN THE MIDDLE OF HIS WINDSHIELD, WHICH	 WAS GETTING RAPIDLY BIGGER. EMERGENCY CHECKLIST FOR CRACKED WINDSHIELD WAS PERFORMED. RELANDING WAS UNEVENTFUL. A/C HAN	DED OVER TO MAINTENANCE. CO-PILOT`S WINDSHIELD REPLACED.				2	H	7	2 	4T			RT	A13NM   					 
2007012600314	20070126	00314	NM  	2007	1	26	CA061107008      	1	20061101	G	3310	3280080	TRIM PANEL      			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	COCKPIT	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			6671 								(CAN) ENROUTE THE PILOT REPORTED A STRONG SMELL AND A FLASH OF LIGHT FROM CENTER CONSOLE AREA. THEY TURNED THE INTERIOR 	DOME LIGHT ON A CONFIRMED THAT A PLASTIC LIGHTING PANEL WAS MELTING ON THE RUDDER LIMITER AND STANDBY ELEVATOR BUTTONS. 	HE POKED THE SPOT WITH A PEN WHICH RESULTED IN FURTHER ARCING AND SMOKE. HE REQUESTED A LOWER ALTITUDE AND LANDED. MAINT	ENANCE WAS CONTACTED AND DISPATCHED TO THE AIRCRAFT. MAINTENANCE FOUND THE LIGHTING PANEL FOR THE TRIM HAD SHORTED. IT W	AS DISABLED AND THE INTERIOR LIGHTING TESTED WITH NO FURTHER PROBLEMS. THE ITEM WAS DEFERRED AND THE AIRCRAFT RETURNED T	O SERVICE.  THE PILOT REPORTED THAT THE CB DID NOT POP AND THAT HE HAD A HARD TIME IN LOCATING THE CORRECT CB TO ISOLATE	2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2006120500077	20061205	00077	EA  	2006	12	5	CA061107009      	2	20061106	G	7414		DISTRIBUTOR GEAR	CONT        		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			249  			E01HA137R					(CAN) DURING CRUISE FLIGHT, THE PILOT NOTICED A CHANGE IN ENGINE NOISE AND A SLIGHT YAW FOLLOWED BY THE LOW ROTOR HORN. 	PILOT DECREASED POWER WHICH RESULTED IN THE ROTOR RPM RECOVERING TO A NORMAL SETTING. THE PILOT FINISHED THE SHORT FLIGH	T AT A LOWER POWER SETTING AND LANDED THE AIRCRAFT WITHOUT FURTHER INCIDENT. AFTER LANDING, A MAGNETO CHECK WAS CONDUCTE	D WHICH RESULTED IN THE ENGINE QUITING WHEN THE R/H MAG WAS SELECTED. WHEN THE MAGNETO WAS REMOVED, A FEW TEETH WERE FOU	ND BROKEN OFF THE DISTRIBUTOR GEAR.		1	G	7	1 	3O	3	O		H11NM   	E295				 
2006120500160	20061205	00160	EA  	2006	12	5	CA061107011      	1	20061103	G	2130	92E204	CHECK VALVE     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PRESS BULKHEAD	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) THE CREW REPORTED THAT ON DESCENT THEY HAD PRESSURIZATION PROBLEMS. DURING THE DESCENT THEY GOT AUTO PRESS1 AND AU	TO PRESS 2 FAIL AND MASKS DEPLOYED AND WERE USED. ALSO LT PACK HAD A BLOWN DUCT. LH PACK AIR CONDITIONING DUCT P/N601R89	5211-113 REPLACED BOTH 4.5 BUKHEAD CHECK VALVES REPLACED. NR 1 FOUND WITH NO SPRING LEFT. SB A601R-21-054 PG. 2 OF 18 EV	IDENCE SECTION STATES: "AN AIRCRAFT WAS DEPRESSURIZED WHEN A FLAPPER ON THE BULKHEAD CHECK VALVE DETACHED AND AN AIR DUC	T UPSTREAM OF THE BULKHEAD CHECK VALVE IS DISCONNECTED". BOTH CONSITIONS WERE PRESENT. O2 GENERATORS WERE REPLACED, SB A	PPLIED AND TEST FLIGHT WAS CARRIED OUT. AIRCRAFT RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500074	20061205	00074	EU  	2006	12	5	CA061108001      	1	20061107	G	5340	350A35101700	MOUNT           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYDRAULIC PUMP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION IT WAS DISCOVERED THAT TWO OF THE FOUR RIVETS USED TO ATTACH THE BEARING SUPPORT TO T	HE PUMP MOUNT WERE BROKEN.  THE BEARING SUPPORT AND ATTACHING RIVETS ARE NOT LISTED IN THE AS350 ILLUSTRATED PARTS CATAL	OG, AS THEY ARE PART OF THE PUMP MOUNT.  THE PUMP MOUNT WILL BE REPLACED AND THE AIRCARFT RETURNED TO SERVICE. (TC# 2006	1108001)			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2006121100367	20061211	00367	SW  	2006	12	11	CA061108002      	1	20060929	G	7120	2060621021	MOUNT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					LT ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY INSPECTION PILOT NOTICED UNUSUAL PIECE OF METAL IN THE ENGINE BAY. INVESTIGATION REVEALED BROKEN LOWE	R LT ENGINE MOUNT. (TC NR 20061108002)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007012600315	20070126	00315	CE  	2007	1	26	CA061108003      	1	20060919	G	5320	5042002815	FLOOR SUPPORT   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLOOR SUPPORT ANGLE P/N UNKNOWN FOUND CRACKED. ANGLE IS PART OF BULKHEAD ASSY. P/N 50420028-15. ANGLE IS LOCATED U	NDER CENTRE FLOOR PANEL. (TC NR 20061108003)					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2007080800119	20070808	00119	CE  	2007	8	8	CA061108004      	1	20060828	G	5520	17121532	HINGE BRACKET   			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  	MCAULY	2D34C	B2D34C211   	GL  	RT STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT STABILIZER HINGE BRACKET FOUND CRACKED AT FASTENER LOCATION. (TC NR 20061108004)						1	H	7	1 	3O	3	O		A13CE   	E286	5	C	P7EA	 
2006121100371	20061211	00371	EU  	2006	12	11	CA061108005      	1	20060912	G	5753	137203B5761	BRACKET         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP SLAT BRACKETS CRACKED AT RADIUS. (TC NR 20061108005)						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2007012600318	20070126	00318		2007	1	26	CA061108006      	4	20061105	G	3497	KG102A	CONNECTOR       			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	REMOTE GYRO	CONTAMINATED    	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING TRAINING IN IMC CONDITIONS, ATC REPORTED TO STUDENT THAT HE WAS WAY OFF TRACK, PILOT CONFIRMED THAT HSI SYS	TEM HAD FAILED. AIRCRAFT RETURNED TO BASE WITH HELP FROM ATC WITH NO OTHER INCIDENCE. MAINTENANCE DUPLICATED DEFECT, HSI	 SYSTEM INSPECTED AND FOUND WATER ON CONNECTOR TO REMOTE GYRO. CONNECTOR DRIED AND CLEANED, OPS CHECKED SYSTEM OK. GYRO 	IS LOCATED IN NOSE COMPARTMENT. CLOSE OUT PANEL CAN LET IN SMALL AMOUNTS OF WATER IF PANEL IS NOT FIT  PROPERLY BEFORE T	IGHTENING THE SCREWS. THERE IS NO SEAL ON THIS PANEL. PANEL FIT AND INSTALLED CORRECTLY. (TC NR 20061108006)		1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2006120500194	20061205	00194	EU  	2006	12	5	CA061108008      	1	20061030	G	3230		DIODE           			BAG   	JETSTM	JETSTM3212  	1500217	EU  										MLG CONTROL	MELTED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DEFECT LANDING GEAR FAILED TO EXTEND. CIRCUIT BREAKER RESET AS PER QRH. GEAR LOWERED NORMALLY.  RECTIFICATION LAND	ING GEAR WARNING SYSTEM TROUBLESHOT. FOUND DIODE 1GA28(P/N IN4007) TO BE MELTED. ALSO FOUND CAPACITOR 1GA26(P/N 114-1915	2) TO BE UNSERVICEABLE. NEW CAPACITOR AND DIODE INSTALLED. GROUND TEST CARRIED OUT AND FOUND SERVICEABLE. REF. W/O 1612 	AND LOG PAGE 5037. DATE CLEARED OCTOBER 31, 2006. (TC# 20061108008)			2	L	7	2 	4T			RT	BA15CAA 					 
2007080800120	20070808	00120	CE  	2007	8	8	CA061109001      	1	20061108	G	5520	656530128	TUBE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPLIENCE WITH CAMPAIGN NOTICE 851-27-20-035 (RUDDER AND ELEVATOR CABLE GUARDS) BOTH ELEVATOR CABLE GUARDS	 WERE FOUND TO BE UNSERVICEABLE. ALL (4) CLAMPS WERE DISTORTED AND CAUSED DISTORSION TO THE TUBES WHEN CLAMPED CAUSING C	RACKS IN THE TUBES. BOTH ELEVATOR CABLE GUARD TUBES P/N 6565301-28 AND (4) CLAMPS P/N MS21919WD10 WERE REPLACE WITH NEW 	PARTS. THE RUDDER CABLE GUARDS WERE INSPECTED AND FOUND SERVICEABLE. (TC NR 20061109001)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007080800121	20070808	00121	CE  	2007	8	8	CA061109004      	1	20060922	G	5520	12430192	BRACKET         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	RT ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRACKET P/N 1243019-2 FOUND LOOSE AGAINST TORQUE TUBE P/N 1234650-2. LOOSE FASTENERS REMOVED AND REPLACED. (TC NR 	20061109004)					1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P21EA	 
2006121300074	20061213	00074	EU  	2006	12	13	CA061109005      	1	20060904	G	5753	137204B5167	BRACKET         			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						SDJ13614					(CAN) IB FLAP P/N 13760B463, SLAT BRACKETS P/N 137204B51 AND 137205B67 FOUND CRACKED AT BEND RADIUS. REMOVED AND REPLACE	D WITH NEW. (TC NR 20061109005)					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2008022000004	20080220	00004	SW  	2008	2	20	CA061109006      	1	20061109	G	5330		SKIN            			BELL  	206   	206L4       	1182110	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FUSELAGE	CRACKED         	W				O	K			OTHER                   	NONE                    			O			OTHER                     			IN	INSP/MAINT     	1			CA			4113 								(CAN) CRACK FOUND IN SKIN UNDER FWD BEARING OIL COOLER SUPPORT RT STA 192.00 BUTT 4.0.  REPAIR WAS MADE IAW BHT-206-SRM-	4-2 (TC NR 20061109006)					1	G	7	1 	3U	3	U	NC	H2SW    	E4CE				 
2006120500169	20061205	00169	NM  	2006	12	5	CA061109007      	1	20061102	G	3230	104071	JOURNAL         	MESSIER     		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			41530	21725		DCL2048797					(CAN) AIRCRAFT WAS POSITIONED ON GATE FOR NEXT FLIGHT. IT WAS THEN FOUND THAT RT MAIN LANDING GEAR PIN COULD NOT BE REMO	VED. TROUBLESHOOTING BY MAINTENANCE FOUND ON THE FOLLOWING ON THE RT MAIN LANDING GEAR STABILIZER STAY ASSEMBLY. THE AFT	 LINED JOURNAL BUSHING (ITEM 305) FOUND TO HAVE EXCESSIVE WEAR (1/16TH 3/32ND) CAUSING THE DOWN LOCK PIVOT POINT LOCK LI	NK ASSEMBLY (ITEM 280) TO OVERCENTER TOO FAR. THE STAY ASSEMBLY WAS REPLACED PER DHC 8 AMM 32-10-26, OPERATION AND LEAK 	CHECKS CARRIED OUT WITH NO FAULTS, AND THE AIRCRAFT RETURNED TO SERVICE. REFERENCE MESSIER-DOWTY COMPONENT MAINTENANCE M	ANUAL 32-10-04 FIG 1, PAGES 1010-1016.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500073	20061205	00073	EA  	2006	12	5	CA061109008      	2	20061107	G	8520	LW18729	PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			CA			1005 								(CAN) HIGH OIL TEMPERATURE AND BURNING ODOR IN CABIN PROMPTED RETURN TO AIRPORT. COMPRESSION CHECK REVEALED LOW COMPRESS	ION NR 3 CYLINDER, REMOVAL REVEALED A PORTION OF THE SECOND RING LAND APPROX. 1.5 INCHES LONG BROKEN OFF THE PISTON AT T	HE 10 O`CLOCK POSITION VEIWED FROM TOP.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2006121200082	20061212	00082	NM  	2006	12	12	CA061110002      	1	20060911	G	2530	DL561064	MOTOR           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 3 OVEN	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			9283 			990412511					(CAN) A OPERATOR MADE A UNSCHEDULED LANDING DUE TO HEAVY SMELL COMING FROM AFT GALLEY. INVESTIGATION SHOWED THAT THE BLO	WER MOTOR OF ONE GALLEY OVEN SHOWS BURN DAMAGE. OVEN REMOVED AND SENT FOR REPAIR. (TC NR 20061110002)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022000005	20080220	00005	SO  	2008	2	20	CA061110003      	1	20061109	G	3000	7961502	SHROUD          	PIPER       	7961502     	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	CABIN	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA			13564	13564							(CAN) PART FOUND DEFORMED ABD DISCOLORED AND HEAT BLISTERS. (TC NR 20061110003)						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2006120500167	20061205	00167	EU  	2006	12	5	CA061110005      	1	20061102	G	2612	37200000	FIRE DETECTOR   			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					APU BAY	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) APU EMERG SHUTDOWN ECAM FOLLOWED BY FIRE WARN AND MASTER CAUTION, APU SHUTDOWN VIA MASTER SWITCH, ECAM APU EMERG S	HUTDOWN MSG CONTINUED WITH FIRE WARN LIGHT. APU FIRE EXT BUTTON PUSHED, INDICATIONS REMAINED, FIRE BOTTLE DISCHARGED AS 	PRECAUTION. NO VISIBLE SIGNS OF FIRE OR SMOKE  NOTICED. FIRE WARN INDICATION REMAINED, AIRPORT FIRE DEPT CALLED AS PRECA	UTION.  PLEASE NOTE THAT MANUFACTURER IS L HOTELLIER, LOUIS AND DOES NOT EXIST ON DROP-DOWN LIST. (TC# 20061110005)			2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2008022000006	20080220	00006	WP  	2008	2	20	CA061110006      	1	20061109	G	5410	C04623	FRAME           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					NACELLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			333  								(CAN) DURING INSPECTION FOR SB NR 59, C046-23 FOUND BROKEN AT THE EAR AS DESCRIBED IN THE SB PART, ON ORDER FOR REPLACEM	ENT AND A KIT KI-185 TO PREVENT VIBRATION OF THE TUBE WILL BE INSTALLED. FRAME WILL BE SENT TO MFG FOR EVALUATION IAW TH	EIR REQUEST.  (TC NR 20061110006)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2006120500224	20061205	00224	WP  	2006	12	5	CA061110007      	2	20061026	G	7250	TFE73120BR	ENGINE          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P116549C			(CAN) DURING POST/PREFLIGHT INSPECTION MAINTENANCE PERSONNEL NOTICED NICKS ON 2 OF THE THE THIRD STAGE TURBINE BLADES.  	ENGINE HAS BEEN REMOVED AND SENT TO AN HEAVY MAINTENANCE FACILITY FOR INVESTIGATION AND REPAIR. A RENTAL ENGINE HAS BEEN	 INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE  (TC# 20061110007)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007012600323	20070126	00323	NE  	2007	1	26	CA061113001      	2	20061105	G	7200	PT6AD	ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  		MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											(CAN) .5 HRS AFTER A SCHEDULED REPLACEMENT OF THE NR 3 AND NR 4 BEARING ASSY AND THE NR 1 AND NR 2 POWER TURBINE DISC`S 	DUE TO CYCLE LIFE LIMIT BEING REACHED, THE ENGINE LOST OIL PRESSURE AND WAS SHUTDOWN AND AIRCRAFT RETURNED TO DEPARTURE 	FIELD WITHOUT FURTHER INCIDENT. AWAITING TEAR DOWN REPORT FOR ADDITIONAL DETAILS. (TC NR 20061113001)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006120500064	20061205	00064	EU  	2006	12	5	CA061114001      	3	20061113	G	6197	697070212	BUSS BAR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R4304	R4304*      	EU  	PROPELLER ASSY	CHAFED          	W				E				ENGINE SHUTDOWN         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NO.1 ENGINE SHUTDOWN MANUALLY IN FLT DUE PEC FAIL CAUTION AND PROP SPEED AT 1060 RPM. FAULT CODES LH CH A/B 160 AN	D 162. MAINT DISPATCHED TO T/S. FOUND BUSBAR FOR PROPELLER DEICE CHAFING ON MPU BRACKET, CAUSING MPU TO PICKUP SENS FROM	 BUSBAR. MPU ADJUSTED AND NEW BUSBAR INSTALLED.  ENGINE GROUND RUNS C/O NORMAL. (TC# 20061114001)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P890	 
2006120500072	20061205	00072	EU  	2006	12	5	CA061114003      	1	20061107	G	7830	32143304	SHUTOFF VALVE   			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					THRUST REVERSER	LEAKING         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA						AEX10603					(CAN) DURING TAKE OFF AT APPROXIMATELY 100 KNOTS NR 1 ENGINE THRUST REVERSER UNLOCKED LIGHT ILLUMINATED ACCOMPANIED WITH	 EAM MESSAGE NR 1 ENG REV UNLOCK. THE FLIGHT CREW REJECTED THE TAKE OFF ROLL, CYCLED THE REVERSER WITH NO FAULTS. CREW 	THEN ELECTED TO RETURN TO GATE. TO AVOID FURTHER DELAY, THE REVERSER WAS DEACTIVATED AND THE FLIGHT WAS DISPATCHED UNDER	 MEL. DURING TROUBLE SHOOTING FOUND THE PRESSURE REGULATING AND SHUT OFF VALVE BYPASSING. PRESSURE REGULATING/SHUT OFF V	ALVE REPLACED AND SYSTEM TESTED SERVICEABLE.		2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2007012600330	20070126	00330	CE  	2007	1	26	CA061114005      	1	20061110	G	2730	656530128	GUARD           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLYING WITH COMPANY CAMPAIGN NOTICE CN 851-27-20-035, BOTH ELEVATOR CABLE GAURDS WERE FOUND CRACKED ADJAS	ENT TO THE CLAMPS. THE TUBES WERE FOUND WITH .5 INCH LONGITUDINAL CRACKS. ADDITIONALLY ONE OF THE ATTACH CLAMPS WAS FOUN	D TO HAVE THE WRONG PN MS 21919WH10 INSTEAD OF MS 21919WDG10. MAINTENANCE ENTRIES WERE MADE WITH RESPECT TO THE WORK ACC	OMPLISHED IN THE CONDITION AND CORRECTION SHEET ASD MP-01-860-10-30-01. (TC NR 20061114005)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2006120500066	20061205	00066	EU  	2006	12	5	CA061114006      	1	20061112	G	2150		A/C PACK        			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					NR 2	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) IN CLIMB OUT ECAM WARNING MIN EQUIPMENT BAY SMOKE CAME ON WITH BURNING ODOR AND A SMALL AMOUNT OF SMOKE IN THE FLI	GHT DECK AND FWD CABIN. AIRCRAFT RETURNED TO THE STATION. MAINTENANCE INSPECTED THE MIN EQUIPMENT COMPARTMENT (NO FINDIN	G). DURING ECS COMPARTMENT INSPECTION FOUND A BOOT LEAKING ON NR 2 PACK HEAT EXCHANGER WITH A BURNING ODOR COMING OUT OF	 THE PACK. NR 2 ENGINE BLEED AND NR 2 PACK DEACTIVATED AND RELEASE UNDER MEL. GROUND RUN PERFORMED WITH NR 1 SYSTEM AND 	NO FURTHER WARNING AND BURNING ODOR. DURING INVESTIGATION THE BROKEN BOOT COUPLING WAS REPLACED ON NR 2 PACK. THE AIR-CO	OLING SYSTEM WAS CLEANED AS PER M/M AND NR 2 COALESCOR BAG WAS REPLACED. SYSTEM WAS  GROUND CHECKED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2007012600335	20070126	00335	SO  	2007	1	26	CA061114007      	1	20061110	G	7603	454253	THROTTLE CABLE  			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN)  RT ENGINE THROTTLE CABLE FAILURE:  DURING A ROUTINE FLIGHT, THE PILOT, ENROUTE , NOTED THAT THE RT ENGINE THROTTL	E CONTROL WAS STIFF ON APPROACH. THE AIRCRAFT EXPERIENCED A NORMAL LANDING, ONCE ON THE GROUND THE PILOT REPORTED THAT T	HE RT ENGINE WAS RUNNING AT IDLE AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. THE AIRCRAFT WAS TAXIED TO THE RAMP AND SH	UTDOWN.  THE RT ENGINE WAS INSPECTED, AND MAINTENANCE DETERMINED THE RT THROTTLE CABLE IN THE CABIN PEDESTAL HAD FAILED.	 THE THROTTLE CABLE WIRES HAD SEVERED APPROXIMATELY .2500 FROM THE SWAGED PORTION OF THE ROD END. UNFORTUNATELY ON A ROU	TINE INSPECTION THIS PORTION OF THE CABLE IS COVER BY THE CABLE SLEEVE AND CANNOT BE INSPECTED.   THE RT ENGINE THROTTLE	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2006120500185	20061205	00185	NM  	2006	12	5	CA061114008      	1	20061101	G	5610	58935734	WINDOW          			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			10744								(CAN) ON NOV. 1, 2006 A/C 216 EXPERIENCED A CRACKED NR 4 RT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT	 ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED.BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE REL	ATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTIO	N TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006120500219	20061205	00219	NM  	2006	12	5	CA061114009      	1	20061027	G	5610	58935733	WINDOW          			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			14236								(CAN) ON OCT. 27, 2006 A/C 201 EXPERIENCED A CRACKED NR 4 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOU	T ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED.  BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE 	RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OP	TION TO REPLACE THENR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.	  (TC# 20061114009)		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006120500191	20061205	00191	NM  	2006	12	5	CA061114010      	1	20061031	G	5610	58935733	WINDOW          			BOEING	737   	7377CG      	13844FA	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			14250								(CAN) ON OCT. 31, 2006 A/C 202 EXPERIENCED A CRACKED NR 4 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOU	T ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED. BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE R	ELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPT	ION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2006120500081	20061205	00081	NM  	2006	12	5	CA061114011      	1	20061106	G	5610	58935841	WINDOW          			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			13936								(CAN) ON NOV. 6, 2006 A/C 011 EXPERIENCED A CRACKED NR 5 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT	 ANY FURTHER EVENTS. THE NR 5 WINDOW WAS REPLACED.BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE REL	ATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTIO	N TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007012600341	20070126	00341	EA  	2007	1	26	CA061114012      	1	20061114	G	2612	2155101681	BRACKET         			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	FIRE WARNING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF PN 215-51016-816 RELAY BRACKET ASSY, (IPC 26-10-00 FIG 2 PAGE 4) 3 OF THE RELAY BASES (ITEM 3	5) WERE FOUND CRACKED. THE MOUNTING HARDWARE (ITEM 36) WAS INCORRECT FROM NEW, ACCORDING TO THE DIAGRAM AND INCOMPATIBLE	 WITH THE RELAYS, 4 OF ON THIS ASSY. 2 OTHER AIRCRAFT WERE INSPECTED  AND ONE RELAY BASE WAS FOUND CRACKED ON EACH OF TH	EM. THESE RELAYS ARE PART OF THE FIRE WARNING, LANDING GEAR INDICATION AND WATER DOOR SYSTEM. THE RELAY BASES WILL BE RE	PLACED WITH SERVICEABLE UNITS. WE WOULD LIKE TO SUGGEST OTHER OPERATORS INSPECT THESE RELAY BASES FOR CRACKS. (TC NR 200	61114012)	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2007012500118	20070125	00118	SO  	2007	1	25	CA061115001      	2	20061115	G	8500		UNKNOWN         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE	UNKNOWN         	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			138  								(CAN) REPORTED DEFECT, ON APPLICATION OF FULL POWER, ENGINE WOULD ALMOST CUT-OUT, THEN CATCH AND ACHIEVE FULL POWER. THE	 AIRCRAFT HAD PREVIOUSLY BEEN SNAGGED FOR QUITING SHORTLY AFTER LANDING, ON OCT. 17TH, AT WHICH TIME THE FUEL SYSTEM HAD	 BEEN INSPECTED, AND ADJUSTED IAW SID 97-3C AND RELEASED. THEREFORE MFG WAS CONTACTED AND ELECTED TO SEND A TECH REP TO 	OUR FACILITIES AND REPLACED MECHANICAL FUEL PUMP, THROTTLE BODY, FUEL MANIFOLD, WITH NEW UNITS. COMPLETE FUEL SYSTEM WAS	 FLUSHED AND FUEL INJECTOR NOZZLES CLEANED. FUEL SYSTEM SET UP IAW SID97-3C AND AIRCRAFT RELEASED. (TC NR 20061115001)		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2006121300075	20061213	00075		2006	12	13	CA061115002      	1	20060616	G	6120	8210263	CSD             								GARRTT	TFE731	TFE731*     	01518	WP  					PROPELLER	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) S/N 2479220  UNIT OVERHAULED AT MFG. UNIT WAS INSTALLED ON ENGINE IN A TEST CELL AND WAS RETURNED WITH TSO: 0.0 AN	D REPORTED SNAG OF RESET PRESSURE TOO LOW, PART REJECTED.  AFTER DISASSEMBLY AT OUR FACILITY IT WAS NOTICED THAT THE INT	ERNAL SHAFT ASSEMBLY WAS SCORING THE HOUSING, MAKING METAL AND PROGRESSING TOWARD SEIZURE AND POSSIBLE SHAFT SHEARING. A	LTHOUGH THE CAUSE HAS NOT BEEN DETERMINED, OIL STARVATION IS SUSPECTED.  UNIT HAS BEEN SENT TO (OEM) FOR A LABORATORY IN	VESTIGATION TO DETERMINE THE FAILURE ROOT CAUSE. RESULTS OF THE INVESTIGATION WILL FOLLOW.  (TC NR 20061115002)							4	F			E6WE				 
2006120500067	20061205	00067	EU  	2006	12	5	CA061115004      	1	20061112	G	3230	005LG005B	CONTROL UNIT    			AIRBUS	330   	A330243     	3930330	EU  										MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			16519								(CAN) DURING CLIMB, CREW RETRACTED THE LANDING GEAR AND THE LEFT HAND GEAR UNLOCK LIGHT REMAINED ILLUMINATED ALONG WITH 	ASSOCIATED ECAM NR 1 SYSTEM LT GEAR TRIANGLE AND INTERMITTENT NOSE GEAR UNLOCK LIGHT. THE FLIGHT CREW ELECTED TO DIVERT 	INTO A MAIN MAINTENANCE BASE FOR RECTIFICATION OF THE FAULT. RECTIFICATION; NR 1 LGCIU REPLACED.				2	L	7	2 	4F			RT	A46NM   					 
2006120500079	20061205	00079	WP  	2006	12	5	CA061115005      	2	20061106	G	7314	307085063	PUMP            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE FUEL	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			9218 								(CAN) AIRCRAFT WAS CLEARED FOR T/O.  POWER WAS ADVANCED TO 93.5% N1 ON BOTH ENGINES.  APPROXIMATELY 1 SECOND LATER LT EN	GINE FAILED.  T/O WAS REJECTED.  AME TROUBLESOT THE SNAG AND DISCOVERED THAT THE LT ENGINE FUEL PUMP PRESSURE WAS NOT WI	THIN ACCEPTABLE LIMITS.  FUEL PUMP AND FUEL CONTROL UNIT REPLACED.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007012500119	20070125	00119	SO  	2007	1	25	CA061115006      	1	20061114	G	5511	4653003	RIB             			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			407  								(CAN) DURING AN EVENT NR 1 INSPECTION THE LT HORIZONTAL STABILIZER OB RIB WAS FOUND CRACKED WHERE THE ELEVATOR OB HINGE 	ATTACH POINT IS.  THE RIB WAS REPLACED. (TC NR 20061115006)					1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2007012500121	20070125	00121	SW  	2007	1	25	CA061115007      	1	20061101	G	5330		SKIN            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14725								(CAN) DURING SCHEDULED MAINTENANCE, IN COMPLIANCE WITH CF-91-35 (CABIN ROOF BOXBEAM INSPECTION),  A CRACK WAS DISCOVERED	 IN THE BOXBEAM LOWER SKIN ORIGINATING FROM AN INSPECTION PANEL CUT-OUT RIVET HOLE.  THIS SKIN WAS CRACKED ACROSS THE RI	VET HOLE ABOUT 1.25 INCHES IN EACH DIRECTION. (TC NR 20061115007)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120500071	20061205	00071	EA  	2006	12	5	CA061116001      	1	20061109	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			11003								(CAN) AIRPLANE DIVERTED FOUND:  RT SIDE-WINDOW CRACKED. RT SIDE WINDOW REMOVED ACC.AMM.  RT SIDEWINDOW INSTALLED ACC AMM	 56-12-01-400-801.  CABIN PRESS TEST PERF,. OK					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500078	20061205	00078	EA  	2006	12	5	CA061116002      	1	20061106	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											(CAN) NOTIFED BY SOC (OPERATIONS) THAT AIRCRAFT WAS DIVERTING TO IND DUE TO CAPT FWD WINDSHIELD CRACKED AT 39,000 FEET O	N OUTER PLY. C/A - RAR CAPT W/S IAW CRJ 700 AMM 56-11-01 OPS CHECK LEAK CHECK GOOD.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2006120500057	20061205	00057	EA  	2006	12	5	CA061116003      	1	20061116	G	5712	600911545	BULKHEAD        			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF343A      	30015	NE  					BS 559	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BULKHEAD STRUCTURE AT STATION 559.00 CRACKED ON TWO AILERON MIXER  (P/N 600-91154-5)  ATTACHMENTS BOLTS. A/C HOURS	:25688 A/C CYCLES:30488					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500069	20061205	00069	EU  	2006	12	5	CA061116004      	1	20061110	G	2497		CABLE           			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	DC GENERATOR	ARCED           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) ON START UP THE NR 2 STARTER GENERATOR `PLUS` CABLE ARCED THROUGH A FEW INCHES FROM THE CONNECTION AT THE STARTER.	THE CABLE WAS COMPLETELY SEVERED AND THE ADJACENT CONDUCTORS WERE DAMAGED. THE NR 2 GENERATOR, AFFECTED CONDUCTORS AND T	HE INVERTER WERE REPLACED AND THE AIRCRAFT RETURNED TO BASE WHERE ADDITION ASSESSMENT IS ON GOING.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006120500062	20061205	00062	NM  	2006	12	5	CA061116005      	1	20061113	G	7540	8209074	SWITCH          			BOMBDR	DHC8  	DHC8402     	1390042	NM  										RT NACELLE	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			135  	135  							(CAN) BLEED HOT CAUTION NR 2 CAME ON. CDS INTEREGATION FAULT CODE 1701. RIGHT BLEED OVERTEMPERATURE SWITCH FLAGGED. REPL	ACE SWITCH.  SERIAL NUMBER 0781.					2	H	7	2 	4T			RT	A13NM   					 
2007012500124	20070125	00124	CE  	2007	1	25	CA061116006      	1	20061116	G	5330	1014302051	SKIN            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BS 251	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABIN BOTTOM SKIN FOUND CRACKED ADJACENT TO ROTATING BEACON DOME MOUNTING. REPAIR DRAWING REQUESTED. (TC NR 200611	16006)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007012500127	20070125	00127	SW  	2007	1	25	CA061117001      	1	20061103	G	7334	2060615357	TRANSDUCER      			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					FUEL PRESSURE	READS LOW       	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) UNDER READING FUEL PRESSURE. REMOVED AND INSTALLED REPLACEMENT PRESSURE TRANSDUCER PN BSE 206-30G SN2617-1-251 (TC	 NR 20061117001)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008030600273	20080306	00273	SO  	2008	3	6	CA061117002      	2	20060921	G	8560	4707829003R	CONTROLLER      			CESSNA	206   	TU206A      	2073318	CE  	CONT  	O520  	TSIO520C    	17040	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	OIL PRESSURE	FAILED          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				1350 							(CAN) ERRATIC MANIFOLD PRESSURE DUE TO CONTROLLER FAILURE TO REGULATE OIL PRESSURE FROM WASTEGATE (TC NR 20061117002)						1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P25EA	 
2007080800122	20070808	00122	CE  	2007	8	8	CA061117003      	1	20061116	G	5753	8005T20062	DOUBLER         			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF34C	3AF34C*     	GL  	TE FLAP	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			1324 								(CAN) DURING A ROUTINE INSPECTION, DISCOVERED LT AND RT WING RIBS AT STA 117.48 TO BE CONFLICTING WITH THE RIB AT SIMILA	R LOCATION WHEN FLAPS ARE RETRACTED.  AFTER INSPECTION, FOUND THAT THE SPOILER DOUBLER INSTALLED IN 1995 WAS THE WRONG D	IMENSION ALLOWING WING RIB TO BE POSITIONED INCORRECTLY.   ON FURTHER INVESTIGATION FOUND THE TEMPLATE NR 8005T AND THE 	INSTALLATION INSTRUCTIONS NR SP8000 SUPPLIED WITH THE STC SA4948NM TO BE CONTRADICTING EACH OTHER IN RESPECT TO THE NEW 	LOCATION OF THE WING RIB.  IF ONE OF THE FLAPS BECAME INOPERATIVE DUE TO THE FACT THAT THE RIBS HOOKED ON EACH OTHER. (T	C NR 20061117003)	1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
2006120500084	20061205	00084	EA  	2006	12	5	CA061117004      	2	20061104	G	8530	SL36006WA1	CYLINDER HEAD   			BEECH 	95    	95          	1153402	CE  	LYC   	O360  	IO360B1B    	41514	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1989 								(CAN) DURING A ROUTINE 100 HOUR INSPECTION A CRACK WAS FOUND ON THE RH ENGINE #4 CYLINDER STARTING AT THE TOP SPARK PLUG	 HOLE AND CONTINUING DOWN TO THE EXHAUST PORT. THE CYLINDER WAS REMOVED AND REPLACED. (TC# 20061117004)					1	L	7	2 	3O	3	O		3A16    	1E10				 
2006120500082	20061205	00082	NM  	2006	12	5	CA061117005      	1	20061106	G	3220	69601002	SUPPORT         			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ON WALK AROUND AFTER LANDING FOUND CENTER SUPPORT ASSY OF GRAVEL DEFLECTOR CRACKED.  CENTER SUPPORT ASSY CRACK REP	AIRED.  ASSEMBLY SUPPORT FITTING P/N69-60100-2 REPLACED AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006120500063	20061205	00063	EA  	2006	12	5	CA061117006      	1	20061113	G	4990	38004882	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						OVERSERVICED    	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		DE	DESCENT        	1			CA			17877	17877							(CAN) APPROXIMATELY 10 MINUTES FROM DESTINATION, AIRCRAFT DECLARED AN EMERGENCY DUE TO SMOKE IN THE LAVATORY. AIRCRAFT W	AS DESCENDING THROUGH 5,000 FT WHEN THE BLEEDS WERE SWITCHED FROM ENGINES TO APU. WITHIN A SHORT PERIOD OF TIME A BURNT 	OIL SMELL WAS OBSERVED IN THE CABIN, AND THE LAV SMOKE DETECTOR WAS GOING OFF. THE CREW ALSO RECEIVED A "TOILET SMOKE" C	AUTION MESSAGE. CREW REQUESTED EMERGENCY SERVICES BE ALERTED FOR ARRIVAL. SHORTLY THEREAFTER THE SMOKE INDICATION WENT O	UT. FLIGHT LANDED SAFELY. MAINTENANCE INVESTIGATED AND FOUND THE APU OVER SERVICED. EXCESS OIL WAS DRAINED TO AN ACCEPTA	BLE LEVEL, AND LT & RT COALESCER BAGS P/N 753689-3 REPLACED IN ACCORDANCE WITH THE AMM 21-51. AIRCRAFT WAS THEN RUN ON A	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007080800123	20070808	00123	EU  	2007	8	8	CA061117007      	1	20061102	G	8011	A2042C	PDU             			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	LT START RELAY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							340A019				(CAN) WHEN GROUND POWER WAS ATTACHED TO THE AIRCRAFT THE LT ENGINE BEGAN AN UNCOMMANDED START SEQUENCE.  THE FAULT WAS T	RACED TO THE LT STARTER RELAY CONTACTS LOCATED IN THE LT POWER DISTRIBUTION UNIT (PDU).  THE PDU WAS REPLACED AND THE AI	RCRAFT OPERATED NORMALLY. (TC NR 20061117007)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2006120500055	20061205	00055	NE  	2006	12	5	CA061118001      	2	20061117	G	7230		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1	BIRD INGESTION  	W				A				UNSCHED LANDING         				C	E	J	F.O.D.                    	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) AFTER GEAR-UP SELECTION THE AIRCRAFT ENCOUNTERED A VIBRATION, FELT THROUGHOUT ENTIRE PLANE,THAT WOULD INCRESE/DECR	EASE WITH THROTTLE MOVEMENT. AIRCRAFT RETURNED TO THE ORIGINATING DEPARTURE STATION AND LANDED SAFELY. MAINTENANCE FOUND	 NR 1 ENGINE FAN BLADES DAMAGED & BIRD REMAINS ON OIL COOLER, DUE TO A LARGE BIRD INGESTION.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500129	20070125	00129	SW  	2007	1	25	CA061120001      	1	20061104	G	7333	205061635005	SWITCH          			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					FUEL FLOW	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) REMOVED LT FUEL FLOW SWITCH DUE TO LEAKING. INSTALLED FUEL FLOW SWITCH PN 205-061-635-005 SN 9607 (TC NR 200611200	01).					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007012500131	20070125	00131	SO  	2007	1	25	CA061120002      	2	20060930	G	7323	5038901029	GOVERNOR        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			1121 								(CAN) SNAS: ENGINE GOVERNOR CONTROL NO RESPONSE. FOUND LT GOVERNOR CABLE END, SEPARATE FROM CRIMPED END FILET ATTACHED T	O ROD END. (TC NR 20061120002)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2007012500132	20070125	00132	SO  	2007	1	25	CA061120003      	1	20061115	G	2700	62701153	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	STABILATOR	SEVERED         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LOSS OF EFFECTIVE ELEVATOR CONTROL DURING ROUTINE TRAINING FLIGHT. AIRCRAFT RETURNED TO BASE WITH S	TABILATOR CONTROL MANAGED MAINLY BY STABILATOR TRIM SYSTEM. AIRCRAFT LANDED SAFELY.  INITIAL INSPECTION OF STABILATOR SY	STEM CONFIRMED LIMITED RESPONSE TO CONTROL YOKE MOVEMENT.  FURTHER INSPECTION OF CABLES REVEALED THAT THE SWAGED END OF 	THE AFT LOWER CABLE WAS BROKEN AND SYSTEM WAS HELD TOGETHER BY TURNBUCKLE SAFETY LOCK WIRE. AFFECTED CABLE HAS BEEN REMO	VED FOR FURTHER INSPECTION AND REPLACEMENT.  CABLE DEFECT LOCATED BETWEEN FUSELAGE STA: 156.00 AND 191.00. PART TOTAL TI	ME IS UNKNOWN.  AIRCRAFT TOTAL TIME IS 6593.3 HRS. (TC NR 20061120003)	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006120500037	20061205	00037	NE  	2006	12	5	CA061120005      	2	20061119	G	7230	4114T15P02	FAN BLADE       			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF348E5     	30015	NE  					ENGINE	BENT            	W				O				OTHER                   				C			F.O.D.                    			AP	APPROACH       	1			CA			4477 	182  				194301			(CAN) ON APPROACH CREW SAW LARGE WHITE BIRD , FELT AND HEARD THUMP ON LEFT SIDE OF AIRCRAFT. MAINTENANCE INSPECTION FOUN	D #1 ENGINE INLET BYPASS FAN BLADES POSITIONS 1 THRU 5 DAMAGED AND BENT. BORESCOPE OF ENGINE COMPRESSOR FOUND NO OTHER D	AMAGE. AIRCRAFT WILL BE RETURNED TO SERVICE AFTER BLADE REPLACEMENT AND SATISFACTORY GROUND RUNS. (TC# 20061120005)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008012400321	20080124	00321	SW  	2008	1	24	CA061120006      	1	20061120	G	2720	41621L	RUDDER PEDAL    			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  	SNSNCH	74D	74DM        	EA  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1739 								(CAN) DURING REPLACEMENT OF THE FUEL SHUTOFF VALVE THE LT FRONT RUDDER/BRAKE PEDAL WAS FOUND CRACKED BETWEEN THE BRAKE P	EDAL UPRIGHT AND THE OB PEDAL HINGE. THE DEFECT APPEARS TO BE CAUSED BY BRAKING FORCES APPLIED BY THE FLIGHT INSTRUCTOR 	IN THE REAR SEAT, THE LINK ROD AND BELLCRANK ON THE FRONT PEDAL TWIST THE PEDAL TO ACTUATE THE MASTER CYLINDERS, LOCATED	 FORWARD OF THE FRONT PEDALS. THE TWISTING BENDS AND CRACKS THE PEDAL.     THIS IS THE OLD-STYLE PEDAL. THE NEWER STYLE 	IS PLATE-SHAPED RATHER THAN TEE-SHAPED AND SHOULD BE MORE RESISTANT TO THE TWISTING FORCES. (TC NR 20061120006)		1	H	7	1 	3O	3	O	NC	A759    	E274	5	N	P88614	 
2007012500133	20070125	00133	EU  	2007	1	25	CA061120007      	1	20061117	G	6310	350A35105901	COUPLING        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					M/R DRIVESHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 1000 HR INSPECTION DISC COUPLING FOUND CRACKED.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2006120500056	20061205	00056	NE  	2006	12	5	CA061120008      	3	20061117	G	6111	78229911	SPACER          	HAMSTD      		AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	PROPELLER	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER BLADE INSPECTED AND FOUND TIGHT IN HUB. INVESTIGATION REVEALED PROP BLADE SPACER HAD FAILED. PROP BLADE 	REMOVED AND NEW SPACER INSTALLED. PROP BLADE REINSTALLED AND GROUND RUN CHECKED SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2006120500039	20061205	00039	NE  	2006	12	5	CA061120009      	2	20061118	G	7230	652244143	DUCT            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D9       	52048	NE  					13TH STAGE SADDL	RUPTURED        	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ENROUTE TO DESTINATION, #2 ENGINE FIRE WARNING. CHECKLIST ACCOMPLISHED, ENGINE SHUTDOWN.  13TH STAGE SADDLE DUCT F	OUND RUPTURED, REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC# 20061120009)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006120500035	20061205	00035	NE  	2006	12	5	CA061121001      	2	20061119	G	7200		ENGINE          			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					NR 2	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA			25945	4946 				690285			(CAN) AFTER TAKE OFF AND DURING LEVEL AT 40,000 FT CREW GOT ECAM MESSAGE MIN EQUIPMENT SMOKE  WITH OVERHEAD WITH OVERHEA	D LIGHT ON AND ODOR IN THE CABIN AND COCKPIT. CREW DECIDED TO RETURN BACK TO THE AIRPORT. QRH PROCEDURES WERE FOLLOWED. 	BOROSCOPE CARRIED OUT ON BOTH ENGINES. FOUND EVIDENCE OF OIL IN NR 2 ENGINE COMPRESSOR. NR 2 ENGINE REPLACED.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2007012500135	20070125	00135	SW  	2007	1	25	CA061121002      	1	20060826	G	6320	206040156101	MAGNETIC SEAL   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R GEARBOX	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)  MAIN ROTOR GEARBOX MAGNETIC SEAL HAS EXCESSIVE LEAKAGE FROM MAIN INPUT SEAL. (TC NR 20061121002)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120500032	20061205	00032	NM  	2006	12	5	CA061121003      	1	20061120	G	5720	82920010255	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	WING	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT ZONAL INSPECTION 263 AND 264, BOTH WING ROOT DRAIN LINES WERE FOUND BLOCKED AT THE BELLY DRAINS	. THE ACCUMULATED WATER IN THE DRAIN LINE IN TURN FROZE AND SPLIT THE DRAIN LINE CAUSING PRESSURIZATION LEAK AND WATER A	ND SKYDROL TO LEAK IN THE BELLY. (TC# 20061121003)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500031	20061205	00031	SW  	2006	12	5	CA061122001      	1	20061120	G	8120	4709549001	WASTEGATE VALVE 			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  						FAILED          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				2124 							(CAN) WHEN THE PILOTS APPLIED MAX POWER FOR TAKE-OFF THE LH ENGINE WOULD ONLY PRODUCE 30 INCHES M.P.  THE TAKE-OFF WAS S	TOPPED AND THE AIRCRAFT RETURNED TO CHALKS. AFTER FOUND NO FAULTS. THE TURBO WHEEL WAS ABLE TO TURN FREELY. THE WASTE GA	TE WAS CHANGED OUT. REMOVED S/N WC-60101 AND INSTALLED S/N ML0144. THE AIRCRAFT WAS GROUND RUN AND THE MANIFOLD PRESSURE	 WAS AT MAX 44 INCHES AS REQUIRED. SYSTEMS CHECKED SERVICEABLE. (TC# 20061122001)			1	L	7	2 	3O	3	O		A12SW   	E14EA				 
2007012500136	20070125	00136	SW  	2007	1	25	CA061122002      	1	20061103	G	2435	03600923	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STARTER GEN	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			167  	167  		13955					(CAN) CUSTOMER REPORTED BEARING FAILURE ON MAIN SHAFT OF STARTER/GENERATOR.  BEARING CAGE CAME APART.  UPON INSPECTION. 	 IT WAS FOUND THE BEARING CAGE WAS NON-EXISTANT.  WE CONTACTED OUR SUPPLIER. (TC NR 20061122002)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007012500142	20070125	00142	SO  	2007	1	25	CA061122003      	1	20061121	G	3097	2937102	TERMINAL        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DE ICE SYSTEM	BURNED          	W				O				OTHER                   				L			NO TEST                   			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED PROP AND ENGINE INLET BOOTS DE-ICE SYSTEM U/S ON LT ENGINE. SYSTEM HAS BEEN INSPECTED. FOUND NO POW	ER FROM CB TO MAIN POWER RELAY. PLATE ASSEMBLY CIRCUIT PROTECTOR FORWARD MOUNTING LT REMOVED AND DISCOVERED THAT WIRE FR	OM CB BURNED OUT AT TERMINAL CONNECTION DUE OVERHEAT OF TERMINAL. OVERHEATING OF TERMINAL APPEARED TO BE DUE CORROSION O	F TERMINAL AND LOST OF CONDUCTIVITY THAT INCREASE THE RESISTANCE AND GENERATE ADDITIONAL HEAT. (TC NR 20061122003)			1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2006120500028	20061205	00028	NE  	2006	12	5	CA061122004      	2	20061122	G	7250		GAS GENERATOR   								PWA   	120   	PW123D      	52152	NE  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SEE REPORT ATTACHED REGARDING SMOKE IN THE EXHAUST DURING ENGINE SHUTDOWN.  ENGINE S/N AG0060 DISASSEMBLY OF ENGIN	E REVEALED LARGE AMOUNT OF COKED OIL IN THE TURBINE SUPPORT CASE (NR 5 BEARING VENT TUBE AREA), WHICH IS TYPICALLY INDIC	ATIVE OF CRACKS IN THE NR 5 BEARING SUPPORT AREA OF THE GAS GENERATOR CASE. OIL FROM THESE CRACKS CONTAMINATED THE P3 AI	R SYSTEM. (TC# 20061122004)								4	T			E20NE				 
2007012500144	20070125	00144	SO  	2007	1	25	CA061122006      	1	20061106	G	3211	67042013	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8804 								(CAN) AT INSPECTION NOTICED CRACK RIGHT THROUGH TRUNNION ASSY 67042-013.						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2006120500068	20061205	00068		2006	12	5	CA061122007      	4	20061111	G	3421	5040002902	INDICATOR       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DEPARTING THE CAPT`S HORIZON FAILED DURING TAKE-OFF. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT.	 MAINTENANCE REPLACED THE GYRO AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC# 20061122007)					2	L	7	2 	3T	4	T		A24EU   	A196				 
2006120500030	20061205	00030	EA  	2006	12	5	CA061122008      	1	20061121	G	2750	NA	FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	JAMMED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA			10727	10727							(CAN) DURING MISSED APPROACH WHEN FLAP RETRACTION SELECTED, FLAPS REMAINED AT FULL 45DEG EXTENSION. CREW RECEIVED FLAP F	AIL MESSAGE. DUE TO WEATHER CONDITIONS AIRCRAFT DIVERTED TO ALTERNATE AIRPORT WITH FLAPS REMAINING EXTENDED AT 45DEG. IN	-FLIGHT FLAP RE-SET PROCEDURE CARRIED OUT WITH NO SATISFACTORY RESULT. AIRCRAFT LANDED NORMALLY AT ALTERNATE AIRPORT. AF	TER ARRIVAL ON GROUND AIRCRAFT ELECTRICAL POWERED DOWN AND THEN RE-POWERED. FLAP SYSTEM FUNCTIONED NORMALLY. AIRCRAFT PO	SITIONED TO MAINTENANCE BASE FOR FURTHER INVESTIGATION. (TC# 20061122008)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007080800124	20070808	00124	EA  	2007	8	8	CA061123001      	1	20061123	G	2497	21551226808	WIRE            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	DC POWER SYS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DC OVERHEAD PANEL WIRES CHAFING ON AIRCRAFT STRUCTURE.  (TC NR 20061123001)						2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2006120500023	20061205	00023	NE  	2006	12	5	CA061123002      	2	20061123	G	7200	PW121	ENGINE          								PWA   	PW121 	PW121       	52124	NE  						MAKING METAL    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)  METAL CONTAMINATION OF TURBOMACHINE OIL SYSTEMS DETECTED VIA TREND MONITORING ANALYSIS.											4	T			E20NE				 
