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
2008011100135	20080111	00135	SO  	2008	1	11	0001             	2	20070925	G	8530	AEC631397	CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT ENGINE	CRACKED         	B			FCPR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	09	919FA	1120 				414A0628	276632R			PILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT C	OULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE N	R 4 CYLINDER TO BE CRACKED AT THE PARTING SURFACE. EXHAUST WAS ESCAPING FROM THE CRACK CAUSING THE (AIR PULSING) SOUND.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007050400163	20070504	00163	GL  	2007	5	4	050207           	1	20070502	G	5210	649	ROD END         	CIRRUS      		CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					CABIN DOOR	BROKEN          	G				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	13	299JW	300  				1034				CABIN DOOR DEPARTED AIRCRAFT IN FLIGHT DUE TO THE ROD END HINGE FAILURE. IT APEARS THE ROD END FAILED DUE TO FATIGUE. TH	E ROD END SHOULD BE MADE OF A STRONGER MATERIAL.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007062500013	20070625	00013	CE  	2007	6	25	061371           	1	20070613	G	3397	NTE5916	DIODE           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										LIGHTS	OVERHEATED      	B				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CE	01	800RC	745  	745  			258660				PILOT'S NOTED THAT LANDING AND TAXI PULSE LIGHT SYSTEM WAS INOPERATIVE ... LIGHTS WOULD NOT PULSE IN FLIGHT.  SYSTEM HAD	 BEEN UPDATED PER RAYTHEON MANDATORY SERVICE BULLETIN 33-3682.  UPON INSPECTION AND TROUBLE SHOOTING SYSTEM, THE CONNECT	ORS ATTACHED TO THE DIODES (CR1 THRU CR4) THAT WERE ADDED TO THE SYSTEM AS A RESULT OF THE BULLETIN, WERE LOOSE AND APPE	AR TO HAVE OVERHEATED. IN DISCUSSIONS WITH RAYTHEON, IT WAS DETERMINED THAT POSITION OF THE DIODE INSULATORS ON PAGE 25 	OR 39 OF THE SERVICE BULLETINS IS INCORRECT AND SHOWN OPPOSITE OF WHAT THEY SHOULD BE.  AS A RESULT, THE THINNER INSULAT	OR CRACKS AND ALLOWS THE TERMINAL TO SHORT TO GROUND AND OVERHEAT.   VISUALLY INSPECT DIODE PANEL AND VERIFY THAT THE 	2	L	7	2 	4F			RT	A3EU    					 
2007091700014	20070917	00014	WP  	2007	9	17	090107           	2	20070904	G	7200	TFE7312B	ENGINE          			LEAR  	35    	36A         	5170603	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  						UNKNOWN         	E			ESPA	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			SO	11	545PA	11017	14   			028	74118			DURING CLIMB OUT SHORTLY AFTER TAKEOFF LT ENGINE QUIT.  CREW DECLARED AN EMERGENCY WITH DEPARTURE CONTROL, THEY VECTOR A	IRPLANE TO PROPER MSA ALTITUDE AND RETURN FOR LANDING. CREW ELECTED, IN FLIGHT ENGINE START CHECK LIST, THE LT ENGINE ST	ARTED, AND WAS OPERATING NORMAL. AT THIS POINT CREW NOTIFIED ATC THAT LT ENGINE WAS BACK UNDER NORMAL OPERATING CONDITIO	NS. AIRPLANE LANDED UNEVENTFULLY.			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2008010800358	20080108	00358	CE  	2008	1	8	102N07110026     	1	20071015	G	3597		CABLE           			BEECH 	56    	56TC        	1152736	CE  	LYC   	O541  	TIO541*     	41536	EA  					OXYGEN SYSTEM	CHAFED          	F				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			UK	UNKNOWN        	1			NM	09	420S	463  	463  			TG74				ISSUE WITH THE FIXED OXYGEN SYSTEM DISPLAY FOR STC SA01078SE WHERE THE DISPLAY (NOT IN CONTACT WITH OXYGEN) RIBBON CABLE	 CHAFED AND CREATED A SHORT TO GROUND WHERE THE RIBBON CABLE SMOKED BUT DID NOT FAIL, THE INDICATOR LIGHT OF THE SYSTEM,	 NOR FAILED TO OPERATE.  ISSUE WAS NOTED DURING ANNUAL INSPECTION AND NOT REPORTED AT THE TIME OF INCIDENT.  MFG HAS BEE	N IN CONTACT WITH THE ACO AND IS ISSUING A SERVICE BULLETIN.			1	L	7	2 	3O	3	O		3A16    	E10EA				 
2007120500060	20071205	00060	SO  	2007	12	5	110107           	1	20071120	G	6320		WARNING LIGHT   	ROTOL       		GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART529     	54507	EU  					GEARBOX	ILLUMINATED     	C				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	11	810CB				148599	023				DURING CRUISE FLIGHT MISSION, THE RT GEARBOX LIGHT CAME ON STEADY. THE ENGINE WAS SHUTDOWN IAW AFM PROCEDURES. THE AIRCR	AFT LANDED UNEVENTFULLY, AND TAXIED TO THE RAMP. NO EMERGENCY WAS DECLARED.					2	L	7	2 	4T	4	T		1A17    	E297				 
2007061500196	20070615	00196	GL  	2007	6	15	110DJ0507        	1	20070515	G	5522		SKIN            			AMTR  	500   	ECLIPSE500  	05614K5	GL  										RT ELEVATOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	110DJ	117  			203452	000007				DURING REMOVAL OF THE ELEVATORS, A SMALL CRACK WAS DISCOVERED ON RT ELEVATOR SKIN BY OB MOST HINGE BRACKET ATTACH POINT.						1	L	7	2 	3F			RT	EXPA1L72					 
2008010900392	20080109	00392	EU  	2008	1	9	120107           	2	20071217	G	7200		ENGINE          			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					LEFT	VIBRATION       	E			ESPA	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			SO	11	183PA					108	8571			AFTER LANDING, TEMP.AROUND -12C, FREEZING FOG, CREW ELECTED TO TURN OFF ANTI-ICE AFTER LND.  