2006120500024	20061205	00024	EA  	2006	12	5	CA061123003      	2	20061123	G	7230		IMPELLER        								PWA   	PT6   	PT6A50      	52043	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) "IMPACT DAMAGE AND A CRACKED IMPELLER". A CRACK IN THE OUTER IMPELLER WAS FOUND.   (TC# 20061123003)											4	T			E4EA				 
2008030600278	20080306	00278	EA  	2008	3	6	CA061123005      	2	20061121	G	7322	055211313	FLAPPER VALVE   	CESSNA      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CARB HEAT BOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			705  	705  							(CAN) DURING PROGRESSIVE CARE OPERATION NR 2, INSP OF THE CARBURETOR HEAT BOX (P/N 05521644) REVEALED THAT THE 2 ALUMINU	M RIVETS THAT HOLD THE FLAPPER DOOR TO THE ACTUATOR SHAFT WERE VERY CLOSE TO SHEARING OFF. IF THE ALUMINUM RIVETS DID SH	EAR, AND THE AC WAS FLYING IN CARBURETOR ICING CONDITIONS, ENGINE FAILURE COULD OCCUR. THERE IS ALSO THE CONCERN OF PIEC	ES OF RIVETS BEING INGESTED INTO THE ENGINE. THE CARB AIR BOX WAS PURCHASED NEW FROM MFG, INSTALLED 16 MONTHS AGO AND IN	 SERVICE ON THIS ENGINE FOR 704.7 HRS. NOT SO LONG AGO, MFG USED STEEL RIVETS INSTEAD OF ALUMINUM. THIS DID NOT SEEM TO 	BE A PROBLEM IN THE PAST WITH STEEL RIVETS. (TC NR 20061123005)	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082000028	20070820	00028	CE  	2007	8	20	CA061123006      	1	20061120	G	5420	085150047	CAP             			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK NOTED AT LT NACELLE CANTED BULKHEAD CAP.  CAP REPAIRED. (TC NR 20061123006)						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2006120500027	20061205	00027	EA  	2006	12	5	CA061123008      	1	20061122	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			7288 								(CAN) RH WINDSHIELD CRACK WHILE IN CRUISE. (TC# 20061123008)						2	L	7	2 	4F			RT	A21EA   					 
2006120500025	20061205	00025	EA  	2006	12	5	CA061124001      	2	20061123	G	7230		COMPRESSOR      								PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENGINE TEARDOWN RELATED TO AN IFSD AND A POSSIBLE COMPRESSOR FAILURE.  TEARDOWN NOT YET CONCLUSIVE. IT WAS NOT A C	OMPRESSOR FAILURE BUT APPEARS TO BE FAILURE OF ONE OR MORE CT BLADES AND THEN CAUSED A STRUCTURAL FAILURE OF THE GAS GEN	ERATOR CASE, WHICH THEN RESULTED IN COMPRESSOR DAMAGE.  COMPRESSOR ROTOR WAS LOCKED UP BUT THE PT ROTOR WAS FREE TO ROTO	ATE. IT APPEARS TO BE UNECONOMICAL TO REPAIR THIS ENGINE. (TC# 20061124001)								4	T			E4EA				 
2006120500026	20061205	00026	EU  	2006	12	5	CA061124002      	3	20061123	G	6197	697070212	BUSS BAR        		R408        	BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R4304	R4304*      	EU  	NR 1 PROP	SHORTED         	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				10   		NA					(CAN) NO.1 ENGINE SHUTDOWN DURING FLIGHT DUE PEC FAIL CAUTION LIGHT AND PROP SPEED AT 1060 RPM. FAULT CODES LH CH A/B 16	0 AND 162. MAYDAY CALLED AND A NORMAL LANDING PERFORMED. PAX DEBRIEFED DURING TAXING AND AFTER PARKING. MAINTENANCE DISP	ATCHED TO TROUBLE SHOOT. NOTE PROP ASSY ONLY INSTALLED LAST WEEK. TECHNICIAN FOUND PROP HEATER BUSBAR ASSEMBLY CHAFED BY	 NO.1 PROP MPU BRACKET. BUSBAR REPLACED AND BUSBAR/PICK-UP CLEARANCE CHECKED OK. ENGINE RUN, PROP RPM AND PROP DE-ICE CH	ECKED OK. (TC# 20061124002)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P890	 
2007082000029	20070820	00029	EA  	2007	8	20	CA061124003      	1	20061123	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			11151	11151							(CAN) DURING APPROACH UPON INITIAL FLAP DOWN SELECTION, FLAP FAILED TO MOVE AND CREW RECEIVED (FLAP FAIL) MESSAGE ON EIA	CS. APPROACH CONTINUED AND NORMAL FLAPLESS LANDING CARRIED OUT. MAINTENANCE INSPECTION CARRIED OUT, NO EVIDENCE OF TWIST	ING, SKEWING OR DEFORMATIONS NOTED. FECU (FLAP ELECTRONIC CONTROL UNIT) CIRCUIT BREAKERS CYCLED IAW RE-SET PROCEDURE AND	 FLAPS FUNCTION CHECKED NORMAL OPERATIONS. (TC NR 20061124003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007082000030	20070820	00030	SW  	2007	8	20	CA061124005      	1	20061121	G	5753	2736041001	CHANNEL         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19186								(CAN) DURING OVERHAUL OF THE RT FLAP ASSY, THE CENTER HINGE CHANNEL WAS REMOVED FOR REPLACEMENT AND WAS FOUND CRACKED BE	TWEEN (2) RIVET HOLES. THE CHANNEL HAS BEEN REPLACED.   (TC NR 20061124005)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2006120500020	20061205	00020	CE  	2006	12	5	CA061124006      	1	20061124	G	3060		BOOT            	MCAULY      	B3D36C432   	CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	PROPELLER DE-ICE	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			294  			030476					(CAN) DURING PHASE NR 2 INSPECTION IT WAS NOTED ON PRE-INSPECTION RUNUP THAT THE PROP DE-ICE WAS INOPERATIVE. INVESTIGAT	ION REVEALED THAT 2 OF THE 3 DE-ICE BOOT LEADS WERE DEFECTIVE. NEW PARTS ORDERED.					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P58GL	 
2007013100102	20070131	00102	SW  	2007	1	31	CA061124007      	1	20061124	G	5531	410009505	SPAR CAP        			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN LT HAND SPAR CAP 1.5 IN. FROM BOTTOM. (TC NR 20061124007)						1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
2007082000031	20070820	00031	CE  	2007	8	20	CA061124008      	1	20061124	G	3210	0541121497	SUPPORT         			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18284								(CAN) AIRCRAFT BEING SERVICED FOR MFG CARE NR 4 (200-HOUR) INSPECTION AND CHANGED OVER TO SKIS.  LT OB SUPPORT FOR LANDI	NG GEAR WAS FOUND TO HAVE SEVERAL CRACKS.  PART WAS REPLACED WITH NEW.   AIRCRAFT IS OPERATED AS FLOATPLANE AND SKIPLANE	 FOR FLIGHT TRAINING. (TC NR 20061124008)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2006120500029	20061205	00029	NM  	2006	12	5	CA061124009      	1	20061121	G	5610	58935734	WINDOW          			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13516								(CAN) ON NOV. 22, 2006 A/C 208 DURING INSPECTION OF THE NR 5 RT EYEBROW WINDOW IT WAS NOTED THAT THE NR 4 RT EYEBROW WIN	DOW WAS DELAMINATED BEYOND LIMITS. THE AIRCRAFT WAS REMOVED FROM SERVICE AND THE NR 4 RT EYEBROW WINDOW WAS REPLACED. BO	EING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED S	ERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL 	PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007012500147	20070125	00147	SW  	2007	1	25	CA061124010      	1	20061120	G	6320	204040353023	CASE            	BELL        		BELL  	205   	205A1       	1181414	SW  										TRANSMISSION	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			10966	1520 		ABT364					(CAN) CRACKING AT INPUT QUILL BOSS OF MAIN ROTOR TRANSMISSION. (TC NR 20061124010)						1	G	7	1 	4U				H1SW    					 
2007012500148	20070125	00148	SW  	2007	1	25	CA061124011      	1	20061114	G	7810	23008052	COLLECTOR       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1278 				CAT28028			(CAN) DURING ENGINE MAINTENANCE, THE HORIZONTAL FIRESHIELD WAS REMOVED AND (2) CRACKS WERE NOTED AT THE 5 O`CLOCK AND 7 	O`CLOCK POSTION IN THE EXHAUST COLLECTOR.   TURBINE REMOVED REPAIRED RE-INSTALLED. (TC NR 20061124011)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007012500150	20070125	00150	CE  	2007	1	25	CA061127001      	1	20061123	G	3230	MC815AS1	CONTROLLER      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLIGHT CREW REPORTED LANDING GEAR WOULD NOT RETRACT AFTER TAKE-OFF. AFTER TROUBLESHOOTING THE MOTOR CONTROLLER WAS	 FOUND UNSERVICEABLE.  MOTOR CONTROLLER WAS REPLACED, GEAR SWINGS COMPLETED AND THE AIRCRAFT RETURNED TO SERVICE. THIS U	NIT HAD 928 LANDINGS SINCE OVERHAUL; INSPECTION REQUIREMENTS ARE 8000 LANDING OVERHAUL AND 1000 LANDING POINT CHECK.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2007012500152	20070125	00152	CE  	2007	1	25	CA061127002      	1	20061126	G	3260		UNKNOWN         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	UNKNOWN         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED, DURING CLIMB THE LANDING GEAR RED UNSAFE LIGHT ILLUMINATED. GEAR WAS CYCLED AND LIGHT WOULD NOT	 EXTINGUISH. GEAR WAS SELECTED DOWN AND (3) GREEN ILLUMINATED WITH NO RED HANDLE. CREW ELECTED TO RETURN TO MAINTENANCE.	  MAINTENANCE INSPECTED AND SWUNG GEAR WITHOUT FAULT.  AIRCRAFT OPERATING WITHOUT FURTHER INSTANCE. WEATHER EXTREMELY CO	LD ON DAY OF OCCURRENCE. (TC NR 20061127002)			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006120500021	20061205	00021	EA  	2006	12	5	CA061127003      	1	20061123	G	5712	600102211	RIB             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT WING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IN LEFT HAND WING TANK INBOARD BAY, STEAL BRAIDED FUEL LINE PART NUMBER 00624-AE7013343N0220 WAS FOUND CHAFING ON 	THE WING RIB STIFFENER PART NUMBER 600-10221-1. CHAFING OCCURRED APPROXIMATELY 9 1/2 INCHES FROM BOTTOM OF TANK. DAMAGE 	EXTENDS OVER AN AREA OF APPROXIMATELY 3/4 OF AN INCH WITH THE MAIN DAMAGE COVERING APPROXIMATELY 5/8 OF AN INCH INSIDE T	HE 3/4 INCH AREA. SEE ATTACHED PHOTOS. DAMAGE IS TAPERED FROM 0 INCHES TO APPROXIMATELY 0.120 INCHES AREA HAS NOT YET BE	EN DRESSED SO FINAL DEPTH MEASUREMENTS ARE NOT AVAILABLE.   (TC# 20061127003)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008020100098	20080201	00098	SW  	2008	2	1	CA061128001      	1	20061124	G	2810	206063688001	LINE            			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FUEL SYSTEM	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA											(CAN) DURING A SCHEDULED FLIGHT, FUEL FUMES WERE DETECTED IN REAR CABIN AREA. A/C RETURNED TO BASE WITH NO PROBLEMS NOTE	D. A/C INSPECTED AND FWD FUEL TANK VENT LINE FOUND WEEPING WHEN REAR TANK WAS FILLED TO CAPACITY. LINE REMOVED AND REPLA	CED. LINE INPECTED AND FOUND TO BE ORIGINAL FROM DATE OF A/C MFG 1975. RECOMMEND REPLACEMENT DATE OF FLEX HOSE BE ADDED 	TO MM. (TC NR 20061128001)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120500022	20061205	00022		2006	12	5	CA061128002      	4	20061123	G	3421	ASN43	INDICATOR       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					NR 1 HORIZON	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA				1459 							(CAN) DURING DEPARTURE THE CAPTAINS HORIZON FAILED ON CLIMB OUT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FUR	THER PROBLEM. MAINTENANACE REPLACED THE NO1. GYRO AND THE AIRCARFT WAS RETURNED TO SERVICE. (TC# 20061128002)					2	L	7	2 	3T	4	T		A24EU   	A196				 
2007012500153	20070125	00153	CE  	2007	1	25	CA061128003      	1	20061116	G	5712	20062	RIB             			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF34C	3AF34C*     	GL  	RT WING	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA			1324 								(CAN) DURING A ROUTINE INSPECTION DISCOVERED LT AND RT WING RIBS AT STATION 117.48 TO BE CONFLICTING WITH THE FLAP RIB A	T SIMILAR LOCATION WHEN FLAPS ARE RETRACTED.  AFTER INSPECTION FOUND THAT THE SPOILER DOUBLER INSTALLED IN 1995 WAS THE 	WRONG DIMENSION ALLOWING WING RIB TO BE POSITIONED INCORRECTLY.  UPON FARTHER INVESTIGATION FOUND THE TEMPLATE NR 8005T 	AND THE INSTALLATION INSTRUCTIONS NR SP8000 SUPPLIED WITH THE STC SA4948NM TO BE CONTRADICTING EACH OTHER IN RESPECT TO 	THE NEW LOCATION OF THE WING RIB. THIS COULD BE VERY SERIOUS, IF ONE OF THE FLAPS BECAME INOPERATIVE DUE TO THE FACT THA	T THE RIBS HOOKED ON EACH OTHER. (TC NR 20061128003)	1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
2008021900102	20080219	00102	SW  	2008	2	19	CA061128004      	1	20061117	G	5320	206031202015	SUPPORT         	BELL        	206031200   	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14060								(CAN) STRAP PN 206-031-200-076 WAS FOUND CRACKED AT INSPECTION.  WHEN IT WAS REMOVED, SUPPORT PN 206-031-202-015 WAS ALS	O FOUND CRACKED. BOTH WERE REPLACED IAW MFG INSTRUCTIONS. (TC NR 20061128004)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2006120500059	20061205	00059	EA  	2006	12	5	CA061128005      	2	20061115	G	7230		COMPRESSOR      			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					NR 2 ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			12099	7187 							(CAN) ON POWER APPLICATION FOR TAKEOFF, THE #2 ENGINE ACCELERATED NORMALLY TO TAKEOFF POWER.  AS THE AIRCRAFT BEGAN TO C	LIMB ONTO THE STEP, THE F/O OBSERVED A FLASH OF LIGHT AND HEARD A BANG FROM THE ENGINE.  THE TAKEOFF WAS REFECTED AND TH	E AIRCRAFT RETURNED TO THE DOCK.  THE ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  INVESTIGATION REVEA	LED THAT THE COMPRESSOR SECTION OF THE ENGINE HAD FAILED.  RESULTS OF THE TEARDOWN WILL BE FORTHCOMING.  THIS ENGINE HAS	 BEEN OPERATING "ON CONDITION"  SINCE PURCHASE IN 2002. (TC# 20061128005)		1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2008021900114	20080219	00114	CE  	2008	2	19	CA061128008      	1	20061120	G	2432	40576	BATTERY         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	MAIN	THERMAL RUNAWAY 	W				H				DEACTIVATE SYST/CIRCUITS				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			3112 	55   							(CAN) WHILE CONNECTED TO A GPU, DURING ROUTINE MAINTENANCE, THE TECHNICIANS NOTED SMOKE IN THE AREA OF THE BATTERY BOX C	OMPARTMENT. THE GPU WAS IMMEDIATELY DISCONNECTED, BATTERY POWER TURNED OFF AND THE BATTERY DISCONNECTED FROM THE AIRCRAF	T BY REMOVAL OF THE ALCON CONNECTOR AT THE BATTERY. THE BATTERY HAD OVERHEATED AND WENT INTO A THERMAL RUNAWAY CONDITION	. THE BATTERY WAS REPLACED AS WELL AND THE BATTERY CHARGE MONITORING PRINTED CIRCUIT CARD. (TC NR 20061128008)			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008021900120	20080219	00120	EA  	2008	2	19	CA061129003      	1	20061124	G	2710	N025	MASTER LINK     			FOUND 	FBA   	FBA2C       	3640102	EA  										AILERON CONTROL	DEFECTIVE       	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			31   								(CAN) DURING FIGHT ID 2C3-30 THE MASTER LINK (N025) FELL OFF THE COPILOTS AILERON CHAIN CAUSING A LOSS OF AILERON CONTR	OL FROM THE COPILOTS SIDE. THE FLIGHT TEST ENGINEER WAS ABLE TO COLLECT ALL THE PIECES FROM THE MASTER LINK DURING THE 	FLIGHT HOLD AND THE CHAIN FROM JAMMING THE AILERON CONTROL FOR THE REST OF THE FLIGHT. THE PILOT WAS ABLE TO FLY AND LAN	D THE AC SAFELY WITHOUT USING THE AILERONS. THE AC IS AN EXPERIMENTAL AC IN A FLIGHT TEST PROGRAM, THIS MODEL USES THE S	AME AILERON CONTROL SYS AS THE 2C1 AND 2C2 MODELS. BEING THE MFG WE HAVE INITIATED A MATERIAL REVIEW AND WILL BE ISSUING	 A SB.  (TC NR 20061129003)	1	H	7	1 	3O				A7EA    					 
2006120500004	20061205	00004		2006	12	5	CA061129004      	4	20061129	G	2210		CLAMP           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					BRIDLE CABLE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS DEFECT WAS ORIGINALLY IDENTIFIED IN THE SUBJECT AIRCRAFT FLIGHT LOG DATED OCTOBER 26, 2006.SUBSEQUENT INVESTI	GATION BY OUR QUALITY ASSURANCE DEPARTMENT GENERATED THE REQUEST THAT A SDR BE FILED. THE AIRCRAFT ARRIVED IN OTTAWA FOR	 A SCHEDULED INSPECTION WITH A REPORTED AUTO-PILOT SNAG. " AUTO-PILOT U/S - SOMETIMES WON`T ENGAGE, WHEN IT DOES - IT YA	WS & BANKS". ON SUBSEQUENT GROUND TESTING THE "BRIDAL CABLES" TO THE RUDDER SERVO-MOTOR WERE FOUND TO BE COMPLETELY WITH	OUT TENSION. THE INSTALLATION WAS INSPECTED AND IT WAS DETERMINED THAT EVEN THOUGH THE BRIDLE CABLE TO RUDDER CABLE CLAM	PS WERE INSTALLED AND TORQUED CORRECTLY THE WITNESS MARKS WERE NOT VISIBLE. IT IS BELIEVED THAT THE CLAMP SLIPPED ON THE	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2007012500154	20070125	00154	CE  	2007	1	25	CA061129005      	1	20061129	G	2820	050011849	LINE            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	FUEL RETURN	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			2810 								(CAN) A FUEL LEAK WAS NOTED ON THE AIRCRAFT.  UPON INSPECTION THE FUEL LINE BETWEEN THE FCU AND FUEL RESERVOIR WAS FOUND	 WORN.  THE NOSE WHEEL STEERING ROD HAD BEEN RUBBING INTO THE LINE, AND WORN A GROOVE DEEP ENOUGH TO ALLOW FUEL TO LEAK.	  THE FUEL LINE IS ALUMINIUM, AND THE STEERING ROD IS STEEL.  NO DAMAGE WAS NOTED ON THE STEERING ROD.  (2) OF THESE TYP	E OF AIRCRAFT ARE OPERATED, AND THE SECOND WILL BE INSPECTED FOR THE SAME TYPE OF PROBLEM. (TC NR 20061129005)			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2006120500005	20061205	00005	EA  	2006	12	5	CA061129006      	1	20061129	G	3220	AW24VDU	BEARING         			CNDAIR	CL215 	CL2151A10   	1900320	EA  										LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT FOLDING STRUT LOWER BEARING CRACKED AT 4 PLACES.						2	H	7	2 	4R			RT	A14EA   					 
2006120500019	20061205	00019	NM  	2006	12	5	CA061130001      	1	20061124	G	2740	3994001013	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					PITCH TRIM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) PITCH TRIM CAUTION LIGHT AND AUTO TRIM FAIL MESSAGE APPEARED DURING CLIMB.  AIRCRAFT RETURNED TO BASE. WIRING CHEC	KS CARRIED OUT BETWEEN THE FCECU AND PITCH TRIM ACTUATOR. (FCECU CODES 67, 63, E7 AND E3) ACTUATOR REPLACED. (TC# 200611	30001)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2006120500070	20061205	00070	CE  	2006	12	5	CA061130002      	1	20061109	G	5740	122005311	ATTACH BRACKET  			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8544 								(CAN) AILERON ATTACH BRACKET CRACKED ON RADIUS LWR LT INBD FWD. PART REMOVED AND REPLACED WITH NEW P/N 1220053-17, ALL O	THER BRACKETS CHECKED NO CRACKS FOUND.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2006121200097	20061212	00097	EU  	2006	12	12	CA061130003      	1	20061001	G	2613	51533172	ELEMENT         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F26 	NE  	OVERTEMP	CHAFED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CL	CLIMB          	1			CA			45559								(CAN) AIRCRAFT RETURNED TO BASE SHORTLY AFTER DEPARTURE DUE TO A NR 2 BLEED AIR LEAK LIGHT ILLUMINATION DURING CLIMB OUT	. THE BLEED AIR WAS SELECTED OFF BUT THE LIGHT REMAINED ILLUMINATED. IAW THE REQUIRED PROCEDURES THE ENGINE WAS SHUTDOWN	 AND THE AIRCRAFT LANDED UNEVENTFUL. INSPECTION OF THE AIRCRAFT BY MAINTENANCE DETERMINED THAT THE WARNING LIGHT WAS A F	ALSE INDICATION CAUSED BY A CHAFED BLEED AIR SENSE LINE IN THE AFT RT WING TRAILING EDGE. THE AFFECTED SENSE LINE WAS RE	PLACED. AN ADDITIONAL INSPECTION OF THIS AREA HAS BEEN ISSUED FOR COMPLETION ON THE ADJACENT SIDE OF THIS AIRCRAFT AS WE	LL AS A PLANNING CARD TO INSPECT THE SECOND AIRCRAFT IN THE FLEET.     (TC NR 20061130003)	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2007012500155	20070125	00155	EA  	2007	1	25	CA061130004      	1	20061128	G	3234		RELEASE CABLE   			CNDAIR	CL600 	CL6002B19   	1900309	EA  										MLG LEVER	DISLODGED       	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING OF OPERATIONAL TEST OF THE LANDING GEAR MANUAL RELEASE SYSTEM THE NLG HAS NOT BEEN EXTENDED.AFTER INVESTIGA	TION FOUND THAT NLG RELEASE CABLE IS OUT OF PULLEY INSTALLED INSIDE OF THE LEVER P/N 600-85015-29. SEVERAL DAYS LATER IN	SPECTING ANOTHER AIRCRAFT.  A SIMILAR SNAG HAS BEEN DETECTED. BOTH CABLES WERE REINSTALLED AND ADJUSTED IAW AMM,OPERATIO	NAL TEST CARRIED OUT AND FOUND SERVICEABLE. SEE ATTACHMENTS: LEVER AFFECTED IS ITEM NR 225 AND PULLEY IS ITEM NR 155.			2	L	7	2 	4F			RT	A21EA   					 
2007012600346	20070126	00346	NM  	2007	1	26	CA061130005      	1	20061126	G	4920	APS2000	APU             			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					APU BAY	DAMAGED         	W				K				NONE                    				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			19477	82   							(CAN) MFG WAS GETTING READY TO DEPART. ON ATTEMPTING TO START THE APU, THE FAULT LIGHT CAME ON AND THE APU FAILED TO STA	RT.  THE ITEM WAS DEFERRED TO (MEL) MINIMUM EQUIPMENT LIST AND THE FLIGHT CONTINUED TO ITS DESTINATION.  ON INVESTIGATIO	N THERE WAS CONSIDERABLE DAMAGE TO THE GEARBOX AND STARTER SHAFT.  THIS UNIT WAS REMOVED FOR A SIMILAR PROBLEM 82 HOURS 	PREVIOUSLY AND HAD BEEN OVERHAULED.  ONCE A TEARDOWN REPORT IS RECEIVED, A FOLLOW UP WILL BE SUBMITTED. (TC NR 200611300	05)		2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2006120500016	20061205	00016	EA  	2006	12	5	CA061130006      	1	20061128	G	2913	6619003	PUMP            			CNDAIR	CL600 	CL600*      	       	EA  										HYDRAULIC SYS	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			3569 								(CAN) DURING CRUISE, THE NR 1 HYDRAULIC SYSTEM WAS DEPLETING AND WAS DOWN TO 20% OF CAPACITY. NO ASSOCIATED EICAS MESSAG	E. AIRCRAFT WAS DIVERTED TO MAINTENANCE BASE.LEAK WAS FOUND AT NR 1 HYDRAULIC PUMP. PUMP WAS REPLACED. AIRCRAFT GROUND R	UNS CARRIED OUT, SYSTEM REPLENISHED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2006120500002	20061205	00002	EA  	2006	12	5	CA061201001      	1	20061201	G	2710	21592315122	CONTROL CABLE   			CNDAIR	CL215 	CL2151A10   	1900320	EA  										AILERONS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			151  								(CAN) LT AILERON CONTROL CABLE WORNED IN FAIRLEAD, ACCESS  PANEL 740-2 (RT SIDE). CABLE NEEDS REPLACEMENT. THIS CABLE HA	S BEEN REPLACED ON 2005-11-22 AND CUMULATED 151 HOURS FLYING TIME.					2	H	7	2 	4R			RT	A14EA   					 
2008021900122	20080219	00122	EA  	2008	2	19	CA061201002      	1	20061129	G	5541	33700K5	SPAR            	SCWZER      	33700K3     	SCWZER	SG2   	SGS233A     	8051606	EA  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3891 								(CAN) DURING THE COMPANY 12 YEAR STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), A CRACK WAS FOUND IN ON RUDDER SPAR ON	 THE OUTER LT EDGE OF THE UPPER HINGE ATTACH POINT. LPI INSPECTION WAS USED TO VERIFY THE CRACK (TC NR 20061201002)					1	K	0	0 	  				G2EA    					 
2008021900125	20080219	00125	EA  	2008	2	19	CA061201003      	1	20061129	G	5541	33700K5	SPAR            	SCWZER      	33700K3     	SCWZER	SG2   	SGS233A     	8051606	EA  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4138 								(CAN) DURING THE COMPANY 12 YEAR STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), A CRACK WAS FOUND ON THE RUDDER SPAR O	N THE OUTER LT EDGE OF THE UPPER HINGE ATTACH POINT. (TC NR 20061201003)					1	K	0	0 	  				G2EA    					 
2008021900128	20080219	00128	SW  	2008	2	19	CA061201004      	1	20061124	G	2810	714931L	TANK            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	WING	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			2504 								(CAN) AIRCRAFT HAD RETURNED TO MAINTENANCE FACILITY FOR WINTER STORAGE. FUEL STAINS WERE NOTICED ON THE BOTTOM OF THE WI	NG NEAR THE TRAILING EDGE. LT IB TANK WAS REMOVED AND A 1.5 INCH CRACKED WAS FOUND ON THE RADIUS OF THE LATERAL RE-ENFOR	CEMENT INDENT OF TANK. (TC NR20061201004)				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2007012600349	20070126	00349	EA  	2007	1	26	CA061201006      	1	20061104	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					WING	MALFUNCTIONED   	W				K				NONE                    				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4750 	4750 							(CAN) DURING APPROACH WHEN FLAPS SELECTED TO 45 DEG , FLAPS REMAINED AT 30DEG AND (FLAP FAIL) MESSAGE ON EICAS, CONTINUE	D APPROACH AND NORMAL LANDING WITH FLAPS AT 30 DEG EXTENSION.  MAINTENANCE CLEANED AND LUBRICATED FLAP DRIVE SHAFTS, FLA	P ACTUATORS GREASED/PURGED. NO WATER INDICATIONS NOTED. FLAPS CYCLED NUMEROUS TIMES, NORMAL OPERATION AIRCRAFT RETURNED 	TO SERVICE. (TC NR 20061201006)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012600354	20070126	00354	EA  	2007	1	26	CA061201007      	1	20061101	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					WING	MALFUNCTIONED   	W				K				NONE                    				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4760 	4760 							(CAN) DURING APPROACH FLAPS 20DEG SELECTED AND FLAPS AT 20DEG, WHEN 30DEG SELECTED FLAPS REMAINED AT 20DEG. NORMAL LANDI	NG WITH FLAPS AT 20DEG. MAINTENANCE UNABLE TO DUPLICATE FAULT ON GROUND. AIRCRAFT FERRIED TO MAINTENANCE BASE. MAINTENAN	CE CARRIED OUT TORQUE CHECK OF FLAP DRIVE, NO FAULTS FOUND. OPERATIONAL TEST OF FLAPS CARRIED OUT WITH NO FAULTS FOUND. 	(TC NR 20061201007)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006120500018	20061205	00018	NM  	2006	12	5	CA061204001      	1	20061128	G	5610	NP15790213	WINDOW          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			32287								(CAN) DURING CRUISE, THE PILOT`S SIDE WINDOW OUTER PANE SHATTERED. AN UNEVENTFUL LANDING WAS CONDUCTED. ENGINEERING INSP	ECTED THE AIRCRAFT AFTER LANDING AND FOUND THE SIDE WINDOW OUTER PANE HAD SHATTERED.  THE SIDE WINDOW ASSEMBLY WAS REPLA	CED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20061204001)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2006120500003	20061205	00003	EA  	2006	12	5	CA061204002      	1	20061130	G	3320	336710	BALLAST         			DHAV  	DHC3  	DHC3        	2800202	EA  										CABIN LIGHTS	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA			91   								(CAN) ON POWER UP OF AIRCRAFT, CABIN LIGHT BALLASTS FAIL. THIS AIRCRAFT HAS HAD 10 BALLAST UNITS 3367-10 REPLACED. (TC# 	20061204002)					1	H	7	1 	3R				A815    					 
2007012600357	20070126	00357	WP  	2007	1	26	CA061204003      	2	20061204	G	7200	TPE33112UHR	ENGINE          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  		MAKING METAL    	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE MAINTENANCE, IT WAS NOTICED THAT THE ENGINE OIL FILTER BYPASS PIN HAD POPPED. THE OIL FILTER WAS REM	OVED AND INSPECTED. METAL CONTAMINATION WAS FOUND AND A SOAP SAMPLE WAS TAKEN. (TC NR 20061204003)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007012600360	20070126	00360	EU  	2007	1	26	CA061204004      	1	20061128	G	2161	9599020135	CONTROL VALVE   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN TEMP	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			13094	13094							(CAN) AIRCRAFT WAS ON CLIMBOUT GOING THROUGH 6000 FEET WHEN ECS LIGHT CAME ON AND CABIN STARTED TO DE-PRESSURIZE. AIRCRA	FT RETURNED TO RANKIN INLET WHERE MAINTENANCE DISCOVERED THAT TCA VALVE WAS STUCK IN THE FULL OPEN POSITION AND EXCESS H	EAT TRIPPED THE SYSTEM OFF. TCA VALVE WAS REPLACED AND ECS SYSTEM CHECKED OK. (TC NR 20061204004)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007012600364	20070126	00364	EA  	2007	1	26	CA061204005      	1	20061201	G	3244	362K821	TIRE            			CNDAIR	CL600 	CL600*      	       	EA  										NR 3	SEPARATED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) NR 3 TIRE HAS THROWN A TREAD. CREW INSPECTED FLAP/ GEAR FOR DAMAGE, NO DAMAGE FOUND JUST RUBBER TRANSFER.   SUSPEC	T IT HAPPENED ON ARRIVAL LAST NIGHT. BUT NOT DISCOVERED UNTIL IN THE AM. (TC NR 20061204005)					2	L	7	2 	4F			RT	A21EA   					 
2007012600370	20070126	00370	NE  	2007	1	26	CA061204006      	2	20061204	G	7230		BLADES          								PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8000 	4100 							(CAN) SEE REPORT ATTACHED  CRACK INDICATIONS WERE FOUND ON THE CT BLADES AT OVERHAUL. CRACKS WERE FATIGUE RELATED ON ALL	 THE CT BLADES. HOWEVER, THE ATTACHED REPORT STATES THAT THE CT BLADES DID NOT FAIL IN CREEP AS DETAILED IN MFG SILS, DU	E TO OVERTEMP OR EXCEEDING ENGINE LIMITATIONS. FAILURE APPEARS TO BE DUE TO FLAP MODE VIBRATIONS.  PLEASE REFER TO ATTAC	HED ENGINEERING REPORT FOR DETAILS. (TC NR 20061204006)								3	T			E4EA				 
2007012900142	20070129	00142	NM  	2007	1	29	CA061204007      	1	20061201	G	2910	MS219134	O-RING          	PARKERHANFIN	9451693     	DHAV  	DHC8  	DHC8*       	       	NM  										HYDRAULIC SYS	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			16   	16   		0841					(CAN) WHILE ON APPROACH AT 10,000 FEET CREW NOTICED NR 2 HYD QTY WAS LOW.  SHORTLY AFTER THAT THE NR 2 HYD ISO VLV CAUTI	ON LIGHT CAME ON.  ALTERNATE LANDING GEAR EXTENSION CARRIED OUT.  FOUND THE O-RING FOR THE NR 4 PLUG-BLANKING ON THE NR 	2 HYDRAULIC SYSTEM MANIFOLD-FILTER HAD FAILED.  (TC NR 20061204007)				2	H	7	2 	4T			RT	A13NM   					 
2007012900145	20070129	00145	NM  	2007	1	29	CA061204008      	1	20061130	G	2910	82950010273	HYDRAULIC LINE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			41474								(CAN) SMALL PIN HOLE IN BEND RADIUS OF NR DIAMETER 4 TUBE ASSY, NR 1 GROUNDING ITEM IS THE HYDRUALIC LINES ON THE DASH 8	`S. (TC NR 20061204008)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012600374	20070126	00374	NM  	2007	1	26	CA061205001      	1	20061204	G	3213	10300555	YOKE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED A CHECK, RT MLG YOKE WAS FOUND TO HAVE A CRACKED FITTING AT THE AUX ACTUATOR ATTACH POINT. (TC NR	 20061205001)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012900148	20070129	00148	EA  	2007	1	29	CA061205002      	1	20061204	G	2750		FLAP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AT APROX 2500-3000 FT ON FINAL APPROACH THE CREW RECEIVED A FLAP FAIL MESSAGE. THE QRH WAS FOLLOWED AND THE FLAPS 	WERE INDICATING AT 30 DEGREES.  THE CREW LANDED WITHOUT INCIDENT AND PERFORMED A CIRUIT BREAKER REST AND THE FLAPS RETUR	NED TO ZERO. FLT TO WHERE THE FLAPS OPERATED NORMALLY. (TC NR 20061205002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900153	20070129	00153	EA  	2007	1	29	CA061205003      	1	20061201	G	2750		BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					T/E FLAP	OUT OF RIG      	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE CREW REPORTED THAT THE FLAPS WERE FAILED AT 4 DEGREES. THE AIRCRAFT WAS FERRIED WITH THE FLAPS AT 	4 DEGREES. LINE MAINTENANCE COMPLETED TASK 27-51-10-830-801( RIGGING OF THE BPSU`S). BOTH WERE FOUND OUT OF RIG ALSO THE	 NR 7 DFECU POTENTIOMETER OUT OF RIG. ALSO THE FOLLOWING TASKS WERE COMPLETED 000-27-160-001, 000-27-160-103, 000-27-580	-103, 000-27-590-001, 000-27-59-104, 000-27-680-001, 000-27-680-103,000-27-690-001 & 000-27-690-104. LT FLEX DRIVE CORE 	NR 1 FOUND DAMAGED AND WAS REPLACED. ALL RT AND LT FLAP ACTUATORS WERE REMOVED AND COLD SOAKED/TORQUE CHECK IAW 27-53-00	-750-8011 AND SL RJ-SL-27-036. ALL ACTUATORS FOUND SERVICEABLE AND RE-INSTALLED IAW AMM 27-53-01 & 27-53-05, FUNCTION CH	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500158	20070125	00158	EA  	2007	1	25	CA061205004      	1	20061204	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED THAT ON APPROACH THEY RECEIVED THE (FLAP FAIL) CAUTION MESSAGE. ON APPROACH INTO.  CIRCUIT BREAK	ER RESET OF 1F4 AND 2F4 THE FLAPS RETURNED TO NORMAL FOR FLIGHT CONDITION. UPON ARRIVAL THE FLAPS WERE AT 0 DEGREES AND 	INSPECTED FOR BINDING OR TWISTING WITH NO FAULT FOUND. CYCLED TO 45 DEGREES WITH NFF. FECU LOG FAULT CODE FOR LEG ARE 5 	1B, 5 2B, 171A, 172B, 25BC, 33 PC, FLAPS SYSTEM TESTED SERVICEABLE WITH OAT -7 DEGREES. AIRCRAFT RELEASED INTO SERVICE. 	(TC NR 20061205004)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900154	20070129	00154	NM  	2007	1	29	CA061205005      	1	20061130	G	3246	314802OPT4	BEARING         			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			7209 								(CAN) WHEN THE AC ARRIVED TO THE PARKING POSITION, A BIG HYDRAULIC LEAKAGE WAS NOTED ON THE RUNWAY. AT THE SAME TIME, ML	G WHEEL NR 3 WAS FOUND TO BE DISPLACED FROM ITS NORMAL POSITION. THE WHEEL OUTER BEARING WAS FOUND DAMAGED.  RT MLG SHOC	K STRUT AND WHEEL ASSY REPLACED. (TC NR 20061205005)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012900158	20070129	00158	GL  	2007	1	29	CA061205006      	3	20061114	G	6110		SHIM            	HAMSTD      	24PF309     	DHAV  	DHC7  	DHC7*       	       	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	PROP BLADE	BROKEN          	W				O				OTHER                   				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CA			4025 	43   							(CAN) AFTER LANDING, A POST-FLIGHT INSPECTION REVEALED AN OIL LEAK IN THE NR1 PROP. FURTHER INVESTIGATION SHOWED THAT TH	E BLADE SHIMS HAD BEEN INSTALLED ON THE WRONG SIDE OF THE BLADE RETAINING RING. THE SHIMS HAD BROKEN AND DAMAGED THE OIL	 SEALS. THE OTHER 3 PROPS WERE CHECKED AND THE SAME PROBLEM WAS FOUND ALONG WITH MORE DAMAGED SEALS. (TC NR 20061205006)				2	H	7	4 	4T	4	T	RT	A20EA   	E4EA	6	C	P1NE	 
2007012500162	20070125	00162	EA  	2007	1	25	CA061205007      	1	20061201	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4762 	4762 							(CAN) DURING APPROACH WHEN FLAPS SELECTED, FLAPS REMAINED RETRACTED (0 DEG). AIRCRAFT DID FLAPLESS LANDING. ON GROUND FL	AP CIRCUIT BREAKER RE-SET CARRIED OUT, FLAPS FUNCTIONED NORMALLY. AIRCRAFT DEPARTED FOR MAINTENANCE BASE FOR ADDITIONAL 	INSPECTIONS (TC NR 20061205007)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500163	20070125	00163	CE  	2007	1	25	CA061205008      	1	20061205	G	3233	AN6289D6	NUT             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					LT MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14603			2324					(CAN) NUT ON HYDRAULIC LINE LEADING TO LT MAIN LANDING ACTUATOR FOUND CRACKED DURING DAILY INSPECTION.  THE NUT WAS REPL	ACED, GEAR SWINGS CARRIED OUT, AIRPLANE IS NOW SERVICEABLE. (TC NR 20061205008)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007012500164	20070125	00164	EA  	2007	1	25	CA061206001      	1	20061011	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			25777	25777							(CAN) ON APPROACH FLAPS SELECTED TO 8 DEG, FLAP DID NOT TRAVEL AND (FLAP FAIL) MESSAGE DISPLAYED.  NORMAL FLAP ZERO LAND	ING .  AFTER LANDING , FLAP CIRCUIT BREAKER RESET PROCEDURE CARRIED OUT .  FLAPS INSPECTED AND NO FAULTS FOUND. FLAPS CY	CLED WITH NO FAULTS FOUND. (TC NR 20061206001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500166	20070125	00166	EA  	2007	1	25	CA061206002      	1	20061202	G	5520	NAS620413D	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT ELEVATOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT ELEVATOR, FOUND NUT/BOLT COMBINATION INCORRECTLY INSTALLED ON LT NR 1 PCU JAM TOLERANT MECHANISM.  AIRFRAME HOU	RS: 25355:05. CYCLES: 20701. (TC NR 20061206002)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500168	20070125	00168	NE  	2007	1	25	CA061206003      	2	20061202	G	7230		BLADES          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) UNUSUAL NOISE AND VIBRATION FROM LT ENGINE. FOUND FAN BLADES NRS: 8,9,10,11,22,23,24 AND 25 BENT AND DAMAGED.  AIR	FRAME HOURS=5306:19. CYCLES=3929. (TC NR 20061206003)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500169	20070125	00169	EA  	2007	1	25	CA061206004      	1	20061206	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			11187	11187							(CAN) (FIRST FLIGHT OF DAY, AIRCRAFT HAD BEEN OUTSIDE ON GATE OVERNIGHT, OAT AT -20DEG OR LOWER) DURING TAXI FROM GATE U	PON SELECTING FLAP TO 8DEG POSITION, (FLAPS FAIL) MESSAGE AND FLAPS FAILED TO EXTEND. AIRCRAFT RETURNED TO GATE. FLAP CI	RCUIT BREAKER RE-SET PROCEDURE CARRIED OUT UNSUCCESSFUL. AIRCRAFT COMPLETELY POWERED DOWN. UPON POWER UP, FLAPS FUNCTION	ED NORMAL. FLAP VISUAL INSPECTED AND FUNCTIONED SEVERAL TIMES. AIRCRAFT DEPARTED AS SCHEDULED FLIGHT. UPON FLAP SELECTIO	N AT DESTINATION AIRPORT, FLAPS FAILED TO EXTEND, FLAP (O) LANDING CARRIED OUT. AIRCRAFT TO BE FERRIED TO MAIN MAINTENAN	CE BASE FOR INSPECTION. (TC NR 20061206004)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500171	20070125	00171	CE  	2007	1	25	CA061206005      	1	20061124	G	2810	244224152	HOSE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1266 								(CAN) AFTER AIRCRAFT WAS PARKED OVERNIGHT WITH FULL FUEL, A MINOR FUEL SEEP WAS DISCOVERED COMING FROM RT FUSELAGE FUEL 	TANK TO WING FLEX HOSE ASSY. DURING REPLACEMENT OF RT HOSE WITH FULL LT WING FUEL IT WAS DISCOVERED THE LT FUSELAGE TO W	ING FUEL FLEX HOSE ALSO HAD A MINOR SEEP. THIS IS ONLY NOTICEABLE WHEN THE AIRCRAFT IS SITTING FOR A FEW HOURS WITH FULL	 FUEL IN THE WINGS. ON INVESTIGATION OF OUR OTHER AIRCRAFT IT WAS DISCOVERED THE RT FLEX HOSE HAD THE SAME PROBLEM.  THE	SE ARE P/N 244224151 AND 244224152 FLEX HOSE ASSEMBLIES.  (TC NR 20061206005)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007012500173	20070125	00173	CE  	2007	1	25	CA061207001      	1	20061206	G	2897		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL CELL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5877 								(CAN) THE FUEL TANKS SHOW EVIDENCE OF LOCALIZED DISCOLORATION AND VARIOUS NICKS ON OUTER JACKETS OF FUEL QUANTITY PROBE 	WIRING. THERE IS ALSO DISCOLORATION ON THE TERMINALS OF THE VARIOUS FUEL PROBES. THIS DAMAGE IS PROBABLY CAUSED BY IMPRO	PER USE OF THE TYRAP TOOL MOST LIKELY AT THE FACTORY LEVEL. THIS IS THE SECOND TIME THIS TYPE OF DAMAGE HAS BEEN FOUND O	N A COMPANY AIRCRAFT. (TC NR 20061207001)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007012500261	20070125	00261	EU  	2007	1	25	CA061207002      	1	20061207	G	5310	F10A212107	WINDOW FRAME    			AMD   	FALC10	FALCON10    	2730101	EU  										WINDOW	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6674 								(CAN) REMOVED FRONT WINDSHIELDS TO COMPLY WITH COCKPIT WINDOW FRAME INSPECTION REQUIREMENT OF THE C2 INSPECTION.  FOLLOW	ING REMOVAL OF PILOTS WINDSHIELD, SEVERE EXFOLIATION CORROSION WAS FOUND ON LOWER FRAME APPROX. 16 INCHES FROM OUTER RA	IL OVER AN 8 INCH WIDTH ON THE FRAME.  (TC NR 20061207002)				2	L	7	2 	4F				A33EU   					 
2007012900166	20070129	00166	EU  	2007	1	29	CA061207003      	1	20061203	G	5230	17040238003	PLATE           		17040236407 	EMB   	ERJ170	ERJ170100   	       	EU  	GE    	CF34  	CF348E5A1   	30015	NE  					CARGO DOOR	BENT            	W				O				OTHER                   				W	P		INADEQUATE Q C            	NO WARNING INDICATION     		TX	TAXI/GRND HDL  	1			CA			2611 								(CAN) ACFT WAS TAXIING TO DE-ICING BAY, WHERE THE DEICING PERSONNEL NOTICED THAT THE C1 CARGO DOOR WAS AJAR BY 2 INCHES.	  MAINTENANCE WAS CALLED IN, AND THEY NOTICED THAT BOTH HANDLES WERE STOWED. THE DOOR WAS OPENED TO CHECK FOR OBSTRUCTIO	NS, AND FOUND THE COVER PLATE TO BE BENT.  NO OTHER DAMAGE WAS NOTED, AND THE DOOR WAS CLOSED NORMALLY.  THE GREEN INDIC	ATION ON THE DOOR WINDOW WAS APPARENT.  THIS INFO WAS THEN PASSED ON TO THE F/O.  ALSO, THE COCKPIT INDICATION DID NOT S	HOW DOOR TO BE OPENED.  CREW DID NOT REALIZE DOOR WAS OPENED.  IT IS SUSPECTED THAT THE MIDWAY LATCH WAS ROTATED BY A BE	NT PLATE, WHICH THEN ALLOWED THE HANDLES TO BE STOWED WITHOUT THE LATCH CAMS ENGAGED AROUND THE LATCH PINS. (TC NR200612	2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2007012900168	20070129	00168	SW  	2007	1	29	CA061207004      	1	20061207	G	7921	8543909	OIL COOLER      			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON AIRCRAFT RETURNING TO BASE IT WAS NOTED THAT THERE WAS OIL ON THE TAILBOOM. ON INVESTIGATION THE SOURCE OF THE 	OIL WAS FOUND TO BE THE OIL COOLER. COOLER CHANGED. (TC NR 20061207004)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007012900179	20070129	00179	SO  	2007	1	29	CA061207005      	1	20061206	G	8011		DRIVE GEAR      		MHB4014R    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	STARTER	DESTROYED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				1926 		C120571					(CAN) WHILE AIRCRAFT WAS AWAY FROM BASE ON A SCHEDULED RUN THE CREW WAS ATTEMPTING TO STAR THE NR 2 ENGINE. THEY NOTED N	O ENGAGEMENT OF THE STARTER (ENGINE DID NOT TURN OVER). A MAINTENANCE CREW WAS DISPATCHED TO REPAIR THE AIRCRAFT, WHEN T	HE COWLINGS WERE REMOVED SEVERAL PIECES OF METAL WERE OBSERVED. UPON REMOVAL OF THE STARTER IT WAS DISCOVERED THAT THE E	NGAGEMENT GEAR ON THE BENDIX DRIVE HAD DISINTIGRATED, DAMAGING THE DRIVE HOUSING AS THE PIECES DEPARTED. THE STARTER WAS	 LESS THAN 80 HRS FROM OVERHAUL. AFTER DISCUSSION WITH THE CREW, THEY STATED THEY DID NOT DOUBLE TAP THE START SWITCH. A	N INVESTIGATION IS STILL IN PROGRESS. (TC NR 20061207005)	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007012900181	20070129	00181	EA  	2007	1	29	CA061208001      	1	20061206	G	2752	20222788	ACTUATOR        			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					T/E FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4684 								(CAN) DURING SCHEDULE LUBRICATION OF THE FLAP ACTUATORS, THE TECHNICIAN NOTICED GREASE WAS OOZING OUT OF A CRACKED WELD 	ON THE HOUSING OF THE LT OB FLAP ACTUATOR JACK SCREW. (TC NR 20061208001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007020200122	20070202	00122	SW  	2007	2	2	CA061208003      	1	20061205	G	6340	22A656	TACH GENERATOR  			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  						WORN            	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) GREASE FOUND WASHED OUT CAUSING PREMATURE WEAR OF DRIVE SPLINES LEADING TO HYDRAULIC SYSTEM FAILURE.  298.7 HRS SI	NCE PREVIOUS LUBRICATION. (TC NR 20061208003)					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2008021900139	20080219	00139	SW  	2008	2	19	CA061208004      	1	20061205	G	2913	206076030111	PUMP            			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					HYDRAULIC SYSTEM	LACK OF LUBE    	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) GREASE FOUND WASHED OUT CAUSING PREMATURE WEAR OF DRIVE SPLINES LEADING TO HYDRAULIC SYSTEM FAILURE. 198.3 HRS SIN	CE PREVIOUS LUBRICATION. (TC NR 20061208004)					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2007012900182	20070129	00182	NE  	2007	1	29	CA061208005      	2	20061203	G	7230	9324M70G06	COMPRESSOR      			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					ENGINE	STALLED         	W				E				ENGINE SHUTDOWN         				M	E		OVER TEMP                 	VIBRATION/BUFFET          		CR	CRUISE         	1			CA			29961	4857 							(CAN) IN CRUISE, 2 HOURS FROM DESTINATION THE ENGINE STALLED AND EGT WAS RISING.  WHEN EGT REACHED 1010 DEG. C, THE ENGI	NE WAS SHUTDOWN. THE OIL PRESSURE WENT TO ZERO AND BOTH N1 AND N2 ROTORS WERE ROTATING.  DFDR DATA SHOWS: N2 VIBRATION W	AS HIGH (3.5 TO 5.5 UNITS) AFTER THE STALL, RAPIDLY REDUCED TO 2.O UNITS AND THEN SLOWLY REDUCED TO ZERO BEFORE ENGINE S	HUTDOWN.  N1 VIBRATION WAS LOW AFTER THE STALL (0.5-2 UNITS) AND RAPIDLY INCREASED AFTER STALL TO 5-5.5 UNITS AND STAYED	 THERE.  N1, N2, FUEL FLOW HAD A RAPID DECREASE AFTER THE STALL AND RECOVERED SLIGHTLY, THEN SLOWLY DECREASED WITH EGT R	ISING.  AFTER AIRCRAFT LANDED, BASE MAINTENANCE CARRIED OUT A VISUAL INSPECTION WITH THE FOLLOWING FINDINGS: NO DAMAGE O	2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2007012900183	20070129	00183	EA  	2007	1	29	CA061211001      	1	20061203	G	5610	NP13932100	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) RT SIDE WINDSHIELD SHATTERED (TC NR 20061211001)						2	L	7	2 	4F			RT	A21EA   					 
2007012900184	20070129	00184	EA  	2007	1	29	CA061211002      	1	20061203	G	5610	601R3303311	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) LT SIDE WINDOW SHATTERED. (TC NR 20061211002)						2	L	7	2 	4F			RT	A21EA   					 
2007012900185	20070129	00185		2007	1	29	CA061211003      	4	20061210	G	3417	7000700940	ADC             			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2	MALFUNCTIONED   	W				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE F/O ALTIMETER OFF FLAG CAME INTO VIEW ON NUMEROUS OCCASSIONS. THE EGPWS FAULT LIGHT ALSO ILLUMI	NATED.  PILOT ELECTED TO PERFORM AN AIR TURN BACK.  NR 2 DIGITAL AIR DATA COMPUTER REPLACED. (TC NR 20061211003)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012900186	20070129	00186	EA  	2007	1	29	CA061211004      	1	20061207	G	7120	601370541	PLUG            	CNDAIR      	ASB1810617  	CNDAIR	CL600 	CL6002B19   	1900309	EA  										LT ENGINE	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING OF C-CHECK INSPECTION FOUND THAT PLUG ASSY P/N 60137054-1 IS NOT INSTALLED AT THE AFT ENGINE TRUST FITTING 	P/N ASB18106-17 OF LT ENGINE. TO INSTALL THE PLUG ENGINE NEED TO BE REMOVED. (TC NR 20061211004)					2	L	7	2 	4F			RT	A21EA   					 
2007012500186	20070125	00186	NE  	2007	1	25	CA061211005      	3	20061207	G	6111	14SF23	BEARING RACE    			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1 PROP	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			24284								(CAN) LIGHT TO MODERATE PROP VIBRATION IN CRUISE, AS POWER WAS REDUCED FOR DESCENT VIBRATION BECAME EXCESSIVE.  AS A RES	ULT THE NR 1 PROP (CONDITION LEVER) WAS SELECTED TO START FEATHER (VIBRATION STOP) AND THEN NR 1 ENGINE WAS SHUTDOWN.  A	LL ENGINE PARAMETERS WERE NORMAL PRIOR TO SHUTDOWN.  FOLLOWING THE IFSD AS DESCRIBED ABOVE, MAINTENANCE PERFORMED A LOW 	POWER RUN TO VERIFY THE VIBRATION AS REPORTED. THE VIB WAS CONFIRMED AND THE ENGINE SHUTDOWN.  OIL WAS THEN NOTED DRIPPI	NG FROM THE VICINITY OF THE NR 1 PROP.  INITIAL INVESTIGATION HAS REVEALED THAT THE NR 1 PROP, NR 4 BLADE BEARING RACE H	AS FRAGMENTED INTO SEVERAL PARTS. (TC NR 20061211005)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012500209	20070125	00209	EA  	2007	1	25	CA061211006      	1	20061203	G	4930	38301552	LINE            	HONEYWELL   		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUEL MANIFOLD	BROKEN          	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		AP	APPROACH       	1			CA			15268	15268		P365C					(CAN) RT AIR CONDITIONING PACK WAS DEFERRED AND CREW HAD TO SHUTDOWN APU ON APPROACH BECAUSE OF OIL/FUEL ODOR IN THE CAB	IN.  CREW REPORTED A PRESSURE BUMP WHEN APU WAS SHUTDOWN.  APU WAS SUSPECTED TO BE OVER SERVICED, BUT EVEN AFTER DRAININ	G A LITRE OF OIL APU WOULD NOT RE-START.  FURTHER TROUBLESHOOTING FOUND THE PRIMARY FUEL MANIFOLD LINE BROKEN.  ONCE REP	LACED APU OPERATED SERVICEABLE. (TC NR 20061211006)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500212	20070125	00212		2007	1	25	CA061211007      	4	20061209	G	2211	7003974730	COMPUTER        	HONEYWELL   		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FLIGHT GUIDANCE	FAULTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			38718	15860		90012118					(CAN) LEVELING OFF AT 4000 FT, AFCS FAILED, ID802 SHOWED LINES, YD AND FLIGHT DIRECTOR FAILED, CAPT AND F/O ADI`S FLAGGE	D OFF. AIRCRAFT RETURNED TO ORIGINATING AIRPORT FOR NORMAL LANDING.  MAINTENANCE INSPECTION OF FLIGHT FAULT SUMMARY SHOW	ED FAILURE OF RIGHT FLIGHT GUIDANCE COMPUTER. COMPUTER REPLACED AND FUNCTION CHECKED. AIRCRAFT RETURNED TO SERVICE. (TC 	NR 20061211007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012500214	20070125	00214	SW  	2007	1	25	CA061211008      	1	20061208	G	2932	27191543	TRANSDUCER      			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD PRESS TRANS	SPLIT           	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) AIRCRAFT LOST HYD PRESSURE ON LANDING.  THERE WAS NO INDICATION OF PRESSURE ON GAUGE AND ON THE ANUNCIATOR PANEL. 	 HYDRAULIC PRESSURE TRANSDUCER FOUND SPLIT AROUND HYDRAULIC FITTING END.  TRANSDUCER AND SHUTTLE VALVE WERE REPLACED AND	 AIRCRAFT RETURNED TO SERVICE. (TC NR 20061211008)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007012500215	20070125	00215	NM  	2007	1	25	CA061211009      	1	20061209	G	5610	141A481014	WINDOW          			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			19028								(CAN) WINDOW FLT COMPARTMENT DELAMINATED, CRACKED NR 2 LT DESCENDED TO FL210 + INC CABIN ALT TO 9000 FT, WHICH GAVE US A	 CABIN DIFF OF 3.6 PSI.  CAPT`S NR 2 SLIDING WINDOW REPLACED IAW AMM 56-12-11, GND CHECKED SERVICABLE. COCKPIT WINDOW FA	ILURES ARE PART OF A SAFETY RELATED SERVICE PROBLEM SRP 56-0018 WITH MFG.  ICA ISSUANCE IS AWAITED FOR PERMANENT RECOMME	NDED ACTION. (TC NR 20061211009)			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007012500218	20070125	00218	EA  	2007	1	25	CA061212001      	2	20061210	G	7200		ENGINE          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	FAILED          	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			X	A		ENGINE FLAMEOUT           	FLAME/FIRE                		DE	DESCENT        	1			CA			20124	214  				42129			(CAN) SHORTLY AFTER COMPLETING THE DESCENT CHECKS FOR A LANDING (WITH ENGINES OPERATING NORMALLY, ENGINE INSTRUMENTS IN 	THE GREEN, THE CREW HEARD A LOUD NOISE FOLLOWED BY A SUDDEN LOSS OF POWER ON THE RT ENGINE. IMMEDIATELY FOLLOWING THE SU	DDEN LOSS OF POWER THE RT ENGINE CAUGHT ON FIRE. THE PROCEDURES FOR AN IN-FLIGHT ENGINE FIRE WERE CARRIED OUT AND THE FI	RE WAS EXTINGUISHED. AFTER INITIAL INSPECTION THE CAUSE OF THE ENGINE FAILURE WAS DUE TO AN INTERNAL FAILURE OF THE ENGI	NE. ITEMS NOTICED DURING INITIAL INSPECTION ARE AS FOLLOWS: POWER SECTION SEIZED, OIL VISIBLE IN BOTH EXHAUST STACKS, NO	 EXTERNAL INDICATION OF FIRE DAMAGE TO ENGINE VISIBLE (FIRE WAS LIMITED TO EXHAUST STACKS DUE TO OIL LOSS FROM INTERNAL 	1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2007012500219	20070125	00219	SO  	2007	1	25	CA061212002      	1	20061112	G	6100		PROPELLER       			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 4	DAMAGED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE AT FL240 AFTER DEPARTURE THE CREW OBSERVED LOW OIL QTY ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE A	IRCRAFT CONTINUED TO DESTINATION.  SHORTLY AFTER RE-ESTABLISHING  CRUISE AT FL220 THE CREW OBSERVED LOW OIL QTY ON NR 4 	PROPELLER. THE PROP WAS SELECTED TO MECHANICAL GOVERNING AND THE AIRCRAFT CONTINUED TO DESTINATION. THE NR 4 ENGINE WAS 	SHUTDOWN ON DESCENT TO PRECLUDE PROP OVERSPEED. THE AIRCRAFT ARRIVED WITHOUT FURTHER PROBLEMS. MAINTENANCE REPLACED THE 	NR 2 ENGINE SCAVENGE FILTER AND THE NR 4 PROPELLER ASSY. AIRCRAFT SATISFACTORILY GROUND RUN AND RETURNED TO SERVICE.		2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007012500220	20070125	00220	NM  	2007	1	25	CA061212003      	1	20061211	G	7500	8209074	SWITCH          			BOMBDR	DHC8  	DHC8402     	1390042	NM  										RT NACELLE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			40   								(CAN) NR 2 BLEED HOT CAUTION LIGHT COME ON 4 MILES OUT.  CDS INTEROGATION FAULT CODES 7005, 7001 AND 1701. (TC NR 200612	12003)					2	H	7	2 	4T			RT	A13NM   					 
2007012500221	20070125	00221	EA  	2007	1	25	CA061212004      	1	20061202	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			3695 	3695 							(CAN) DURING CRUISE CAPTAINS FRONT WINDSHIELD SHATTERED. (NO PRESSURIZATION LOSS).  CREW DECLARED EMERGENCY AND DESCEND	ED TO 10000 FT AND DIVERTED TO NEAR BY ALTERNATE AIRPORT.  MAINTENANCE REPLACED WINDSHIELD AND AIRCRAFT RETURNED TO SERV	ICE. (TC NR 20061212004)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500223	20070125	00223	SO  	2007	1	25	CA061212005      	1	20061210	G	2913	65WE002241	PUMP            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYDRAULIC	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) (5) MINUTES AFTER AN ENGINE FAILURE OF THE RT ENGINE (SDR 20061212001) THE HYDRAULIC LIGHT CAME ON EVEN THOUGH THE	 LT ENGINE WAS OPERATING NORMALLY. THE CREW ATTEMPTED TO EXTEND THE LANDING GEAR NORMALLY BUT IT WOULD NOT LOCK. THE GEA	R WAS THEN SUCCESSFULLY HAND PUMPED DOWN.  A FAILURE OF THE LT ENGINE DRIVEN HYDRAULIC PUMP IS SUSPECTED TO BE THE CAUSE	 OF NOT BEING ABLE TO EXTEND THE LANDING GEAR NORMALLY.  THE HYDRAULIC PUMP WILL BE REMOVED AND SENT OUT FOR A TEARDOWN.	 (TC NR 20061212005)		1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2007012500263	20070125	00263	NM  	2007	1	25	CA061212006      	1	20061212	G	3230	54C546349	SEQUENCE VALVE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) UPON RETRACTION OF THE LANDING GEAR THE CREW HEARD A STRANGE NOISE FOLLOWED BY HYDRAULIC FLUID QUANTITY LOSS IN TH	E NR 2 SYSTEM. THE CREW CARRIED OUT THE APPLICABLE PROCEDURES TO EXTEND THE LANDING GEAR BUT WERE NOT ABLE TO GET THE NO	SE LANDING GEAR TO EXTEND. THE CREW FLEW THE AIRCRAFT FOR SEVERAL HOURS TO BURN OFF FUEL AND TRY TO GET THE NOSE GEAR TO	 EXTEND BUT WERE UNSUCCESSFUL AND COMPLETED A NOSE GEAR RETRACTED LANDING ON A SNOW PACKED RUNWAY. THE AIRCRAFT WAS SUBS	EQUENTLY DAMAGED IN THE NOSE LANDING GEAR DOOR AND RADOME AREAS. UPON INITIAL INVESTIGATION BY MAINTENANCE IT WAS FOUND 	THAT THE LT MLG DOOR SEQUENCING SOLENOID VALVE WAS RUPTURED CAUSING THE LOSS OF THE NR 2 HYDRAULIC SYSTEM FLUID.  IT IS 	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012500225	20070125	00225	WP  	2007	1	25	CA061212007      	2	20061030	G	7250	310210610	TURBINE WHEEL   								GARRTT	TPE331	TPE33110U   	01514	WP  					NR 2	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1122 								(CAN) FOUND UPON DOING A HSI INSPECTION THAT THE NR 2 ROTOR THE RIVETS WERE FOUND LOOSE TO THE POINT THAT THEY WERE GOIN	G TO START COMING OUT. THIS WHEEL IN QUESTION ONLY HAD 1409 CYCLES TOTAL ON IT. (TC NR 20061212007)										4	T			E4WE				 
2007012500228	20070125	00228	WP  	2007	1	25	CA061212008      	2	20061212	G	7250	310210610	TURBINE WHEEL   		310210610   						GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3598 								(CAN) FOUND UPON INSPECTION AT THE HSI INSPECTION THAT THE RIVETS WERE LOOSE AND DEFORMED TO THE POINT THAT THE RIVETS W	ERE GOING TO COME OUT AND POSSIBLY WOULD CAUSE MORE DAMAGE INSIDE THE ENGINE. (TC NR 20061212008)										4	T			E4WE				 
2007012500230	20070125	00230	EA  	2007	1	25	CA061212009      	1	20061121	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			11593	11593							(CAN) ON APPROACH WHEN FLAPS SELECTED, (FLAP FAIL) MESSAGE AND FLAPS REMAINED AT ZERO DEG., FLAPLESS LANDING. ON GROUND 	FLAP CIRCUIT BREAKERS RESET PROCEDURE CARRIED OUT, FLAPS FUNCTION CHECKED NORMAL. (TC NR 20061212009)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500231	20070125	00231	EU  	2007	1	25	CA061213001      	1	20061210	G	5210	19017111401	DOOR            			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					COCKPIT	DISLODGED       	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			250  								(CAN) FLIGHT DECK DOOR CAME FREE ON FRAME WHEN OPENED FROM CABIN SIDE IN FLIGHT.  BOTTOM LOCATING PIN FOUND BENT AND TEM	PORARILY FIXED.  TOP PIN DOES NOT REMAIN IN FRAME BRACKET.  DOOR SERVICEABLE FOR REMAINDER OF FLIGHT ONLY. (TC NR 200612	13001)				2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2007012500233	20070125	00233	EA  	2007	1	25	CA061213002      	1	20061208	G	2620	13739002	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										EXTINGUISHER	JAMMED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) BOTH CARGO FIRE X-BOTTLES DISCHARGED WHEN , NORMAL CARGO SMOKE PUSH) SWITCH-LIGHT ACTUATED TO ARM THE DISCHARGE SQ	UIBS. AFTER INVESTIGATION FOUND THAT BOTTLE ARMED (PUSH TO DISCHARGE) SWITCH-LIGHT JAMMED IN THE (PUSH) POSITION. (TC NR	 20061213002)				2	L	7	2 	4F			RT	A21EA   					 
2007012900187	20070129	00187	EA  	2007	1	29	CA061213003      	1	20061208	G	2612	13739002	LIGHT           	BOMBDR      	601R5107083 	CNDAIR	CL600 	CL6002B19   	1900309	EA  										FIRE WARNING	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DUE TO INCIDENT, CARGO FIREX PANEL TESTED AND FOUND THAT (NORMAL BOTTLE ARMED PUSH TO DISCH) SWITCH-LIGHT IS INTER	MITTENT OR JAMMED IN THE CLOSE POSITION. (TC NR 20061213003)					2	L	7	2 	4F			RT	A21EA   					 
2007012900188	20070129	00188	EA  	2007	1	29	CA061213004      	1	20061208	G	2612	13739002	LIGHT           	CNDAIR      	601R5107083 	CNDAIR	CL600 	CL6002B19   	1900309	EA  										FIRE WARNING	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DUE TO INCIDENT ON AC N639BR, CARGO  FIREX PANEL TESTED AND FOUND THAT (NORMAL BOTTLE ARMED PUSH TO DISCH) SWITCH-	LIGHT IS INTERMITTENT OR JAMMED IN CLOSE POSITION. (TC NR 20061213004)					2	L	7	2 	4F			RT	A21EA   					 
2007012900189	20070129	00189	NM  	2007	1	29	CA061213005      	1	20061210	G	7921	28E997	OIL COOLER      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA				301  							(CAN) OIL COOLER SEAM WELD CRACKED DURING FLIGHT ALLOWING LEAKAGE AND LOW ENGINE OIL PX. (TC NR 20061213005)						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012500235	20070125	00235	EA  	2007	1	25	CA061214001      	1	20061213	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE CREW SELECTED FLAP 40 AND THE FLAPS FAILED AT 20 DEGREES. THE AIRCRAFT LANDED WITHOUT INCIDENT AND	 WAS LATER FERRIED WHERE IT IS CURRENTLY UNDERGOING INSPECTION. (TC NR 20061214001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500237	20070125	00237	SO  	2007	1	25	CA061214002      	2	20061207	G	7314		SEAL            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FUEL PUMP	LEAKING         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA			1337 								(CAN) AIRCRAFT BROUGHT IN FOR 50 HR.MAINTENANCE CHECK FOUND FUEL ON BOTTOM OF COWL AND IT WAS TRACED BACK TO THE ENGINE 	DRIVEN FUEL PUMP. THE SEALS IN THE FUEL PUMP HAD STARTED TO FAIL OR HAD FAILED AROUND THE MIXTURE CONTROL LEVER ASSY. TH	E TOP COVER ALSO WAS LEAKING FUEL. FUEL PUMP WAS REMOVED AND SENT FOR REPAIRS. UNIT REPAIRED AND RELEASED ON 24-0078  NR	 A47159 (TC NR 20061214002).			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007012500239	20070125	00239	EU  	2007	1	25	CA061214003      	1	20061129	G	3010		BOOT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DEICE SYSTEM	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6085 	6085 							(CAN) AIRCRAFT RETURNED FROM FLIGHT TO ARCTIC.  ALL DE-ICE BOOTS ON AIRCRAFT WERE FOUND SPLIT ALONG CHORD AND HAD TO BE 	REPLACED.  THE PRESSURE REGULATOR WAS TESTED AND FOUND TO BE FUNCTIONING NORMAL.  WE WERE UNABLE TO DETERMINE THE CAUSE 	OF THE FAILURE.  THE PILOT REPORTED IT WAS COLD AT ALTITUDE AND NOT SURE IF THE BOOTS WERE ACTIVATED.  (TC NR 2006121400	3)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007012900190	20070129	00190	NE  	2007	1	29	CA061214004      	2	20061214	G	7230	5009T34P01	BLADE           	GE          	5012T75624  						GE    	CT58  	CT581402    	30011	NE  					COMPRESSOR	MISSING         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA				893  		HAAH2079					(CAN) RECEIVED THIS ENGINE WITH A DEFECT OF LOW POWER. IT WAS RUN ON THE TEST STAND TO CONFIRM THE POWER OUTPUT WHICH WA	S 1440 SHP.  WHEN THE ENGINE WAS DISASSEMBLED THEY FOUND THAT A BLADE WAS MISSING FROM THE COMPRESSOR 4TH STAGE.  THERE 	WAS NO DAMAGE TO THE FIRST 3 SECTIONS BUT IT RESULTED IN DAMAGING THE DOWNSTREAM BLADES AND VANES. THE 4TH STAGE BLADES 	ARE CURRENTLY AT INVESTIGATIION. THIS ENGINE IS OWNED BY OPERATOR AND A COPY OF THIS SDR WILL BE SUBMITTED.  THERE IS MO	RE INFORMATION TO FOLLOW.  THE OWNER OF THE ENGINE IS HELI-ONE AND IT WAS BEING OPERATED ON A POWER BY THE HOUR PROGRAM.	 (TC NR 20061214004)						4	U			1E3				 
2007012500241	20070125	00241	GL  	2007	1	25	CA061215001      	2	20061202	G	7261		FILTER          			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	SCAV PUMP	UNKNOWN         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON DEPARTURE, THE CREW OBSERVED NR 2 ENGINE OIL LEVEL DROPPING TO 2.75 GAL. WITH A LOW OIL LIGHT ILLUMINATED. THE 	AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 2 SCAVENGE OIL FILTER AND REPLENISHED THE OIL QUANT	ITY TO 10 GAL. THE AIRCRAFT WAS FOUND SATISFACTORY AND RETURNED TO SERVICE. (TC NR 20061215001)				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007012500242	20070125	00242	CE  	2007	1	25	CA061215002      	1	20061212	G	5520	115520219	HINGE           	BEECH       		BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9051 			BE114A					(CAN) DURING PHASE NR 2 INSPECTION, IT WAS NOTICED THAT THE LT ELEVATOR WAS LOOSE AT THE OB HINGE.  AREA INSPECTED AND F	OUND THAT THE 4 BOLTS THAT ATTACH THE HINGE TO THE HORIZONTAL STAB WERE LOOSE. THE HINGE WAS REMOVED AND FOUND THAT THE 	HOLES WERE ELONGATED. THE HINGE AND ATTACHING STRUCTURE WERE REPLACED.				1	L	7	2 	3T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007012500243	20070125	00243		2007	1	25	CA061216001      	4	20061214	G	3100	A6611	IGNITION SWITCH 			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					INSTRUMENT PANEL	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REPLACED IGNITION SWITCH DURING 2200 HR O/H AND REINSTALLED IN INSTRUMENT PANEL.  THE SEATING OF THE SWITCH STOPPE	D THE CONSOLE FROM OPENING AGAIN.  THE SWITCH WAS REMOVED AND RESEATED TO ALLOW TRAVEL PAST THE INSTRUMENT CONSOLE.  WE 	COULD NOT ALIGN THE SWITCH TO PREVENT THE TERMINAL (RT MAG CONNECTION) FROM CONTACTING THE SIDE WALL OF THE LOWER CONSOL	E. THE TERMINAL ONLY MAKES CONTACT DURING THE TRANSITION FROM OPEN TO CLOSE AND VICE-VERSA.  ONCE THE CONSOLE IS CLOSED 	THERE IS NO CONTACT OF THE TERMINAL, SIDEWALL OR LIP. WE ARE TALKING WITH MFG TO SEE IF THERE MAYBE A FIX.  COULD BE IGN	ITION SWITCH MAYBE HAVE TO BE DESIGNED A LITTLE SMALLER OR MORE ROOM ON PANEL. (TC NR 20061216001)	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007012500244	20070125	00244	CE  	2007	1	25	CA061216002      	1	20061215	G	3242	1013810127	VALVE           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LANDING GEAR	FALSE INDICATION	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			28   								(CAN) NEW VALVE WAS INSTALLED. LANDING GEAR VALVE FAILS TO INDICATE THAT IT IS OPEN WHEN SELECTED. VALVE WORKS CORRECTLY	, BUT FAILS TO INDICATE TO CREW THAT IT IS WORKING. SEEMS TO BE JUST AN ISSUE WITH THE INDICATION SIDE OF THE VALVE AND 	NOT THE ACTUAL MECHANICS. (TC NR 20061216002)				2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2007012500245	20070125	00245	NM  	2007	1	25	CA061216003      	1	20061212	G	2910	BACH8C08NN0290	LINE            			BOEING	727   	727243      	138408D	NM  										HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER T/O DURING CLIMB (B) PUMP LOW PX LITE ILLUMINATED WITH FLUID QTY DROP.  RETURNED TO DEPARTURE, HYD LINE REPL	ACED IN B COMPT.  (TC NR 20061216003)					2	L	7	3 	4F			RT	A3WE    					 
2007012500246	20070125	00246	SO  	2007	1	25	CA061217001      	1	20061216	G	3210	4025700	TORQUE LINK     			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	RT MLG STRUT	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE PILOT REPORTED NOTICING A VIBRATION DURING TAXI BUT ATTRIBUTED IT TO RUNWAY CONDITION.  IN FLIGHT HE WAS UNABL	E TO RETRACT THE LANDING GEAR. UPON LANDING HE WAS UNABLE TO EXECUTE TURNS.  AFTER DEPLANING HE FOUND THE FORWARD LUG ON	 THE UPPER TORQUE LINK OF THE RT MLG BROKEN.  THE TORQUE LINK ASSEMBLY WAS HELD IN PLACE ONLY BY THE BOTTOM TORQUE LINK 	ATTACH BOLT. THE BOLT THAT ATTACHES THE UPPER TORQUE LINK WAS MISSING ALONG WITH THE BROKEN LUG.  A CAUSE COULD NOT BEEN	 DETERMINED.  THE AIRCRAFT WAS TOWED TO THE HANGER. (TC NR 20061217001)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2007012500247	20070125	00247	EA  	2007	1	25	CA061218001      	1	20061216	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) THE CREW REPORTED THAT CLIMBING THROUGH FL220  (FLAP FAILED) MESSAGE CAME ON. THE CREW ELECTED TO CONTINUE AND THE	 FLIGHT LANDED WITHOUT FURTHER INCIDENT.  LINE MAINTENANCE FOUND THE FOLLOWING FAULT CODES 1-12-2B RH BPSU. FECU TEST CA	RRIED OUT NFF. WIRING BETWEEN FECU AND BPSU COMPLETED. BPSU REMOVED, NEW ONE INSTALLED AND RIGGED IAW AMM 27-51-10 FLAPS	 FUNCTION CHECKED SEVERAL TIMES AIRCRAFT RELEASED FOR SATISFACTORY TEST FLIGHT THEN RELEASED INTO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500248	20070125	00248	EA  	2007	1	25	CA061218002      	2	20061126	G	7414	K3823	BRUSH BLOCK     	SLICK       		FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			587  			05061176					(CAN) THE DISTRIBUTOR GEAR BRUSH WAS EXCESSIVELY WORN FOR HAVING 587.2 HOURS ON IT IN A COMPONENT DESIGNED WITH A 2000 H	OUR TBD. BRUSH BUSHING AND MOUNT OF POOR QUALITY WHICH IF LEFT UNDETECTED WOULD RESULT IN FAILURE IN 2 OR 300 MORE HOURS	 IF BEARING AND BUSHING AND BRUSH. (TC NR 20061218002)				1	H	7	1 	3O	3	O		A7EA    	1E4	5	C	P25EA	 
2007012500249	20070125	00249	SO  	2007	1	25	CA061218003      	2	20061106	G	7414	K3823	DISTRIBUTOR GEAR	SLICK       		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	MAGNETO	BURNED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA			727  			05012258					(CAN) DURING RUNUP AND PRE-TAKE OFF THE PILOT OBSERVED LARGE MAG DROPS AND POWER FLUCTUATIONS. THE AIRCRAFT WAS BROUGHT 	INTO THE SHOP. THE MAGNETOS WERE REMOVED AND INSPECTED.  UPON INSPECTION, IT WAS DISCOVERED BOTH DISTRIBUTOR BLOCK AND G	EAR HOUSINGS WERE BURNED THRU AT THE BRUSH HOLDER.  ONE BRUSH WAS MISSING. THE COIL WAS ARCING THRU TO THE MAGNET.  INVE	STIGATION DETERMINED THE BUSHINGS AND DISTRIBUTOR GEAR BRUSH HAS WORN ABNORMALLY.  THE BUSHINGS GOT VERY LOOSE CAUSING T	HE SECONDARY BRUSH TO WEAR AND ARC. THE DISTRIBUTOR GEAR AND HOUSING ARE PLASTIC. THE PLASTIC MELTED AND BOTH MAGS WERE 	ABOUT TO TOTALLY FAIL, DO NOT KNOW HOW IT KEPT RUNNING.	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2007012500253	20070125	00253	EU  	2007	1	25	CA061218004      	1	20061120	G	7930	0292005340	ENGINE          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  						MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			779  					22364			(CAN) AIRCRAFT HAD AN INFLIGHT ENGINE CHIP LIGHT.  PILOT LANDED AS SOON AS POSSIBLE.  AIRCRAFT WAS LANDED UNDER ITS OWN 	POWER (NORMAL LANDING).  PILOT THEN SHUT THE AIRCRAFT DOWN TO CHECK ALL ENGINE CHIP DETECTORS.  HE FOUND METAL ON THE EL	ECTRIC CHIP PLUG, ENGINE OIL TANK CHIP PLUG AND THE ENGINE MOI CHIP PLUG. ENGINE WAS REMOVED AND SENT TO MFG.  ANOTHER E	NGINE WAS INSTALLED. (TC NR 20061218004)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007012500255	20070125	00255	CE  	2007	1	25	CA061218005      	1	20060724	G	3110	903640143	CIRCUIT BOARD   			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	ANNUNCIATOR PANE	MALFUNCTIONED   	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) ANNUNCIATOR PANEL SHOWED A FALSE WARNING INDICATION FOR MASTER CAUTION LIGHT.  SYSTEM TROUBLESHOOTING CARRIED OUT 	AND FOUND FAULT WARNING CIRCUIT BOARD UNSERVICEABLE AND FAULT WARNING CIRCUIT BOARD REPLACED.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2007012500265	20070125	00265	GL  	2007	1	25	CA061218006      	2	20061205	G	7310		DRAIN MAST      			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2 ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ENROUTE AFTER MISSED APPROACH AT SNAP LAKE THE CREW OBSERVED A FUEL LEAK AT THE DRAIN MAST ON NR 2 ENGINE.  THE EN	GINE WAS SHUTDOWN AND THE AIRCRAFT CONTINUED TO DESTINATION WITHOUT FURTHER PROBLEM. MAINTENANCE DETERMINED THE LEAK SOU	RCE TO BE FROM THE MANIFOLD DRAIN COLLECTOR. THE MANIFOLD WAS CAPPED AND THE AIRCRAFT COMPLETED A SATIFACTORY GROUND RUN	 BEFORE RETURN TO SERVICE. (TC NR 20061218006)			2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007050700111	20070507	00111	NE  	2007	5	7	CA061218007      	1	20061202	G	7931		OIL SYSTEM      			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA								638214			(CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS.  AS THE AIRCRAFT WAS APPROACHING THE LOG LANDING WITH 	A LOAD, THE FLIGHT CREW WERE ALERTED BY A LOW OIL PRESSURE WARNING LIGHT FOR THE NR (2) ENGINE. A SCAN OF THE CORRESPOND	ING OIL PRESSURE INDICATOR CONFIRMED THE ENGINE OIL PRESSURE HAD DROPPED TO 20 PSI. AS THE PILOT RELEASED THE LOAD OF LO	GS ON THE LOG LANDING THE OIL PRESSURE RETURNED TO NORMAL. THE FLIGHT CREW ELECTED TO RETURN TO THE SERVICE LANDING TO H	AVE THE MAINT PERSONNEL INVESTIGATE THE PROBLEM. ENROUTE THE LOW OIL PRESSURE LIGHT ILLUMINATED AGAIN WITH THE CORRESPON	DING OIL PRESSURE INDICATION DROPPING TO 20 PSI. AT THIS TIME THE FLIGHT CREW ELECTED TO SHUTDOWN THE NR (2) ENGINE AS A	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2007012500266	20070125	00266	EA  	2007	1	25	CA061218008      	2	20061216	G	8530	05K21108	SLEEVE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CYLINDER	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				930  				RL90768A			(CAN) DURING INSPECTION OIL WAS NOTED ON THE BOTTOM COWL OF ENGINE. UPON CLOSER INSPECTION,  NR 4 CYLINDER WAS FOUND TO 	BE WET AT THE CYLINDER TO HEAD FLANGE. AFTER CLEANING, OIL WAS SEEN TO BE SEEPING FROM FLANGE AREA. THERE WAS NO VISIBLE	 CRACK SO DYE PENETRANT WAS CARRIED OUT, AT THIS TIME A PINHOLE WAS REVEALED. COMPRESSION WAS GOOD DURING THE INSPECTION	, THE JUG WAS CHANGED OUT FOR A NEW ONE. (TC NR 20061218008)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007050700112	20070507	00112	CE  	2007	5	7	CA061218009      	1	20061215	G	5520	1156100103	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				958  							(CAN) DURING COMPLIANCE WITH SB 2145, CHANGED OUT THE DUE TORQUE TUBES AND REPLACE THEM WITH INSPECTED ONES. WHEN THE LT	 WAS REMOVED A CRACK WAS NOTED GOING FROM THE TAPER PIN HOLE TO THE EDGE OF THE TORQUE TUBE MOUNT BRACKET. IT APPEARS TH	AT THE PIN WAS OVER-TORQUED DURING ASSEMBLY LEADING TO THE CRACK. (TC NR 20061218009)				1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007050700192	20070507	00192	NE  	2007	5	7	CA061218010      	1	20061121	G	5302	NAS146A37	BOLT            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					TAIL BOOM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS.  THE YARDING PROFILE WAS A DOWN HILL FLIGHT FROM THE H	ARVEST CUT BLOCK TO A ROAD SIDE LOG LANDING. AFTER ENCOUNTERING DOWN FLOWING WIND CONDITIONS THROUGH OUT THE FIRST LOGGI	NG CYCLE OF THE DAY THE FLIGHT CREW ELECTED TO SHUTDOWN AND WAIT FOR MORE FAVORABLE WIND CONDITIONS.  DURING A ROUTINE P	OST FLIGHT INSPECTION OF THE AIRCRAFT, THE MAINTENANCE PERSONNEL WERE CHECKING THE HORIZONTAL STABILIZER FOR GENERAL CON	DITION AND SECURITY WHEN THEY DISCOVERED IT TO BE LOOSE. FURTHER INSPECTION OF THE STABILIZER TO PYLON FORWARD ATTACHMEN	T FITTINGS REVEALED THE BOLT THAT ATTACHES THE (2) FITTINGS WAS MISSING. A VISUAL INSPECTION OF THE ENTIRE AIRCRAFT UNCO	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
2007050700113	20070507	00113	CE  	2007	5	7	CA061218011      	1	20061215	G	5520	1156100103	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				988  							(CAN) DURING COMPLIANCE WITH SB 2145 (REMOVED THE DUE TUBES TO SEND OUT FOR NDT AND REPLACE WITH INSPECTED SERVICEABLE O	NES), A CRACK WAS DISCOVERED RADIATING FROM ONE OF THE TAPER PIN HOLES TO THE EDGE OF THE ATTACH BOSS ON THE LT TUBE. IT	 APPEARS THAT THE TAPER PIN WAS OVERTORQUED DURING ASSEMBLY CAUSING THE CRACK. THE TUBE HAS BEEN SCRAPPED. (TC NR 200612	18011)			1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007012500293	20070125	00293	NE  	2007	1	25	CA061218012      	2	20061215	G	7261		OIL SYSTEM      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	CONTAMINATED    	W				A				UNSCHED LANDING         				C	J		F.O.D.                    	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			8331 	215  							(CAN) NON ALLOWABLE DEBRIS FOUND IN OIL SYSTEM, CONFIRMED BY OIL ANALYSIS REPORT. ENGINE SENT BACK TO MANUFACTURER FOR I	NVESTIGATION. ENGINE EXCHANGED, WILL NOT BE SENT BACK TO THE OPERATOR. ENGINE TSO 214.7 TSN 8330.9 (TC NR 20061218012)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007012500294	20070125	00294	NM  	2007	1	25	CA061218013      	1	20061129	G	3260	H1010153	SWITCH          			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					MLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE WITH LANDING GEAR SELECTED DOWN.  VISUALLY INSPECTED TO ENSURE NOSE GEAR 	WAS DOWN AND LOCKED THROUGH VIEWPORT AND CONFORMED NOSE GEAR WAS DOWN AND LOCKED.  AS A PRECAUTIONARY ACTION NOSE GEAR L	OCK SWITCH REMOVED AND REPLACED ALONG WITH CONNECTOR D298 IAW MM 32-61-71. FUNCTION CHECKED SERVICEABLE. NO FURTHER OCCU	RRENCE REPORTED. (TC NR 20061218013)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007012500295	20070125	00295	GL  	2007	1	25	CA061218014      	3	20061218	G	6111	A163395	SEAL            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				226  		810380			810380		(CAN) BLADE GREASE SEAL FAILED. GREASE LEAVING HUB. PROP REMOVED AND SENT TO REPAIR FACILITY WHERE NEW SEALS WERE INSTAL	LED. PROP REINSTALLED AND A/C SERVICEABLE (TC NR 20061218014).					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2007012500296	20070125	00296	EA  	2007	1	25	CA061218015      	1	20061218	G	2913		PUMP            			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					HYDRAULIC  SYS	DAMAGED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			1371 			2353858					(CAN) LOST OF NR 3 SYSTEM HYDRAULIC FLUID IN FLIGHT. THE NR 3B PUMP HAS FAILED ON FLANGE GASKET.  THE PUMP HAS BEEN REPL	ACED AND A\C RETURNED TO SERVICE. A/C HOURS:  6816:27 A/C CYCLES ; 7302  (TC NR 20061218015)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050700114	20070507	00114	SW  	2007	5	7	CA061218016      	1	20061108	G	2910	70060T000X186	HOSE            			BELL  	427   	427         	1182207	SW  										HYD SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HOSE ASSEMBLY 70-060T000X186 (18.750 INCHES LONG) RUBS AGAINST SUPPORT 427-001-005 WHEN THE COLLECTIVE STICK IS DO	WN AND THE CYCLIC STICK IS  CENTER AND FULL FORWARD. (TC NR 20061218016)					1	G	7	1 	3U				R00001RC					 
2007012500297	20070125	00297	EA  	2007	1	25	CA061218017      	1	20061117	G	7603	2100140003	GEARBOX         			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30015	NE  					THROTTLE	STIFF           	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			4134 								(CAN) PILOT REPORTED LT POWER LEVER STIFF TO MOVE AS COMPARED TO RT. TROUBLESHOOTING REVEALED THAT INPUT SHAFT ON GEARBO	X ATTACHED, (COULD BARELY BE RETACTED BY HAND).  SB601-0583 (TC NR 20061218017)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500298	20070125	00298	NM  	2007	1	25	CA061218018      	1	20061218	G	2710	82740191053	ROD             			DHAV  	DHC8  	DHC8102     	2809003	NM  										AILERON	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK, A INSPECTOR FOUND THE AILERON INPUT ROD NOT PROPERLY INSTALLED ON BOTH SIDE LT AND RT AILERON.  TH	E ROD END WAS FABRICATED WITH A CUT OUT FOR AVOID THE CONTACT BETWEEN THE ROD END AND THE QUADRANT SHAFT.  ON THE SAME A	/C, WE FOUND THE BOTH ROD DIRECTLY IN CONTACT WITH THE SHAFT IN FULL TRAVEL POSITION.  ATTACH 2 VERY CLEAR PICTURES WITH	 THIS FDR. (TC NR 20061218018)			2	H	7	2 	4T			RT	A13NM   					 
2007012500299	20070125	00299		2007	1	25	CA061218019      	4	20061218	G	6113	05503214	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50   								(CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATES	T SB.  THE (FORWARD SPINNER BULKHEAD) IS CRACKED AGAIN WITH LESS THEN 50 HOURS TSN, CRACKS RADIATING .2500 TO 1 INCH FRO	M 3 OF THE 6 HOLES.   YOU HAVE TO LOOK VERY CARFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND 	HIDE UNDER THE FACTORY PRIMER. (TC NR 20061218019)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007012500300	20070125	00300	EA  	2007	1	25	CA061218020      	1	20061124	G	6123	8190026	PRESSURE SWITCH 			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AUTOFEATHER	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) ON INVESTIGATION OF THE REPORTED AUTOFEATHER DEFECT, THE LT ENGINE PRESSURE SWITCH, PN 8190026, WAS FOUND TO BE DE	FECTIVE. REPLACEMENT OF THE COMPONENT CURED THE PROBLEM WHICH IS CONSIDERED TO BE AN ISOLATED RANDOM FAILURE. (TC NR 200	61218020)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007012500321	20070125	00321	NM  	2007	1	25	CA061219001      	1	20061126	G	7500	655881313	DUCT            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					BLEED AIR SUPPLY	DISCONNECTED    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) LOWER AFT BODY HEAT WARNING LIGHT ILLUMINATED IN FLIGHT. FLIGHT CREW FOLLOWED EMERGENCY CHECKLIST AND LIGHT EXTING	UISHED WHEN NR 3 BLEED AND THRUST LEVER CLOSED.  UPON INVESTIGATION MAINTENANCE DISCOVERED SUPPLY DUCT FORWARD OF STA 11	83 DISCONNECTED AND DUCT DAMAGED. DUCT AND CLAMPS REPLACED, ENGINE RUNS AND LEAK CHECKS CARRIED OUT. NO FURTHER PROBLEMS	 NOTED. (TC NR 20061219001)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007012500322	20070125	00322	NM  	2007	1	25	CA061219002      	1	20061116	G	5610	58935733	WINDOW          			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SERVICING THE L4 WINDOW WAS FOUND CRACKED.  WINDOW REPLACED IAW MM 56-11-31, FUNCTION CHECKED SERVICEABLE W	ITH NO FURTHER FAULTS REPORTED. (TC NR 20061219002)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007012500324	20070125	00324	NM  	2007	1	25	CA061219003      	1	20061122	G	3242		DISC            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BRAKE ASSY	DETACHED        	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						A0726					(CAN) WHILE TOWING AIRCRAFT TO LINE IT WAS REPORTED THAT NR 1 BRAKE WAS TRYING TO LOCK UP. UPON REMOVAL OF BRAKE ASSEMBL	Y THE DISC RING WAS FOUND DETACHED FROM THE ASSEMBLY. A RIVET WAS FOUND SHEARED AND THE DISC RING CAME APART.  FURTHER T	O FOLLOW AFTER STRIP REPORT IS RECEIVED FROM OVERHAUL FACILITY. (TC NR 20061219003)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007050700115	20070507	00115	GL  	2007	5	7	CA061219004      	2	20061121	G	7323	23036657	GOVERNOR        			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	ERRATIC         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1889 							(CAN) HIGH TIME GOVERNOR TSO 1889.2, REMOVED FOR O/H DUE TO ERRATIC RPM   REPLACED WITH NEW GOVERNOR PN 23076061 SN HR47	346 TSN 0:0 (TC NR 20061219004)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007050700116	20070507	00116	GL  	2007	5	7	CA061219005      	2	20061121	G	7323	718513	ACTUATOR        			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REMOVED LINEAR ACTUATOR PN 7185-13 SN 0296A DUE TO INTERNAL LOCKING CLIP FALLING OFF. INSTALLED SERVICEABLE USED L	INEAR ACTUATOR PN 206-062-721-003 SN 11842. (TC NR 20061219005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007050700117	20070507	00117	SO  	2007	5	7	CA061219006      	1	20060123	G	2497	KA39	CONVERTER       			PIPER 	PA31  	PA31350     	7103110	SO  										NR 1 NAV COMM	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) VOLTAGE CONVERTER SUPPLYING POWER TO NR 1 NAV COM FAILED CAUSING LOSS OF POWER TO RADIO (TC NR 20061219006)						1	L	7	2 	3O				A20SO   					 
2007050700118	20070507	00118	CE  	2007	5	7	CA061219007      	1	20061106	G	2497	1385	RELAY           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	OVERVOLTAGE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF ON CLIMB-OUT THE RT GENERATOR CHARGING SYSTEM FAILED. THE AIRCRAFT RETURNED TO BASE. SYSTEM TROUBLES	HOOTING CARRIED OUT AND FOUND THE OVER VOLTAGE RELAY HAD FAILED. (TC NR 20061219007)					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2007012500326	20070125	00326	CE  	2007	1	25	CA061219009      	1	20060913	G	8010	S1991A1	RELAY           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	STARTER	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) POWER ON STARTER WITH WHEN MASTER SWITCH ON.  FOUND MASTER RELAY STUCK IN POSITION. NEW RELAY S-1991-A1 INSTALLED.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007012500327	20070125	00327	SW  	2007	1	25	CA061219010      	1	20061215	G	8011	3108281	INSERT          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	STARTER	WORN            	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) UPON START PROP STARTED TO ROTATE AND THEN STOPPED.  STARTER CONTINUED TO TURN.  TORLON INSERT WAS WORN ENOUGH THA	T THE STARTER TURNED INSIDE THE TORLON INSERT.  INSERT WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 2006121	9010)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007012500328	20070125	00328	NE  	2007	1	25	CA061219011      	2	20061107	G	7530		LINE            			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       	 	NE  					P3	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING A MAINTENANCE TEST FLIGHT A LOUD NOISE WAS HEARD ACCOMPANIED BY AN ENGINE FIRE WARNING.  THE ENGINE WAS SHU	TDOWN IN FLIGHT AND FIRE BOTTLES DISCHARGED.  SUBSEQUENT INSPECTION REVEALED A FRACTURED ENGINE P3 BLEED AIR TUBE. (TC N	R 20061219011)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007012500329	20070125	00329	NE  	2007	1	25	CA061219012      	2	20061022	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						UNKNOWN         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) IN FLIGHT A LOUD NOISE WAS HEARD AND THE WINDSHIELD BECAME COVERED IN OIL.  A FORCED LANDING FOLLOWED RESULTING IN	 AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007012500330	20070125	00330	EA  	2007	1	25	CA061219013      	2	20061103	G	7530	3035279	TUBE            			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	FCU	FRACTURED       	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) ENGINE POWER ROLLED BACK UNCOMMANDED DURING CLIMB.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO	 POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PRESSURE LINE TO THE FUEL CONTROL UNIT. (TC NR 20061	219013)				2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2007012500331	20070125	00331		2007	1	25	CA061219014      	3	20061109	G	6110		SEAL            			BAG   	ATP   	ATP         	       	EU  	PWA   	PW120 	PW126A      	 	NE  					PROPELLER SHAFT	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE OIL PRESSURE BEGAN TO FLUCTUATE IN THE RED BAND.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND 	THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A LEAK AT THE PROP SHAFT OIL SEAL.  MFG WILL	 INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219014)				2	L	7	2 	4T	4	T	RT	A27NM   	E2ONE				 
2007012500336	20070125	00336	EA  	2007	1	25	CA061219015      	2	20061101	G	7200		ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  						DAMAGED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) ON TAKEOFF, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE.  THE FIGHT CONTINUED AND ON DESCENT ENGINE OIL PRESSURE FEL	L TO ZERO RESULTING IN A PROPELLER AUTOFEATHER.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  GROUND INSPECTION REVEALED INTERNAL	 ENGINE DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2007012500338	20070125	00338	CE  	2007	1	25	CA061219016      	1	20061116	G	7312	311705601	HEATER          			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FUEL	LEAKING         	W				E				ENGINE SHUTDOWN         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING FLIGHT ENGINE FUEL PRESSURE BEGAN TO FLUCTUATE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS 	SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT C	AUSE ONCE DETERMINED. (TC NR 20061219016)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007012500340	20070125	00340	NE  	2007	1	25	CA061219017      	2	20061115	G	7310		MANIFOLD        			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					FUEL SYSTEM	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A	K	J	FLAME/FIRE                	FLUID LOSS                	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN) ON DESCENT THE ENGINE FIRE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  POST FLIGHT INSPECTION REVEAL	ED LEAKAGE FROM THE ENGINE FUEL MANIFOLD AND EVIDENCE OF BURNING OF THE ENGINE INNER BYPASS DUCTING. (TC NR 20061219017)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007012500344	20070125	00344	EA  	2007	1	25	CA061219020      	2	20061115	G	7200		ENGINE          			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A27      	52043	EA  						FAILED          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								24085			(CAN) DURING TAXI, THE ENGINE EMITTED A NOISE AND LOST POWER.  SUBSEQUENT INSPECTION REVEALED INTERNAL ENGINE DAMAGE.  M	FG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2007012500366	20070125	00366	NE  	2007	1	25	CA061219021      	2	20061120	G	7261	JT5D5	ENGINE          			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA						100119		100119			(CAN) THE ENGINE OIL FILTER BYPASS INDICATOR ACTIVATED IN DESCENT AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL INVES	TIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007012500367	20070125	00367	EA  	2007	1	25	CA061219022      	2	20060925	G	7261	PT6A64	ENGINE          			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  						LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								111106			(CAN) IN FLIGHT THE ENGINE OIL TEMPERATURE INCREASED ACCOMPANIED BY A LOSS OF OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN 	FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION OF THE OIL SYSTEM, INTERNAL OIL LEAKAGE AND SEIZURE OF THE R	EDUCTION GEAR BOX.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2007012500368	20070125	00368	EU  	2007	1	25	CA061219023      	1	20061123	G	7712		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE THE ENGINE EXPERIENCED TORQUE FLUCTUATIONS ACCOMPANIED BY INCREASED ITT TEMPERATURES.  THE ENGINE WAS SH	UTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVIS	E OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219023)				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007012500369	20070125	00369	NE  	2007	1	25	CA061219024      	2	20061126	G	7250		TURBINE BLADES  			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	DAMAGED         	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKE-OFF, THE ENGINE FIRE WARNING ACTIVATED AND THE CREW SHUT THE ENGINE DOWN IN FLIGHT AND DISCHARGED THE FIRE	 BOTTLES.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES AND	 METAL IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061219024)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007012500370	20070125	00370	SW  	2007	1	25	CA061219025      	1	20061120	G	5610	2719442003	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			3868 								(CAN) DURING FLIGHT THE LT COCKPIT HEATED WINDSHEILD SHATTERED BUT REMAINED INTACT. THE AIRCRAFT IMMEDIATLY RETURNED TO 	THE AIRPORT AND THE WINDOW WAS REPLACED BY MAINTENANCE.  NO CAUSE COULD BE DETERMINED AS TO WHY THIS WINDOW SHATTERED. (	TC NR 20061219025)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2007012500371	20070125	00371	EA  	2007	1	25	CA061219026      	2	20061128	G	7250		TURBINE BLADES  			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  SUBSEQUENT INSPECTION REVEALED FRACTURED TURBINE BLADES	 AND VANES AND A PUNCTURED GAS GENERATOR CASE.  LIGHT IMPACT DAMAGE WAS FOUND ON THE AIRCRAFT WING LEADING EDGE AND FUSE	LAGE WINDOWS.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219026)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007012500372	20070125	00372	SW  	2007	1	25	CA061219027      	1	20061215	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			1299 								(CAN) DURING FLIGHT THE RT COCKPIT HEATED WINDSHEILD SHATTERED BUT REMAINED INTACT. THE FLIGHT CREW DECALRED AN EMERGENC	Y AND RETURNED TO THE AIRPORT UNEVENTFULLY. THE WINDOW WAS REPLACED BY MAINTENANCE. THE CREW EXPLAINED THAT PRIOR TO THE	 WINDOW SHATTERING A ELECTRICAL DISCHARGE WAS WITNESSED GOING ACROSS THE WINDSHIELD. OTHER THAN THE STATIC DISCHARGE, NO	 CAUSE FOR THE WINDOW TO SHATTER HAS BEEN DETERMINED. (TC NR 20061219027)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2007012500373	20070125	00373	NM  	2007	1	25	CA061219028      	1	20061213	G	5230	6557204520	ROD             			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CARGO DOOR	BENT            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON ROTATION, NR 2 CARGO DOOR LIGHT ILLUMINATED.  NR 3 ENGINE SURGED AND A SHUTDOWN PROCEDURE WAS CARRIED OUT. THE 	A/C LANDED SAFELY, WHERE A LEVEL 1 BORESCOPE INSPECTION WAS CARRIED OUT, WITH NO FOD DAMAGE FOUND. UPON INSPECTION, THE 	CARGO DOOR WAS FOUND TO BE OPEN BUT IN THE LATCHED POSITION. THE CARGO DOOR WOULD NOT CLOSE. FURTHER INSPECTION FOUND 4 	BENT DOOR HINGE ROD ARMS. THE NR 2 CARGO DOOR, HINGE ARMS AND POSITIONING SWITCH WERE REPLACED. THE ASSEMBLY FUNCTIONED 	PROPERLY AND THE A/C WAS RETURNED TO SERVICE.   (TC NR 20061219028)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007012900345	20070129	00345	EU  	2007	1	29	CA061219029      	2	20061210	G	7310		FUEL            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	FUEL SYSTEM	CONTAMINATED    	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT OBSERVED ENGINE NR 1 FUEL FILTER DE-ICING WARNING LIGHT ILLUMINATED IN CRUISE FLIGHT. SHORTLY AFTER APPLYING	 FUEL HEAT, ENGINE NR 1 QUIT.  PILOT FEATHERED PROPELLER AND LANDED UNEVENTFUL. MAINT REMOVED ENGINE NR 1 LOW PRESSURE F	UEL FILTER AND FOUND A LACK OF FUEL. MAINT THEN DRAINED CONTENTS OF NR 1 FUEL COLLECTOR TANK INTO A BUCKET AND OBSERVED 	.5 LITER OF WATER PRESENT IN FUEL. MAINT FILLED AND DRAINED TANK 3 MORE TIMES TO ENSURE ALL WATER CONTAMINATION HAD BEEN	 REMOVED. NR 1 ENGINE FUEL SYS WAS RESTORED IAW MM. ENGINE WAS RUN AND TESTED SERVICEABLE. MAINT CHECKED FOR WATER CONTA	MINATION IN THE LT WING SUMP, RT WING SUMP AND NR 2 FUEL COLLECTOR TANK AND FOUND NO EVIDENCE OF WATER. OPERATOR CHECKED	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007012500374	20070125	00374	SW  	2007	1	25	CA061220001      	1	20061220	G	2750	21903	CABLE           			BBAVIA	8     	8GCBC       	1220803	SW  										FLAP HANDLE ASSY	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FOUND FRAYED AT FWD END WHERE CABLE BENDS HARD OFF OF HANDLE TRACK TO FWD CABLE ATTACH POINT. (TC NR 2006122	0001)					1	H	7	1 	3O				A21CE   					 
2007012500375	20070125	00375	NM  	2007	1	25	CA061220002      	1	20061127	G	7931	30C2083	TRANSDUCER      			AMD   	FALC50	FALCON2000  	2730170	NM  										OIL PRESS TRANSD	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) ENGINE OIL PRESSURE INDICATION FLUCTUATED IN FLIGHT AND FELL BELOW 35 PSI.  AS A PRECAUTION, THE ENGINE WAS SHUTDO	WN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED A FAULTY MAIN OIL PRESSURE TRANSDUCER. (TC NR 20061220002)					2	K	7	2 	4F			RT	A50NM   					 
2007012500380	20070125	00380	EA  	2007	1	25	CA061220003      	2	20061022	G	7230		TURBINE BLADES  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								41691			(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A DECAY ON ENGINE PARAMETERS.  THE ENGINE WAS SHUTDOW	N IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO COMPRESSOR AND POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGAT	ION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2007012500382	20070125	00382	EA  	2007	1	25	CA061220004      	2	20061128	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  						MALFUNCTIONED   	W				C	E			ABORTED TAKEOFF         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA								32399			(CAN) THE ENGINE EMITTED A LOUD NOISE ON TAKE-OFF ROLL.  TAKE-OFF WAS ABORTED AND THE ENGINE SHUTDOWN.  MFG WILL MONITOR	 INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061220004)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2007012500383	20070125	00383	NE  	2007	1	25	CA061220005      	2	20061010	G	7210		BOLT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					1ST STAGE CARRIE	SHEARED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND THEN DECAY TO ZERO.  THE ENGINE WAS SHUTDOWN IN  F	LIGHT.  SUBSEQUENT INVESTIGATION REVEALED A SHEARED 1ST STAGE REDUCTION GEAR BOX CARRIER BOLT. (TC NR 20061220005)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007012500384	20070125	00384	CE  	2007	1	25	CA061220006      	1	20061214	G	2840	66082813	INDICATOR       			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					FUEL SYSS	CHAFED          	W				O				OTHER                   				W	J		INADEQUATE Q C            	WARNING INDICATION        		DE	DESCENT        	1			CA			4429 	4429 							(CAN) LT FUEL QUANTITY CAUTION LIGHT ILLUMINATES DURING DESCENT. FAULT CODE INDICATES PROBES NR 3 DEFECTIVE.  PROBE NR 3	 REPLACED AND FURTHER INVESTIGATION REVEALED THAT THE WIRING IN LT TANK FOUND CHAFING AT (2) PLACES (WS 116.0) ON TOP OF	 FUEL PILOT VALVE LINE DUE HARNESS ASSEMBLY WAS NOT SUPPORTED PROPERLY DURING THE PRODUCTION ASSEMBLY PROCESS.  NO CHAFI	NG WAS FOUND IN RT FUEL TANK, BUT SIMILAR DEFECTIVE ATTACHMENT WAS FOUND. A SERVICE CONDITION REPORT (SCR NR 268343) WAS	 DONE TO AIRCRAFT.  (TC NR 20061220006)		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007012500385	20070125	00385		2007	1	25	CA061220007      	1	20061218	G	3246		BEARING         								CFMINT	CFM567	CFM567B22   	13802	NE  					MLG WHEEL	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			*    								(CAN) ON DECEMBER 18, THE CREW REPORTED THAT SOME SLIGHT DRAG WAS FELT IN BRAKING UPON ARRIVAL. INVESTIGATION REVEALED W	HAT APPEARS TO BE A NR 4 WHEEL, IB BEARING FAILURE. AN INVESTIGATION INTO THE ROOT CAUSE OF THE FAILURE HAS BEEN INITIAT	ED AND THIS ITEM WILL BE UPDATED ONCE THOSE RESULTS ARE AVAILABLE (TC NR 20061220007)									4	F			E00055EN				 
2007012500386	20070125	00386	NM  	2007	1	25	CA061220008      	1	20061216	G	2913	623303	PUMP            			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA						MX607076					(CAN) LT ACMP LEAKING FLUID CAUSING LOSS OF HYDRAULIC QUANTITY AND SYSTEM PRESSURE.  AIRCRAFT LANDED AND WAS TOWED OFF T	HE RUNWAY DUE TO NO NOSE WHEEL STEERING. (TC NR 20061220008)					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2007012500387	20070125	00387	WP  	2007	1	25	CA061220009      	2	20061219	G	7530	2762026311	LINE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	BLEED AIR	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ENGINE FIRE WARNING LIGHT ILLUMINATED. THE ENGINE WAS SHUTDOWN. THE FIRE LIGHT EXTINGUISHED, WHE	N THE STOP FEATHER LEVERS WERE PULLED BACK. THE CREW BLEW A FIRE BOTTLE, DECLARED AN EMERGENCY AND LANDED.  A DAMAGED FI	RE DETECTOR (1000 DEG F) P/N 17343-61-600 WAS FOUND AND A CRACKED BLEED AIR LINE P/N 27-62026-311  (TC NR 20061220009)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007012500388	20070125	00388	NM  	2007	1	25	CA061221001      	1	20061216	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			1754 								(CAN) DURING DESCENT NR 1 ENG HYD PUMP CAUTION LIGHT ILLUMINATED. CONTINUED TO DESTINATION AIRPORT FOR LANDING WITH OUT 	INCIDENT. MAINTENANCE CONFIRMED NR 1 ENG DRIVEN PUMP INTERNAL FAILURE.  CASE DRAIN AND PRESSURE FILTERS CONTAMINATED WIT	H METAL. (TC NR 20061221001)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007012500389	20070125	00389	CE  	2007	1	25	CA061221002      	1	20061218	G	5210	5043003211	LATCH           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	PAX DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT THE CREW NOTICED AIR LEAKING OUT THE PASSENGER DOOR AND THE AIRCRAFT BEGAN TO DEPRESSURIZE. THE CREW	 DESCENDED TO 9000 FT FOR THE REMAINDER OF THE FLIGHT AND LANDED WITHOUT FURTHER INCIDENT. UPON LANDING THEY NOTICED THE	 LT UPPER DOOR HOOK WAS UNSERVICEABLE. FURTHER INSPECTION BY MAINTENANCE REVEALED THAT THE AFT CABIN DOOR HOOK LATCH BRA	CKET ATTACHMENT PIN P/N MS20392-2C35 HAD FAILED. THIS FAILURE RENDERED THE DOOR HOOK UNSERVICEABLE. THE DAMAGED WAS NOT 	LIMITED TO THE CLEVIS PIN IT WAS ALSO FOUND THAT THE MOUNTING BRACKET WAS BENT AND THE BUSHING WAS LOOSE.  THE FRAME, TH	E BUSHING AND THE PIN WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20061221002)	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2007050700121	20070507	00121	CE  	2007	5	7	CA061221003      	1	20061218	G	3230	1153800025	MOTOR           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	LANDING GEAR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING FLIGHT THE LANDING GEAR WOULD NOT EXTEND AND AN EMERGENCY WAS DECLARED. A MANUAL GEAR EXTENSION WAS COMPLET	ED THE (3) GREEN LIGHTS ILLUMINATED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.   MAINTENANCE INVESTIGATED AND FOU	ND THAT THE LANDING GEAR MOTOR HAD FAILED. THE MOTOR WAS REPLACED, GEAR SWINGS COMPLETED AND THE AIRCRAFT RETURNED TO SE	RVICE. THIS MOTOR HAS A 2500 LANDING OVERHAUL INTERVAL AND ONLY HAD 390 LSO.  (TC NR 20061221003)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007050700163	20070507	00163		2007	5	7	CA061221004      	4	20061218	G	2210		AUTOPILOT SYS   			BELL  	412   	412EP       	1182205	SW  											MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) DURING AN APPROACH TO RUNWAY 24 RIGHT AT THE MFG PLANT,  BOTH AUTO-PILOTS WENT OFF LINE. THE MASTER CAUTION LIGHTS	 WERE OFF ON THE AUTO-PILOTS. A/C WAS ABLE TO LAND. (TC NR 20061221004)					1	G	7	2 	4U				H4SW    					 
2007012500390	20070125	00390	EA  	2007	1	25	CA061221005      	1	20061221	G	2820	AE7010000N130	HOSE            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL SYS	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			15   								(CAN) UPON SHUTDOWN ON THE RAMP, CREW NOTICED A STRONG SMELL OF FUEL WHEN MAIN CABIN DOOR WAS OPENED.  LT MAIN GEAR WAS 	SITTING IN A PUDDLE OF FUEL.  FOUND ENGINE FUEL FEED AUX TANK LINE RUPTURED.  (IPC 28-21-16 NR 285) (TC NR 20061221005)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500391	20070125	00391	EA  	2007	1	25	CA061221006      	1	20061218	G	2700	C6R1806135	CABLE ASSY      			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLT CONTROLS	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN AN OPERATOR TRIED TO INSTALL ONE OF THESE CABLE ASSEMBLIES HE FOUND THAT THE END THAT ENGAGES THE SERVO CAPST	AN WOULD NOT FIT PROPERLY SO THAT THE LOCK SCREW COULD BE INSTALLED. UPON INVESTIGATION IT WAS FOUND THAT THE ORIGINAL D	RAWING FOR THE CABLE ASSEMBLY PICTORIALLY SHOWED THIS CABLE END SWAGED ON INCORRECTLY. THE DRAWING HAS BEEN CORRECTED AN	D A SERVICE LETTER WILL BE ISSUED TO CHECK FOR ANY INCORRECTLY INSTALLED CABLE ASSEMBLIES OR SPARES ON HAND THAT MAY BE 	AFFECTED. (TC NR 20061221006)		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007012500392	20070125	00392	NE  	2007	1	25	CA061222002      	2	20061217	G	7310	AE7010000N0130	HOSE            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF348E5A1   	30015	NE  					FUEL SYSTEM	TORN            	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) FUEL LEAK WAS FOUND FROM HOSE ASSY P/N AE7010000N0130 AFTER THE SECOND ENGINE RUN.  NOTE: PRIOR RUN, LINE WAS REPL	ACED IAW (DISCLOSURE LETTER), BATCH RECALL DUE TO DEFECTIVE HOSE (BATCH NR 8740850) (TC NR 20061222002)					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2007012500393	20070125	00393	EU  	2007	1	25	CA061222003      	1	20061214	G	2800	0725145	ELEMENT         		0725185     	AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					REFUEL COUPLING	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) WHILE REFUELING, IT WAS NOTICED THAT FUEL WAS LEAKING FROM THE ELEMENT ASSY.  INITIALLY IT WAS THOUGHT THAT THE CO	UPLING HAD BEEN DAMAGED BUT ON INSPECTING THE PART IT WAS DETERMINED THAT THE 8 SECURING SCREWS HAD ROTATED APPROX A HAL	F TURN LOOSE. (TC NR 20061222003)				2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2007050700196	20070507	00196	SW  	2007	5	7	CA061222004      	1	20061204	G	6220	204011116001	NUT             			BELL  	205   	205B        	       	SW  	LYC   	T53   	T5317A      	41549	NE  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14698			A49					(CAN) THE ACORN NUTS WERE SENT OUT FOR NDT IAW THE REQUIREMENT OF THE OVERHAUL OF THE M/R HEAD ASSY.  THE NDT SHOP FOUND	 A CRACK DEVELOPING NEAR THE BASE IN THE TRANSITION AREA OR CURL  OF THE DOME AND THE GEAR PART OF THE ACORN NUTS. THE E	STIMATED TIME ON THE ACORN NUTS IS 14698 HOURS IAW M/R HEAD ASSY. (TC NR 20061222004)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007012500394	20070125	00394	GL  	2007	1	25	CA061222005      	2	20061208	G	7261		OIL SYSTEM      			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2 ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE THE CREW OBSERVED LOW OIL QUANTITY ON THE NR 2 ENGINE. FLUID WAS OBSERVED DEPARTING THE DRAIN MAST.  THE E	NGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND AN AIR LEA	K OCCURING AT THE OIL QUANTITY TRANSMITER ACCESS PANEL ON THE OIL TANK.  FOAMING RESULTED DUE TO LOSS OF PNEUMATIC HEAD 	PRESSURE CAUSING THE SYSTEM TO VENT.  THE ACCESS PANEL BOLTS WERE RETORQUED ENGINE OIL REPLENISHED.  THE AIRCRAFT WAS GR	OUND RU AND RETURNED TO SERVICE.		2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007012500395	20070125	00395	EU  	2007	1	25	CA061222006      	1	20061209	G	7712	567775080	INDICATOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	TORQUE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) ENROUTE THE CREW OBSERVED DRAMATIC FLUCTUATION IN THE NR 2 ENGINE TORQUE INDICATOR. THE AIRCRAFT RETURNED TO POINT	 OF DEPARTURE WITHOUT INCIDENT. AFTER TROUBLE SHOOTING MAINTENANCE REPLACED THE NR 1 TORQUE INDICATOR AND THE SYSTEM WAS	 CHECKED SERVICEABLE. (TC NR 20061222006)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007012500396	20070125	00396	CE  	2007	1	25	CA061222007      	1	20061220	G	2435	3022376	SEAL            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT NOTICED OIL PRESSURE FLUCTUATIONS IN CRUISE FLIGHT. ENGINE LIMITS NOT EXCEEDED AND THE AIRCRAFT LANDED AT DE	STINATION. ENGINE OIL WAS LOST THROUGH A LEAKING STARTER GENERATOR DRIVE GARLOC SEAL. SEAL REPLACED WITH NEW PN 3059046-	01 IAW MFG CATEGORY 8 (OPTIONAL) SB 3420. GROUND RUNS C/O SATISFACTORY AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061222	007)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2007012500397	20070125	00397	EA  	2007	1	25	CA061225001      	1	20061223	G	7797	2572152545A	CONNECTOR       			CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF34*       	 	NE  					RT ENGINE	SHORT           	W				O				OTHER                   				E	N		VIBRATION/BUFFET          	FALSE WARNING             		AP	APPROACH       	1			CA											(CAN) FLIGHT CREW REPORTED ENGINE VIBRATION.  MAINTENANCE INSPECTION REVEALED A TAR LIKE SUBSTANCE ON ENGINE FAN BLADES.	  SUBSTANCE ALSO FOUND ON UNDERSIDE OF FLAPS BEHIND MAIN WHEELS.  SUBSTANCE WAS CLEANED OFF AND FAN LUBE AND RUNS WERE C	ARRIED OUT, NO FIX VIBES STILL FLUCTUATING BETWEEN .2 AND 5.7 AT IDLE.  N1 SENSORS SWAPPED STILL NO FIX.  AFTER FURTHER 	INSPECTION ENGINE CONNECTOR J554 FOR THE RT ENGINE LOCATED BEHIND THE AFT CARGO BULKHEAD WAS FOUND TO HAVE AN INTERNAL S	HORT.  CONNECTOR REPLACED AND AIRCRAFT FOUND SERVICEABLE. (TC NR 20061225001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012500398	20070125	00398		2007	1	25	CA061227001      	4	20061219	G	3497	34440058	WIRE            			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					AIR COLLISION	BURNED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ON ARRIVAL, FLIGHT CREW REPORTED TCAS AND RA FAILURE FLAGS ON BOTH IVSIS DURING FLIGHT. WHILE TROUBLESHOOTING TCA	S FAILURE, SEVERAL BURNED WIRES WERE DISCOVERED IN A BUNDLE LOCATED BEHIND THE ATC1 AND TCA RACK (500VU). THE WIRE SUSPE	CTED OF CAUSING THE DAMAGE IS THE TCAS POWER SUPPLY WIRE 3444-0058 BETWEEN CONNECTOR 221VC AND TERMINAL BOARD 1487VT MOD	ULE AND PIN A. (REF A-310 AWM 34-44-01 PG 003 SHEET 1). ALL DAMAGED WIRES WERE REPLACED, CONNECTORS VERIFIED AND AS PREC	AUTION AND MFG RECOMMENDATION THE TCAS PROCESSOR AND TCAS POWER SUPPLY CIRCUIT BREAKER WERE REPLACED.  (TC NR 2006122700	1)	2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2007050700197	20070507	00197	CE  	2007	5	7	CA061227002      	1	20061226	G	7931	1013890235	TRANSMITTER     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	OIL PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) ENROUTE FROM RT OIL PRESSURE INDICATED 50 PSI. THERE WAS NO CORRESPONDING R LOW ANNUNCIATOR, DECLARED AN EMERGENCY	 AND PERFORMED A PRECAUTIONARY SHUTDOWN OF THE RT ENGINE.  RETURNED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT INDICATION	 TO A FAULTY OIL PRESSURE TRANSDUCER.  NEW TRANSDUCER INSTALLED, A/C GROUND RUN WITH NO FURTHER INDICATION PROBLEMS (TC 	NR 20061227002)			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007012500399	20070125	00399	EA  	2007	1	25	CA061227003      	2	20061222	G	8500		ENGINE          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2510 							(CAN) DURING SCHEDULED MAINTENANCE, AT A 200HR. INSPECTION, METAL FOUND IN OIL. METAL TURNED OUT TO BE FROM NR 3 CYLINDE	R CONNECTING ROD, LOWER BEARING. (TC NR 20061227003)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007012500400	20070125	00400	EA  	2007	1	25	CA061227004      	2	20061221	G	8500		ENGINE          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1452 							(CAN) DURING 50 HR. OIL CHANGE, HEAVY BRASS-LIKE MATERIAL WAS NOTED IN THE OIL FILTER. CYLINDER WAS REMOVED TO INSPECT E	NGINE CORE. CRANKSHAFT CENTER JOURNAL BEARING WAS FOUND TO BE DISINTEGRATING. ENGINE REMOVED FROM SERVICE. (TC NR 200612	27004)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2007012500401	20070125	00401	EA  	2007	1	25	CA061227005      	2	20061218	G	8520		CRANKSHAFT      			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1976 							(CAN) LT ENGINE DEVELOPED AN OIL LEAK FROM CRANKSHAFT SEAL. DURING SEAL REPLACEMENT, IT WAS NOTICED THAT THE CRANKSHAFT 	FLANGE WHERE PROPELLER BOLTS ON, WAS CRACKED FROM ONE LIGHTNING HOLE TO THE OTHER.  IT LOOKED AS IF THERE WAS AN INDENTA	TION ON THE BACK SIDE OF THE LIGHTNING HOLE. THIS IS THE POINT FROM WHICH THE CRACK APPEARED TO HAVE STARTED. THE MARK/I	NDENTATION APPEARS TO BE FROM A ROUND BAR BEING USED TO TURN THE CRANKSHAFT WHEN THE PROPELLER IS NOT INSTALLED. ENGINE 	IS BEING REMOVED FOR REPLACEMENT. (TC NR 20061227005)		1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
2007012900348	20070129	00348	EA  	2007	1	29	CA061227006      	1	20061227	G	5610	6003303026	WINDSHIELD      			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			2774 								(CAN) RT WINDSHIELD FACE PLY BROKEN IN FLIGHT. APPROX. 7000 INCH ON APPROACH.  FOD INSPECTION CARRIED OUT ON ENGINE INTA	KE AND WINDSHIELD REPLACED.  A/C HOURS; 6836 A/C CYCLES; 7326   (TC NR 20061227006)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050700199	20070507	00199	EU  	2007	5	7	CA061228001      	1	20061221	G	6730	10546662	HOUSING         			BOLKMS	117   	BK117A1     	5626010	EU  										ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2550 								(CAN) DURING A ROUTINE DISASSEMBLY TO CORRECT SEAL LEAKAGE A CRACK WAS FOUND AT THE LEE PLUG ON THE FRONT OF THE ACTUATO	R.  THE CRACK EXTENDS UP TOWARDS THE SERVO VALVE (TC NR 20061228001)					1	G	7	2 	3U				H13EU   					 
2007012900330	20070129	00330	GL  	2007	1	29	CA061228002      	2	20061215	G	7261		GASKET          			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 1 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CR	CRUISE         	1			CA								550302			(CAN) AFTER DEPARTING AND CLIMBING THROUGH 10K FEET THE CREW OBSERVED A LOW OIL QUANTITY CONDITION ON NR 1 ENGINE. VISUA	L CONFIRMATION OF OIL LOSS ACCOMPLISHED AND NR 1 ENGINE SHUTDOWN. THE AIRCRAFT RETURNED WITHOUT INCIDENT TO POINT OF DEP	ARTURE.  MAINTENANCE REPLACED THE NR 1 ENGINE SCAVENGE PUMP AND FILTER. ALSO REPLACED THE GASKET ON THE OIL TANK ACCESS 	PANEL FOR THE QUANTITY TRANSMITTER. THE AIRCRAFT WAS GROUND RUN AND RETURNED TO SERVICE. (TC NR 20061228002)			2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007050700200	20070507	00200	CE  	2007	5	7	CA061229001      	1	20061227	G	3230	1153800025	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA				4    							(CAN) WHEN LANDING GEAR ONLY EXTENDED HALFWAY.  EMERGENCY EXTENSION USED TO EXTEND TO LANDING CONFIGURATION. MOTOR WAS I	NSTALLED AS AN OVERHAULED UNIT 4.4 HRS PRIOR TO FAILURE.  C/B WAS FOUND TRIPPED UNDER CABIN FLOOR. BREAKER RESET AND GEA	R CYCLED. MOTOR WAS LABORING TO OPERATE. NEW MOTOR INSTALLED AND GEAR CYCLES CARRIED OUT WITH NO FAULTS FOUND. (TC NR 20	061229001)			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007012900331	20070129	00331	EA  	2007	1	29	CA061229002      	1	20061227	G	3320	BC10065003	RECEPTACLE      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CABIN	DAMAGED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, PASSENGER ALERTED FA TO SMOKE SMELL IN REAR OF CABIN. SMOKE WAS THEN VISIBLY OBSERVED BY PASSENGERS 	AND FA. FLIGHT RETURNED TO DEPARTURE AIRPORT AND ERS WAS REQUESTED. AIRCRAFT WAS APPROX 2000 LBS OVERWEIGHT BUT LANDED A	ND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT. TROUBLESHOOTING BY MAINTENANCE DETERMINED THAT THE SIDEWALL LIGHTING ASS	EMBLY AT SEAT 6F TO BE AT FAULT. RECEPTACLE FOR LIGHT APPEARED PITTED AND MAY HAVE CAUSED LIGHT ASSEMBLY TO SHORT OUT. L	IGHT ASSEMBLY WAS REPLACED WITH NO FURTHER EVIDENCE OF SMOKE OR ELECTRICAL SMELL. IAW AMM 05-51-01 PAGE 601 AND FIG 601 	NO FURTHER OVER WEIGHT INSPECTIONS REQUIRED. AFTT 26345, TOTAL CYCLES 21861. (TC NR 20061229002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900332	20070129	00332	NM  	2007	1	29	CA070102002      	1	20061225	G	5610	NP15790112	WINDSHIELD      			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) F/O WINDSHIELD SHATTER IN FLIGHT AT FL20. NO EVIDENCE OF ANY IMPACT. AIRCRAFT RETURNED TO BASE AND LANDED WITHOUT 	ANY FURTHER INCIDENT.  WINDSHIELD ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070102002)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012900333	20070129	00333	NE  	2007	1	29	CA070102003      	2	20061223	G	8500	R20007M2	ENGINE          			DOUG  	DC4   	C54EDC      	3021528	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  		MAKING METAL    	W				E				ENGINE SHUTDOWN         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			CA											(CAN) ENGINE BEGAN TO RUN ROUGH, DECREASE IN OIL PRESSURE, ENGINE WAS SHUTDOWN AND FEATHERED.  OIL SCREEN PULLED, MODERA	TE AMOUNT OF ALUMINUM FILINGS, ENGINE REMOVED AND SENT FOR OVERHAUL.  NOTE: SUSPECT LINK PIN (TC NR 20070102003)					2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
2007012900336	20070129	00336	EA  	2007	1	29	CA070102004      	1	20061219	G	2752		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					T/E FLAP	EXCESS PLAY     	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH (FLAPS FAIL) CAUTION MESSAGE APPEARED WHEN THE CREW SELECTED FLAPS FROM 30 - 45 DEG. ON LANDING.  MAIN	TENANCE INSPECTED THE A/C FLAP SYSTEM AND FOUND RT AND LT IB FLAP (O/B ACTUATORS HAD EXCESSIVE SIDE PLAY OVER 0.015) IAW	 AMM 27-53-01-400-801, ALSO RT NR3 AND NR5 FLEX DRIVES FOUND DEFECTIVE.  ALL COMPONENTS WERE REPLACED AND THE A/C WAS RE	TURNED TO SERVICE UPON A SATISFACTORY TEST FLIGHT .  FLAPS FAILED ON FINAL APPROACH AT 30 DEG.  FURTHER INSP. WAS CARRIE	D OUT ON THE FLAP SYSTEM AND THE IB NR1 FLAP ACTUATORS WERE REPLACED DUE TO EXCESSIVE FORE AND AFT PLAY AND THE FLAP DRI	VE UNIT WAS REPLACED.  THE FLAP SYSTEM WAS RIGGED IAW AMM 27-53-00 AND GROUND/FUNCTION CHECKED SERVICEABLE.  THE A/C WAS	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900340	20070129	00340	EU  	2007	1	29	CA070103002      	1	20061229	G	5610	66642023	WINDSHIELD      			AIRBUS	320   	A320214     	3930316	EU  	CFMINT	CFM56 	CFM565B4P   	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			CA											(CAN) WINDOW HEAT CONTROLLER MALFUNCTIONED CAUSING CAPT WINDSHIELD OUTER PLY TO CRACK. (TC NR 20070103002)						2	L	7	2 	4F	4	F	RT	A28NM   	E38NE				 
2007012900341	20070129	00341	NE  	2007	1	29	CA070103003      	2	20061201	G	7200	PT6A42	ENGINE          			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  						MALFUNCTIONED   	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) THE ENGINE WAS REPORTED TO LOSE POWER SHORTLY AFTER TAKEOFF, RESULTING IN A FORCED LANDING AND DAMAGE TO THE AIRCR	AFT.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103003)					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2007012900342	20070129	00342	NM  	2007	1	29	CA070103004      	1	20061226	G	2730	3906001007	PCU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			299  								(CAN) MAINTENANCE NOTICE RT ELEVATOR DROOP WHEN PARKED. FURTHER INVESTIGATION FOUND BROKEN NR 3 RT PCU.  ELEVATOR PCU FA	ILURE CAUSED DAMAGE TO THE HORIZONTAL STABILIZE STRUCTURE.  (TC NR 20070103004)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007012900343	20070129	00343		2007	1	29	CA070103005      	2	20061203	G	7321		SEAL            			AMD   	FALC50	FALCON2000  	2730170	NM  			PW308C      							FUEL CONTROL	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE AND GRADUALLY DECREASE IN CRUISE.  THE ENGINE WAS SHUTDOWN IN FLIGHT	.  SUBSEQUENT INSPECTION REVEALED A LEAKING FUEL CONTROL DRIVE SEAL. (TC NR 20070103005)					2	K	7	2 	4F			RT	A50NM   					 
2007012900344	20070129	00344	NE  	2007	1	29	CA070103006      	2	20061207	G	7261	30B336201	CARBON SEAL     			DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) DURING DESCENT THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT IN	SPECTION REVEALED A LEAKING CARBON SEAL AT THE FUEL CONTROL DRIVE PAD. (TC NR 20070103006)					2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2007012900191	20070129	00191	NE  	2007	1	29	CA070103007      	2	20061211	G	7261		PUMP            			GULSTM	200   	200         	4500308	NM  	PWC   	PW306 	PW306A      	52165	NE  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENGINE OIL PRESSURE WAS REPORTED TO GRADUALLY DECREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE AIRCRAFT DIVERT	ED FOR AN UNSCHEDULED LANDING.  THE ENGINE OIL PRESSURE PUMP WAS SUBSEQUENTLY REPLACED. (TC NR 20070103007)					2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2007012900192	20070129	00192	NE  	2007	1	29	CA070103008      	2	20061209	G	7200	PW305A	ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						FIRE            	W				E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) ON START, FLAMES WERE SEEN EXITING THE ENGINE EXHAUST.  THE START WAS ABORTED.  MFG WILL INVESTIGATE THE INCIDENT 	AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103008)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007012900193	20070129	00193	EA  	2007	1	29	CA070103009      	2	20061210	G	7250		TURBINE BLADES  			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				Z	R	A	SIGNIFICANT FAILURE REPORT	PARTIAL RPM/PWR LOSS      	FLAME/FIRE                	CR	CRUISE         	1			CA								42192			(CAN) DURING CRUISE ENGINE POWER REDUCED UNCOMMANDED, ACCOMPANIED BY A LOUD NOISE AND FLAMES EXITING THE EXHAUST.  SUBSE	QUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND A SEIZED REDUCTION GEARBOX.  MFG WILL MONITOR INVESTIGATION	 OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103009)				1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
2007012900194	20070129	00194	EA  	2007	1	29	CA070103010      	2	20060911	G	7200	PT6A34	ENGINE          			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  						FLAMED OUT      	W				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE FLAMED OUT IN FLIGHT ACCOMPANIED BY A LOUD NOISE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT	 CAUSE ONCE ESTABLISHED. (TC NR 20070103010)					1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2007012900196	20070129	00196	EA  	2007	1	29	CA070104001      	1	20061224	G	5610	NP13932200	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	UNKNOWN         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			11983								(CAN) MAINTENANCE REPLACED SIDE WINDOW. (TC NR 20070104001)						2	L	7	2 	4F			RT	A21EA   					 
2007012900197	20070129	00197	NE  	2007	1	29	CA070104002      	2	20061224	G	7321	6078T39P03	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			10542								(CAN) (DIVERTED, WITH ENGINE PROBLEMS, CREW CALLED WHEN ON GROUND.  ON APPROACH, THE LT ENGINE WOULD NOT IDLE BACK BELOW	 79 PERCENT N1. IT WOULD RESPOND TO INPUTS ABOVE 79 PERCENT.  CREW ELECTED TO SHUTDOWN THE ENGINE, AND DIVERT.)  MX WAS 	UNABLE TO DUPLICATE THIS PROBLEM, WHILE INITIATING START, N1 RAN AWAY SHORTLY AFTER LIGHT OFF.  MX REPLACED FCU. (TC NR 	20070104002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900198	20070129	00198	EA  	2007	1	29	CA070105001      	1	20061230	G	5350		RADOME          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUSELAGE	BIRD STRIKE     	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE CREW WITNESSED A BIRD STRIKE ON THE NOSE OF THE AIRCRAFT. CREW ELECTED TO RETURN TO DEPARTURE AIRP	ORT AND LAND OVERWEIGHT (ESTIMATED AT 49200 LBS). AIR TRAFFIC CONTROL WAS NOTIFIED BUT EMERGENCY EQUIPMENT WAS NOT REQUI	RED.  MAINTENANCE INSPECTION DISCOVERED A DEAD SEAGULL WHICH HAD PENETRATED THE RADOME DAMAGING THE WEATHER RADAR ANTENN	A AND THE NOSE BULKHEAD. FDR REMOVED FOR READING. FURTHER OVERWEIGHT LANDING INSPECTION NOT REQUIRED IAW FDR READOUT AND	 AMM 05-51-01 PAGE 609, SUBTASK 05-51-01-970-004 FOR IMPACT SPEED OF 120 FT/MIN. THE FOLLOWING PART REPLACEMENTS WERE CO	MPLETED: FDR P/N S800-20000-00. ULB DK120. RADOME P/N 4926-201. WEATHER RADAR ANTENNA P/N 622-9302-003. DAMAGE TO BULKHE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900199	20070129	00199	EA  	2007	1	29	CA070105002      	2	20061216	G	7250		TURBINE BLADES  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	FRACTURED       	W				O				OTHER                   				J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) ENGINE OIL PRESSURE WERE REPORTED TO FLUCTUATE IN CRUISE FOLLWED BY A LOUD NOISE AND AN UNCOMMANDED ENGINE SHUTDOW	N.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR 	INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070105002)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007012900200	20070129	00200	NE  	2007	1	29	CA070105003      	2	20061214	G	7250		TURBINE BLADES  	PWC         	PT6A114A    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA						19232		19232			(CAN) THE ENGINE SUFFERED AN INFLIGHT SHUTDOWN IN CRUISE.  SUBSEQUENT INSPECTION REVEALED THE AIRFRAME INLET AIR BOX PAR	TIALLY OPEN WITH A FASTENING PIN MISSING.  THE ENGINE COMPRESSOR WAS FOUND STIFF TO ROTATE WITH DAMAGE EVIDENT TO THE SE	COND STAGE STATOR AND THE POWER TURBINE BLADES WERE FOUND FRACTURED.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND	 ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070105003)			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007012900203	20070129	00203	EA  	2007	1	29	CA070106001      	1	20061227	G	3320	BC10065005	RECEPTACLE      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										CABIN	FAULTY          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT PASSENGER ALERTED FA TO SMOKE SMELL IN REAR OF CABIN , SMOKE WAS THEN VISIBLY OBSERVED BY PASSENGE	RS AND FA. FLIGHT RETURNED TO DEPARTURE AIRPORT AND ERS WAS REQUESTED. AIRCRAFT WAS APPROX. 2000 LBS OVERWEIGHT BUT LAND	ED AND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT.  MAINTENANCE DETERMINED THAT THE SIDEWALL LIGHTING ASSEMBLY AT SEAT 	6F TO BE AT FAULT. RECEPTACLE FOR LIGHT APPEARED PITTED AND MAY HAVE CAUSED LIGHT ASSEMBLY TO SHORT OUT. LIGHT ASSEMBLY 	WAS REPLACED IAW AMM 05-51-01 PAGE 601   (TC NR 20070106001)		2	L	7	2 	4F			RT	A21EA   					 
2007050800193	20070508	00193	EU  	2007	5	8	CA070108004      	1	20061221	G	6320	350A32315520	CASE HALF       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					GEAR BOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3727 							(CAN) HALF SHELLS WERE WORN OUT DUE TO MOVEMENT OF THE SUN GEAR, WEARING S STEP INTO THE SHELLS. THERE IS NO PUBLISHED L	IMITS ON THE SHELLS AND WE HAVE ASKED ECL FOR THIS INFORMATION. THERE IS NORMAL WEAR IN THIS AREA, THIS WAS A BIT EXCESS	IVE WITH SLIVERS OF METAL COMING OFF THE PARTS. THIS WOULD HAVE LEAD TO A CHIP LIGHT EVENTUALLY. (TC NR 20070108004)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007012900211	20070129	00211	EA  	2007	1	29	CA070108005      	1	20061228	G	4930	388273010	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			396  	396  							(CAN) DEC 28/06, AERO CALLOUT 061228/01, ON PUSHBACK, A RAMP AGENT NOTICED A PUDDLE OF FUEL ON THE GROUND AT THE BACK OF	 THE AIRCRAFT.  APPARENTLY, FUEL WAS LEAKING FROM THE APU. THE CAPTAIN CHECKED THE LEAK  AS F/O CALLED APRON.  THE FIRE 	TRUCKS WERE CALLED AS WELL AS CONSOLIDATED FUELERS TO CLEAN UP THE AREA.  THE PASSENGERS WERE DEPLANED AS A PRECAUTION. 	 MAINTENANCE CONFIRMED THAT THE LEAK WAS FROM THE APU FCU DRAIN LINE, THEY THEN DEFERRED THE APU AND THE A/C DEPARTED WI	THOUT INCIDENT.  THE FCU WAS REPLACED AND LEAK CHECKS WERE CARRIED OUT.  TEARDOWN REPORT TO FOLLOW. (TC NR 20070108005)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900212	20070129	00212	NM  	2007	1	29	CA070108006      	1	20061227	G	3222	88295	NUT             	MESSIER     	8800121     	DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	BROKEN          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			CA						DCL051085					(CAN) SUSPECT CAP NUT SHEARED UPON TAKEOFF DUE TO THE UNEVEN RUNWAY.  REF ATTACHED PILOTS REPORTS AND PHOTO`S OF DAMAGED	 CAP NUT.   (TC NR 20070108006)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050800194	20070508	00194	EU  	2007	5	8	CA070108007      	1	20061219	G	2910	MS2771923	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COLLECTIVE	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROBLEM REPORTED BY PILOT IN DECEMBER ABOUT INTERMITTENT SWITCH. THIS HAPPENED ONCE IN THE FIELD. THE A/C WAS BROU	GHT IN FOR AN INSPECTION AT THE END OF DECEMBER/06 AND THE SWITCH WAS REPLACED.  BAD SWITCHES, SHOULD BE REPLACED WITH S	OMETHING BETTER. (TC NR 20070108007)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007012900214	20070129	00214	EA  	2007	1	29	CA070109001      	1	20061207	G	2820	600624623	TUBE            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL SYSTEM	BLOCKED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			65   								(CAN) AUTO SHUTOFF DID NOT OCCUR DURING PRESSURE REFUELING OPERATIONS RESULTING IN FUEL SPILL ON RAMP. OPERATOR REPORTED	 SIMILAR PROBLEMS SINCE TAKING DELIVERY OF NEW AIRCRAFT. IT WAS FOUND THAT A NUMBER OF LT AND RT WING TRANSFER AND BALAN	CING PIPES (TUBES) HAD BEEN PARTIALLY OBSTRUCTED AT THE CONNECTING JOINTS BY SEALANT. AIRCRAFT OEM FIELD SERVICE REPRESE	NTATIVES WERE ON SITE FOR RECTIFICATIONS. (TC NR 20070109001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900220	20070129	00220	EA  	2007	1	29	CA070109003      	1	20061227	G	5220	H341935	HOUSING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  										ESCAPE HATCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			867  								(CAN) ESCAPE HATCH OUTER HANDLE HOUSING WAS FOUND CRACK DURING AN AFTER STORAGE RETURNED TO SERVICE.  INVESTIGATION IS I	N PROGRESS. (TC NR 20070109003)					2	L	7	2 	4F			RT	A21EA   					 
2007012900221	20070129	00221	EU  	2007	1	29	CA070109005      	1	20061108	G	2810	1608565	VALVE           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					FUEL SYSTEM	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DATE OF DELAY NOV 8, 2006 CADORS NR: 2006C2915.  THE FLIGHT CREW WAS NOTIFIED THAT DURING TAXI FOR DEPARTURE FUEL 	WAS LEAKING FROM LT WING.    AIRCRAFT TAXIED OFF RUNWAY BY WHICH TIME THE LEAK HAD STOPPED. FLIGHT CREW IN CONTACT WITH 	MAINTENANCE CONTROL AGREED THAT THE LEAK WAS FROM THE WING TANK VENTING SYSTEM.  AFTER THE SPILL WAS CLEANED, AC DEPARTE	D.  FOLLOW UP ACTION, THIRD OCCURRENCE OF FUEL LEAK FROM THE VENT SYSTEM ON THIS AIRCRAFT. THE FIRST EVENT WHICH OCCURRE	D OCT 28 WAS RECTIFIED WITH REPLACEMENT OF THE SUCTION RELIEF VALVE. SNAG RETURNED NOV 3 AT WHICH TIME MAINTENANCE REFUE	L AND DE-FUEL THE AIRCRAFT SEVERAL TIMES AND COULD NOT FAULT THE SYSTEM. IN FOLLOW UP TO THIS LATEST SNAG, WE HAVE AN EN	2	L	7	2 	4F	4	F	RT	        	E25NE				 
2007012900223	20070129	00223	SO  	2007	1	29	CA070109007      	2	20061206	G	8530	AEC648009PL	PISTON RING     								CONT  	O470  	O470*       	17026	SO  					ENGINE	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			45   								(CAN) MATERIAL FROM THE FACE OF THE TOP COMPRESSION RING HAD FLAKED AWAY ON CYLINDER NR 2 (TC NR 20070109007).											3	O			E273				 
2007012900225	20070129	00225	NM  	2007	1	29	CA070110002      	1	20061217	G	5610		WINDOW          			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE THE RT NR 3 FLT DECK WINDOW SHATTERED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHE	R PROBLEM. THE AIRCRAFT MOVED TO MAINTENANCE BASE UNDER MEL AUTHORITY WHERE A REPLACEMENT WINDOW WAS INSTALLED. (TC NR 2	0070110002)				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2007012900226	20070129	00226	CE  	2007	1	29	CA070110003      	1	20061220	G	3222	05430358	TORQUE LINK     			CESSNA	172   	172D        	2072410	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3691 								(CAN) PRIOR TO INSTALLATION ON AIRCRAFT, NOSE GEAR SHOCK STRUT ASSEMBLY WAS THOROUGHLY INSPECTED.  SEVERAL CRACKS WERE F	OUND ON UPPER TORQUE LINK.  NEW MFG PART WAS INSTALLED. (TC NR 20070110003)					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P920	 
2007012900227	20070129	00227		2007	1	29	CA070110005      	4	20061009	G	2340		WARNING SYSTEM  		6225342001  	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			CA						3054					(CAN) THE REFERENCED AIRCRAFT AN EVENT INVOLVING THE AUTOMATIC SILENCING OF CABIN CHIMES.   NORMALLY THE FLIGHT CREW WIL	L ADVISE THE FLIGHT ATTENDANTS TO TAKE THEIR POSITIONS FOR LANDING WITH 3 CHIMES SELECTED MANUALLY IN THE COCKPIT.  IT A	PPEARS HOWEVER IN LANDING CONFIGURATION THAT THE CHIMES ARE SILENCED AND STORED UNTIL THE NR 1 ENGINE IS SHUT DOWN.  THE	 CHIMES ARE INHIBITED  AT CERTAIN FLIGHT PHASES.  AS INDICATED MAINTENANCE WAS ABLE TO DUPLICATE THE FAULT.  BY PUTTING 	THE AIRCRAFT INTO FLIGHT MODE.  ONCE THE AIRCRAFT WAS PUT BACK INTO GROUND MODE (ENGINES NOT RUNNING) THE STORED CHIMES 	SOUNDED.  WE HAVE POSED THIS ISSUE TO MFG.  WE HAVE REVIEWED THE SBS SL AND SEDS BUT FOUND NO INFORMATION  PERTAINING	2	L	7	2 	4F	4	F	RT	        	E25NE				 
2007012900228	20070129	00228	SO  	2007	1	29	CA070111001      	1	20061224	G	3260		SWITCH          			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	RT MLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE THE RT MLG CONTINUED TO INDICATE DOWN AND LOCKED AFTER THE GEAR WAS SELECTED UP. THE AIRCRAFT CON	TINUED TO DESTINATION, ENROUTE THE GEAR WAS CONFIRMED UP. THE GEAR WAS VISUALLY CONFIRMED AND THE AIRCRAFT LANDED WITHOU	T FURTHER PROBLEM.  MAINTENANCE REPLACED THE RT MLG FORWARD MICROSWITCH AFTER A SATISFACTORY GEAR SWING THE AIRCRAFT WAS	 RETURNED TO SERVICE. (TC NR 20070111001)			2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007012900237	20070129	00237		2007	1	29	CA070111014      	4	20061230	G	3425	7004544713	SYMBOL GENERATOR			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 1	FAILED          	W				A				UNSCHED LANDING         				I			FLT. ATTITUDE INST.       			CR	CRUISE         	1			CA											(CAN) THE CAPTAINS EFIS SCREEN CIRCUIT BREAKER TRIPPED. THE BREAKER WAS RESET AND TRIPPED AGAIN AND THE AIRCRAFT RETURNE	D TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 SYMBOL GENERATOR UNIT (SGU)THE AIRCRAFT WAS RETURNED TO SERVICE A	FTER SATISFACTORY FUNCTION CHECK COMPLETED. (TC NR 20070111014)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007013100108	20070131	00108	NE  	2007	1	31	CA070111016      	2	20061219	G	7230	FW34114	FAN BLADE       			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					LT ENGINE	SEPARATED       	W				O				OTHER                   				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA			650  								(CAN) DURING CLIMB AT APPROXIMATELY 35,000 FEET, THE CREW HEARD A LOUD BANG AND THE LT ENGINE SHUTDOWN.  THE CREW DECLAR	ED AN EMERGENCY AND LANDED UNEVENTFULLY.  AN INSPECTION OF LT ENGINE REVEALED ONE FAN BLADE HAD FRACTURED JUST ABOVE THE	 ROOT. THE BLADE ROOT WAS STILL ATTACHED AND THE FRACTURED PORTION WAS RECOVERED.  DAMAGE WAS ALSO FOUND ON THE INSIDE O	F THE INLET, TO SOME OF THE OTHER FAN BLADES AND TO THE GUIDE VANES. THE FAILURE WAS COMPLETELY CONTAINED AND NO DAMAGE 	WAS FOUND ON THE EXTERIOR OF THE NACELLE OR AIRCRAFT STRUCTURE. (TC NR 20070111016)		2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2007050900065	20070509	00065	EU  	2007	5	9	CA070112001      	1	20061209	G	5540	9408328506	BEARING         			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 INSPECTION OF TAIL TOP ATTACH BOLT FOUND TO HAVE EXCESSIVE WEAR. RUDDER REMOVED FOR REPAIR. DURING REPAIR A	NCHOR NUT WAS DAMAGED. NEW OVERSIZED BUSHING INSTALLED, WITH NEW BOLT, BEARING AND ANCHOR NUT. MFG WAS NOTIFIED OF THIS 	DEFECT. (TC NR 20070112001)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007050900074	20070509	00074	NE  	2007	5	9	CA070115006      	1	20061214	G	6320	92351510042	GEARBOX         			SKRSKY	S92   	S92A        	       	NE  										MAIN ROTOR	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			LD	LANDING        	1			CA			2076 	2076 							(CAN) MAIN GEARBOX HAD SEVERAL OCCURENCES OF OIL PRESSURE DROPPING TO THE PRECAUTIONARY RANGE IN OPERATION.  (TC NR 2007	0115006)					2	G	7	2 	4U				R00024BO					 
2007012900267	20070129	00267	NE  	2007	1	29	CA070115008      	2	20061009	G	7250	ARRIEL2B	ENGINE          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  						FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			709  								(CAN) AIRCRAFT FAILED POWER CHECK: ON INSPECTION ON WHY WE DID A BORESCOPE INSPECTION ON THE ENGINE AND FOUND THAT WE HA	D A POSSIBLE TURBINE RUB. AS THIS ENGINE IS A RENTAL FROM MFG, WE CHANGED OUT THE MODULE 2 AND 3 AND SENT IT BACK TO THE	M. THE NEW M02 AND M03 MODULES FIXED OUR FAILED POWER CHECK.  WE DO NOT KNOW FOR SURE WHAT CAUSED OUR PROBLEM.  (TC NR 2	0070115008)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007012900272	20070129	00272	NE  	2007	1	29	CA070115009      	2	20061217	G	7310	AE7010000N0130	FUEL LINE       			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF348E5A1   	30015	NE  					ENGINE	TORN            	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FUEL LEAK WAS FOUND FROM HOSE ASSEMBLY P/N AE7010000N0130 ON THE SECOND ENGINE RUN AFTER THAT HOSE WAS REPLACED.  	NOTE: THIS LINE WAS REPLACED AS REQUESTED BY MFG (DISCLOSURE LETTER), BATCH RECALL DUE TO DEFECTIVE HOSE (BATCH NR 84085	0).  (TC NR 20070115009)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2007012900296	20070129	00296	EA  	2007	1	29	CA070115010      	2	20061216	G	7250	3013102	TURBINE         	PWC         	PT6A27      	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	DISINTEGRATED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA				2741 		PCE41266					(CAN) DURING CRUISE FLIGHT, THE CREW NOTICED OIL PRESSURE ON THE NR 2 ENGINE FLUCTUATING BETWEEN 60-70 PSI, WITHIN SECON	DS THE TQ PRESSURE STARTED TO FLUCTUATE. THE ENGINE MADE 3 BIG BANGS AND SHUTDOWN. THE CREW LANDED THE AIRCRAFT AT THE N	EAREST AIRPORT WITHOUT INCIDENT. MAINTENANCE FOUND METAL IN THE OIL FILTER AND IN THE RGB. MOST OF THE PT BLADES EXITED 	THE EXHAUST. ENGINE SENT TO OVERHAUL SHOP FOR INVESTIGATION. (TC NR 20070115010)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007012900301	20070129	00301	WP  	2007	1	29	CA070115011      	2	20061126	G	7260	3586763	PLANETARY GEAR  								GARRTT	TPE331	TPE33110UG  	01514	WP  					ENGINE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA				206  							(CAN) UPON DOING A OIL SAMPLE, METAL WAS NOTED IN THE OIL FILTER. THE ENGINE P-63235C WAS REMOVED. ENGINE WAS FORWARDED 	TO THE ENGINE SHOP FOR INSPECTION OF THE METAL AND FOUND THAT 1 PLANETARY GEAR WITH THE INNER RACE PEELING METAL AND 3 P	LANETARY GEARS WITH PITTING ON THE GEAR TEETH. ALL 4 PLANETARY GEARS HAVE 205.9 HRS SINCE O/H. (TC NR 20070115011)									4	T			E4WE				 
2007082000035	20070820	00035	SW  	2007	8	20	CA070115012      	1	20061214	G	5312	320035501	ANGLE           			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16737								(CAN) FLIGHT CREW REPORTED LOWER THAN NORMAL CABIN DIFFERENTIAL PRESSURE. A GROUND PRESSURIZATION CHECK WAS CARRIED OUT 	AND FOUND LEAK IN AREA OF AFT PRESSURE BULKHEAD LOWER SECTION. FURTHER INSPECTION REVEALED A CRACK IN THE BEND RADIUS OF	 ANGLE P/N 320035-501.  P/N M690003-4 FIGURE 2-56D ITEM II. NEW ANGLE INSTALLED AND SEALED. GROUND PRESSURIZATION CHECK 	CARRIED OUT OKAY. (TC NR 20070115012)			1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2007082000036	20070820	00036	SW  	2007	8	20	CA070115013      	1	20061219	G	5720	1101918	FILLET          			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16738								(CAN) DURING INSPECTION OF THE AIRCRAFT A CRACK WAS SUSPECTED IN THE RT UPPER FILLET WING TO FUSELAGE.  NON DESTRUCTIVE 	TESTING CONFIRMED (2) CRACKS, 25 MM AND 18 MM LENGTH.  LT UPPER FILLET INSPECTED BY NDT AND NO CRACKS FOUND. AN APPROVED	 REPAIR CARRIED OUT.  (TC NR 20070115013)				1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2007012900306	20070129	00306		2007	1	29	CA070117001      	4	20061216	G	2215	4015373823	SERVO           			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					AUTOPILOT SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE OPERATOR REPORTED AILERON CONTROL DIFFICULTIES AT FL470 WHILE ENROUTE.  THE AIRCRAFT DEPARTED IN HEAVY RAIN.  	THE PILOT-IN-COMMAND (PIC) DISCONNECTED THE AUTOPILOT AFTER AN AP TRIM IS LWD CAS MESSAGE WAS ANNUNCIATED AND NOTED THAT	 THE AILERON CONTROL WHEELS WOULD NOT ROTATE WHEN ATTEMPTED BY HAND.  THE CREW OVERPOWERED THE CONDITION AND THEN ELECTE	D TO DESCEND TO A LOWER ALTITUDE.   THE PIC STATED THAT AT APPROXIMATELY FL440 THE CONTROL WHEEL LOCKED UP AGAIN AND THE	 CONDITION WAS OVERPOWERED BY THE CREW.  THE FORCE APPLIED TO OVERPOWER THE CONTROL WHEEL FOR BOTH OCCURRENCES WAS APPRO	XIMATELY 20 LBS.  THE PIC ALSO STATED THAT THE AILERON CONTROL SYSTEM WAS BACK TO NORMAL FOR THE DURATION OF THE FLIGHT 	2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2007050900191	20070509	00191		2007	5	9	CA070118007      	4	20061207	G	3417	0102AH2AF	PROBE           			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					TAT	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			372  								(CAN) DURING CRUISE AT 43,000 FEET, CREW HAD EICAS MESSAGE AIR DATA COMPUTER (ADC) 3 MISCOMPARE ANNUNCIATED FOR 2 MINUTE	S FOLLOWED MOMENTARILY BY ADC 1 MISCOMPARE AND THEN ADC 2 MISCOMPARE MESSAGES.  AFTER THE MESSAGES WENT OUT, COCKPIT IND	ICATIONS STARTED TO SHOW DECREASING AIR SPEED AND ENGINE PRESSURE RATIO (EPR) WHICH COULD NOT BE MAINTAINED WITH THE THR	OTTLE LEVERS AT THE MAXIMUM SETTING.  A STALL WARNING ANNUNCIATION WAS POSTED ON THE PRIMARY FLIGHT DISPLAYS WITH STICK 	SHAKER ACTIVATED AND THE CREW BEGAN A DESCENT TO 39,000 FT.  AT THAT ALTITUDE, THE ENGINE POWER INDICATIONS RETURNED TO 	NORMAL ACCOMPANIED WITH HIGHER THAN NORMAL ENGINE VIBRATION (WITHIN ALLOWABLE LIMITS) WHICH REMAINED UNTIL THE A/C DESCE	2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2007051100010	20070511	00010	GL  	2007	5	11	CA070119002      	2	20061019	G	7323	23076061	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					POWER TURBINE	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			17   								(CAN) THE GOVERNOR WAS INSTALLED WITH ZERO TSN. GROUND RUNS AND RIGGING WERE CARRIED OUT IAW THE MM WITH NO DIFFICULTIES	. THE AIRCRAFT WAS FLOWN AND IT WAS NOTICED BY THE PILOT THAT HE WAS ALWAYS CHASING THE N2 TO KEEP IT WITHIN LIMITS (ERR	ATIC N2 OPS). THE ERRATIC OPS DID NOT IMPROVE AND SEEMED TO WORSEN. THE AIRCRAFT WAS THEN GROUNDED. THE PT GOVERNOR WAS 	RETURNED FOR WARRANTY.  (TC NR 20070119002)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007051100012	20070511	00012	SW  	2007	5	11	CA070119006      	1	20061013	G	2435		SPRING          	LUCAS       		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					STARTER-GEN	BROKEN          	W				E				ENGINE SHUTDOWN         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		TX	TAXI/GRND HDL  	1			CA						1289					(CAN) THE STARTER GENERATOR WAS THEN INSTALLED.  UPON FIRST GROUND RUN OF THE AIRCRAFT, SPARKS WERE NOTICED TO BE COMING	 FROM THE BRUSH AREA. THE AIRCRAFT WAS SHUTDOWN, THE STARTER GENERATOR WAS REMOVED. UPON REMOVAL WE HEARD SOMETHING LOOS	E/RATTLING AROUND. WE REMOVED THE BRUSH COVER AND FOUND THAT ONE OF THE SPRINGS WHICH HOLD DOWN THE BRUSHES WAS BROKEN O	FF AND RATTLING AROUND CAUSING ARCING. THIS STARTER-GENERATOR WAS RETURNED TO FOR FULL WARRANTY AND A NEW UNIT WAS SENT 	TO US. (TC NR 20070119006)		1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007051100014	20070511	00014	GL  	2007	5	11	CA070119008      	2	20061016	G	7321	23070606	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA				460  							(CAN) THE AIRCRAFT WAS STARTED AND WARMED UP. THE PILOT THEN BEGAN TO SPOOL THE AIRCRAFT UP FROM GROUND IDLE TO FLIGHT I	DLE, HOWEVER NOTHING HAPPENED. THIS WAS TRIED A FEW TIMES BUT STILL NO RESPONSE. OTHER TROUBLESHOOTING WAS PERFORMED WIT	H NO FINDINGS. THE FUEL CONTROL UNIT (FCU) IN QUESTION WAS REMOVED AND AN OVERHAULED UNIT WAS INSTALLED. THE DEFECT WAS 	RECTIFIED.  (TC NR 20070119008)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007051100054	20070511	00054	NE  	2007	5	11	CA070123011      	2	20060112	G	7261	PT6A67D	ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					NR 1	OIL CONSUMPTION 	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			10488	10488				PCEPSO290			(CAN) CREW NOTED THEIR NR 1 OIL PRESSURE, FLUCTUATING AROUND 75 PSI. THEY RETURNED TO THE GATE AND REPORTED TO MAINTENAN	CE. INSPECTION OF THE CHIP DETECTOR AND OIL FILTER REVEALED NO FAULTS. THE ENGINE WAS FILLED WITH OIL AND GROUND RUN WIT	H NO CONSUMPTION OF OIL NOTED.  THE OIL BREATHER LINE WAS BAGGED AND THE A/C RAN FOR 30 MINUTES ON THE GROUND UNDER TARG	ET TORQUE LOADS AND VERY LITTLE CONSUMPTION WAS NOTED. THE A/C WAS SENT ON AN HOUR LONG TEST FLIGHT WHEN IT RETURNED IT 	WAS APPROX .5 LITER LOWER ON THE OIL LEVEL. SINCE THE OIL LEVEL WAS STILL AT .75 OF A LITER LOW,  MAINTENANCE LATER DETE	RMINED THE ENGINE HAD RETURNED TO ITS NORMAL OIL LEVEL. THE A/C WAS FLOWN ON A COUPLE MORE SHORT HOP ROUTS WITH NO OIL U	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007051100072	20070511	00072	EA  	2007	5	11	CA070126003      	2	20060705	G	7414	BL3493704	MAGNETO         			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	LOOSE           	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			1403 								(CAN) ROUGH RUNNING ON RUNUP. FOUND ATTACHMENT FLANGE ON MAGNETO LOOSE. (TC NR 20070126003)						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
2007051100073	20070511	00073	EU  	2007	5	11	CA070126004      	1	20060831	G	7921	8406E	OIL COOLER      			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  		CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			1400 								(CAN) OIL LEAK AROUND CASTING PORT ON THE OIL COOLER ASSEMBLY.  (TC NR 20070126004)						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
2007051100189	20070511	00189		2007	5	11	CA070129006      	4	20061221	G	3497		CONNECTOR       			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	ADF	DISCONNECTED    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ADF INTERMITTENT NDB AND HEADING. AFTER SWAPPING RECEIVERS, ANTENNA, REPLACING ANTENNA TRAY AND CONNECTOR, REPLACI	NG PINS IN RECEIVER TRAY, FOUND CO-AX CONNECTOR INNNER CORE TOUCHING SHIELDING AT RECEIVER TRAY. SNAG ONLY APPREARED WHE	N WIRING HARNESS WAS PULLED ON. SOLDERED PORTION OF CONNECTOR HAD WEAKENED OVER TIME AND COULD NO LONGER SUPPORT THE CO-	AX WHICH LED TO THE SHORTING. (TC NR 20070129006)			1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2007080800134	20070808	00134	CE  	2007	8	8	CA070131006      	1	20060929	G	5730		SKIN            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 2 CRACKS WERE DETECTED ON THE WING SKIN JUST UNDER THE LEADING EDGE ON BOTH WINGS. THE WING ATTACHMENT FITTINGS OF	 THE AIRCRAFT WERE INSPECTED AND NO FURTHER CRACKS WERE DISCOVERED.  THE WINGS WERE REMOVED TO CONDUCT A MORE DETAILED E	XAMINATION AND THE AMO IS IN CONTACT WITH MFGV FOR REPAIR INSTRUCTIONS. (TC NR 20070131006)				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2007051400001	20070514	00001	NM  	2007	5	14	CA070201002      	1	20061218	G	2821	218371	FUEL FILTER     			BOEING	767   	767300      	1385204	NM  	PWA   	R985  	R985AN14B   	52008	NE  						DIRTY           	W				J	A			DUMP FUEL               	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB (L ENG FUEL FILT) EICAS MSG. RETURNED TO DEPARTURE.  FUEL FILTER INSPECTED AND FOUND DIRTY.  (NO DEBRIS) 	TECH NOTED NOT TO THE EXTENT THAT WOULD CAUSE THE EICAS INDICATION.  FILTER REINSTALLED. LT ENG DIFFERENTIAL PRESS SW CO	NX FND CORRODED. CONX CLEANED  NR DIFF PRESS SW REPLACED. CKD SERV ON GRND RUN. REPEAT SNAG ON NEXT T/O. FILTER REPLACED	 AND CKD SERV ON HIGH PWR GROUND RUN.  (TC NR 20070201002)			2	L	7	2 	4F	3	R	RT	A1NM    	5E1				 
2007051400124	20070514	00124	SO  	2007	5	14	CA070207004      	2	20060303	G	8530		VALVE           			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	CYLINDER	STUCK           	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA			1291 					253128			(CAN) STUCK VALVE - ENGINE WAS ROUGH RUNNING. FOUND TO BE A STUCK VALVE.  (TC NR 20070207004)						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007051400126	20070514	00126	SO  	2007	5	14	CA070207005      	2	20060120	G	7322		PUMP            			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ACCELERATOR	FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA			5800 								(CAN) ON ADDING FULL POWER THE ENGINE STALLED AND STOPPED RUNNING. - FOUND TO BE THE ACCELERATOR PUMP WAS NOT WORKING PR	OPERLY.  (TC NR 20070207005)					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007051400128	20070514	00128	SO  	2007	5	14	CA070207006      	1	20060120	G	5343		TRUNNION        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C509   	GL  	NLG	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NOSE GEAR TRUNNION DAMAGED AND REPAIRED. (TC NR 20070207006)						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2007051400170	20070514	00170	EA  	2007	5	14	CA070209006      	2	20061220	G	7250		TURBINE BLADES  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					POWER SECTION	FRACTURED       	W				O				OTHER                   				X			ENGINE FLAMEOUT           			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND SHUTDOWN UNCOMMANDED.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTUR	E.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND A	DVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209006)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2007051400171	20070514	00171	NE  	2007	5	14	CA070209007      	2	20060918	G	7250		TURBINE BLADES  			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	120   	PW120       	 	NE  					ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH THE ENGINE FIRE WARNING ACTIVATED, ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION.  THE CREW DISCHARGED	 FIRE BOTTLES AND SHUT THE ENGINE DOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION AT MFG REVEALED LPT BLADE FRACTURE IN CREEP.	 (TC NR 20070209007)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007051500197	20070515	00197	NE  	2007	5	15	CA070209018      	2	20061230	G	7310		PACKING         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					FUEL MANIFOLD	LEAKING         	W				E				ENGINE SHUTDOWN         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) THE ENGINE LOST POWER IN CRUISE AND WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION FOUND A LEAK AT THE FUEL MANIF	OLD TRANSFER TUBES.  ALL TRANSFER TUBE O-RING PACKINGS WERE REPLACED. ON JAN 4TH FUEL LEAKAGE FROM THE SAME TRANSFER TUB	ES WAS OBSERVED DURING GROUND OPERATIONS.  MFG IS INVESTIGATION PACKING INSTALLATION PROCEDURES AND PROCUREMENT SOURCE A	ND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209018)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007051600172	20070516	00172	SW  	2007	5	16	CA070216007      	1	20060919	G	6330	206031554003	SPINDLE         			BELL  	206   	206B        	1181511	SW  										RT GEARBOX	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA				1667 							(CAN) THE RT TRANSMISSION PYLON SUPPORT SPINDLE FAILED IN-FLIGHT AND AIRCRAFT SUBSEQUENTLY HAD AN UNCONTROLLED COLLISION	 IN THE WATER.  REFERENCE: TRANSPORT SAFETY BOARD OCCURENCE BULLETIN NR A06P0190 (TC NR 20070216007)					1	G	7	1 	3U				H2SW    					 
2007051700130	20070517	00130	EU  	2007	5	17	CA070221008      	1	20060904	G	2913	350A35109222	PULLEY          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYDRAULIC	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			343  								(CAN) HYDRAULIC PULLEY BEARING CONTACT SURFACE WORN CAUSING PULLEY WOBBLE AND LOSS OF BELT TENSION.   (CLICKING) NOISE D	URING START UP AND SHUT DOWN, PULLEY AND BEARING REPLACED NEW. (TC NR 20070221008)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007053000022	20070530	00022	GL  	2007	5	30	CA070226003      	3	20061212	G	6110	HCA3V203	PROPELLER       			STOLAM	RC3   	RC3         	3080203	NM  	LYC   	O480  	GO480G1A6   	41527	EA  	HARTZL	HCA3V	HCA3V203    	GL  		CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				304  					FC33		(CAN) PROP COME IN FOR 10 YEAR OVERHAUL. PIS, CLEAN, NDT, VISUAL INSPECTION, LUB UNSERVICEABLE DUE TO RUST. LINK ARMS P/	N 861-3C WORN UNSERVICEABLE, P/N A971 BEARING CORRODED UNSERVICEABLE P/N VL9333C-5 BLADE BORES CORRODED HAD TO BE REAMED	 AND RE-SHOT PEENED.  THIS PROP NORMALLY WOULD COST APPROXIMATELY  NR 4,500 TO OVERHAUL WITH REPLACED PARTS AND REWORKED	 BLADE BORES.  THIS OVERHAUL HAS BECOME  NR 14,000. (TC NR 20070226003)			1	H	7	1 	3O	3	O	RC	A769    	E275	5	C	P6EA	 
2007053000023	20070530	00023	SO  	2007	5	30	CA070226004      	1	20061220	G	3210	4025700	TORQUE LINK     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MLG	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			11942								(CAN) PILOT NOTICED A VIBRATION ON LT WHEEL. AIRCRAFT RETURNED TO RAMP. LT MAIN LANDING GEAR UPPER TORQUE LINK WAS FOUND	 CRACKED/BROKEN AT ATTACH LUG. THE TORQUE LINK WAS REPLACED.  (TC NR 20070226004)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007053000026	20070530	00026	SW  	2007	5	30	CA070226007      	1	20061103	G	3246	D2571	SADDLE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					SKID TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT SKID SADDLE WAS FOUND CRACKED. (TC NR 20070226007)						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007053000034	20070530	00034	GL  	2007	5	30	CA070227007      	2	20060915	G	7323		CONTROL LEVER   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				271  							(CAN) THE CONTROL LEVER SHAFT ON THE GOVERNOR WAS FOUND HARD TO MOVE.   SO STIFF THAT THE LINEAR ACTUATOR HAD TO WORK HA	RD TO MAKE IT TO MOVE. (TC NR 20070227007)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007053000036	20070530	00036	GL  	2007	5	30	CA070227009      	2	20060616	G	7323		CONTROL LEVER   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				734  							(CAN) LEVER CONTROL LEVER HARD TO MOVE ON A FUNCTIONAL CHECK. (TC NR 20070227009)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007053000037	20070530	00037	GL  	2007	5	30	CA070227011      	2	20061023	G	7323	23065123	CONTROL LEVER   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				152  							(CAN) ON A FUCTIONAL CHECK OF THE GOVERNOR CONTROL THERE APPEARED THAT THE CONTROL LEVER ON THE GOVERNOR WAS HARD TO MOV	E. THIS WAS CONFIRMED AND THE GOVERNOR WAS REMOVED FOR REPAIR. (TC NR 20070227011)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007053000042	20070530	00042	SW  	2007	5	30	CA070228004      	1	20061016	G	5302	212030132037	SPLICE          	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10085			ADW03247					(CAN) SPLICE CORRODED,TAIL BOOM REPLACED, A/C RETURNED TO SERVICE. (TC NR 20070228004)						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007053000043	20070530	00043	SW  	2007	5	30	CA070228005      	1	20060925	G	7921	R34665	BLADE           	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					BLOWER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				434  		10880704					(CAN) VIBRATION ON OIL COOLER BLOWER, FURTHER INVESTIGATION REVEALED ONE BLADE MISSING. SERVICEABLE OIL COOLER BLOWER IN	STALLED, A/C RETURNED TO SERVICE. (TC NR 20070228005)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007052400209	20070524	00209		2007	5	24	CA070302003      	4	20061212	G	2370	3LO4534	SWITCH          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	VOICE RECORDER	TRIPPED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING REMOVAL OF THE CVR FOR TESTING IT WAS DETERMINED THAT THE INERTIA SWITCH HAD BEEN PREVIOUSLY TRIPPED CAU	SING THE REQUIRED DATA NOT TO BE RECORDED. A RESET OF THE SWITCH HAD THE SAME RESULTS WITH PREMATURE ACTIVATION CAUSING 	THE RECORDING TO STOP. THE SWITCH WAS REPLACED WITH A NEW ASSEMBLY. (TC NR 20070302003)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007061300135	20070613	00135	EU  	2007	6	13	CA070315006      	2	20061018	G	7322	963178	BOWL            								ROTAX 	914   	ROTAX914    	 	EU  					CARBURETOR	DISTORTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			330  								(CAN) CARB FLOAT BOWL NUT WAS OVERTORQUED DURING A PREV MAINTENANCE EVENT. THIS DISTORTED THE FLOAT BOWL AND CAUSED THE 	FLOAT PINS TO BEND OUTWARDS. THIS CAUSED THE FLOATS TO CONTACT THE SIDE OF THE BOWL DURING OPERATION. OPERATOR NOTED INT	ERMITTENT ROUGH RUNNING THAT WAS ELIMINATED AFTER FLOAT BOWL WAS REPLACED. MM CONTAINS A CONVERSION ERROR THAT INCORRECT	LY LISTS THE TORQUE FOR THIS NUT IN FOOT POUND INSTEAD OF INCH POUNDS. THE METRIC TORQUE LISTED IS CORRECT. THIS MM IS C	URRENTY BEING REVISED. (TC NR 20070315006)							3	O			EXPE3I				 
2007060400035	20070604	00035	GL  	2007	6	4	CA070322002      	1	20061115	G	8011	656762	GEAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	STARTER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			206  					650200			(CAN) THE FACT THAT IT IS POSSIBLE TO ACCIDENTALLY ENGAGE THE STARTER DRIVE WHILE THE ENGINE IS RUNNING AND THAT THE STA	RTER GEAR ENGAGES INTO THE ACCESSORY CASE OF THE ENGINE WHICH WOULD RESULT IN SIMILAR DAMAGE, IT WAS SUSPECTED AT THE TI	ME THAT THE DAMAGE FOUND WAS A RESULT OF SUCH ENGAGEMENT. THEREFORE AT THE TIME A SDR DID NOT SEEM REQUIRED.   METAL WAS	 FOUND IN THE OIL FILTER ON INSPECTION, STARTER WAS REMOVED AND BOTH STARTER GEAR AND CLUSTER GEAR WERE FOUND DAMAGED BE	YOND MFG LIMITS DESCRIBED IN SB04-7.  FURTHER INSPECTION AT A LATER DATE INDICATED THAT THESE WERE MOST LIKELY NOT DUE T	O ACCIDENTAL ENGAGEMENT AS THE DAMAGED AREA ON THE CLUSTER GEAR WAS CONCENTRATED 180 DEGREES APART WHICH WOULD BE CONSIS	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007060400036	20070604	00036	GL  	2007	6	4	CA070322003      	1	20061129	G	5540	2055450001	BUSHING         	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	RUDDER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			102  								(CAN) DURING INSPECTION IT WAS NOTED THAT THE TOP RUDDER ATTACHMENT PIN BUSHING WAS MISSING. FURTHER INSPECTION REVEALED	 THE BUSHING HAD FALLEN OUT AND WAS SITTING IN A VOID AREA BELOW THE ASSEMBLY. THE BUSHING WAS RE-INSTALLED IAW MFG INST	RUCTION. THE RUDDER HAD NEVER BEEN REMOVED SINCE MANUFACTURE. (TC NR 20070322003)				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007060400051	20070604	00051	CE  	2007	6	4	CA070327004      	1	20060812	G	2434	DOFF300JR	ALTERNATOR      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	FAILED          	W				B				EMER. DESCENT           				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA				300  							(CAN) BURNING ELECTRICAL SMELL IN COCKPIT, LOSS OF CHARGING SYSTEM. (TC NR20070327004)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2007060400053	20070604	00053	NE  	2007	6	4	CA070327007      	2	20060610	G	8500	R985	ENGINE          			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  		MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) ENGINE NOT PRODUCING FULL TAKEOFF MANIFOLD PRESSURE.  (TC NR 20070327007)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007050300025	20070503	00025	CE  	2007	5	3	CA070402005      	1	20060102	G	3246	9543991	WHEEL           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					NR 3	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				147  							(CAN) DURING ROUTINE PRE-FLIGHT INSPECTION, NR 3 MAIN WHEEL ASSY FOUND TO BE ASSEMBLED INCORRECTLY. WHEEL HALF`S WERE MI	SALIGNED BY ONE BOLT HOLE. AMM 32-A2-00 PG.210. FORGED NRS AND LOT NRS WERE NOT ALIGNED. MAIN WHEEL ASSEMBLY REMOVED FRO	M AIRCRAFT, REPAIRED AND RE-ASSEMBLED IAW AMM 32-42-00 AND CMM AP-480 32-40-35. (TC NR 20070402005)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007050300028	20070503	00028	GL  	2007	5	3	CA070402007      	1	20060710	G	3246	C2UF2291	MECHANISM       	EDOFLOATS   		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FLOAT WIRE PULL	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						489					(CAN) FORWARD RT WIRE PULL BROKE, NEW WIRE PULL P/N C2UF2291 FOUND TO BE TOO SHORT. INVESTIGATION REVEALED WRONG TIE ROD	S AND WIRE PULLS INSTALLED IAW APPROVED DRAWINGS ACCEPTED REPLACEMENT PARTS INSTALLED IAW APPROVED DRAWINGS. (TC NR 2007	0402007)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2007050400105	20070504	00105	NM  	2007	5	4	CA070404005      	1	20060426	G	5697		TERMINAL BLOCK  	BOEING      		BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					WINDOW	OVERHEATED      	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						0525141740					(CAN) UNKNOWN ODOR IN CONTROL CABIN THOUGHT TO BE FROM LAVATORY. ISOLATED TO FLIGHT DECK. ON DESCENT INTO AIRPORT, ODOR 	DISSIPATED AND FAULT COULD NOT BE FOUND. AIRCRAFT CONTINUED WITH NO FUMES BUT SLIGHT ODOR WAS PRESENT AT END OF FLIGHT. 	TERMINAL BLOCK ON SLIDING WINDOW WAS FOUND OVERHEATED.  WINDOW WAS REPLACED. (TC NR 20070404005)				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2007080800160	20070808	00160	CE  	2007	8	8	CA070502013      	1	20060603	G	2720	051010551	CONTROL CABLE   			CESSNA	185   	185A        	2072804	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	RUDDER CONTROL	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE BOLT THAT ATTACHES THE LT FORWARD RUDDER CABLE TO THE RUDDER PEDAL SETUP WAS ORIGINALLY TOO TIGHTLY DONE UP. T	HE CABLE ATTACHMENT FORK WAS NOT ABLE TO MOVE FREELY ON END, IN THE FORK, AND BREAK UNDER LOAD.  (TC NR 20070502013)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007080900037	20070809	00037	CE  	2007	8	9	CA070517003      	1	20061214	G	2701	0411257	CONTROL WHEEL   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EXCESSIVE PLAY IN (U) JOINT ON LT CONTROL WHEEL. (TC NR 20070517003)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2008031900138	20080319	00138	CE  	2008	3	19	CA070517004      	1	20060918	G	3710	211CW	PUMP            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					VACUUM SYS	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				629  							(CAN) LOSS OF VACUUM DURING START-UP. (TC NR 20070517004)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007061800160	20070618	00160	EA  	2007	6	18	CA070517005      	2	20061203	G	7414		COIL            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MAGNETO	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1785 							(CAN) RT MAGNETO DEAD ON RUN-UP. (TC NR 20070517005)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007061800161	20070618	00161	EA  	2007	6	18	CA070517006      	2	20061125	G	8500		ENGINE          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  						SMOKE           	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA								17262921			(CAN) SMOKE SEEN COMING FROM COWLS INDUCTION FIRE SUSPECTED, SHUTDOWN AND PILOT DISCHARGED FIRE EXTINGUISHER INTO COWLIN	G.  (TC NR 20070517006)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082000111	20070820	00111	SO  	2007	8	20	CA070716004      	2	20060511	G	8530	AEC631397	CYLINDER        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NR 4	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 4 CYLINDER FOUND CRACKED DURING INSPECTION (TC IN20070716004)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2007082000138	20070820	00138	EA  	2007	8	20	CA070720009      	1	20060727	G	5610	6003303025	WINDSHIELD      			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF348E5A1   	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1233 								(CAN) LT WINDSHIELD OUTER PANE CRACKED IN FLIGHT WITH NO LOSS OF PRESSURIZATION.  FLIGHT CONTINUED NORMALLY.  NEW WINDSH	IELD INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070720009)					2	L	7	2 	4F	4	F	RT	A21AE   	E00063EN				 
	20081104		CE  	2008	11	4	CA070726005      	1	20061230	G	8011	EBB75A	GEAR            		MZ4206      	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			241  								(CAN) ENGINE WOULD NOT START, STARTER REMOVED, BENDIX FOUND SHATTERED. (TC NR 20070726005)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082000162	20070820	00162	GL  	2007	8	20	CA070731003      	1	20060929	G	5540	C2CF17778	TORQUE TUBE     			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK ON RUDDER TORQUE TUBE RT SIDE OB. (TC NR 20070731003)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007082000163	20070820	00163	CE  	2007	8	20	CA070731004      	1	20061023	G	2720	07123094	BELLCRANK       			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BELLCRANK HAS CRACKS ADJACENT TO AN3 BOLT HOLES.  (TC NR 20070731004)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2008013100050	20080131	00050		2008	1	31	CA071018002      	4	20061113	G	2562	AK450	ELT             			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					CABIN	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) SENT 2 ELTS TO INLAND COMMUNICATIONS FOR SERVICING, BOTH ELTS HAD FAULTY G-SWITCHES AND COULD NOT BE REPAIRED. SEN	T CORE IN FOR NEW AK-450 S/N 485068 THAT WAS INSTALLED ON NOV 13/06, WENT OFF ON LANDING AND AGAIN IN FLIGHT. REMOVED EL	T ON HOV 14/06. INSTALLED NEW AK-450-1 ELT S/N 485603 JAN 11/07, FAILED ON MAR 4/07 AND REMOVED. INSTALLED ANOTHER NEW A	K-450-1 ELT S/N 484979 ON MAY 30/07 AND IS STILL SERVICE. (TC NR 20071018002)			1	G	7	1 	3O	3	O		H10WE   	E286				 
2008022500084	20080225	00084	NE  	2008	2	25	CA071207001      	3	20061005	G	6111	6903A10	BLADE           	HAMSTD      		CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				405  		N196694					(CAN) DURING INSPECTION IAW AD 81-13-06R2 AND S/B 664, A CRACK WAS FOUND EMINATING FROM THE BLADE BUSHING SCREW HOLE. CR	ACK WAS FOUND TO BE TOO LARGE TO BE REMOVED. BLADE WAS RENDERED UNSERVICEABLE. BLADE S/N 852006. (TC NR 20071207001)					2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2008022500088	20080225	00088	SW  	2008	2	25	CA071210002      	1	20061227	G	6330	204031927005	MOUNT           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					TRANSMISSION	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			775  			A124043					(CAN) DURING ROUTINE POST FLIGHT DAILY INSP, (3) OF THE (4) AN4H6A BOLTS THAT ATTACH THE TRANSMISSION AFT (5TH) MOUNT TO	 THE AIRFRAME FITTING ASSY WERE FOUND SHEARED OFF. FLIGHT OPERATION WERE NOT AFFECTED AND CONSIDERED TO BE NORMAL AT THE	 TIME. THE MOUNT AND FITTING WERE REMOVED, INSPECTED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20071210002)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008022500100	20080225	00100	NE  	2008	2	25	CA071212001      	2	20061227	G	7200		ENGINE          			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					NR 2	MAKING METAL    	W				E				ENGINE SHUTDOWN         				K	M	J	FLUID LOSS                	OVER TEMP                 	WARNING INDICATION        	NR	NOT REPORTED   	1			CA								P115243			(CAN) ON DESERT TO BASE CREW NOTICED NR 2 ENGINE OIL PRESSURE AND TEMPERATURE CLIMBING, POWER REDUCED TO IDLE. OIL PRESS	URE DROPPED TO BELOW MINIMUMS (IN YELLOW ARC). CREW PERFORMED PRECAUTIONARY SHUTDOWN AND LANDED NORMALLY.   SUBSEQUENT I	NVESTIGATION REVEALED OIL HAD VENTED OUT THROUGH BREATHER. CHIP DETECTOR AND GEARBOXES CONTAMINATED WITH METAL PARTICLES	. ENGINE RETURNED FOR REPAIR AND INVESTIGATION OF CAUSE. (TC NR 20071212001)			2	L	7	3 	4F	4	F		A46EU   	E1NM				 
2008022500116	20080225	00116	EU  	2008	2	25	CA071212015      	1	20061123	G	2822	2260961	PUMP            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	FUEL BOOST	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) RT FUEL BOOST PUMP FAILED. (TC NR 20071212015)						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2008022000045	20080220	00045	NM  	2008	2	20	CA080123009      	1	20061218	G	2910	82590010239	LINE            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			43213								(CAN) LEAK FROM PIN HOLE IN HYD LINE RT WING, ON GROUND PRIOR TO TAXI TO GATE A/C GROUNDED. HYD LINE ASSY FOR RT WING SP	OILERS REPLACED WITH NO FURTHER INCIDENT OR LEAKAGE. (TC NR 20080123009)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081107		SO  	2008	11	7	CA080717004      	1	20060517	G	2435		FRICTION DISC   			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GENERATOR FRICTION DISC WAS WORN OUT AND WAS ALLOWING THE STARTER GENERATOR SHAFT TO WHIP ABOUT 6000 RPM (OPERATIN	G RANGE)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081107		EA  	2008	11	7	CA080915001      	1	20060802	G	2820	G201G202	FITTING         			FOUND 	FBA   	FBA2C1      	3640103	EA  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	UNDERTORQUED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			532  								(CAN) FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEADER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME	 OF SERVICE 532 HRS. PIPE THREAD FITTINGS HAD NO THREAD LUBE/SEALANT. THE VENDOR NOTED THAT THE FUEL FITTINGS WERE NOT P	ROPERLY TORQUED. THIS MAY REPRESENT A QUALITY CONTROL ISSUE AT THE FOUND ACFT PRODUCTION FACILITY. AT PRESENT THE USDOI,	 AVIATION MANAGEMENT DIRECTORATE, IS INVESTIGATING THIS EVENT WITHIN ITS FLEET."			1	H	7	1 	3O	3	O	NC	A7EA    	1E4				 
2006070500012	20060705	00012	NE  	2006	7	5	CHI2852          	2	20060419	G	7250	2002T29P01	LOCK NUT        	GE          		BOEING	107   	1072        	9420604	EA  	GE    	CT58  	CT581401    	30011	NE  					PWR TURBINE	FAILED          	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	6672D				52	2	280102L			UPON RECEIPT OF ENGINE FOR MAINTENANCE, IT WAS DISCOVERED THAT THE POWER TURBINE LOCKNUT HAD LOST TORQUE AND BACKED OFF 	OF THE POWER TURBINE TIE BOLT.  THE PROBABLE CAUSE WAS LOSS OF TORQUE.  A SPECIAL INSPECTION WAS INITIATED TO INCLUDE IN	SPECTING RUN-ON TORQUE.  A SPECIAL INSPECTION WAS INITIATED TO INCLUDE INSPECTING RUN-ON TORQUE AND PERFORMING AN NDT IN	SP OF ALL LOCKNUTS IN INVENTORY AND THOSE UNDERGOING MAINT.  ALL LOCKNUTS CURRENTLY INSTALLED ON AC WILL BE REPLACED AND	 THOSE LOCKNUTS WILL BE RETURNED TO REPAIR STA FOR INSP.  MFG WILL BE NOTIFIED OF INCIDENT IMMEDIATELAY.  (K)		2	G	7	2 	4U	4	U		1H16    	1E3				 
2006070500009	20060705	00009	EA  	2006	7	5	CHI44188         	1	20060518	G	6300	107D25535	COVER           			BOEING	107   	1072        	9420604	EA  										MIXER BOX	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	194CH	858  				404				CRACK DISCOVERED IN THE MIX BOX COVER, PN 107D25535.  THE CRACK RUNS FROM JUST UNDER THE WEB ON THE TOP OF THE MIX BOX L	T SIDE, INTO THE O-RING GROOVE IN THE FRONT OF THE COVER.  CRACK IS APPROX 6 INCHES OVERALL IN LENGTH.  DAMAGED AREA OF 	THE COVER HAS BEEN SENT TO LABORATORY FOR ANALYSIS.  (K)				2	G	7	2 	4U				1H16    					 
2006070600103	20060706	00103	EA  	2006	7	6	CHIR823CA        	1	20060608	G	6410	114R170244	BLADE           			BOEING	234   	234         	1385049	EA  										TAIL ROTOR	DEBONDED        	C			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	CFHFB	21142				MJ005				ROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329 APPROXIMATELY	 475-500 SQ INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE.  UNBONDED SKIN WAS REMOVED	 TO EXPOSE HONEYCOMB CORE FOR INSPECTION.  HONEYCOMB WAS OIL FREE AND APPEARED TO BE IN GOOD CONDITION.  THE ROTOR BLADE	 WILL UNDERGO FURTHER INVESTIGATION TO DETERMINE THE PROBABLE CAUSE AND REPAIR SCHEME, IF POSSIBLE.  MFG HAS BEEN NOTIFI	ED.  (K)		2	G	7	2 	4U				H9EA    					 
2006032100058	20060321	00058		2006	3	21	CMRR200602002    	4	20060227	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	OVERTEMP        	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	406FJ	9042 			00046519	3156				THE HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED JUST PRIOR TO TAKEOFF.  THE SUSPECTED SPECIFIC COMPONENT FAIL	URE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006031600040	20060316	00040		2006	3	16	CMRR200602003    	4	20060222	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					COCKPIT	OVERTEMP        	B			CMRR	K				NONE                    				H	M		ELECT. POWER LOSS-50 PC   	OVER TEMP                 		IN	INSP/MAINT     	1			SO	13	406FJ	9042 			99095560	3156				+THE NR 1 PFD DU-870 DISPLAY UNIT REFERENCED HERE IN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT F	AILURE IS THE HIGH VOLTAGE POWER SUPPLY PN 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL B	E REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006032200049	20060322	00049		2006	3	22	CMRR200603004    	4	20060314	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	OVERTEMP        	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	423FJ	7360 			00107696	3181				THE NR 1 PFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC CO	MPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECT	ION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006032100067	20060321	00067		2006	3	21	CMRR200603005    	4	20060314	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	OVERTEMP        	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	423FJ	7360 			00107818	3181				THE NR 2 MFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPEC	TED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  	FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006032100049	20060321	00049		2006	3	21	CMRR200603006    	4	20060314	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	OVERTEMP        	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	423FJ	7360 			00107817	3181				THE NR 1 MFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPEC	TED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  	FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006032100120	20060321	00120		2006	3	21	CMRR200603007    	4	20060314	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	OVERTEMP        	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	423FJ	7360 			00107359	3181				THE NR 2 PFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPEC	TED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  	FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006032100181	20060321	00181		2006	3	21	CMRR200603008    	4	20060314	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	OVERTEMP        	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	423FJ	7360 			00036246	3181				THE EICAS HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPECTED	 SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FUR	THER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006042700133	20060427	00133		2006	4	27	CMRR200603009    	4	20060324	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B			CMRR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	13	423FJ	7360 			0201A741	3181				THE EICAS HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING TAXI PRIOR TO FERRY.  THE SUSPECTED SPECIFIC COM	PONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. THIS PARTICUL	AR DU POSITION WAS PREVIOUSLY REPLACED AS WELL ON 3-14-06 BUT THE CUSTOMER DID NOT WANT AN UPGRADED MOD K UNIT INSTALLED	.  FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.			2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006051000224	20060510	00224		2006	5	10	CMRR200604010    	4	20060426	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B			CMRR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	13	407FJ	8913 			00046519	3157				THE NR 1 PFD DISPLAY UNIT REFERENCED HERE IN FAILED DURING TAXI OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPO	NENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECT	IONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006051000225	20060510	00225		2006	5	10	CMRR200604011    	4	20060426	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY UNIT	FAILED          	B			CMRR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	13	407FJ	8913 			00036262	3157				THE NR 1 MFD DISPLAY UNIT REFERENCED HERE IN FAILED DURING TAXI OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPO	NENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPEC	TIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006061900177	20060619	00177		2006	6	19	CMRR200606012    	4	20060526	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			SO	13	403FJ	9553 			00036143	3149				THE NR 1 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMP	ONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN: 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPE	CTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006062000019	20060620	00019		2006	6	20	CMRR200606013    	4	20060526	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					DISPLAY	FAILED          	B			CMRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	403FJ	9553 			00087125	3149				THE NR 1 PFD HONEYWELL DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FLIGHT.  THE SUSPECTED SP	ECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FU	RTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100128	20061031	00128		2006	10	31	CMRR200610014    	4	20061027	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	428FJ	6881 			01028536	3193				THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100129	20061031	00129		2006	10	31	CMRR200610015    	4	20061027	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	428FJ	6881 			01059291	3193				THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100130	20061031	00130		2006	10	31	CMRR200610016    	4	20061027	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	428FJ	6881 			01018337	3193				THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS T	HE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQ	UIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100131	20061031	00131		2006	10	31	CMRR200610017    	4	20061027	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	428FJ	6881 			00097242	3193				THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100132	20061031	00132		2006	10	31	CMRR200610018    	4	20061027	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	428FJ	6881 			00097260	3193				THE NR 5 PFD DISPLAY UNIT REFRENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS	 THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE R	EQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100133	20061031	00133		2006	10	31	CMRR200610019    	4	20061019	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	405FJ	9298 			00036374	3155				THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS T	HE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQ	UIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100134	20061031	00134		2006	10	31	CMRR200610020    	4	20061023	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	420FJ	8290 			00046474	3178				THE NR 5 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100135	20061031	00135		2006	10	31	CMRR200610021    	4	20061023	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	420FJ	8290 			00107614	3178				THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100136	20061031	00136		2006	10	31	CMRR200610022    	4	20061019	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	405FJ	9298 			00067009	3155				THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006103100137	20061031	00137		2006	10	31	CMRR200610023    	4	20061023	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	420FJ	8290 			02014704	3178				THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006110100112	20061101	00112		2006	11	1	CMRR200611024    	4	20061017	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	365SK	8912 			00066818	3165				THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006110100111	20061101	00111		2006	11	1	CMRR200611025    	4	20061017	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	365SK	8912 			00066839	3165				THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS T	HE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQ	UIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006110100115	20061101	00115		2006	11	1	CMRR200611026    	4	20061017	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	365SK	8912 			00066873	3165				THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006110100114	20061101	00114		2006	11	1	CMRR200611027    	4	20061017	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	365SK	8912 			00128053	3165				THE NR 5 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2006110100113	20061101	00113		2006	11	1	CMRR200611028    	4	20061017	G	3160	7018704902	POWER SUPPLY    	HONEYWELL   	DU870       	DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					EFIS	FAILED          	B			CMRR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SO	13	365SK	8912 			00066838	3165				THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE I	S THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE 	REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.				2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2007010400023	20070104	00023	NM  	2007	1	4	COOSDR060032     	1	20060824	G	5712		RIB             			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					RT WING	CRACKED         	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	563AU					23551				RT WING AT WBL 114 RIB UPPER CHORD CRACKED NEAR STR-2.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007010400024	20070104	00024	NM  	2007	1	4	COOSDR060034     	1	20060825	G	3320	S283U00816	BALLAST         			BOEING	737   	7377Q8      	1384418	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					CABIN	OVERHEATED      	B			EE4Y	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	23	161LF					28224				PAX CABIN LIGHT BALLAST OVERHEATED BURNING INSULATION BLANKET AT BS 328, STR 1.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2007012500020	20070125	00020	CE  	2007	1	25	CWQD200701       	1	20061225	G	2910	AE1011888G0106	HOSE            			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					HYD SYSTEM	LEAKING         	E			DXTA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			GL	05	990QS	4918 				7500190				DURING FINAL APPROACH THE GEAR WAS SELECTED DOWN AND THE (A) HYDRAULIC QTY FELL TO 6 PERCENT WITH (HYD VOL LOW) CAS MESS	AGE.  JACKED AIRCRAFT, REMOVED PANEL 184DB AND FOUND THE RT GEAR MLG ACTUATOR RETRACT HOSE ASSY HAD A HOLE IN IT.					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2006040500002	20060405	00002	CE  	2006	4	5	CWQR2006001      	1	20060302	G	2710	666000216	TURNBUCKLE      			CESSNA	560   	560XL       	2076702	CE  										CONTROL CABLE	MISMANUFACTURED 	B			DXTA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	631QS					5605131				DURING A CABLE CHANGE ON THE AILERON SYSTEM, THE PROPER CABLE TENSION COULD NOT BE BROUGHT UP.  UPON INSPECTION FOUND NE	W CABLE ASSEMBLY TERMINAL END WAS NOT PROPERLY MACHINED.  BECAUSE THE NECK (AREA BETWEEN THREADS AND TOOL HOLE) WAS NOT 	REDUCED THE TURNBARREL BOTTOMS ON THREADS AND CAN NOT BE ADJUSTED TO TENSION REQUIRED.				2	L	7	2 	4F			RT	A22CE   					 
2006040500036	20060405	00036	CE  	2006	4	5	CWQR2006002      	1	20060302	G	5100	991406742	OXYGEN BOTTLE   			CESSNA	750   	750         	2076810	CE  											UNSERVICEABLE   	B			DXTA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	942QS					7500024				RECEIVED OXYGEN CYLINDER AND REGULATOR FROM CESSNA WITH A CYLINDER BEYOND ITS SERVICE LIFE.  BOTTLE HAS 15 YEAR SERVICE 	LIFE PER CE750 M/M CHAP 5. BOTTLE MFD DATE 9/87.  RED TAGGED BOTTLE AND RETURNED TO CESSNA PARTS.					2	L	7	2 	4J			RT	T00007WI					 
2006050100239	20060501	00239	CE  	2006	5	1	CWQR2006003      	1	20060308	G	3411	68C48	DRAIN VALVE     			CESSNA	560   	560XL       	2076702	CE  										PITOT STATIC SYS	LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	633QS					5605526				FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.						2	L	7	2 	4F			RT	A22CE   					 
2006041100048	20060411	00048	CE  	2006	4	11	CWQR2006004      	1	20060308	G	3411	68C48	DRAIN VALVE     			CESSNA	560   	560XL       	2076702	CE  										STATIC SYSTEM	LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	648QS					5605574				FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.						2	L	7	2 	4F			RT	A22CE   					 
2006032400034	20060324	00034	CE  	2006	3	24	CWQR2006005      	1	20060308	G	3411	68C48	DRAIN VALVE     			CESSNA	560   	560XL       	2076702	CE  										STATIC SYS	LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	609QS					5605522				FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE.						2	L	7	2 	4F			RT	A22CE   					 
2006041100049	20060411	00049	CE  	2006	4	11	CWQR2006006      	1	20060308	G	3411	68C48	DRAIN VALVE     			CESSNA	560   	560XL       	2076702	CE  											LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	650QS					5605150				FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.						2	L	7	2 	4F			RT	A22CE   					 
2006041100050	20060411	00050	CE  	2006	4	11	CWQR2006007      	1	20060308	G	3411	68C48	DRAIN VALVE     			CESSNA	560   	560XL       	2076702	CE  											LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	664QS					5605264				FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.						2	L	7	2 	4F			RT	A22CE   					 
2006033100116	20060331	00116	CE  	2006	3	31	CWQR2006008      	1	20060308	G	3411		RETAINER        			CESSNA	560   	560XL       	2076702	CE  										DRAIN VALVE	LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	651QS					5605251				FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE.						2	L	7	2 	4F			RT	A22CE   					 
2006050100246	20060501	00246	CE  	2006	5	1	CWQR2006009      	1	20060417	G	2701	666000269	CABLE ASSY      			CESSNA	560   	560XL       	2076702	CE  										FUSELAGE	DAMAGED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										DURING A SCHEDULED MAINTENANCE VISIT BEFORE REPLACING A CABLE ASSEMBLY ON A THE CABLE TERMINAL END WAS FOUND TO HAVE BEE	N DRILLED TO A DEPTH OF .3750-.5 INCH AT AN ANGLE AND DAMAGED THE THREADS. THIS CABLE ASSEMBLY WAS ORDERED FROM AND DOCU	MENTED AS NEW.				2	L	7	2 	4F			RT	A22CE   					 
2006050100247	20060501	00247	CE  	2006	5	1	CWQR2006010      	1	20060427	G	3250	55423043	FORK            			CESSNA	560   	560XL       	2076702	CE  										NOSE STEERING	GOUGED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	638QS	2260 				5605363				DURING AN INSPECTION FOUND THE NOSE GEAR STEERING LOWER FORK ASSY (5542304-3) GOUGED. FURTHER INVESTIGATION FOUND THE FO	RK ASSY IS GOUGED ONLY DURING A MAINTENANCE GEAR RETRACTION TEST, WHEN THE RUDDER PEDALS ARE DEFLECTED FULL RT AND LT. R	EMOVED FORK ASSY, MEASURED GOUGE WAS BEYOND LIMITS.  REPLACED FORK AND PREFORMED GEAR RETRACTION TEST, THE NEW FORK ASSY	 WAS MEASURED AND PREFORMED NDT, WAS WITHIN LIMITS IAW MM.  SUBMITTED SERVICE CONDITION REPORT MFG UNDER NR 234220 DATED	 04/27/2006.		2	L	7	2 	4F			RT	A22CE   					 
2006062900109	20060629	00109	CE  	2006	6	29	CWQR2006011      	1	20060626	G	2731	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	692QS					5605092				DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZO	NTAL STABILIZER.  THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND IT DOES NOT LOOK AS IF IT WAS DAMAGED DURING INS	TALLATION.  AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER 242171.				2	L	7	2 	4F			RT	A22CE   					 
2006062900110	20060629	00110	CE  	2006	6	29	CWQR2006012      	1	20060626	G	2731	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	684QS					5605084				DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZO	NTAL STABLIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND IT DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTA	LLATION.  AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER 242172.				2	L	7	2 	4F			RT	A22CE   					 
2006071400058	20060714	00058	CE  	2006	7	14	CWQR2006013      	1	20060628	G	2731	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	671QS					5605071				DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZO	NTAL STABILIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALL	ATION. AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER # 242686				2	L	7	2 	4F			RT	A22CE   					 
2006071900001	20060719	00001	CE  	2006	7	19	CWQR2006014      	1	20060712	G	2731	666000134	CABLE ASSY      			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	637QS					5605137				REQUESTED CABLE INSPECTION OF AFT ELEVATOR TRIM CABLE, BECAUSE AC IN THE FLEET OF THIS SN BLOCK AND TIME SHOWED SIGNS OF	 FRAYING. DURING INSPECTION FOUND THE CABLE FRAYED AS IT TRANSVERSED THE PULLEY. REMOVED CABLE AND CHAIN ASSEMBLY AND PR	EFORMED LOOP CHECK, THIS SHOWED MORE STRANDS BROKEN THEN WHEN VISUALLY INSPECTED ON AIRCRAFT.  PRIOR TO REMOVAL THE CABL	E TENSION WAS CHECKED AND FOUND TO BE WITHIN LIMITS, CABLE AND PULLEYS HAD GOOD ALIGNMENT AND NO ABNORMAL WEAR ON THE PU	LLEYS. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 244358		2	L	7	2 	4F			RT	A22CE   					 
2006072500237	20060725	00237	CE  	2006	7	25	CWQR2006015      	1	20060717	G	2731	666000134	CABLE           			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			GL	05	690QS					5605090				DURING A SCHEDULED INSP ON THIS AIRCRAFT THE OPERATOR REQUESTED THAT WE INSPECT THE AFT CABLES ON THE ELEVATOR TRIM SYST	EM. PRIOR TO REMOVAL WE CHECKED THE CABLE TENSION, FOUND IT TO BE 30 LBS CABLE TENSION SHOULD BE 45 +/-5 LBS AT 75 DEGRE	ES.  INSP AFTER THE CABLE WAS REMOVED REVEALED 1 COMPLETE STRAND BROKE AND SEVERAL WIRES. THE DAMAGED AREA WAS LOCATED D	IRECTLY OVER THE PULLEY WHEN THE TAB IS IN THE 2-3 DEGREE DOWN POSITION. THIS IS THE FIFTH ELEVATOR TRIM CABLE THIS REPA	IR STATION HAS FOUND DAMAGED ON THIS MODEL AIRCRAFT WITH TOTAL TIME OF 5000 +/-500 HOURS. AN SCR HAS BEEN SUBMITTED TO M	FR UNDER NR 244926	2	L	7	2 	4F			RT	A22CE   					 
2006081600309	20060816	00309	CE  	2006	8	16	CWQR2006016      	1	20060728	G	2731	666015021	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATORS	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	694QS					5605194				DURING PHASE 1-4 INSPECTION, IAW OPERATOR REQUEST WE INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND A 	SINGLE BROKEN WIRE. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL MORE BROKEN WIRES. PRIOR TO DISASSEMBLY THE 	CABLE TENSION, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SCR HAS BEEN SUBMITTED UN	DER NR 246824.			2	L	7	2 	4F			RT	A22CE   					 
2006081400144	20060814	00144	CE  	2006	8	14	CWQR200617       	1	20060731	G	2731	666015011	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	687QS					5605187				DURING PHASE B INSPECTION, IAW OPERATOR REQUEST, INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND 3 BROK	EN WIRES. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL BROKEN WIRES IN EACH STRAND. THE BROKEN WIRES WERE FOU	ND IN THE AREA AS IT CROSSES THE PULLEY, WITH TAB NEUTRAL TO 1-2 DEGREES DOWN. PRIOR TO DISASSEMBLY THE CABLE TENSION WA	S CHECKED, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SDR HAS BEEN SUBMITTED TO MFG	 UNDER NR 246824.		2	L	7	2 	4F			RT	A22CE   					 
2006082500041	20060825	00041	CE  	2006	8	25	CWQR200618       	1	20060807	G	2731	666000133	CABLE ASSY      			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	659QS					5605359				DURING A PHASE B INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN	 WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP 	TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SI	RS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCAR HAS BEEN SUBMITTED TO MFG U	NDER NR 248175.		2	L	7	2 	4F			RT	A22CE   					 
2006082500051	20060825	00051	CE  	2006	8	25	CWQR200619       	1	20060809	G	2731	666000133	CABLE ASSY      			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	605QS					5605321				DURING A PHASE B INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN	 WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY.  THE CABLE WAS REMOVED AND LOOP	 TEST SHOWED MORE BROKEN WIRES.  THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS 	SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO UNDE	R NR 248556.		2	L	7	2 	4F			RT	A22CE   					 
2006082500034	20060825	00034	CE  	2006	8	25	CWQR200620       	1	20060814	G	2731	666000133	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	610QS					5605210				DURING A PHASE B-INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN	 WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY.THE CABLE WAS REMOVED AND LOOP T	EST SHOWED MORE BROKEN WIRES.  THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SD	RS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO UNDER 	NR 249122.		2	L	7	2 	4F			RT	A22CE   					 
2006082500035	20060825	00035	CE  	2006	8	25	CWQR200621       	1	20060821	G	2731	666000133	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	640QS					5605240				DURING A PHASE B-INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN	 WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP 	TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SD	RS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO MFG UN	DER NR 250170.		2	L	7	2 	4F			RT	A22CE   					 
2006082500016	20060825	00016	CE  	2006	8	25	CWQR200622       	1	20060821	G	2731	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	FRAYED          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	621QS					5605280				DURING A PHASE B-INSPECTION, OPERATOR REQUESTED, INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION FOUND BROKEN WIRE	S, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST 	SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SU	BMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO MFG UNDER N	R 250168.		2	L	7	2 	4F			RT	A22CE   					 
2006082500032	20060825	00032	CE  	2006	8	25	CWQR200623       	1	20060821	G	2720	666000228	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										RUDDER	FRAYED          	B			DXTA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			GL	05										THE CABLE ASSEMBLY WAS RECEIVED FROM MFG, WITH AN 8130 SHOWING IT TO BE NEW. THE CABLE HAS SEVERAL BROKEN WIRES THAT APP	EARS TO BE A MANUFACTURING DEFECT. THIS REPORT AND PICTURES WILL BE FORWARDED TO THE OPERATOR AND MFG. AN SCR HAS BEEN S	UBMITTED TO MFG UNDER NR 250181.				2	L	7	2 	4F			RT	A22CE   					 
2006091300145	20060913	00145	CE  	2006	9	13	CWQR200624       	1	20060821	G	2740	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	BROKEN          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	668QS					5605268				DURING A PHASE 1-4 INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROK	EN WIRES. TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED ON THE PULLEYS. THE CABLE WAS REMOVED AN	D LOOP TEST SHOWED MORE BROKEN WIRES. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250293.				2	L	7	2 	4F			RT	A22CE   					 
2006092200105	20060922	00105	CE  	2006	9	22	CWQR200625       	1	20060829	G	2720	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										TRIM	BROKEN          	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	646QS					5605246				DURING A ROUTINE MAINTENANCE VISIT, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND	 ABOUT .333 OF THE CABLE STRANDS BROKEN. TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED ON THE PU	LLEYS. THE CABLE APPEARS TO HAVE THE MOST DAMAGE CENTERED ON THE PULLEY WITH THE ELEVATOR TRIM TAB IN THE NEUTRAL TO 1-2	 DEGREE DOWN POSITION. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 251700.			2	L	7	2 	4F			RT	A22CE   					 
2006051800232	20060518	00232	EU  	2006	5	18	D20060502        	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA					029007				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2007010800275	20070108	00275	WP  	2007	1	8	DJSA20061202     	2	20061202	G	7200	TFE7315BR2C	ENGINE          			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  						FAILED          	E			DJSR	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			GL	23	531FL	5815 	961  			113	P95155C			UNCONTAINED ENGINE FAILURE DURING CLIMB AT 600 FEET AGL.  AIRCRAFT RETURNED, MAKING AN UNEVENTFUL LANDING.  ENGINE HAS B	EEN RETURNED TO MANUFACTURER FOR TEARDOWN AND EVALUATION TO DETERMINE CAUSE OF FAILURE.					2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2006051800229	20060518	00229	EU  	2006	5	18	DOSS002          	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA					029007				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800197	20060518	00197	EU  	2006	5	18	DOSS01           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										ZONE 200	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	434BA	1330 				029011				LONGERON WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INS	PECTION. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FO	OT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SC	REWS.  THIS WAS ENCOUNTERED ON TWELVE OUT OF SEVENTEEN AIRCRAFT (L13AC AND L23).			1	K	0	0 	  			RC	G24EU   					 
2006051800228	20060518	00228	EU  	2006	5	18	DOSS02           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA					029007				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS.  IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOO	T WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2006052200211	20060522	00211	EU  	2006	5	22	DOSS03           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	426BA	1115 	92   			029008				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCRE	WS.		1	K	0	0 	  			RC	G24EU   					 
2006051800233	20060518	00233	EU  	2006	5	18	DOSS04           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	427BA	873  	14   			029009				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2006053000168	20060530	00168	EU  	2006	5	30	DOSS05           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	428BA	1123 	5    			029010				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE REAR COCKPIT (RCP) LT RUDDER	 PEDAL DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME IN	SPECTION OF ALL MODELS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE 	WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS 	AT THE ATTACH SCREWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800234	20060518	00234	EU  	2006	5	18	DOSS06           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	430BA	1461 				029012				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION.   SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF 	ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FO	OT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH S	CREWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800235	20060518	00235	EU  	2006	5	18	DOSS07           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	431BA	1120 	68   			029013				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800236	20060518	00236	EU  	2006	5	18	DOSS08           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	433BA	978  				029014				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800237	20060518	00237	EU  	2006	5	18	DOSS10           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	438BA	524  	41   			029016				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCR	EWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800231	20060518	00231	EU  	2006	5	18	DOSS102          	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA					029007				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION.  SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF A	LL MDS.  IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FO	OT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH S	CREWS.		1	K	0	0 	  			RC	G24EU   					 
2006051800238	20060518	00238	EU  	2006	5	18	DOSS11           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	419BA	1320 	71   			029006				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION.  SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF A	LL MDS.  IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FO	OT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH S	CREWS.		1	K	0	0 	  			RC	G24EU   					 
2006053000163	20060530	00163	EU  	2006	5	30	DOSS12           	1	20060502	G	5313		LONGERON        			LET   	L13   	L13ACBLANIK 	1360312	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	422BA	1109 	54   			028903				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE REAR COCKPIT (RCP) LT RUDDER	 PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME I	NSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT, MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS	/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE A	TTACH SCREWS.		1	K	0	0 	  				G24EU   					 
2006051800258	20060518	00258	EU  	2006	5	18	DOSS13           	1	20060502	G	5313		LONGERON        			LET   	L23   	L23         	1360308	EU  										REAR COCKPIT	CRACKED         	B			PF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	410BA	1109 	54   			029005				FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING 	A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF AL	L MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT	 WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCRE	WS.		1	K	0	0 	  			RC	G24EU   					 
2006101300040	20061013	00040	WP  	2006	10	13	DSC4L6255        	2	20061003	G	7210	18118	BEARING         								GARRTT	TPE331	TPE33111U   	01514	WP  					GEARBOX	FAILED          	B			DSC4	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	15		6475 					P44628C			ENGINE RECEIVED FOR REPORTED METAL IN OIL.  UPON DISASSEMBLY, FOUND BEARING PN: 18118 (FAA-PMA REPLACEMENT  PN: 3103585-	1) INSTALLED IN ACCESSORY GEAR ASSY PN: 3103598-1 HAD FAILED, CAUSING MULTIPLE ACCESSORY GEAR DAMAGE AND METAL CONTAMINA	TION IN GEARBOX / OIL SYSTEM.									4	T			E4WE				 
2006041100027	20060411	00027	NM  	2006	4	11	DU4R2006342      	1	20060313	G	5330		SKIN            			BOEING	727   	727223      	1384074	NM  										BS 1074 S18-19L	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				FUSELAGE SKIN DENTED AT BS 1074 BETWEEN S-18L - 19L.     CUT OUT DENTED AREA IAW B727 SRM 53-30-2 FIG. 1 HFEC AROUND CUT	 OUT PER D6-48875, PT 6, 51-10-00 FIG. 23. NO RELEVANT INDICATION NOTED. FABRICATED AND INSTALLED REPAIR DOUBLER 12" X 1	1.7" X 7.55" FROM 2024-T3 .063 IAW B727 SRM 51-30-3 FIG. 1, 51-10-2, 51-30-2, 53-30-3 CLASS "A" REPAIR.				2	L	7	3 	4F				A3WE    					 
2006041100028	20060411	00028	NM  	2006	4	11	DU4R2006343      	1	20060313	G	5330		SKIN            			BOEING	727   	727223      	1384074	NM  										BS 1079	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				FUSELAGE SKIN DENTED AT BS 1079 BETWEEN S-13-14L.   CUT OUT DENTED AREA IAW B727 SRM 53-30-3 FIG. 13A. FABRICATED AND IN	STALLED REPAIR DOUBLER 5.80 DIAMETER FROM 2024-T3 .090 IAW B727 SRM  51-10-2 PG. 7, AMM 51-20-23 PG. 704. CLASS "A" REPA	IR.				2	L	7	3 	4F				A3WE    					 
2006041100024	20060411	00024	NM  	2006	4	11	DU4R2006344      	1	20060320	G	5330		SKIN            			BOEING	727   	727223      	1384074	NM  										BS 1145	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				FUSELAGE SKIN DENTED AT BS 1145 BETWEEN S18-19L.   FABRICATED AND INSTALLED REPAIR DOUBLER 10-3/4" X 9" FROM 2024-T3 .06	3 IAW B727 SRM  53-30-3 AND 51-30-2. CLASS "A" REPAIR.					2	L	7	3 	4F				A3WE    					 
2006041100026	20060411	00026	NM  	2006	4	11	DU4R2006345      	1	20060322	G	5315	65255896	FLOORBEAM       			BOEING	727   	727223      	1384074	NM  										BS 760 RBL 1	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				CRACK IN CABIN FLOOR SUPPORT BS 760 RBL 1.    REMOVED AND REPLACED FLOOR SUPPORT WITH  IAW B727 SRM  51-30-2 AND 51-30-5	.					2	L	7	3 	4F				A3WE    					 
2006041100023	20060411	00023	NM  	2006	4	11	DU4R2006346      	1	20060326	G	5310		STRUCTURE       			BOEING	727   	727223      	1384074	NM  										BS 1166	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				RT AFT LAV SUB FLOOR HAS CORROSION IN SEVERAL PLACES AT BS 1166. CUT OUT CORROSION. FABRICATED AND INSTALLED WEB REPAIR 	15-3/4" X 4-3/4" FROM 2024-T3 .071 IAW B727 SRM  51-40-2, 51-30-2, 51-10-2 AND AMM 51-20-23.					2	L	7	3 	4F				A3WE    					 
2006041100025	20060411	00025	NM  	2006	4	11	DU4R2006347      	1	20060326	G	5347	656426110	SEAT TRACK      			BOEING	727   	727223      	1384074	NM  										BS1120-1133	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				CORROSION ON LT O/B SEAT TRACK BS 1100-1133.  REMOVED CORRODED SEAT TRACK FROM BS 1070 TO BS 1137 AND REPLACED IAW B727 	SRM 51-30-2, 51-10-2 AND AMM 51-20-23.					2	L	7	3 	4F				A3WE    					 
2006041100022	20060411	00022	NM  	2006	4	11	DU4R2006355      	1	20060331	G	5330		SKIN            			BOEING	727   	727223      	1384074	NM  										BS 1137 S20L	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				FUSELAGE SKIN BELOW NR 1 ENGINE DENTED AT LAP SEAM BS 1137 S-20L.  CUT OUT DENTED AREA. FABRICATED AND INSTALLED EXTERNA	L REPAIR 7.75" X 9.25" X5.75" X 2.5" FROM 20240-T3 .063 AND LAP SPLICE REPAIR 10" X 4.25" X 4.5" X 2.75" X 4.5" FROM 202	4-T3 .050 IAW B727 SRM 53-30-3 FIG. 5, 51-10-3.				2	L	7	3 	4F				A3WE    					 
2006051800178	20060518	00178	NM  	2006	5	18	DU4R2006358      	1	20060412	G	5752		TAB             			BOEING	727   	727223      	1384074	NM  										RT AILERON	DELAMINATED     	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001; NR 21453 - RT IB AILERON TAB DELAMINATED AT LOWER SURFACE OUTER L/E AREA.  CUT OUT DISBONDED SKIN. FABRICATE	D AND BONDED DOUBLER 10.5  X 3.7500 INCH X 9 X 3.5 X 2.2500 INCH AND FILLER 8 INCH X 1.7500 INCH X 7.2500 INCH X 1 INCH 	X 1 INCH FROM 2024-T3, .012 IAW SRM 51-40-20 PG. 14, 15, 42 - 47 AND 62, 51-60-3 AND 51-80-3.				2	L	7	3 	4F				A3WE    					 
2006051200159	20060512	00159	NM  	2006	5	12	DU4R2006359      	1	20060412	G	5753		FLAP            			BOEING	727   	727223      	1384074	NM  										LT WING	DELAMINATED     	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001   N/R 21634 - LT IB FORE FLAP UPPER SIDE HAS DISBOND AFT OF CENTER ACCESS PANEL.  CUT OUT DISBONDED UPPER SKI	N AND HONEYCOMB. FABRICATED AND BONDED DOUBLERS 13-5/8" X 11" AND 12-1/2" X 11-1/4"  AND 9-1/4" X 8? X 5" X 5" X 5" FROM	 2024-T3 .016 AND AND 2 EA. HONEYCOMB REPAIRS 9-1/4" X 5" X 5" X 5" X 8" FROM BMS4-4 IAW B727 SRM 57-50-2 PG. 5, 51-40-2	0 PG. 15, 22, 23, 44 - 47, 53-57, 59, 62 AND 51-40-23 PG. 1-8.			2	L	7	3 	4F				A3WE    					 
2006051800260	20060518	00260	NM  	2006	5	18	DU4R200636       	1	20060412	G	5320		FLOOR SUPPORT   			BOEING	727   	727223      	1384074	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)  N/R 21660, CORROSION ON FLOOR SUPPORT THAT ATTACHES TO CUSP WEB AT BS 1070 - 1030 LT.  MECHANICALLY REMOVED	 CORROSION FOUND OUT OF LIMITS.  CUT AND TRIMMED CORRODED SECTION. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLES 88.0 IN	CHES X 4.50 FROM 7075-T6 .080 AND 10.0INCHES X 1.80 INCHES X 1.50 INCHES 7075-T6 .090 IAW SRM 51-30-2.				2	L	7	3 	4F				A3WE    					 
2006051800226	20060518	00226	NM  	2006	5	18	DU4R2006360      	1	20060412	G	5753		FLAP            			BOEING	727   	727223      	1384074	NM  										LT WING	CHAFED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)  N/R 21637 - LT IB FORE FLAP UNDER SIDE LEADING EDGE 8 INCHES FROM OB END HAS CHAFED AREA.  BLENDED CHAFED A	REA, FOUND OUT OF LIMITS, FABRICATED AND INSTALLED DOUBLER 3.750 INCHES X 6.0 INCHES FROM 2024-T3 .063 IAW SRM 57-50-04 	PG. 2-3.				2	L	7	3 	4F				A3WE    					 
2006051800227	20060518	00227	NM  	2006	5	18	DU4R2006361      	1	20060412	G	5753		FLAP            			BOEING	727   	727223      	1384074	NM  										LT WING	DEBONDED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)   N/R 21640 - LT IB FT FLAP IB END HAS AREA OF DEBOND.  REPAIRED BY CLEANING, PREPPED AND REPAIRED IAW SRM 5	1-40-21 FIG. 1.					2	L	7	3 	4F				A3WE    					 
2006051800225	20060518	00225	NM  	2006	5	18	DU4R2006362      	1	20060412	G	5347	BAC1518338	FLOORBEAM       			BOEING	727   	727223      	1384074	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)  N/R 21652 - CORROSION ON BS 1070 LBL 10 FLOOR BEAM.  CUT OUT CORRODED AREA.  FABRICATED AND INSTALLED FLOOR	BEAM REPAIR 22.20 INCHES FROM BAC1505-100617 7075-T73 AND 22.20 INCHES FROM BAC1490-2831 7075-T6 IAW SRM 53-10-8 FIG. 8,	 AND 51-10-1.				2	L	7	3 	4F				A3WE    					 
2006051800224	20060518	00224	NM  	2006	5	18	DU4R2006363      	1	20060412	G	5347	BAC1518338	SEAT TRACK      			BOEING	727   	727223      	1384074	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001, N/R 21653 - CORROSION ON IB SIDE OF SEAT TRACK ALONG RADIUS AT BS 1090 - 1030 LBL 40.   CUT OUT CORRODED ARE	A OF SEAT TRACK.  FABRICATED AND INSTALLED SEAT TRACK REPAIR 18 INCHES X 3.5 FROM BAC1520-792 IAW SRM 51-30-2, 51-20-2 A	ND 51-10-1.				2	L	7	3 	4F				A3WE    					 
2006051800249	20060518	00249	NM  	2006	5	18	DU4R2006364      	1	20060412	G	5347	656426110	SEAT TRACK      			BOEING	727   	727223      	1384074	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)  N/R 21656, CORROSION ON LT OB SEAT TRACK AT BS 1080.  MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS.  	REMOVED AND REPAIRED SEAT TRACK WITH P/N 65-64261-10 IAW SRM 51-30-2.					2	L	7	3 	4F				A3WE    					 
2006051800259	20060518	00259	NM  	2006	5	18	DU4R2006365      	1	20060412	G	5320		FLOOR SUPPORT   			BOEING	727   	727223      	1384074	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001) N/R 21660, CORROSION ON FLOOR SUPPORT THAT ATTACHES TO CUSP WEB AT BS 1070 - 1030 LT.  MECHANICALLY REMOVED 	CORROSION FOUND OUT OF LIMITS.  CUT AND TRIMMED CORRODED SECTION. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLES 88.0 INC	H X 4.50 FROM 7075-T6 .080 AND 10.0 INCHES X 1.80 INCHES X 1.50 INCHES 7075-T6 .090 IAW SRM 51-30-2.				2	L	7	3 	4F				A3WE    					 
2006051800250	20060518	00250	NM  	2006	5	18	DU4R2006366      	1	20060412	G	5330		SKIN            			BOEING	727   	727223      	1384074	NM  										FUSELAGE	GOUGED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)   N/R 21743,  2 GOUGES IN SKIN ON LT SIDE OF FS 460 AND 4 INCHES BELOW S-14 BELOW NR 5 WINDOW.  FABRICATED A	ND INSTALLED 2 EA. DOUBLERS 4.5 INCH AND 4.3 DIAMETER FROM 2024-T3 .071 AND 1 EA, .7500 INCH DIAMETER FROM 2024-T3 .050 	IAW SRM 53-30-3 FIG. 13, MM 25-21-01.				2	L	7	3 	4F				A3WE    					 
2006051800270	20060518	00270	NM  	2006	5	18	DU4R2006367      	1	20060412	G	5754		SKIN            			BOEING	727   	727223      	1384074	NM  										RT WING SLAT	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001, N/R 23584 - RT WING NR 5 SLAT TOPSIDE L/E DENTED.  CUT OUT DENT THAT WAS OUT OF LIMITS. FABRICATED AND INSTA	LLED REPAIR SKIN DOUBLER 5.5 INCH X 5.5 INCH FROM 2024-T3 .016 AND 2 EA.  SKIN REPAIR DOUBLERS 4.1 INCH X 4.1 INCH AND 1	.6 INCH X 1.6 INCH 2024-T3 .040 IAW SRM 55-50-3 FIG. 1, AND 51-30-2.				2	L	7	3 	4F				A3WE    					 
2006051800264	20060518	00264	NM  	2006	5	18	DU4R2006368      	1	20060412	G	5751		AILERON         			BOEING	727   	727223      	1384074	NM  										RT WING	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)  N/R 24581, RT WING IB AILERON NUMEROUS DENTS.   REMOVED DENTED SKIN. FABRICATED AND INSTALLED REPAIR SKIN D	OUBLER 5.5 INCH X 5.5 INCH FROM 2024-T3 .016 AND 2 EA. SKIN REPAIR DOUBLER 24 INCH X 54 INCH FROM 2024-T3 .040 IAW SRM 5	1-10-2 AND 51-30-2.				2	L	7	3 	4F				A3WE    					 
2006051800251	20060518	00251	NM  	2006	5	18	DU4R2006369      	1	20060412	G	3230	6523369	FRAME           			BOEING	727   	727223      	1384074	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				S/O 304001)  N/R 24783  CORROSION FOUND INSIDE THE HOLE OF UPLOCK HOOK INSTALL FITTING BOTH FWD AND AFT SIDE.  REMOVED 2	 EA BUSHINGS (REPAIR SLEEVES) IAW SOPM 32-32-51. REWORKED FRAME HOLE 9 IAW OHM 32-37-02 AND SRM 51-10-1. FABRICATED AND 	INSTALLED 2 EA. REPAIR SLEEVES IAW OHM 32-37-02 FIG. 404, 405 AND SOPM 20-50-3. REINSTALLED UPLOCK FRAME AND UPLOCK ASSY	 IAW MM 32-32-51.			2	L	7	3 	4F				A3WE    					 
2006051200046	20060512	00046	NM  	2006	5	12	DU4R2006370      	1	20060414	G	5753		SKIN            			BOEING	727   	727223      	1384074	NM  										RT WING,FOREFLAP	DELAMINATED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				NR 24718  DENTED AND DISBONDED RT IB FORE FLAP UPPER SKIN 19 INCHES FROM IB EDGE.  REPAIRED DENTED AND DISBONDED RT IB F	ORE FLAP UPPER SKIN 19 INCHES FROM IB EDGE BY CUTTING OUT DELAMINATED AREA, APPROX 5 INCHES IN DIAMETER. FABRICATED AND 	INSTALLED DOUBLER AND FILLER 8 INCHES DIAMETER AND 5 INCHES FROM 2024-T3 .016 IAW SRM 51-40-20 PARA. 7, 8, 10, 14, 15, 1	8, 20, 21, 22.			2	L	7	3 	4F				A3WE    					 
2006051800161	20060518	00161	NM  	2006	5	18	DU4R2006371      	1	20060414	G	5753		SKIN            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D        	 	NE  					LT FLAP	DELAMINATED     	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				N/R 24751)  FOUND SMALL AREA OF DELAMINATION OF UPPER IB SKIN LT IB FORE FLAP.  CUT OUT DELAMINATED (DISBONDED) AREA ON 	UPPER SKIN LT IB FORE FLAP. FABRICATED AND BONDED DOUBLER 6.5 X 5.6250 INCH AND FILLER 3.3750 INCH X 1.2500 INCH FROM 20	24-T3 .016 IAW SRM 57-50-2 PG. 5, 51-40-20 PG. 11-16, 42-47, 57-59, AND 62.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006051800173	20060518	00173	NM  	2006	5	18	DU4R2006372      	1	20060414	G	5512		SKIN            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D*       	 	NE  					RT STABILIZER	TORN            	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	289MT					22467				NR 24794  FOUND RT HORIZ STAB. T/E UPPER SKIN TORN BOTH IB AND OB SIDE OF NR3 BALANCE BAY STAB. STA. 157 AND 195 AFT OF 	AFT SPAR.  CUT OUT TORN SKIN OF RT HORIZ. STAB. T/E BOTH IB AND OB END OF NR3 BALANCE BAY.  FABRICATED AND INSTALLED DOU	BLERS 10.8 X 5.3 INCHES, 4.7 X 4.6 INCHES AND 3.8 X .7 INCHES FROM 2024-T3 .032 IAW SRM 51-40-20 FIG. 1.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006051000251	20060510	00251	NE  	2006	5	10	DU4R2006373      	2	20060416	G	7230		DISC            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D        	 	NE  					ENGINE	UNSERVICEABLE   	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	289MT					22467	702863			S/O 304001 NR 24710 C-1 DISK REQUIRES REPLACEMENT.  PERFORMED VIBRATION CHECK ON NR 1 ENGINE AFTER C-1 DISK REPLACEMENT 	IAW P/W MM 72-00-00, PG. 571 TEST I AND MM 71-00-00 PG. 500. FOUND ALL VALVES WITHIN LIMITS.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006092600063	20060926	00063	EA  	2006	9	26	DYCR0596101      	2	20060831	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	MISOVERHAULED   	B			DYCR	O				OTHER                   				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			GL	07	173QS	4017 	31   			17280460	L2749851A			A STUDENT PILOT WITH AN INSTRUCTOR ON BOARD WERE PRACTICING STALLS WHEN THE ENGINE CUT OFF, THEY WERE ABLE TO RESTART TH	E ENGINE WITHOUT FURTHER INCIDENT. DURING THE SAME FLIGHT, WHILE ON APPROACH FOR LANDING THE ENGINE CUT OFF AGAIN. THE S	TUDENT AND THE INSTRUCTOR WERE ABLE TO LAND THE AIRCRAFT ON THE RUNWAY WITHOUT INCIDENT. IN BOTH CASES THE PROPELLER WAS	 WINDMILLING. THE AIRCRAFT WAS TOWED TO MAINTENANCE FROM THE RUNWAY. MAINTENANCE CHECKED FUEL SYSTEM FOR FOD, LEAKS, CHE	CKED RIGGING AND COMPLIED WITH AD 2001-06-17. MAINTENANCE WAS UNABLE TO DUPLICATE PROBLEM ON THE GROUND. FUEL SERVO WAS 	STILL SUSPECT AFTER READING OTHER SDR'S ON LIKE MODEL AIRCRAFT WITH SIMILAR PROBLEMS SO SERVO WAS REMOVED AND SENT TO A 	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2006103100166	20061031	00166	SO  	2006	10	31	EDRCCUI          	2	20061021	G	8550	629448	GEAR SHAFT      	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	SHEARED         	D				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	08	9QCUI	404  				U20606373	679590			DURING PREFLIGHT, ENGINE RUNUP PILOT WAS UNABLE TO CYCLE PROP AND THEN NOTICED ZERO OIL PRESSURE ON THE OIL PRESSURE GAU	GE, ENGINE SHUTDOWN.  INSPECTION REVEALED THE GEAR SHAFT ASSY IN THE OIL PUMP HOUSING WAS SHEARD.  MFG HAS ASKED US TO S	END THE ENGINE BACK TO THE FACTORY FOR EXAMINATION.  WE HAVE PHOTOS OF THE FAILED PART IF YOU TELL US HOW TO SEND THEM T	O YOU.			1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P36EA	 
2006111500298	20061115	00298	CE  	2006	11	15	EVGR1113735      	1	20061109	G	5310		DOOR FRAME      			BEECH 	90    	65A901      	1152901	CE  	PWA   	PT6   	PT6A20      	52043	EA  					BS 255	CORRODED        	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	65JA	13353	173  			LM34				CORROSION WAS FOUND AT THE AFT DOOR FRAME AT FUSELAGE STATION 255.5 JUST BELOW AND OUT BOARD OF THE DOOR SNUBBER MOUNT. 	 DAMAGE WAS REPAIRED IAW SIRM PN 9839006C, DATED MARCH 2003, ATA 20-10-03 FIGURE 202, PAGES 204 AND 205 AND ATA 20-10-34	, FIGURE 201, PAGES 201 AND 202.				1	L	7	2 	3T	3	T		3A20    	E4EA				 
2006092200071	20060922	00071	EA  	2006	9	22	EVGR20060915     	2	20060913	G	7414	103571651	COIL            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	WORN            	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	628PM	498  			E04JA347	1493	L2642740A			DURING THE FIRST 500 HOUR MAGNETO INSPECTION, THE TAB ON THE COIL WAS MISALIGNED AND EXHIBITED EXCESSIVE WEAR.						1	G	7	1 	3O	3	O		H11NM   	E295				 
2006051200031	20060512	00031	GL  	2006	5	12	EY2R0079965      	3	20060421	G	6114	E71693	HUB             			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CORROSION ON PROPELLER HUB.						1	L	7	2 	3O				A23CE   		5	C	P36EA	 
2006071800177	20060718	00177	CE  	2006	7	18	FAA0607001       	1	20060627	G	5312	12534095	FIREWALL        			CESSNA	210   	210K        	2073446	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	D3A34	D3A34C402   	GL  	ZONE 100	CRACKED         	B				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17	8142G	6980 				21059442	289152R	931755		WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTA	CH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD.					1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P47GL	 
2006071800178	20060718	00178	CE  	2006	7	18	FAA0607002       	1	20060627	G	5312	12534095	FIREWALL        			CESSNA	210   	210K        	2073446	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	D3A34	D3A34C402   	GL  	ZONE 100	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	8142G	6980 				21059442	289152R	931755		WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTA	CH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD.					1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P47GL	 
2007010800308	20070108	00308	CE  	2007	1	8	FAA061214001     	1	20061214	G	3230	963800225	MOTOR           			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LAND GEAR	SHORTED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CE	03	8950U	4094 	164  			TD641				LANDING GEAR MOTOR CIRCUIT BREAKER BLEW WHEN GEAR WAS RETRACTED ON TAKEOFF. AT THE SAME TIME THE ALTERNATORS DROPPED OFF	LINE.  PILOT SWITCHED TO THE OTHER VOLTAGE REGULATOR AND THE ALTERNATORS CAME BACK ONLINE.  AIRCRAFT WAS FLOWN FOR AN HO	UR OR MORE TO BURN OFF FUEL. PRIOR TO LANDING.  AN EMERGENCY WAS DECLARED.  PILOT WAS ABLE TO CRANK THE GEAR DOWN AND LA	ND WITHOUT INCIDENT. DISCOVERED THAT THE FIELD IN THE EXTEND SIDE OF THE LANDING GEAR MOTOR WAS SHORTED.  REPLACED MOTOR	 WITH OVERHAULED EXCHANGE PART. FUNCTIONALLY CHECKED OK.		1	L	7	2 	3O	3	O		3A16    	1E10				 
2006101200006	20061012	00006	CE  	2006	10	12	FAA1012001       	1	20061007	G	2800		FUEL            			CESSNA	182   	T182T       	2072738	CE  										UNKNOWN	LEAKING         	P				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			SW	99	6004S					T18208508				AFTER AN APPROXIMATELY 30 MILE UNEVENTFUL FLIGHT WITH A LANDING AND TAXIBACK FOR DEPARTURE AT HVN THE AIRCRAFT WAS CLEAR	ED FOR TAKEOFF BY THE TOWER.  THERE WAS A FEW MINUTES OF HOLDING PRIOR TO BEING RELEASED.  ON TAKEOFF FROM HVN RWY 2, TH	E AIRCRAFT FUNCTIONED NORMALLY UNTIL THE FIRST POWER REDUCTION AT 700 FEET AGL.  THE THROTTLE, PROP AND MIXTURE CONTROLS	 WERE FULL FORWARD.  THE PRIVATE PILOT ON BOARD PULLED THE THROTTLE BACK TO REDUCE THE TAKEOFF MANIFOLD PRESSURE FROM 32	 TO 25 INCHES.  DURING THIS REDUCTION, THE ENGINE LOST POWER, SURGED BRIEFLY AND LOST POWER AGAIN.  THE THROTTLE APPEARE	D TO HAVE BEEN RETARDED SLOWLY AND CORRECTLY FOR THE EXPECTED POWER REDUCTION.  THE THROTTLE WAS ADVANCED AND NO POWER B	1	H	7	1 	3O			NT	3A13    					 
2006101200076	20061012	00076		2006	10	12	FAA1012002       	4	20060926	G	6113		BALANCE WEIGHT  			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MCAULY	2D34C	B2D34C208   	GL  	SPINNER	TORN            	C				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	27	177SD	10   	10   			177RG0997				PROPELLER WAS BALANCED IN PLACE.  10 FLIGHT HOURS LATER, IN CRUISE OVER WYOMING EN ROUTE TO OSHKOSH, SIGNIFICANT VIBRATI	ON OCCURRED, CAUSING DIVERSION TO THE NEAREST AIRPORT.  UPON LANDING, BYSTANDERS RAN TOWARD THE AIRPLANE TO EFFECT RESCU	E, ASSUMING THE AIRPLANE TO BE ON FIRE FROM THE LARGE CLOUDS OF SMOKE.  BALANCE WEIGHTS HAD BEEN ATTACHED BY SCREW RADIA	LLY INSIDE THE SPINNER BACKING PLATE.  THE WEIGHTS (THREE WASHERS ON ONE SCREW) HAD PULLED THROUGH THE ALUMINUM OF THE B	ACKING PLATE, AND THE RESULTANT PROJECTION DAMAGED THE COWL MOUNT SYSTEM AND COWLING, AS WELL AS THE BACKING PLATE, AND 	SEPARATION OF THE BALANCE WEIGHTS.  THE IMBALANCE CREATED BY THIS TEARING OF THE BACKING PLATE CAUSED SEVERE VIBRATION, 	1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
2006102000098	20061020	00098	SW  	2006	10	20	FAA1020001       	1	20060921	G	2823	3610021	SELECTOR VALVE  			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	COCKPIT	STUCK           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	533LJ	71   				290443	688726	FP4606B		FUEL SELECTOR VALVE STUCK IN (OFF) POSITION WHILE AIRCRAFT WAS SITTING ON THE RAMP.  ONCE STUCK IN THE OFF POSITION, IT 	BECAME IMPOSSIBLE TO TURN USING HAND FORCE.  (K)					1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P36EA	 
2006102500087	20061025	00087	EA  	2006	10	25	FAA1023001       	2	20061013	G	8520		EXHAUST VALVE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CE	07	5292S					2826923				PILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND	 ENGINE FAILURE.  PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY.  NO DAMAGE TO AIRCRAFT UPON L	ANDING. RESULTS OF ENGINE EXAMINATION AND PARTICULAR PART FAILURE INFORMATION TO FOLLOW:				1	L	7	1 	3O	3	O		2A13    	E274				 
2006103100144	20061031	00144	NM  	2006	10	31	FAA1031001       	1	20061027	G	5522		SKIN            			ISRAEL	1125  	1125        	       	NM  	ALIDSG	TFE731	TFE7313AR   	 	WP  					ELEVATOR	DELAMINATED     	B			G7QR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	71FS	4861 				071				DEBOND AREA APPROX. 7 IN X 7 IN ON THE RT OB ELEVATOR LOWER COMPOSITE SKIN. ELEVATOR WAS SENT TO MFG FOR EVALUATION AND 	WAS DEEMED (BEYOND ECONOMICAL REPAIR).  A LOANER UNIT WAS INSTALLED WHILE NEW/EXCHANGE UNIT PREPARED. REPLACEMENT ELEVAT	OR INSTALLED ON THIS DATE.				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2006082100082	20060821	00082		2006	8	21	FAA200608001     	1	20060609	G	3244	0398561	TIRE            																	MLG	SEPARATED       	B				C				ABORTED TAKEOFF         				S			AFFECT SYSTEMS            			TO	TAKEOFF        	1			SO	25	0874									LOUD BANG REPORTED BY PILOTS RESULTING IN REJECTED TAKE-OFF. MAINT FOUND  DAMAGE TO ENGINE FROM TIRE.  SHOP INVESTIGATIO	N REVEALED, TIRE TREAD SEPARATED FROM CARCASS.  NO LEAKAGE FROM WHEEL.  PASSED AIR RETENTION AFTER 167 HOURS WITH ACCEPT	ABLE AIR LOSS FROM WHEEL SERIAL NUMBER 01466.  CAUSE IS UNDETERMINED TO WHY TREAD SEPARATED, TIRE TO BE SENT TO MICHELIN	 FOR TIRE INVESTIGATION.																 
2006120700245	20061207	00245	SO  	2006	12	7	FAA200612001     	2	20061206	G	8530		CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  						SEPARATED       	B				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			WP	23	93PJ		554  			421C0824	245999R			DURING TAKEOFF ROLL PILOT REPORTED A LOUD POP FROM THE LEFT ENGINE AND THE AIRCRAFT YAWED TO THE LEFT. THE TAKEOFF WAS A	BORTED. VISUAL INSPECTION REVEALED THE NUMBER SIX CYLINDER HEAD HAD SEPARATED FROM THE BARREL. THE ENGINE HAD 554 HOURS 	SINCE OVERHAUL. THIS ENGINE WAS INSTALLED ON A CESSNA 421C.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2006101200013	20061012	00013		2006	10	12	FAA63837         	4	20061003	G	6113	D78115P	SPINNER         													HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	58HW	102  						ED4696B		RT PROPELLER SPINNER CRACKED.  CRACKS ORIGINATE FROM 1ST SCREW HOLE ADJACENT TO BLADE OPENING.  THIS IS THE 2RD OCCURANC	E OF THIS DEFECT.  PROBABLE CAUSE UNKNOWN.															5	C	P36EA	 
2006092600044	20060926	00044	GL  	2006	9	26	FASD0601         	1	20060904	G	5210		ROLLER          			BOMBDR	BD700 	BD7001A10   	1390006	GL  										PAX DOOR	OUT OF ADJUST   	B				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	15	889CP					9104				AFTER TAKE-OFF AIRCRAFT CABIN WOULD NOT PRESSURIZE. AIRCRAFT RETURNED TO  AIRPORT WITHOUT INCIDENT.  INVESTIGATION BY GR	OUND CREW FOUND REAR BAGGAGE DOOR MISALIGNED AND AFT ROLLER OUT OF GUIDE TRACK AND REAR LOCKING PIN NOT FULLY ENGAGED, A	LL INDICATIONS IN THE COCKPIT WERE NORMAL AS SENSORS ARE FITTED TO FRONT PIN AND DOOR LOCKING MECHANISM ONLY. DOOR WAS R	E-FITTED INTO THE TRACK CORRECTLY, DOOR SECURED CLOSED NORMALY, AIRCRAFT DEPARTED AND FLIGHT CONTINUED WITHOUT INCIDENT.			2	L	7	2 	4F			RT	T00003NY					 
2007010800171	20070108	00171	NE  	2007	1	8	FCPR20060026     	2	20061213	G	7200	65526022	RING            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RT ENGINE	CRACKED         	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	591DK	940  	300  			5600591				RT ENGINE INLET SUPPORT RING CRACKED.						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007010800217	20070108	00217	CE  	2007	1	8	FCPR20060027     	1	20061215	G	3830	105881	HEATER          			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ44        	66000	GL  					ZONE 100	BURNED          	B			FCPR	O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			NM	09	523BT	1247 	300  			525A0124				AFT TOILET RELIEF TUBE HEATER ELEMENT FAILED WITH EXTERNAL POWER APPLIED BURSTING INTO FLAMES.  IPC REFERENCE 38-30-00 F	IG 3 ITEM 16.					1	L	7	1 	4F	4	F	RT	A1WI    	E3GL				 
2006082900133	20060829	00133	CE  	2006	8	29	FCPR20060030     	1	20060822	G	7931	1013890237	TRANSMITTER     			BEECH 	300   	300BEECH    	1152930	CE  										LT ENGINE	FAILED          	B			FCPR	E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			NM	09	528AM	4273 				FA59				LT ENGINE OIL PRESSURE TRANSMITTER FAILED, GIVING A LOW OIL PRESSURE INDICATION.						2	L	7	2 	4T				A24CE   					 
2006051000237	20060510	00237		2006	5	10	FCPR20060050     	4	20060509	G	2211	4008519	COMPUTER        			CESSNA	500   	S550        	2076607	CE  										COCKPIT	FAILED          	B			FCPR	O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			NM	09	543SC	6347 				S5500144				AUTOPILOT COMPUTER FAILED CAUSING PILOTS ALTIMETER/AIRDATA COMPUTER TO FAIL.						1	L	7	2 	4F			RT	A22CE   					 
2006051100290	20060511	00290	CE  	2006	5	11	HAG06002         	1	20060406	G	5313	25FN86	LONGERON        			RAYTHN	DH125 	DH125       	4230106	CE  										FUSELAGE	CRACKED         	B			J7EA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	125CK	10555				25266				CRACK IN KEEL LONGERON BETWEEN FRAMES 4 AND 5, APROXIMATE STATION 175.00.CRACK IS ONLY IN LONGERON, NOT IN MAIN BEAM.  C	RACK LOCATED IN LOWER AFT HOLE FOR NOSE GEAR ATTACH BRACKET.  DISCOVERED DURING REQUIRED CHECK OF ATTACH BOLT TORQUE, AL	L BOLTS FOUND LOOSE.  BRACKET REMOVED FOR HIDDEN DAMAGE INSPECTION.				2	L	7	2 	4J			RT	A3EU    					 
2006111700139	20061117	00139	NE  	2006	11	17	HL01102006001    	1	20061031	G	6320	SB24102	BEARING         	SKRSKY      		SKRSKY	S64   	CH54A       	8142501	NE  										M/R GEARBOX	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23			357  		77	6818447				MAIN GEAR BOX BEGAN MAKING METAL, THIS WAS NONFERROUS METAL, UPON REMOVAL AND DISASSEMBLY IT WAS DISCOVERED THAT THE 1ST	 STAGE PLANETARY BEARING, P/NSB2410-2 HAD FAILED, BEARING WAS REPLACED AND RETURNED TO SERVICE.  FOR FURTHER INFO SEE HE	AVY LIFT WORK ORDER NR.				2	G	7	2 	4U				H16NM   					 
2007010800146	20070108	00146		2007	1	8	HN8R200600001    	4	20061207	G	2200	065001782400	SERVO           			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  					AUTOPILOT	DEFECTIVE       	B			HN8R	C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CE	05	576GA	1    	1    			05076				NOSE DOWN AUTO TRIM INOP WAS REPORTED BY PILOT.  TROUBLESHOOTING REVEALED THE AUTOPILOT COMPUTER WAS NOT RECEIVING INPUT	 CALLING FOR NOSE DOWN TRIM FROM THIS PITCH SERVO.					1	H	7	1 	3O	3	O	NT	        	1E4				 
2007010800221	20070108	00221	EA  	2007	1	8	HN8R200700001    	2	20061223	G	8550		SCREEN          			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE OIL SUMP	CONTAMINATED    	B			HN8R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CE	05	576GA	219  				GA805076	L3033548A			FOUND 2 PIECES OF METAL IN THE OIL SUMP SUCTION SCREEN DURING ANNUAL INSPECTION.  ONE PIECE LOOKS LIKE A DRILLED OUT HEL	I COIL .5 INCH LONG X .25 WIDE AND THE OTHER LOOKS LIKE A PIECE OF CASTING .2 LONG X .125 WIDE.  THE ENGINE WILL BE REMO	VED AND SENT OUT FOR TEARDOWN AND INSPECTION.				1	H	7	1 	3O	3	O	NT	        	1E4				 
2006111500212	20061115	00212	CE  	2006	11	15	IALFAASDR1       	1	20061103	G	2430		WIRE HARNESS    			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					AIR DRIVEN GEN	BROKEN          	H				K				NONE                    				G			MULTIPLE FAILURE          			IN	INSP/MAINT     	1			SO	05	302P					TH952				AIR DRIVEN GENERATOR TEST IN FLIGHT, FOUND NO OUTPUT.  FOUND WIRING HARNESS FROM ADG TO ADG BUSS BURNED-BROKEN AT CONNEC	TOR BACKSHELL.  CONNECTOR AND WIRING REPLACED ADG INSPECTED AND TESTED SERVICEABLE.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
2006051200079	20060512	00079	CE  	2006	5	12	IGL032006007     	1	20060329	G	3222	084200077	STRUT           	CESSNA      		CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG	FAILED          	G				A				UNSCHED LANDING         				K			FLUID LOSS                			LD	LANDING        	1			GL	03	7035L					310K0135				NOSE GEAR STRUT ASSEMBLY COLLAPSED DURING EITHER TAXI OR TAKEOFF.  WHEN GEAR WAS RETRACTED THE NOSE FENDER CAUGHT ON THE	 GEAR DOOR BRACKETS.  MOTOR CONTINUED UNTIL IDLER BELLCRANK BROKE.  AIRCRAFT MADE AN EMERGENCY LANDING WITH THE NOSE GEA	R COLLAPSED.  PILOT REPORTED NO ABNORMAL OBSERVATIONS OF THE NOSE GEAR DURING PREFLIGHT INSPECTION.  IT IS NOT UNCOMMON 	FOR THE STRUT TO BLOW THE SEALS AND LOOSE ALL OF ITS FLUID AND NITROGEN DURING COLD WEATHER.  LOW UTILIZATION MIGHT HAVE	 BEEN A CONTRIBUTING FACTOR AS WELL.		1	L	7	2 	3O	3	O		3A10    	E1CE				 
2006041100031	20060411	00031	CE  	2006	4	11	ISW1520050019    	1	20060223	G	8000	643359K46	ADAPTER         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					STARTER	FAILED          	G				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	15	421LH	714  				421C1207	808393			THE ENGINE QUIT RUNNING AND SEIZED DURING FLIGHT. THE STARTER ADAPTER FAILED AND CAUSED THE ENGINE TO SEIZE.  MAINTENANC	E RECORDS SHOW THAT THE STARTER WAS REPLACED TWO TIMES BECAUSE OF HARD STARTING.  ONCE AT 99 HOURS AND AGAIN AT 90 HOURS	 PRIOR TO ENGINE FAILURE				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007010900001	20070109	00001	CE  	2007	1	9	JEMA11302006A    	1	20061130	G	5610	991438010	WINDSHIELD      			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	545   	PW545A      	 	NE  					COCKPIT	CRACKED         	G			JEMA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CE	01	108EK	2662 				5605032				AIRCRAFT HAD DEPARTED, HAD LEVELED OFF AT 37,000 FEET, ENROUTE. CREW NOTICED A RT WINDSHIELD FAULT WARNING LIGHT. IAW AF	M PROCEDURES RT WINDSHIELD HEAT WAS TURNED OFF. APPROX 3-4 MINUTES LATER CO-PILOT SAW FLASH AND RT WINDSHIELD SPIDER WED	 CRACKED.  FLIGHT CREW MADE A PRECAUTIONARY LANDING AT AIRPORT, WITH NO FURTHER INCIDENTS.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2006071800164	20060718	00164	CE  	2006	7	18	LJCR2453796      	1	20060301	G	3020	45A403041	DUCT            			BEECH 	MU300 	400A        	1155402	CE  											OUT OF LIMITS   	B			LJCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	999JF					RK98				DURING SCHEDULED MAINTENANCE, FOUND BRAIDING AROUND FLEXIBLE BELLOWS DISBONDED FROM ENTIRE CIRCUMFERENCE.  NEW REPLACEME	NT DUCT ASSEMBLIES NOT AVAILABLE FROM MANUFACTURER.  REPLACED WITH SERVICEABLE UNIT.  INSPECTED REPLACEMENT UNIT PER AD 	2001-03-06 EFF. 3-21-2001				2	H	7	2 	4F			RT	A16SW   					 
2006111700159	20061117	00159	GL  	2006	11	17	LX5R200600002    	3	20061115	G	6197	K31C22	WIRE HARNESS    	BEECH       		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	AUTOFEATHER SYS	SHORTED         	C			LX5R	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	19	961LL	3310 				FL264				UPON TAKEOFF ROLL THE CREW GOT THE AUTOFEATHER OFF LIGHT AND THE MASTER CAUTION LIGHT. THE CREW THEN OPTED TO ABORT TAKE	OFF ROLL AND RETURN TO RAMP WITHOUT INCIDENT. UPON RETURNING TO RAMP THE CREW NOTICED THAT THE AUTOFEATHER CIRCUIT BREAK	ER HAD POPPED, IT WAS RESET BUT WOULD POP AGAIN UPON PUSHING THE LT POWER LEVER FORWARD. THE PLANE WAS BROUGHT INTO MAIN	TENANCE AND THE MECHANIC FOUND THAT THERE WAS A CHAFED WIRE BEHIND THE INSTRUMENT PANEL FOR THE AUTOFEATHER SWITCH. THIS	 WIRE WAS REPAIRED AND THE AIRCRAFT WAS OPS CHECKED AND RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2006121200398	20061212	00398		2006	12	12	LX5R200600003    	3	20061115	G	6197	K31C22	WIRE HARNESS    			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	SHORTED         	B			LX5R	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	19	961LL	3310 				FL264				UPON TAKEOFF ROLL, THE CREW GOT THE AUTO FEATHER OFF LIGHT AND THE MASTER CAUTION LIGHT.  THE CREW THEN OPTED TO ABORT T	AKEOFF ROLL AND RETURN TO RAMP WITHOUT INCIDENT.  UPON RETURNING TO RAMP, THE CREW NOTICED THAT THE AUTO FEATHER CRICUIT	 BREAKER HAD POPPED, IT WAS RESET BUT WOULD POP AGAIN UPON PUSHING THE LT POWER LEVER FWD.  THE PLANE WAS BROUGHT INTO M	AINTENANCE AND THE MECHANIC FOUND THAT THERE WAS A CHAFED WIRE BEHIND THE INSTRUMENT PANEL FOR THE AUTOFEATHER SWITCH.  	THIS WIRE WAS REPAIRED AND THE AIRCRAFT WAS OPS CHECKED AND RETURNED TO SERVICE.  (K)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2006051800172	20060518	00172	SO  	2006	5	18	MPVMANIFOLD      	2	20060328	G	7324	63432612A2	FUEL DIVIDER    			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	21	PKMPV	98   				U20605864	532289			FUEL MANIFOLD VALVE IS LEAKING FROM THE VENT PORT.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2006053000156	20060530	00156	CE  	2006	5	30	N6265B           	1	20060524	G	5312	125340956	BULKHEAD        	CESSNA      		CESSNA	210   	210M        	2073450	CE  										FIREWALL	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6265B	4908 				21062727				WHILE UNDERGOING AN ANNUAL INSPECTION, FOUND THE FIREWALL TO BE CRACKED ON THE LT & RT SIDE WHERE THE P/N 1250255-7 EXHA	UST HANGAR BRACKETS ATTACH. THE CRACKS WERE EXTENDING OUT FROM UNDER THE HANGAR BRACKETS AND EXTENDED IN MULTIPLE DIRECT	IONS. ADDITIONAL INSPECTION REVEALED THE LT BULKHEAD P/N 1253409-5 AND RT BULKHEAD P/N 1253409-6 BEHIND THE FIREWALL TO 	BE CRACKED IN MULTIPLE DIRECTIONS ALSO. THE BULKHEAD SECTIONS WERE REPLACED AND THE FIREWALL CRACKS WERE REPAIRED.			1	H	7	1 	3O				3A21    					 
2006071800176	20060718	00176	CE  	2006	7	18	N8142G           	1	20060627	G	5312	12534095	FIREWALL        			CESSNA	210   	210K        	2073446	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	D3A34	D3A34C402   	GL  	FUSLEAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	8142G	6980 				21059442	289152R	931755		WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTA	CH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD.					1	H	7	1 	3O	3	O		3A21    	E3SO	5	C	P47GL	 
2006091400162	20060914	00162	CE  	2006	9	14	NA               	1	20060822	G	5280	3511513022	ANGLE           			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		360  				E3384				DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-2	2, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIG	N OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AN	D MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN 	PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASI	LY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.	1	L	7	1 	3O				3A15    					 
2006051800135	20060518	00135	CE  	2006	5	18	OMKR200600002    	1	20060509	G	5511	45A21104642	RIB             			BEECH 	MU300 	400A        	1155402	CE  										ZONE 300	CRACKED         	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	899TA	4933 				RK292				CRACKED ROLLER RIB ASSEMBLY.						2	H	7	2 	4F			RT	A16SW   					 
2006051600090	20060516	00090	CE  	2006	5	16	OMKR200600003    	1	20060510	G	5514	45A21104641	RIB             			BEECH 	MU300 	400A        	1155402	CE  										HORIZ STAB	CRACKED         	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	686TA					686TA				CRACKED ROLLER RIB SUPPORT.						2	H	7	2 	4F			RT	A16SW   					 
2006071800097	20060718	00097	CE  	2006	7	18	OMKR20064        	1	20060712	G	5740	5012007378	FITTING         			BEECH 	90    	65A90       	1152908	CE  										WING SPAR	CRACKED         	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	66GS	11099				LJ237				DURING ACCOMPLISHMENT OF AD 89-25-10, BOTH THE FOREWARD, LOWER, INBOARD, BATHTUB FITTINGS WERE FOUND WITH TWO EACH 1/4" 	CRACKS.  THE FEATHERED EDGE CRACKS EXTENDED INTO THE BOLT HOLE RADIUS, AND THE SLOT CRACKS EXTENDED UPWARD. BOTH FITTING	S WERE CRACKED VIRTUALLY THE SAME.  PARTS WERE REPLACED WITH NEW.				1	L	7	2 	3T				3A20    					 
2006051000242	20060510	00242	CE  	2006	5	10	PAI5200604049    	1	20060417	G	3242	7540	PLATE           	CLEVELAND   		BEECH 	95    	95B55       	1152729	CE  										RT BRAKE	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	6747V	3103 				TC2316				DURING ANNUAL INSPECTION FOUND RT BRAKE TORQUE PLATE CRACKED .7500 OF THE LENGTH OF THE CALIPER PIN BORE.						1	L	7	2 	3O			RT	3A16    					 
2006072100140	20060721	00140	EU  	2006	7	21	PAI5200641881    	1	20060628	G	5540	80363216801	STOP            			PIAGIO	P180  	P180        	6960204	EU  										RUDDER	BROKEN          	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	153SL	2966 				1054				DURING D CHECK (3000 HOUR INSPECTION) FOUND RUDDER STOP LOCATED AT BOTTOM OF RUDDER BROKEN IN TWO.  BREAK OCCURRED AT SC	REW HOLES USED TO ATTACH WEAR STRIP TO RUDDER STOP.  SMALL AREA OF METAL EXISTS AROUND THE SCREW HOLES, SUGGEST REDESIGN	 OF THIS PART.				1	H	7	2 	3O			RT	A59EU   					 
2006092600027	20060926	00027	NE  	2006	9	26	PAI5200642401    	2	20060825	G	7261	3040124	LINE            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					OIL COOLER	CHAFED          	B			PAI5	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	153SL	2989 				1054	PCERK0064			DURING 3000 HOUR D-CHECK FOUND OIL SCAVENGE LINE PN 3040124 AT SCAVENGE PUMP CHAFED APPROX 50 PERCENT THROUGH BY CONTACT	 WITH CRIMP TYPE CLAMP THAT SECURES HEAT SLEEVE ON OIL COOLER FLEX LINE.  SAME CONDITION FOUND ON BOTH LT AND RT ENGINES	.  INSTALLED NEW SCAVENGE LINE BOTH ENGINES.				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2006091300103	20060913	00103	EU  	2006	9	13	PAI5200642731    	1	20060901	G	3010	80232118401	DUCT            	PIAGIO      		PIAGIO	P180  	P180        	6960204	EU  										WING	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	107SL	2993 				1073				DURING 3000 HOUR D-CHECK FOUND ALL 4 WING LEADING EDGE PANELS WITH CRACKED HEATING DUCTS.  WING LEADING EDGE ASSY P/N'S 	80-232116-401, 80-232116-402, 232117-401, 232117-402.					1	H	7	2 	3O			RT	A59EU   					 
2006062700331	20060627	00331	EU  	2006	6	27	PAI52006S4188    	1	20060622	G	3010	80237666403A	TUBE            			PIAGIO	P180  	P180        	6960204	EU  										ANTI ICE SYS	CHAFED          	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	153SL	2966 	2966 			1054				DURING D-CHECK (3000 HOUR INSPECTION) FOUND WING LEADING EDGE ANTI-ICE PLUMBING CHAFFED 50 PERCENT OF WALL THICKNESS BY 	LEADING EDGE TEMP SENSOR BRACKET.					1	H	7	2 	3O			RT	A59EU   					 
2006080200306	20060802	00306	SO  	2006	8	2	PAI52006S4248    	1	20060726	G	2823		CONTROL CABLE   			PIPER 	PA23  	PA23250     	7102308	SO  										FUEL SELECTOR	BROKEN          	B			PAI5	A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SO	05	18MW					27369				PILOT REPORTED LT ENGINE QUIT IN FLIGHT.  FOUND LT OB FUEL TANK EMPTY, LT IB FUEL TANK HAD FUEL.  FOUND FUEL SELECTOR CO	NTROL CABLE BROKEN AT SELECTOR VALVE IN LT NACELLE.  WHEN SELECTED TO LT IB TANK THE ENGINE RAN NORMALLY.					1	L	7	2 	3O				1A10    					 
2006103100163	20061031	00163	CE  	2006	10	31	PAI52006S4330    	1	20061025	G	3246	300257	WHEEL           			BEECH 	90    	C90A        	1152911	CE  										MLG	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	511KV	3500 				LJ1422				PILOT NOTED RT MAIN TIRE LOW PRESSURE ON PREFLIGHT.  MAINTENANCE FOUND, UPON DISASSEMBLY OF WHEEL, THAT THE INNER WHEEL 	HALF WAS CRACKED IN THE O-RING GROOVE ADJACENT TO THE WHEEL TIE BOLT HOLES.					1	L	7	2 	3T			RT	3A20    					 
2006051800186	20060518	00186	EU  	2006	5	18	PAZR200620412    	1	20060428	G	3211	MY201121605	PLUG            	AMD         		AMD   	FALC20	FALCON20F5  	2730105	EU  										ZONE 700	CORRODED        	B			PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	620A					412				DURING THE COURSE OF REPLACING THE LT MLG ASSEMBLY, THE TECHNICIAN, UPON VISUAL INSPECTION AFTER REMOVAL OF MLG ASSY, FO	UND SIGNS OF CORROSION ON THE PLUG, P/N MY20112-1605.  UPON FURTHER DISASSEMBLY, IT WAS NOTED THAT THE CORROSION HAD GON	E THROUGH THE PLUG. THE SEALANT ON ONE SIDE OF THE PLUG WAS PREVENTING FUEL LEAKAGE.  PART WAS ORDERED FROM MFG AND REPL	ACED WITH A NEW PLUG, P/N MY20112-1605-1. IT APPEARS THAT THE NEW PLUG HAS A DIFFERENT DESIGN AND PAINT PROTECTION SYSTE	M; THUS AIDING IN THE PREVENTION OF FUTURE CORROSION. THE AIRCRAFT WAS MFG. IN 1979.		2	L	7	2 	4F			RT	A7EU    					 
2006063000021	20060630	00021	NM  	2006	6	30	PIDR2006001      	1	20060608	G	5551		ATTACH FITTING  			BOEING	737   	73735B      	13844BM	NM  										HORIZ STAB	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	223DZ					23972				DURING AN A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, MAINTENANCE DISCOVERED A TIME LIMITED BLENDOUT REPA	IR TO THE AFT FACE OF THE LEFT HORIZONTAL STABILIZER LOWER FORWARD ATTACH LUG.  REWORKED AFT FACE OF LOWER FORWARD ATTAC	H LUG PER DELTA ENGINEERING REPAIR/AUTHORIZATION 089066-14 REVISION D DATED 5/10/06 WITH FAA 8100-9 APPROVAL DATED 5/30/	2006.			2	L	7	2 	4F			RT	A16WE   					 
2006071100065	20060711	00065	NM  	2006	7	11	PIDR2006002      	1	20060608	G	5753		SKIN            			BOEING	737   	73735B      	13844BM	NM  										TR FLAPS	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	223DZ					23972				INSPECTION NOTED A CHAFED AREA ON AN EXISTING SRM ALUMINUM REPAIR DOUBLER ON THE RIGHT WING OUTBOARD FLAP MID-FLAP LEADI	NG EDGE 20 INCHES FROM THE INBOARD END.  REPAIRED DAMAGED AREA IN ACCORDANCE WITH PACE AIRLINES REPAIR PROCEDURE REPORT 	EA 57-145 DATED 05/25/06 WITH FAA DER APPROVAL FORM 8110-3 DATED MAY 30, 2006. 				2	L	7	2 	4F			RT	A16WE   					 
2006070500024	20060705	00024	NM  	2006	7	5	PIDR2006003      	1	20060608	G	5330		SKIN            			BOEING	737   	73735B      	13844BM	NM  										FUSELAGE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	223DZ					23972				AN EXISTING REPAIR TO THE FUSELAGE SKIN BETWEEN THE L1 DOOR HINGES JUST FORWARD OF THE DOOR REQUIRES REWORK TO REMOVE TH	E DAMAGE.  REWORKED DAMAGED AREA IAW EA NR 53-146 DATED 05/26/06 WITH FAA DER APPROVED 8110-3 DATED MAY 27, 2006..					2	L	7	2 	4F			RT	A16WE   					 
2006071100064	20060711	00064	NM  	2006	7	11	PIDR2006004      	1	20060608	G	5754		SKIN            			BOEING	737   	73735B      	13844BM	NM  										NR 5 SLAT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	223DZ					23972				INSPECTION NOTED A GOUGE ON THE NR 5 SLAT UPPER LEADING EDGE SURFACE 28 INCHES FROM THE INBOARD END (SS169.0).  REPAIRED	 DAMAGED AREA IN ACCORDANCE WITH PACE AIRLINES REPAIR PROCEDURE REPORT EA 57-140 DATED 05/20/06 WITH FAA DER APPROVED 81	10-3 DATED MAY 20, 2006.				2	L	7	2 	4F			RT	A16WE   					 
2006071100063	20060711	00063	NM  	2006	7	11	PIDR2006005      	1	20060608	G	5754		SKIN            			BOEING	737   	73735B      	13844BM	NM  										NR 5 SLAT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	223DZ					23972				INSPECTION NOTED CRACKS AT SEVERAL FASTENER LOCATIONS IN THE NR 5 SLAT LOWER TRAILING EDGE SKIN PANEL UNDER THE SLAT ACT	UATOR.  REPAIRED DAMAGED AREA IN ACCORDANCE WITH SRM 57-43-01.					2	L	7	2 	4F			RT	A16WE   					 
2006071100062	20060711	00062	NM  	2006	7	11	PIDR2006006      	1	20060608	G	5754		SKIN            			BOEING	737   	73735B      	13844BM	NM  										NR 3 SLAT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	223DZ					23972				INSPECTION NOTED SEVERAL CRACKS IN THE NR 3 SLAT LOWER TRAILING EDGE SKIN BELOW THE SLAT ACTUATOR.  REPAIRED DAMAGED ARE	A PER SRM 57-43-01.					2	L	7	2 	4F			RT	A16WE   					 
2006062700333	20060627	00333	NM  	2006	6	27	PIDR2006007      	1	20060619	G	5330		SKIN            			BOEING	737   	7373L9      	1384470	NM  										BS 887-907	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	231DN					23717				DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, INSPECTION NOTED DENTS BEYOND ALLOWABLE LIMITS IN FUSE	LAGE SKIN FROM BS887 TO BS907 BETWEEN STR20RT AND STR22RT.  REPAIRED IAW SRM 53-00-01.					2	L	7	2 	4F			RT	A16WE   					 
2006063000019	20060630	00019	NM  	2006	6	30	PIDR2006008      	1	20060613	G	5330		SKIN            			BOEING	737   	7373L9      	1384470	NM  										FUSELAGE	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	231DN					23717				DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, INSPECTION NOTED A DENT IN THE FUSELAGE SKIN BEYOND AL	LOWABLE LIMITS AT BS 887 STR 22 LT.  REPAIRED PER SRM 53-00-01.					2	L	7	2 	4F			RT	A16WE   					 
2006063000020	20060630	00020	NM  	2006	6	30	PIDR2006009      	1	20060606	G	5512		SKIN            			BOEING	737   	7373L9      	1384470	NM  										HORIZ STAB	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	231DN					23717				DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, DAMAGE NOTED ON THE RIGHT HORIZONTAL STABILIZER APPROX	IMATELY 8 FEET FROM THE INBOARD END.  REPAIRED PER SRM 55-10-01.					2	L	7	2 	4F			RT	A16WE   					 
2006072400018	20060724	00018	NM  	2006	7	24	PIDR2006010      	1	20060717	G	5300		REPAIR          			BOEING	737   	737330      	13844BJ	NM  										FUSELAGE	IMPROPER        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	241DL					23833				EXISTING REPAIR AT BS887 AND STR25RT NOT IN COMPLIANCE WITH THE SRM.  REPLACED EXISTING REPAIR IAW SRM 53-00-01 REPAIR 3	1.					2	L	7	2 	4F			RT	A16WE   					 
2006083100092	20060831	00092	NM  	2006	8	31	PIDR2006011      	1	20060824	G	5754		SKIN            			BOEING	737   	737330      	13844BJ	NM  										L/E SLAT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	242DL					23834				NUMBER THREE SLAT LOWER SKIN IS CRACKED AT THE ACTUATOR.  REPAIRED PER SRM 57-43-01.						2	L	7	2 	4F			RT	A16WE   					 
2006083100090	20060831	00090	NM  	2006	8	31	PIDR2006012      	1	20060826	G	5330		SKIN            			BOEING	737   	737330      	13844BJ	NM  										FUSELAGE	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	242DL					23834				FUSELAGE SKIN DENTED FROM BS 867 TO BS 947 BETWEEN STR 21 RT AND 22 RT.  REPAIRED PER EA 53-220.						2	L	7	2 	4F			RT	A16WE   					 
2006083100089	20060831	00089	NM  	2006	8	31	PIDR2006013      	1	20060826	G	5313		STRINGER        			BOEING	737   	737330      	13844BJ	NM  										FUSELAGE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	242DL					23834				STRINGER 19 LT AT BS 967 HAS TWO REPAIRS NOT PER THE SRM.  REPLACED SECTION OF STRINGER PER SRM 53-00-03 FIG 201, REPAIR	 1 AND 51-40-2.					2	L	7	2 	4F			RT	A16WE   					 
2006083100091	20060831	00091	NM  	2006	8	31	PIDR2006014      	1	20060824	G	5320		STRUCTURE       			BOEING	737   	737330      	13844BJ	NM  										FUSELAGE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	242DL					23834				DOUBLER UNDER THE L-2 DOOR AT BS 975 HAS NO DOCUMENTATION.  REPLACED EXISTING DOUBLER PER EA 53-221.						2	L	7	2 	4F			RT	A16WE   					 
2006091300239	20060913	00239	NM  	2006	9	13	PIDR2006015      	1	20060823	G	5711		SPAR            			BOEING	737   	737330      	13844BJ	NM  										WING	DAMAGED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	242DL					23834				DURING REPLACEMENT OF THE AFT OB SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM IAW SB 737-1216R2 PART III, NOTED SEVERA	L ATTACHMENT HOLES IN SPAR CHORD AND WEB TO BE OUT OF ROUND.  REPAIRED DAMAGE IAW MFG MESSAGE NR 1-21375291-12 DATED 26 	JULY 2006 AND FAA FORM 8100-9 DATED 7 AUG 2006 AS AN AMOC TO AD 2005-18-08.				2	L	7	2 	4F			RT	A16WE   					 
2006091300238	20060913	00238	NM  	2006	9	13	PIDR2006016      	1	20060823	G	5743	65C365451	FITTING         			BOEING	737   	737330      	13844BJ	NM  										MLG	ELONGATED       	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	242DL					23834				DURING REPLACEMENT OF THE AFT OB SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM IAW SB 737-1216R2, PART III, NOTED SEVER	AL ATTACHMENT HOLES IN THE REPLACEMENT FITTING OUT OF ROUND.  REPAIRED DAMAGE AREA IN FITTING IAW MESSAGE NUMBER 1-21375	2921-12 DATED 26 JUL 2006 AND FAA FORM 8100-9 DATED 7 AUG 2006 WHICH IS AN AMOC TO AD 2005-18-08.				2	L	7	2 	4F			RT	A16WE   					 
2006091300266	20060913	00266	NM  	2006	9	13	PIDR2006017      	1	20060801	G	5711	654532421	SPAR            			BOEING	737   	737330      	13844BJ	NM  										BS 224	DAMAGED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	241DL					23833				FASTENER HOLE IN THE LT UPPER REAR SPAR CHORD AT STA 224.14 (AT THE LANDING GEAR BEAM OB ATTACH FITTING) CRACKED .024 IN	CHES BEYOND ALLOWABLE LIMITS.  REPLACED THE REAR SPAR CHORD SEGMENT FROM THE SIDE OF THE FUSELAGE BODY TO REAR SPAR STA 	285.  NOTE:  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERA	TOR.			2	L	7	2 	4F			RT	A16WE   					 
2006091800009	20060918	00009	NM  	2006	9	18	PIDR2006018      	1	20060814	G	5711		SPAR            			BOEING	737   	737330      	13844BJ	NM  										BS 224	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	241DL					23833				TWO FASTENER HOLES IN THE RIGHT REAR SPAR AT STA 224.14 (AT THE LANDING GEAR BEAM O/B ATTACH FITTING) CRACKED.  REAMED O	NE HOLE PER BOEING SB 737-1216R2 AND REAMED SECOND HOLE AND INSTALLED A FREEZE PLUG PER BOEING MESSAGE 1-210954789-9 WIT	H FAA APPROVED 8100-9 DATED 24 AUG 2006.				2	L	7	2 	4F			RT	A16WE   					 
2006101800029	20061018	00029	NM  	2006	10	18	PIDR2006019      	1	20060928	G	5315		FLOORBEAM       			BOEING	737   	7373B7      	1384580	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 727D	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				UNDERSIDE OF BS 727D+5 FLOORBEAM IN AFT CARGO BIN IS CORRODED FROM LBL17 TO RBL8.  REPAIRED AREA IAW SRM 53-00-53 FIG. 2	01.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006101800028	20061018	00028	NM  	2006	10	18	PIDR2006020      	1	20060928	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 400 S23R	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				EXISTING DOUBLER ON FUSELAGE AT BS 400 AND S23RT HAS A DENT.  REMOVED EXISTING DOUBLER AND INSTALLED NEW IAW SRM 53-00-0	1 FIG. 201.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006101800027	20061018	00027	NM  	2006	10	18	PIDR2006021      	1	20060928	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				FUSELAGE SKIN WORN UNDER DORSAL FIN.  REPAIRED AREA IAW SB 737-55-1057.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006101800026	20061018	00026	NM  	2006	10	18	PIDR2006022      	1	20060928	G	5315		FLOORBEAM       			BOEING	737   	7373B7      	1384580	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 312	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				FLOORBEAM AT BS 312 CORRODED AT NUTPLATE HOLES FROM RBL8 TO RBL32.  REPLACED FLOORBEAM T-CAP IAW SRM 53-10-51.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006101900231	20061019	00231	NM  	2006	10	19	PIDR2006023      	1	20060105	G	5315		FLOORBEAM       			BOEING	737   	7373B7      	1384580	NM  										BS 986	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				BS 986.5 FLOORBEAM CORRODED AT A PREVIOUS REPAIR FROM RBL14 TO RBL18.  REPLACED UPPER T CAP OF FLOORBEAM IAW EA NR 53-26	4.					2	L	7	2 	4F			RT	A16WE   					 
2006101300002	20061013	00002	NM  	2006	10	13	PIDR2006024      	1	20061010	G	5315		FLOORBEAM       			BOEING	737   	7373B7      	1384580	NM  										BS 520	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				VERTICAL WEB OF BS 520 FLOORBEAM DAMAGED AT RBL 36.  REPAIRED DAMAGED AREA IAW EA 53-273.						2	L	7	2 	4F			RT	A16WE   					 
2006101300003	20061013	00003	NM  	2006	10	13	PIDR2006025      	1	20061011	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  										BS 360-540	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				STR 14 LT SKIN LAP HAS SCRIBE LINE DAMAGE IN SEVERAL PLACES FROM BS 360 TO BS 540.  REPAIRED DAMAGED AREA IAW SB 737-53A	1177.					2	L	7	2 	4F			RT	A16WE   					 
2006102000050	20061020	00050	NM  	2006	10	20	PIDR2006026      	1	20061014	G	5311		FRAME           			BOEING	737   	7373B7      	1384580	NM  										BS 767 S13L	CRACKED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CRACK IN BS 767 FRAME AT STR 13 RT.  REPAIRED PER SRM 53-00-07 FIG 201.  NOTE:  PLEASE REMOVE PIDR AS THE OPERATOR DESIG	NATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.					2	L	7	2 	4F			RT	A16WE   					 
2006102000126	20061020	00126	NM  	2006	10	20	PIDR2006027      	1	20061016	G	5311		FRAME           			BOEING	737   	7373B7      	1384580	NM  										BS 867 S13R	CRACKED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				FOUND CRACK IN BS 867 FRAME AT STR 13RT.  REPAIRED FRAME PER SRM 53-00-07 FIG 201.  PLEASE REMOVE PIDR AS THE OPERATOR D	ESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.					2	L	7	2 	4F			RT	A16WE   					 
2006102000127	20061020	00127	NM  	2006	10	20	PIDR2006028      	1	20061016	G	5314		KEELBEAM        			BOEING	737   	7373B7      	1384580	NM  										BS 500D-540	CORRODED        	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CORROSION ON RIGHT KEEL BEAM (STR28RT) FROM BS 500D TO BS 540.  REPAIRED AREA BY SPLICING IN A REPLACEMENT SECTION OF KE	EL BEAM PER EA 53-268.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVI	ATION OPERATOR.				2	L	7	2 	4F			RT	A16WE   					 
2006102000125	20061020	00125	NM  	2006	10	20	PIDR2006029      	1	20061016	G	5330		LAP JOINT       			BOEING	737   	7373B7      	1384580	NM  										BS 360-540	CRACKED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CRACK IN LOWER FASTENER ROW OF STR 10LT SKIN LAP AT BS 500D+10 AND VARIOUS LOCATIONS OF SCRIBE LINES AT STR 10LT LAP ARE	A WERE REPAIRED BY REPLACING THE SKIN LAP PER SB 737-53A1177.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO	 IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.				2	L	7	2 	4F			RT	A16WE   					 
2006102000151	20061020	00151	NM  	2006	10	20	PIDR2006030      	1	20061011	G	5330		LAP JOINT       			BOEING	737   	7373B7      	1384580	NM  										BS 360-540	DAMAGED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				SEVERAL AREAS OF SCRIBE LINE DAMAGE AT STR 14LT FROM BS 360 TO BS 540.  REPAIRED AREA BY REPLACING THE SKIN LAP PER SB 7	37-53A1177.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERA	TOR.				2	L	7	2 	4F			RT	A16WE   					 
2006102600112	20061026	00112	NM  	2006	10	26	PIDR2006031      	1	20061016	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  										BS 350-360 S25L	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CORROSION IN FUSELAGE SKIN AT BS 360 AND STR 25 LT.  CORROSION ON STR 25 LT BEYOND ALLOWABLE LIMITS.  SPLICED A NEW PIEC	E OF STRINGER SECTION AND REMOVED LIGHT SURFACE CORROSION ON FUSELAGE SKIN PER EA 53-270.					2	L	7	2 	4F			RT	A16WE   					 
2006103100152	20061031	00152	NM  	2006	10	31	PIDR2006032      	1	20061022	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  										BS 727A	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CORROSION IN FUSELAGE SKIN IN AREA OF LT KEELBEAM (STR 28LT) AND RT KEELBEAM (STR 28RT)AT BS727A-4.  CUT OUT FUSELAGE SK	IN FOR ACCESS TO LT AND RT KEELBEAMS.  REMOVED CORROSION FROM LT AND RT KEELBEAM AREAS WITHIN LIMITS OF SRM 53-60-12 FIG	. 101.  REPLACED CORRODED SECTION OF FUSELAGE SKIN IAW EA NR 53-275.				2	L	7	2 	4F			RT	A16WE   					 
2006103100154	20061031	00154	NM  	2006	10	31	PIDR2006033      	1	20061016	G	5311		FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 616	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				CRACK IN BS 616 FRAME RT SIDE BELOW FLOOR.  REPAIRED DAMAGED AREA IAW SB 737-53-1182.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006103100153	20061031	00153	NM  	2006	10	31	PIDR2006034      	1	20061013	G	5313		STRINGER        			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 312-328	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				STRINGER 28RT CORRODED BETWEEN BS 312 AND BS 328.  REPLACED STRINGER SECTION IAW SRM 51-40-02.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006103100155	20061031	00155	NM  	2006	10	31	PIDR2006035      	1	20061019	G	5230		BEAM            			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					CARGO DOOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				LOWER LT AND RT INTERNAL BEAMS CRACKED.  REPAIRED BEAMS SB 737-52A1079.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006103100171	20061031	00171	NM  	2006	10	31	PIDR2006036      	1	20061026	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  										BS 328-332	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CRACK IN FUSELAGE SKIN AT AFT LOWER CORNER OF FORWARD SERVICE DOOR (R1).  NDT CONFIRMED ADDITIONAL CRACK IN BONDED DOUBL	ER.  REPAIRED AREA IAW SRM 53-00-01 FIG. 201 REPAIR 32 AND EA NR 53-265.					2	L	7	2 	4F			RT	A16WE   					 
2006103100140	20061031	00140	NM  	2006	10	31	PIDR2006037      	1	20061023	G	5311		FRAME           			BOEING	737   	7373B7      	1384580	NM  										BS 663 S2-3R	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CRACKS IN BS663.75 FRAME AT STR 2RT AND STR 3RT.  REPAIRED FRAME IAW SRM 53-00-07.						2	L	7	2 	4F			RT	A16WE   					 
2006110600081	20061106	00081	NM  	2006	11	6	PIDR2006038      	1	20061027	G	5743		FITTING         			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					LT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				LT MLG FITTINGS CRACKED AT THE NR 2 HOLE.  REPLACED FITTING IAW SB 737-57-1216.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006110600082	20061106	00082	NM  	2006	11	6	PIDR2006039      	1	20061101	G	5753		SKIN            			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					LT FORE FLAP	DELAMINATED     	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				DELAMINATION AT THE IB END OF THE LT OB FORE FLAP.  REPAIRED DAMAGED AREA IAW SRM 51-70-10.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006110600080	20061106	00080	NM  	2006	11	6	PIDR2006040      	1	20061031	G	5752		TAB             			BOEING	737   	7373B7      	1384580	NM  	GE    	CFM56 	CFM56*      	13802	NE  					RT AILERON	SEPARATED       	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				TRAILING EDGE OF THE RT AILERON TAB IS SEPARATED.  REPAIRED MINOR DAMAGE PER SRM 51-70-16. BALANCED TAB, NO WEIGHT CHANG	E.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006111500317	20061115	00317	NM  	2006	11	15	PIDR2006041      	1	20061107	G	5311		FRAME           			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 440	CRACKED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				FORWARD FRAME OF THE FORWARD CARGO DOOR CUTOUT (BS 440 FRAME) CRACKED AT LOWER FORWARD STOP FITTING.  REPAIRED CRACK PER	 INSTRUCTIONS FROM MFG WITH FAA APPROVED 8100-9 DATED NOV.6, 2006.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006111500319	20061115	00319	NM  	2006	11	15	PIDR2006042      	1	20061031	G	5330		BEAR STRAP      			BOEING	737   	737301      	1384611	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUSELAGE	CRACKED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	573US					23560				CRACK INDICATION IN FASTENER HOLE JUST FORWARD AND BELOW THE L1 DOOR UPPER HINGE CUTOUT IN THE BEAR STRAP (SECOND LAYER)	 CONFIRMED BY HFEC.  REPAIRED IAW MFG INSTRUCTIONS WITH FAA APPROVED 8100-9 DATED NOV 3, 2006.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2006111500227	20061115	00227	NM  	2006	11	15	PIDR2006043      	1	20061026	G	5342	65538344	FITTING         			BOEING	737   	7373B7      	1384580	NM  										DRAG ANGLE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				CORROSION ON THE FORWARD FACE AND INSIDE DIAMETER OF THE RT FORWARD DRAG ANGLE FITTING AT THE VERTICAL STABILIZER AFT RT	 ATTACH FITTING.  REPLACED FITTING IAW SRM 51-40-02, 51-40-03, AND DRAWING NR 65-53744.					2	L	7	2 	4F			RT	A16WE   					 
2006111500230	20061115	00230	NM  	2006	11	15	PIDR2006044      	1	20061103	G	5330		SKIN            			BOEING	737   	7373B7      	1384580	NM  										FUSELAGE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				FASTENER HOLES JUST FORWARD AND ABOVE THE RIGHT FWD DOOR UPPER HINGE CUTOUT AND JUST FORWARD OF THE LOWER HINGE CUTOUT A	RE CRACKED.  REPAIRED SKIN AND BEAR STRAP IAW MESSAGES 1-232472835 WITH FAA DER APPROVED 8100-9 DATED NOV. 3, 2006.					2	L	7	2 	4F			RT	A16WE   					 
2006111500228	20061115	00228	NM  	2006	11	15	PIDR2006045      	1	20061103	G	5310		STRUCTURE       			BOEING	737   	7373B7      	1384580	NM  										FUSELAGE	CRACKED         	B			PIDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				FASTENER HOLES CRACKED AT THE UPPER HINGE CUTOUT AND LOWER HINGE CUTOUT OF THE LT FORWARD ENTRY DOOR. REPAIRED AREA IAW 	MESSAGE 1-232472835 WITH FAA DER APPROVED 8100-9 DATED NOV.3, 2006.					2	L	7	2 	4F			RT	A16WE   					 
2006120500007	20061205	00007	NM  	2006	12	5	PIDR2006046      	1	20061115	G	5754		SLAT            			BOEING	737   	7373B7      	1384580	NM  										LT WING	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				LT WING LEADING EDGE AT THE OB END OF THE NR3 SLAT DAMAGED.  REPAIRED DAMAGE PER SRM 51-70-11, 51-70-14, AND 51-70-16.						2	L	7	2 	4F			RT	A16WE   					 
2006111700171	20061117	00171	NM  	2006	11	17	PIDR2006047      	1	20061115	G	5520		HINGE           			BOEING	737   	7373B7      	1384580	NM  										RT ELEVATOR	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	385US					22958				RT ELEVATOR LOWER SIDE AT NR 5 HINGE HAS DAMAGE.  REPAIRED IAW SRM 51-70-17 AND MFG MESSAGE NR 1-247071893 WITH FAA DOA 	APPROVAL FORM 8100-9.					2	L	7	2 	4F			RT	A16WE   					 
2006072400031	20060724	00031	GL  	2006	7	24	PNC2006001       	1	20060718	G	3244	269K431	TIRE            			BOMBDR	BD700 	BD7001A10   	1390006	GL  										LANDING GEAR	BULGED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	03	387PC	78   				20087				SIDE WALL BULGED 4 INCHES BY 4 INCHES BY APPROX 3 INCHES HIGH.  ISSUE ADDRESSED BY ADVISORY WIRE AW300-32-0040.						2	L	7	2 	4F			RT	T00003NY					 
2006081600305	20060816	00305	GL  	2006	8	16	PNC2006004       	1	20060814	G	3244	269K431	TIRE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  										ZONE 700	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	387PC	91   				20087				BULGE IN TIRE ON SIDEWALL THAT EXTENDS ONTO THE TREAD.						2	L	7	2 	4F			RT	T00005NY					 
2006072400084	20060724	00084	GL  	2006	7	24	PNC20062         	1	20060721	G	3244	269K431	TIRE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  										LANDING GEAR	BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	353PC	137  				20053				BULGE ON SIDEWALL OF TIRE THAT EXTENDS INTO THE TREAD.  BULGE SIZE 2.5 INCHES X 2.5 INCHES X .7INCH HIGH.						2	L	7	2 	4F			RT	T00005NY					 
2006072400079	20060724	00079	GL  	2006	7	24	PNC20063         	1	20060721	G	3244	269K431	TIRE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  										LANDING GEAR	SEPARATED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	353PC	94   				20053				TIRE SIDEWALL SEPERTED AT SEVERAL LOCATIONS ABOUT ONE INCH ABOVE BEAD SEAT,NEAR MOLDING MARK. ABOUT A ONE INCH LONG VOID	.					2	L	7	2 	4F			RT	T00005NY					 
2006081600306	20060816	00306	GL  	2006	8	16	PNC20064         	1	20060814	G	3244	269K431	TIRE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  											BULGED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	387PC	91   				20087				BULGE IN TIRE ON SIDEWALL THAT EXTENDS ONTO THE TREAD.						2	L	7	2 	4F			RT	T00005NY					 
2006072400034	20060724	00034	CE  	2006	7	24	PT196042         	1	20060615	G	6123	9638003013	JAM-NUT         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					PROP GOVERNOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	376W	550  				TH1970	684427			RT PROPELLER RPM DECREASES TOWARD FEATHER BEFORE PROP CONTROL IS BROUGHT BACK INTO FEATHER DETENT.  FOUND JAM NUT ON FEA	THER SPEED ADJUSTMENT SCREW HAD WORKED LOOSE AND THE ADJUSTMENT SCREW WAS BACKING OUT.  THE DESIGN OF THESE NUTS HAS BEE	N CHANGED IN THE LAST FEW YEARS, THE EARLY TYPE DID NOT SEEM TO LOOSEN.  IF THE ADJUSTMENT SCREW HAD CONTINUED TO BACK O	UT, THE ENGINE COULD HAVE EXPERIENCED AN UNCOMMANDED FEATHER WITH LITTLE OR NO WARNING.  SUGGEST CHECKING TORQUE OF JAM 	NUT AT EACH INSPECTION AND APPLICATION OF TORQUE PUTTY UNTIL BETTER RETENTION SYSTEM IS DEVELOPED.  (K)		1	L	7	2 	3O	3	O		3A16    	E3SO				 
2006121900155	20061219	00155		2006	12	19	QKPR06001        	1	20060912	G	4930	38828406	FCU             	HONEYWELL   	GTCP36150RR 															ENGINE	LEAKING         	B			QKPR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05										FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUA	LLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO 	EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZZARD.																	 
2006121900108	20061219	00108		2006	12	19	QKPR06002        	1	20060912	G	4930	38828406	FCU             	HONEYWELL   	GTCP36150RR 															ENGINE	LEAKING         	B			QKPR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05										FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUA	LLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO 	EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZZARD.																	 
2006121900156	20061219	00156		2006	12	19	QKPR06003        	1	20060629	G	4930	38828406	FCU             	HONEYWELL   	GTCP36150RR 															ENGINE	LEAKING         	B			QKPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05					P254					FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUA	LLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO 	EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED, IT COULD CREATE A FIRE HAZZARD.    ORIGINAL DIFFICULTY DAT	E 6/29/01.																 
2007010800282	20070108	00282	GL  	2007	1	8	QKPR06007        	1	20060815	G	4930	38828406	FUEL CONTROL    	HONEYWELL   	GTCT36150RR 	DOUG  	A4D   	A4D         	       	GL  										APU	LEAKING         	B			QKPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05										FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUA	LLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO E	XIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD.  * REMOVE AIRCRAFT INFORMATION	. REPORT ORIGINALLY SUBMITTED ON 8/15/01 UNDER R/S NR PIDR318B.			2	L	7	1 	4R			RT	A1GL    					 
2007010800288	20070108	00288	GL  	2007	1	8	QKPR06009        	1	20060918	G	4930	38828406	FUEL CONTROL    	HONEYWELL   	GTCT36150RR 	DOUG  	A4D   	A4D         	       	GL  										APU	LEAKING         	B			QKPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05										FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUA	LLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO E	XIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD.  * REMOVE AIRCRAFT INFORMATION	.			2	L	7	1 	4R			RT	A1GL    					 
2006022400198	20060224	00198	NE  	2006	2	24	R018276          	3	20060120	G	6114	C459	PLATE           	HARTZL      												HARTZL	HCE4N	HCE4N3      	NE  	PROPELLER HUB	GOUGED          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	SJ3R				HH2369			HH2369		C-459 PRELOAD PLATE.  THREE PRELOAD PLATES FOUND TO BE DAMAGED BEYOND REPAIRABLE LIMITS.  GOUGE IS LOCATED OPPOSITE OF T	HE WINDOW AND IS APPROXIMATELY 0.030 WIDE BY 1 INCH LONG BY 0.020 DEEP.															5	C	P10NE	 
2006022400195	20060224	00195	NE  	2006	2	24	R018683          	3	20060120	G	6114		PLATE           	HARTZL      												HARTZL	HCE4N	HCE4N3      	NE  	PROPELLER HUB	GOUGED          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	SJ3R				HH2422			HH2422		C-459 PRELOAD PLATE.  GOUGE IS APPROXIMATELY 1.120 INCH LONG BY 0.050 INCH WIDE.																5	C	P10NE	 
2006020100126	20060201	00126	GL  	2006	2	1	R018909          	3	20060128	G	6110		O-RING          	HARTZL      	HCC2YR4CF   											HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER BLADES	WRONG PART      	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	SJ3R				DN5325B			DN5325B		PROP LEAKING GREASE FROM BLADES. INSPECTION REVEALED INCORRECT BLADE SEALS INSTALLED. SRM 113B REQUIRES ITEM 540, B-3883	-4339 QUAD RING WITH NO ALTERNATE. SEALS REMOVED FROM PROPELLER ARE O-RINGS.															5	C	P920	 
2006032200192	20060322	00192	GL  	2006	3	22	R019142          	3	20060222	G	6110	D32517	HUB             	HARTZL      		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	PROPELLER ASSY	CRACKED         	B			SJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	05	SJ3R				EB2069			EB2069		CUSTOMER WAS INVESTIGATING AN ABNORMAL GREASE LEAK ON THE RIGHT HAND PROPELLER.  REMOVED THE SPINNER, DISCOVERED THAT TH	E ENGINE-SIDE HUB HALF WAS VISIBLY CRACKED.  CRACKS ARE LOCATED ON THE PROPELLER MOUNTING FLANGE HUB HALF, LEAD EDGE SID	E OF BLADE SOCKETS NUMBER 1 AND 2.  CRACKS RUN FROM HUB PARTING SURFACE TO MOUNTING FLANGE.				1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P25EA	 
2006032100048	20060321	00048	GL  	2006	3	21	R019184          	3	20060306	G	6110	B4776	BUSHING         	HARTZL      	HCC3YR1A    	PITTS 	S2B   	S2B         	2210006	SO  	LYC   	O540  	AEIO540D4A5 	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	LOOSE           	B			SJ3R	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	05	SJ3R				EL270B			EL270B		CUSTOMER REMOVED PROP DUE TO OIL LEAKING FROM BLADE.  DISASSEMBLY OF THE PROPELLER REVEALED A LOOSE PITCH CHANGE ROD BOR	E BUSHING CAUSING THE OIL LEAK.  THE PC ROD BUSHING WAS FOUND WEDGED BETWEEN THE FORK AND HUB.  CENTRAL WEB AREA OF HUB 	WAS FULL OF OIL.  THE PC ROD BORE BUSHING HAD BEEN INSTALLED AT OVERHAUL IN ACCORDANCE WITH HARTZELL MANUAL 202A VOLUME 	3 REVISION 28.			1	Q	7	1 	3O	3	O	NC	A8SO    	1E4	5	C	P25EA	 
2006032100118	20060321	00118	NE  	2006	3	21	R019280          	3	20060303	G	6110	D7745	BEARING RACE    	HARTZL      	HCE4A3I     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	BROKEN          	B			SJ3R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	05	SJ3R	2134 			KX201			KX201		CUSTOMER REMOVED PROPELLER DUE TO LOOSE BLADE IAW HARTZELL SERVICE BULLETIN HC-SB-61-283.  ONE D-7745 BLADE SIDE BEARING	 INSTALLED ON BLADE SERIAL NUMBER 2828 WAS FOUND CRACKED CIRCUMFERENTIALLY.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2006053000167	20060530	00167	SO  	2006	5	30	R019692          	1	20060519	G	6120	C6512	ROD             	HARTZL      	PHCG3YF1E   	PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  	HARTZL	HCC2Y	BHCC2Y*     	GL  	ENGINE	WORN            	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	SJ3R	1338 			HP900B			HP900B		THE AREA OF THE PITCH CHANGE ROD THAT IS GUIDED THROUGH THE ENGINE SIDE HUB HALF BORE HAS WORN THROUGH THE CHROME PLATIN	G BEFORE FIRST OVERHAUL.					1	L	7	1 	3O	3	O	RT	A25SO   	E8CE	5	C	P920	 
2006091400072	20060914	00072	NE  	2006	9	14	R020646          	3	20060824	G	6110	1006411	PLATE           		HCE4A3J     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	MISMARKED       	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		522  			HJ1190	UE370		HJ1190		PRELOAD PLATES ARE MARKED WITH PN 100641 BUT CONFIGURED AS PN 100641-1. LOGBOOK INDICATES PROP WAS REMOVED ON 5/17/05 FR	OM AIRCRAFT D2-EVN, S/N UE-370 RT POSITION DUE TO DEEP GOUGE OVER ACCEPTABLE LIMITS.  PROP WAS OVERHAULED ON 7/14/05 WIT	H 824.0 TSN.  PRELOADS MAY HAVE BEEN INSTALLED AT THIS TIME IAW S/B HC-SB-61-278.  I DO NOT KNOW IF THE BEARINGS WERE RE	MOVED TO MAKE P/N 100641-1 OR THE PART WAS INCORRECTLY MARKED AT HPI.			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE	 
2007010400071	20070104	00071	CE  	2007	1	4	RDA113006        	1	20061130	G	2437	VA100	AMMETER         			CESSNA	175   	175         	2072502	CE  											FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	9456B	18   				55256				AEROSPACE LOGIC VA-100 DIGITAL VOLT/AMMETER AMP FUNCTION FAILED.  AMP READING VARIES FROM -12 TO -18.5 AMPS, THIS INDICA	TION IS PRESENT WITH NO LOAD ON SYSTEM OR WITH ENGINE OPERATING AND GENERATOR OPERATING NORMALLY.  VOLT FUNCTION OPERATE	S NORMALLY AND VOLTAGE READING IS NORMAL.  CONSULTED WITH MANUFACTURER AND TROUBLESHOT IAW THEIR PROCEDURE TO VERIFY THA	T GAUGE HAS MALFUNCTIONED.  A REVIEW OF THE MANUFACTURER'S ON-LINE FORUM HAS REPORTS OF SIMILAR FAILURES OF THE VA-100.			1	H	7	1 	3O			NT	3A17    					 
2006022800020	20060228	00020	WP  	2006	2	28	ROBSUL0106       	1	20060203	G	5302	C0231	STRUCTURE       			ROBSIN	R44   	R44RAVENII  	7640122	WP  										TAILBOOM	DENTED          	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	105GK	185  				10527				DURING 100 HOUR/ANNUAL INSPECTION A DENT WAS FOUND ON THE TAILBOOM CAUSED BY M/R BLADE CONTACT WITH BOOM. DUE TO SUSPECT	ED STATIC CONTACT DURING HIGH WIND CAUSING ROTOR SYSTEM TO TEETER RAPIDLY AND CONTACT BOOM.  ADDITIONAL DAMAGE FOUND WIT	H BENDING OF PITCH LINK ROD ENDS AND CONTACT WITH HUB OF THE RUBBER BOOTS OF THE SPINDLE PITCH HORNS.  THIUS DAMAGE CONS	ISTENT WITH BLADE RISING DUE TO HIGH WIND.			1	G	7	1 	3O				H11NM   					 
2006051100254	20060511	00254	SO  	2006	5	11	RX8R2006001      	1	20060410	G	3230	5777402	HYDRAULIC LINE  			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LG RETRACT SYS	DAMAGED         	B			RX8R	A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			SO	15	9085U	5679 				425501034	PCE99076	BUA26367		AFTER TAKEOFF THE LANDING GEAR HANDLE WAS MOVED TO THE UP POSITION THE LANDING GEAR CAME UP BUT THE GEAR DOORS DID NOT C	LOSE. THE LANDING GEAR HANDLE WAS PUT IN THE DOWN POSITION BUT THE LANDING GEAR DID NOT LOCK DOWN. THE EMERGENCY HAND PU	MP WAS USED TO MAKE THE LANDING GEAR LOCK IN THE DOWN POSITION. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. DISCOVERED  HY	DRAULIC LINE FROM HYDRAULIC FILTER WAS RUBBING ON NUT PLATE AND HAD WORN A HOLE IN IT. RIGHT WING TO NACELLE AREA WAS IN	SPECTED AND THE SAME HYDRAULIC LINE WAS FOUND RUBBING IN THE SAME AREA BUT HAD NOT WORN THROUGH. RECOMMEND INSPECTING TH	IS AREA ON ALL PA42-720 AIRCRAFT. AREA LOCATED BEHIND SMALL (FOUR INCH) PANEL JUST INBOARD OF THE ENGINE NACELLE ON LE.	1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2006062000012	20060620	00012	EU  	2006	6	20	RX8R2006002      	1	20060607	G	7603	L810BQ54	SOLENOID        			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					THROTTLE SYS	DEFECTIVE       	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	578AE					3716	22381			TWIST GRIP SOLENOID DOES NOT STAY IN THE MANUAL MODE POSITION (RETRACTED) WHEN MANUAL MODE IS SELECTED.  AFTER APPROXIMA	TELY 5 MINUTES SOLENOID WILL GRADUALLY EXTEND, LOCKING THE TWIST GRIP IN THE AUTO POSITION AS THE SOLENOID HEATS UP FROM	 USE.  THIS COULD CREATE A BIG PROBLEM IN AN EMERGENCY SITUATION WHERE THE PILOT SELECTS MANUAL MODE FOR CONTROL OF TWIS	T GRIP FOR POWER AND WOULD NOT HAVE IT (AFTER APPROX 5 MINUTES) DUE TO SOLENOID LOCKING THE TWIST GRIP.  NOTE: THIS PART	 WAS JUST INSTALLED, NEW.		1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2006081400145	20060814	00145	SO  	2006	8	14	RX8R2006003      	1	20060807	G	5280	4579411AND12	STRUCTURE       			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG DOOR	CRACKED         	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9085U	5726 				425501034	PCE99076	BUA26367		FOUND CRACK IN LT NOSE LANDING GEAR DOOR ON RADIUS OF FRONT STIFFENER SECTION. ALSO FOUND CRACK IN RT NOSE LANDING GEAR 	DOOR AT FORWARD HINGE ATTACH POINT. HAVE PREVIOUSLY FOUND CRACKS IN THE NOSE LANDING GEAR DOORS ON 4 OTHER PA-42'S. THE 	CRACKS ARE USUALLY IN THE DOOR HINGE ATTACH AREA. WE BELIEVE THE CRACKS ARE BEING CAUSED BY IN FLIGHT TURBULENCE, CAUSIN	G THE DOORS TO VIBRATE IN FLIGHT.			1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2006020100075	20060201	00075	NE  	2006	2	1	SJ3R018954       	3	20060128	G	6114	D7745	BEARING         	HARTZL      	HCE4A3I     											HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER HUB	BROKEN          	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05					HJ1533			HJ1533		OPERATOR FAILED PROPELLER FOR BLADE END PLAY IAW SB HC-SB-61-283 AND SERVICE LETTER HC-SL-61-215.  AFTER DISASSEMBLY, IN	SPECTION REVEALED ONE BROKEN D-7745 BLADE THRUST BEARING INSTALLED ON BLADE S/N 288MA LOCATED IN HUB SOCKET NR 3.															5	C	P10NE	 
2006082500048	20060825	00048	GL  	2006	8	25	SJ3R020511       	3	20060809	G	6114	D32511R	HUB             	HARTZL      		INLAND	S300  	S300        	4551002	CE  	LYC   	O540  	AEIO540*    		EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	DAMAGED         	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		790  			HTA1			HTA1		PROPELLER MOUNTING FLANGE HAS EXCESSIVE FRETTING DAMAGE.  HUB IS SCRAP.						1	H	7	1 	3R	3	O		ATC259  	1E4	5	C	P25EA	 
2007012500091	20070125	00091	NE  	2007	1	25	SJ3R021444       	3	20061118	G	6110	D7745	BEARING         	HARTZL      	HCE4A3J     	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	BROKEN          	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05					HJ1797			HJ1797		BLADE POSITION 4, S/N 1091 THRUST BEARING BROKEN.  DAMAGE TO PROPELLER HUB BLADE SOCKET NR 4  IS BEYOND REPAIRABLE LIMIT	S.  MFG SB 287 HAS NOT BEEN PERFORMED ON THIS PROPELLER.					2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE	 
2006051200070	20060512	00070	NM  	2006	5	12	SROM200600001    	1	20060329	G	5313	652072623	LONGERON        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	36455	1951 			23466				DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKS IN UPPER FLANGE RADIUS OF LONGERON/WEB P/N 65-20726-23 AT STA 455 AND 4	70, STR 26R.   REMOVED WEB BETWEEN STA 440 - 493, FABRICATED REPLACEMENT WEB WITH 7075-T6 .063, IN LIEU OF ORIGINAL .056	, AND INSTALLED IAW SRM AND MFG DRAWING NO 65-20726 AS SPECIFIED IN 8110-3 APPROVED DRAWING 5330-236-ERA, REV ORIGINAL, 	DATED 03-23-2006 AND MATERIAL SUBSTITUTION REPORT NO 5330236-ER, REV. ORIGINAL, DATED 03-23-2006.			2	L	7	2 	4F			RT	A16WE   					 
2006051200071	20060512	00071	NM  	2006	5	12	SROM200600002    	1	20060330	G	7830	65MK784132	THRUST REVERSER 			BOEING	737   	737205      	1384456	NM  										ENGINE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				DURING MAINTENANCE INSPECTION FOUND CRACK IN NR 2 LOWER THRUST REVERSER DOOR P/N 65MK78413-2 ALONG IB BUMPER.  REMOVED B	UMPER, STOP DRILLED CRACK, FABRICATE/INSTALL DOUBLER AND TRIPLER.  FABRICATE AND INSTALL NEW CAP TO COMPENSATE FOR DOUBL	ER AND TRIPLER.  ALL WORK ACCOMPLISHED IAW 8110-3 APPROVED DRAWING NR 7830233-1, REV ORIGINAL, DATED 03-20-2006 AND MATE	RIAL SUBSTITUTION REPORT NR 7830233-ER, REV ORIGINAL, DATED 03-20-2006.			2	L	7	2 	4F			RT	A16WE   					 
2006051200072	20060512	00072	NM  	2006	5	12	SROM200600003    	1	20060316	G	5753	657194041	FLAP            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT WING	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA		1951 			23466				DURING HEAVY MAINTENANCE VISIT FOUND DENT ON UPPER SURFACE OF LT IB MIDFLAP.  REPAIRED FLAP BY INSTALLING INTERNAL DOUBL	ER AND FLUSH PART IN IAW SRM 57-50-4, FIG. 4 PG. 8 AND 9.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006051100204	20060511	00204	NM  	2006	5	11	SROM200600004    	1	20060403	G	5730		SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 600	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP		882  			23465				RT WING LEADING EDGE CRACKED AT NR 5 SLAT UPSTOP CUTOUT JUST OB OF THE ACTUATOR.  REPAIRED BY INSTALLING INTERNAL STAINL	ESS DOUBLER IAW DER APPROVED 8110, REPORT NR SCS-5740-001SR.					2	L	7	2 	4F			RT	A16WE   					 
2006053000155	20060530	00155	NM  	2006	5	30	SROM200600005    	1	20060503	G	5313		STRINGER        			BOEING	737   	737201      	1384454	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		1210 			22751				DURING HEAVY MAINTENANCE INSPECTION FOUND CORROSION AT STR 28 LT, STA 1000 TO 1006.  CORROSION FOUND TO BE BEYOND LIMITS	.  STRINGER REPLACED I.A.W. B737 SRM 53-10-2 AND 51-10-1 PG. 9 PARA 7.  STRINGER REPLACED STA 986 - 1016 PLUS/MINUS 28".	  ORIGINAL SPLICE REUSED.  SPLICE PIECE CLEANED AND PAINTED.  LEVEL 1 CPCP ISOLATED TO LAV LEAK AND NOT EXPERIENCED ACRO	SS THE FLEET.			2	L	7	2 	4F				A16WE   					 
2006053000151	20060530	00151	NM  	2006	5	30	SROM200600006    	1	20060510	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		1210 			22751				DURING HEAVY MAINTENANCE INSPECTION FOUND SKIN CRACK UNDER RT WING TO BODY FAIRING AT STA 727B, STR 19R.  REMOVED EXSIST	ING ADJACENT PATCH AT STA 727A, STR 18R.  INSTALLED PATCH, INCORPORATING OLD REPAIR AND NEW DAMAGE IAW B737 SRM FIG. 48,	 55-30-3 AND BOEING ENGINEERING 1-185385517-1.				2	L	7	2 	4F				A16WE   					 
2006053000153	20060530	00153	NM  	2006	5	30	SROM200600008    	1	20060516	G	3210	65461406SPL	BOLT            	BOEING      	B737200     	BOEING	737   	737201      	1384454	NM  										LT MLG	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US	29571	9248 		XC89752	22751				DURING INSPECTION REQUIREMENTS OF AD2005-20-39, SB737-32A1367 FOUND LT MLG TEE BOLT, P/N 65-46140-6SPL, S/N XZ865 CRACKE	D AT RADIUS OF LARGEST BEARING SURFACE CIRCUMFERENCE.  UNIT HAD TOTAL HOURS OF 29571, TOTAL CYCLES 22830.  LAST OVERHAUL	ED 1998 WITH ACCUMULATION OF 9248 HOURS AND 5265 CYCLES SINCE OVERHAUL.  CRACK WAS AROUND 80% OF CIRCUMFERENCE.  REPLACE	D WITH SERVICABLE UNIT.			2	L	7	2 	4F				A16WE   					 
2006053000154	20060530	00154	NM  	2006	5	30	SROM200600009    	1	20060517	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  										FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US	53581	1210 			22751				DURING HEAVY CHECK INSPECTION DISCOVERED 9 CREASE/DENTS ON EXTERIOR SKIN AT STA 305 - 372, STR 23R - STR 24R.  REPAIRED 	EXTERIOR SKIN IAW B 737 SRM FIGURE 48, DETAIL XXIX AND XIX.					2	L	7	2 	4F				A16WE   					 
2006061300380	20060613	00380	NE  	2006	6	13	SROM200600010    	2	20060523	G	7250	648031	CASE            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 2 ENGINE	CRACKED         	I			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		1210 			22751	696531			DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKED OUT SECTION IN REAR EXHAUST CASE OF NR 2 ENGINE.  REPLACED WITH OVERHA	ULED UNIT.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006053000084	20060530	00084	NM  	2006	5	30	SROM200600011    	1	20060510	G	5753	65682979	CARRIAGE        			BOEING	737   	737201      	1384454	NM  										ZONE 500	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		15552			22751				DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING A 10 YEAR CPCP INSPECTION REQUIREMENTS OF THE TRAILING EDGE FLAP CARRIAG	ES FOUND LEVEL 2 CORROSION ON NR 3 CARRIAGE OB CARRIAGE HALF.  REPLACED WITH NEW HALF V/S REPAIR FOR COMPANY CONVENIENCE	.				2	L	7	2 	4F				A16WE   					 
2006053000119	20060530	00119	NM  	2006	5	30	SROM200600012    	1	20060510	G	5753	656829710	CARRIAGE        			BOEING	737   	737201      	1384454	NM  										WING	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		15552			22751				DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING  CPCP 10 YEAR REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE	 NR 3 TRAILING EDGE FLAP CARRIAGE IB CARRIAGE HALF TO HAVE LEVEL 2 CORROSION.  REMOVED AND REPLACED WITH NEW UNIT V/S RE	PAIR FOR COMPANY CONVENIENCE.				2	L	7	2 	4F				A16WE   					 
2006053000121	20060530	00121	NM  	2006	5	30	SROM200600013    	1	20060524	G	5753	655224618	CARRIAGE        			BOEING	737   	737201      	1384454	NM  										TE FLAP	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		15552			22751				DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP REQUIREMENTS TO TRAILING EDGE FLAP CARRIAGES FOUND NR 5 CAR	RIAGE, INBD CARRIAGE HALF CORRODED.  LEVEL 2.  REMOVED AND REPLACED WITH SERVICEABLE UNIT V/S REPAIR FOR CUSTOMER CONVEN	IENCE.				2	L	7	2 	4F				A16WE   					 
2006053000118	20060530	00118	NM  	2006	5	30	SROM200600014    	1	20060524	G	5753	65522469	CARRIAGE        			BOEING	737   	737201      	1384454	NM  										WING	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		15552			22751				DURING HEAVY MAINTENANCE INSPECTION WHILE PERFORMING 10 YEAR CPCP INSPECTION REQUIREMENTS TO THE TRAILING EDGE FLAP CARR	IAGES FOUND THE NR 5 CARRIAGE OTBD CARRIAGE HALF TO BE CORRODED.  LEVEL 2.  REPLACED WITH SERVICABLE UNIT V/S REPAIR FOR	 CUSTOMER CONVENIENCE.				2	L	7	2 	4F				A16WE   					 
2006053000122	20060530	00122	NM  	2006	5	30	SROM200600015    	1	20060524	G	5753	65522111	TORQUE TUBE     			BOEING	737   	737201      	1384454	NM  										ZONE 600	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		15552			22751				DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND NR 5	 FLAP CARRIAGE OUTER TORQUE TUBE TO BE CORRODED.  LEVEL 2.  REPLACED WITH SERVICABLE UNIT V/S REPAIR FOR CUSTOMER CONVEN	IENCE.				2	L	7	2 	4F				A16WE   					 
2006053000120	20060530	00120	NM  	2006	5	30	SROM200600016    	1	20060524	G	5753	65372061	TORQUE TUBE     			BOEING	737   	737201      	1384454	NM  										WING FLAP	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		15552			22751				DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP INSPECTION REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES	 FOUND THE NR 5 CARRIAGE INNER TORQUE TUBE TO BE CORRODED.  LEVEL 2.  REPLACED WITH SERVICEABLE UNIT V/S REPAIR FOR CUST	OMER CONVENIENCE.				2	L	7	2 	4F				A16WE   					 
2006111500246	20061115	00246	NM  	2006	11	15	SROM200600017    	1	20061109	G	3260	6552811109	ACCESSORY UNIT  			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					RT MLG	FAULTY          	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	736BP					23465				DURING DEPARTURE, UPON LANDING GEAR RETRACTION RT MLG INDICATION REMAINED RED.  MOVED LANDING GEAR HANDLE TO OFF AND THE	N BACK TO UP, RED INDICATOR LIGHT REMAINED ON.  SELECTED GEAR DOWN AND GOT 3 GREEN AND NO RED.  RETURNED TO ANC WITH NOR	MAL LANDING.  WITH AIRCRAFT ON JACKS FOUND LANDING GEAR ACCESSORY UNIT TO BE FAULTY. REPLACED LANDING GEAR ACCESSORY UNI	T AND ALL OPERATIONS CHECK NORMAL.  AIRCRAFT RELEASED WITH NORMAL OPERATIONS ON SUBSEQUENT FLIGHTS.			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006121300005	20061213	00005	NM  	2006	12	13	SROM200600018    	1	20061130	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  										FUSELAGE	MISREPAIRED     	C			SROM	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	245US					22751				DURING OWNER REQUEST FOR REPLACEMENT OF FUSELAGE SKIN BS 907 - 1016, STR 20L - 25L (P/N 65C80736-834) TO ELIMINATE PREVI	OUS PERMANENT AND TEMPORARY SKIN REPAIRS, DISCOVERED NON-STANDARD REPAIR AT BS992.80, STR 20L IDENTIFIED AS A CUTOUT IN 	THE ADJACENT UPPER SKIN.  INSTALLED NEW REPAIR PER BOEING REPAIR INSTRUCTION 1-248459651-6, REFERENCE BOEING ISSUED FAA 	FORM 8100-9, DATED 30 NOV 2006.			2	L	7	2 	4F				A16WE   					 
2006121300040	20061213	00040	NM  	2006	12	13	SROM200600019    	1	20061203	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  										BS 895	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				ON POST FLIGHT INSPECTION FOUND THREE INCH SKIN GOUGE AT FUSELAGE BS 895 BETWEEN STRS 22R AND 23R.  REPAIRED WITH SKIN D	OUBLER PER BOEING 737 SRM 53-30-3 AND 51-20-1.					2	L	7	2 	4F			RT	A16WE   					 
2006121300007	20061213	00007	NM  	2006	12	13	SROM200600020    	1	20061130	G	5521	657378443	SPAR            			BOEING	737   	737205      	1384456	NM  										ELEVATOR	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP		4604 			23465				DURING INSPECTION FOUND LT ELEVATOR TAB OUTBOARD HINGE FITTING TO HAVE CONSIDERABLE FLEX.  UPON FURTHER EXAMINATION FOUN	D ELEVATOR REAR SPAR CRACKED IN THE AREA WHERE TAB HINGE FITTING ATTACHES.  AD 2006-14-07/SB 737-55A1078 HAD NOT BEEN AC	COMPLISHED PRIOR TO THIS FINDING.  REPLACED ELEVATOR AND TAB WITH NEW.				2	L	7	2 	4F			RT	A16WE   					 
2007010800189	20070108	00189	NM  	2007	1	8	SROM200600021    	1	20061221	G	3220		LANDING GEAR    			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NLG	CONTAMINATED    	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733PA					23466				UPON DEPARTURE DURING HEAVY SNOW CONDITIONS WITH GRAVEL SKI EQUIPPED AIRCRAFT THE NOSE GEAR UNLOCK LIGHT REMAINED ON AFT	ER LANDING GEAR RETRACTION.  LANDING GEAR EXTENDED AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT WITH NORMAL LANDING.  UPON	 INSPECTION FOUND GRAVEL DEFLECTOR TO BE CONTAMINATED WITH SNOW AND ICE.  REMOVED SNOW AND ICE, JACKED AIRCRAFT AND SWUN	G GEAR WITH NO DEFECTS NOTED.  VERY HEAVY SNOW CONDITIONS ALLOWED FOR SNOW BUILD UP ON DEFLECTOR DURING TAXI OUT.  DEFLE	CTOR WAS DEICED PRIOR TO TAXI.		2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007010400073	20070104	00073	NM  	2007	1	4	SROM200600022    	1	20061227	G	5753		CARRIAGE        			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D15      	52051	NE  					SPINDLE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		64   			22751				DURING ROUTINE ACCOMPLISHMENT OF ULTRASOUND INSPECTION OF THE SPINDLES ON THE OB FLAPS IAW AD 2003-24-08 FOUND THE RT IB	 SPINDLE TO SHOW A CRACK INDICATION.  LAST ULTRASONIC INSPECTION PERFORMED 46 CYCLES AGO.  REPLACED SPINDLE AND CARRIAGE	 ASSEMBLY WITH NEW P/N 65C80736-712.				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2006053000152	20060530	00152	NM  	2006	5	30	SRON200600007    	1	20060516	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  										FUSELAGE	MISDRILLED      	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	245US		1210 			22751				DURING HEAVY MAINTENANCE INSPECTION FOUND SNOWMAN SHAPED HOLE WITH A SOLID AND CHERRY MAX IN IT AT STA 727A, STR 26L.  R	EPAIR PATCH AND DOUBLER INSTALLED PER BOEING ENGINEERING 1-185416133.  FAA FORM 8109-9.0					2	L	7	2 	4F				A16WE   					 
2006053000171	20060530	00171	EU  	2006	5	30	THMN4113SQ116    	1	20060508	G	5414	MY2055270	COWLING         			AMD   	FALCON	FALCON20    	2730103	EU  										ENGINE	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	453SB					308				RT INBOARD ENGINE COWL HAS SMALL CRACK IN SKIN AT TOP/FWD CORNER.  MADE AIRWORTHY REPAIR IAW DASSAULT FALCON 20 SRM 51-1	0-21.					2	L	7	2 	4F			RT	A7EU    					 
2006061300377	20060613	00377	EU  	2006	6	13	THMN4113SQ118    	1	20060508	G	5414	MY20552302	COWLING         			AMD   	FALCON	FALCON20    	2730103	EU  										RT ENGINE	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	453SB					308				RT UPPER ENGINE COWL SKIN CRACKED AT FWD SEAL BRACKET. MADE AIRWORTHY REPAIR IAW SRM 54-20-43.						2	L	7	2 	4F			RT	A7EU    					 
2006051800240	20060518	00240	EU  	2006	5	18	THMN4113SQ120    	1	20060508	G	5420	MY20552302	COWLING         			AMD   	FALCON	FALCON20    	2730103	EU  										ENGINE	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	453SB					308				RT UPPER ENGINE COWL AFT IB BRACKET CRACKED AT CORNER.   MADE AIRWORTHY REPAIR IAW SRM 54-20-43 AND SRM 51-10-22.						2	L	7	2 	4F			RT	A7EU    					 
2006053000172	20060530	00172	EU  	2006	5	30	THMN4113SQ121    	1	20060508	G	5420	MY20552302	COWLING         			AMD   	FALCON	FALCON20    	2730103	EU  										ENGINE	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	453SB					308				R/H UPPER ENGINE COWL CRACKED IN BRACKET UNDER SEAL IN CENTER SECTION.  MADE AIRWORTHY REPAIR IAW FALCON 20 SRM 54-20-43	.					2	L	7	2 	4F			RT	A7EU    					 
2006053000123	20060530	00123	CE  	2006	5	30	THMN4129SQ111    	1	20060522	G	5753		RIVET           			CESSNA	500   	500CESSNA   	2076602	CE  										RT IB FLAP	LOOSE           	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	27SF					64				RT INBOARD FLAP LOWER L/E HAS 7 LOOSE RIVETS.  REMOVED AND REPLACED RIVITS IAW SRM 51-30-1.						1	L	7	2 	4F				A22CE   					 
2006053000157	20060530	00157	CE  	2006	5	30	THMN4129SQ112    	1	20060522	G	5730	552280051	SKIN PANEL      			CESSNA	500   	500CESSNA   	2076602	CE  										LT WING	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	27SF					64				LT WING PANEL PN 5522800-51 CRACKED.  REPLACED PANEL IAW MM 57-30-00						1	L	7	2 	4F				A22CE   					 
2006071800182	20060718	00182	SO  	2006	7	18	THMN4165SQ117    	1	20060630	G	5753		SKIN            			PIPER 	PA30  	PA39        	7103902	SO  										TE FLAP	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	320GC					3960				FLAP LT IB LWR SKIN CRACKED.  MADE AIRWORTHY REPAIR  IAW PA-39 SERVICE MANUAL, CHAPTER 4 PG 1F6 AND AC 43.13-1B SECTION 	4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16.					1	L	7	2 	3O				A1EA    					 
2006071800183	20060718	00183	SO  	2006	7	18	THMN4165SQ118    	1	20060630	G	5730		SKIN            			PIPER 	PA30  	PA39        	7103902	SO  										RT WING	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	320GC					3960				CRACK IN RT WING OB SKIN NEAR SPAR.  MADE AIRWORTHY REPAIR IAW PA-39 SERVICE MANUAL CHAPTER 4 PG 1F6 AND AC43.13-1B SECT	ION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16					1	L	7	2 	3O				A1EA    					 
2006071800184	20060718	00184	SO  	2006	7	18	THMN4165SQ123    	1	20060630	G	5414		SKIN            			PIPER 	PA30  	PA39        	7103902	SO  										LT NACELLE	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	320GC					3960				LT ENGINE COWL CRACKED AT FWD FASTENER.  MADE AIRWORTHY REPAIR IAW PA-39 SRM CHAPTER 4 PG 1F6 AND AC43.13-1B SECTION 4 P	ARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16.					1	L	7	2 	3O				A1EA    					 
2006081500007	20060815	00007	NM  	2006	8	15	TL9R200600001    	1	20060809	G	3246	26123111	WHEEL           			BOEING	737   	737*        	       	NM  										MLG	FRACTURED       	B			TL9R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	13										OPERATOR STATES THAT SMOKE WAS REPORTED COMING FROM A WHEEL/BRAKE ASSEMBLY. TECHNICIANS DISCOVERED THAT THE HUB ON THE I	B WHEEL HAD A COMPLETE CIRCUMFERENTIAL FRACTURE. THE COMPLETE WHEEL ASSEMBLY IS BEING SENT TO MFG FOR EVALUATION.					2	L	7	2 	4F			RT	A16WE   					 
2006081500008	20060815	00008	NM  	2006	8	15	TL9R200600002    	1	20060809	G	3246	26123111	WHEEL           			BOEING	737   	737*        	       	NM  										ZONE 700	FRACTURED       	B			TL9R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	13										OPERATOR STATES THAT SMOKE WAS REPORTED COMING FROM A WHEEL/BRAKE ASSEMBLY. TECHNICIANS DISCOVERED THAT THE HUB ON THE I	B WHEEL HAD A COMPLETE CRCUMFERENTIAL FRACTURE. THE COMPLETE WHEEL ASSEMBLY IS BEING SENT TO HONEYWELL IN SOUTH BEND, IN	DIANA FOR EVALUATION.				2	L	7	2 	4F			RT	A16WE   					 
2006111700172	20061117	00172	EU  	2006	11	17	TL9R200600003    	1	20061116	G	3242	C200601004	BRAKE           			AIRBUS	330   	A300*       	       	EU  										MLG	DEBONDED        	B			TL9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										OPERATOR/CUSTOMER REPORTED THIS BRAKE AS (BRAKE STUCK). SUBSEQUENT INSPECTION OF THE BRAKE AT THIS REPAIR STATION DOCUME	NTED THAT THE TEMPERATURE SENSOR WAS BENT, AND PARTS OF THE HEAT STACK HAD DELINED.					2	L	7	2 	4F			RT	A26NM   					 
2006032300156	20060323	00156	CE  	2006	3	23	UVVR200600001    	1	20060221	G	5711	NAS12913	NUT             			RKWELL	NA265 	NA26560     	7630106	CE  	PWA   	JT12  	JT12A8      	52042	NE  					WINGS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	71CC					30671				WHILE PERFORMING MAINTENANCE ON AIRCRAFT, IT WAS DISCOVERED THAT APPROXIMATELY 10 NUTS ON EACH WING THAT SECURES UPPER W	ING PLANK TO REAR SPAR UPPER FLANGE, FROM REAR SPAR STATION 161.1 TO 281.8 WERE CRACKED, WITH SOME MISSING PARTS OF THE 	NUT. AS A PRECAUTION, A TOTAL OF 96 SCREWS AND NUTS AT THESE LOCATIONS WERE REPLACED WITH NEW HARDWARE.				2	L	7	2 	4J	4	J	RT	A2WE    	1E9				 
2006032300056	20060323	00056	CE  	2006	3	23	UVVR200600002    	1	20060223	G	5744	258WF71A	FITTING         			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										LT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	877DM	3668 				258279				WHILE CHANGING A BONDING BRAID ON THE LT OB FLAP ATTACH FITTING, THE INNER SURFACE OF THE LOWER ATTACH POINT FLANGE WAS 	FOUND CORRODED.   APPROXIMATELY .050 INCH DEEP AROUND THE BOLT HOLE. THE PART WAS REPLACED WITH A NEW FITTING.					2	L	7	2 	4F			RT	A3EU    					 
2006101800045	20061018	00045	GL  	2006	10	18	WI5R1005001      	2	20061005	G	7250	73792	TURBINE BLADES  			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					ENGINE	FRACTURED       	G			WI5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	103CS	588  	588  			5250438	1903			DURING A PRE-BUY A/C INSPECTION, ENGINE SN 1903 WAS FOUND TO EXHIBIT A FRACTURED TRAILING EDGE OF HP TURBINE BLADE.						1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2006103100168	20061031	00168		2006	10	31	WL7R200600001    	4	20061005	G	2564	1218FAUL03011	LIFE RAFT       																		UNSERVICEABLE   	B			WL7R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	35										LIFE RAFT HAD A PARACHUTE CORD TIED AROUND THE INFLATABLE PORTION OF THE LIFE RAFT, WHICH WOULD HAVE CAUSED THE LIFE RAF	T TO STRANGLE AND THE LIFE RAFT WOULD HAVE FAILED TO DEPLOY.																		 
2006103100149	20061031	00149		2006	10	31	WL7R200600002    	4	20061005	G	2564	1218FAUL03011	LIFE RAFT       																		UNSERVICEABLE   	B			WL7R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	35										LIFE RAFT HAD A PARACHUTE CORD TIED AROUND THE INFLATABLE PORTION OF THE LIFE RAFT, WHICH WOULD HAVE CAUSED THE LIFE RAF	T TO STRANGLE AND THE LIFE RAFT WOULD HAVE FAILED TO DEPLOY.  PICTURE AVAILABLE.																		 
2006111500253	20061115	00253	WP  	2006	11	15	WP07110306       	2	20061103	G	7200	3103336	BEARING         								GARRTT	TPE331	TPE3312U    	01514	WP  					ENGINE	FAILED          	B			ZN3R	E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			WP	07		1566 					P70176C			ENGINE WAS SENT TO MFG FOR A FLAME OUT INVESTIGATION. AT RECEIPT 2 KEY OBSERVATIONS WERE MADE. FIRST THE FILTER BYPASS I	NDICATOR WAS EXTENDED AND SECOND THE ROTATING GROUP WOULD NOT ROTATE. ONCE THE NOSE CONE AND DIAPHRAGM WERE REMOVED META	L WAS SEEN SHED THROUGHOUT GEARBOX. THE BINDING WAS FOUND TO BE DUE TO DAMAGE BETWEEN THE BULL GEAR AND HIGH SPEED PINIO	N MATING TEETH. UPON FURTHER DISASSEMBLY, COMPRESSOR BEARING WAS DESTROYED. MFG BELIEVES THE COMPRESSOR BEARING AND NUT 	LOST THEIR FUNCTIONALITY, CAUSING THE ROTATING GROUP TO SHIFT FORWARD AND CAUSE RUBS. OVERALL THE SECONDARY DAMAGE DUE T	O THIS EVENT WAS MINOR.						3	T			E3WE				 
2006102000042	20061020	00042		2006	10	20	WSAOCT182006     	4	20061018	G	3100	704A46814049	LIGHT           			SNIAS 	350   	AS350B3     	8680954	EU  										INSTRUMENT PANEL	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	578AE	702  				3716				A TECHNICIAN REMOVED THE INSTRUMENT PANEL GRADUATOR, LIGHT (LIGHTING DIMMER) FOR ACCESS PURPOSES. IT WAS FOUND UPON REMO	VAL THAT THE 24 PIN ELECTRICAL CONNECTOR ON THIS DIMMER HAD MODERATE CORROSION ON OVER HALF OF THE CONNECTOR PINS WITH S	IGNS OF CORROSION ON THE PC BOARD. THE SOURCE OF THE CORROSION IS BELIEVED TO BE WATER INGRESS FROM THE FRESH AIR DUCT L	OCATED ABOVE THIS PART.			1	G	7	1 	3U				H9EU    					 
2006022700145	20060227	00145	CE  	2006	2	27	WTXR10549        	1	20060208	G	5340		ATTACH BRACKET  			LEAR  	35    	35A         	5170602	CE  										FUSELAGE	CRACKED         	C			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99						113				FOUND CRACK AT LT AND RT FUSELAGE FRAME 20 AT THE WING ATTACH POINT.  LT CRACK IS APPROX 1.0 INCHES IN LENGTH, RT CRACK 	IS APPROX .75 INCHES IN LENGTH.					2	L	7	2 	4F				A10CE   					 
2006052200205	20060522	00205	SW  	2006	5	22	YTRR109168       	1	20060504	G	6520	206033426001A	GEARBOX         			BELL  	206   	206L4       	1182110	SW  										TAIL ROTOR	CRACKED         	B			YTRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	410RL	1387 			52310	52310				DURING ROUTINE 100-HOUR AIRFRAME INSPECTION, FOUND TAIL ROTOR GEARBOX CASTING CRACKED.						1	G	7	1 	3U			NC	H2SW    					 
2006033000100	20060330	00100	EA  	2006	3	30	ZB0R200600001    	2	20060309	G	8530		CYLINDER        			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	O360C1C     	41514	EA  					ENGINE	SEPARATED       	B			ZB0R	E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	05	15143					28R7335027	L958451A			ON RUN-UP, PILOT AND INSTRUCTOR FELT ENGINE VIBRATION.  MAG DROPS WERE GOOD.  AIRPLANE WAS TAXIED TO MAINTENANCE.  MECHA	NIC FOUND NR 3 CYLINDER WITH 4 BROKEN MOUNT STUDS AND OIL COMING FROM EXHAUST.  CYLINDER REMOVED AND REPAIRED BY ENGINE 	SHOP.  ENGINE INSPECTION REVEALED NO FURTHER DAMAGE.  SUSPECT DETONATION AS CAUSE.				1	L	7	1 	3O	3	O		2A13    	E286				 
2006080700241	20060807	00241	SO  	2006	8	7	ZB0R20060001     	1	20060725	G	3242	16402000	BRAKE DISC      			PIPER 	PA28  	PA28236     	7102815	SO  										RT MLG	BROKEN          	B			ZB0R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	05	270SW		25   			287911118				ON LANDING ROLLOUT, PILOT LOST RIGHT BRAKING. MAINT DISCOVERED RIGHT BRAKE DISK BROKEN AT WELD COMPLETELY AROUND CIRCUMF	ERENCE. SUSPECT CORROSION ATTRIBUTED TO WELD FAILURE. PART REPLACED BY MAINT.					1	L	7	1 	3O				2A13    					 
2006102000096	20061020	00096	CE  	2006	10	20	ZB0R20060002     	1	20061016	G	3242	0500118127	LINE            			CESSNA	172   	172S        	2072439	CE  										BRAKE SYSTEM	CORRODED        	B			ZB0S	O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			SO	05	3513K	1147 	15   			172S8917				DURING PREFLIGHT, PILOT NOTICED HYD FLUID COMING FROM RT BRAKE AREA. REPORTED TO MAINTENANCE. FOUND RT BRAKE LINE LEAKIN	G. REMOVED LINE AND DISCOVERED PINHOLE CORROSION UNDER CHAFE PROTECTOR AT LOWER BEND OF LINE. SUSPECT WATER ENTERED CHAF	E PROTECTOR AND CAUSED CORROSION. THE CHAFE PROTECTOR SHOULD BE SEALED AT EACH END TO PREVENT MOISTURE FROM ENTERING. RE	PLACED PART - OPS CK OK.			1	H	7	1 	3O			NT	3A12    					 
2006120400109	20061204	00109	SO  	2006	12	4	ZB0R20060003     	1	20061120	G	2720	67174000	BAR             			PIPER 	PA28  	PA28R200    	7102811	SO  										RUDDER PEDALS	CRACKED         	B			ZB0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	15143	4068 	48   			28R7335027				DURING PROGRESSIVE INSPECTION, FOUND PILOT LT RUDDER BAR CROSS-OVER JOINT CRACKED AT WELD.						1	L	7	1 	3O				2A13    					 
2006020300082	20060203	00082	WP  	2006	2	3	ZN3R556712       	2	20060103	G	7230	30745557	STATOR          			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  						SEPARATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	650TA	2556 				6500088	P87152C			ENGINE 4TH LPC STATOR HAD INNER RING FRACTURE, LEADING TO A SINGLE VANE SEPARATING FROM THE STATOR ASSEMBLY.  THE VANE C	AUSED DAMAGE TO THE HPC AREA OF THE ENGINE.  AIRCRAFT DID NOT EXPERIENCE ANY PROBLEMS WITH ENGINE DURING FLIGHT, AND PER	FORMED SCHEDULED LANDING WITHOUT INCIDENT.				2	L	7	2 	4F	4	F		A9NM    	E6WE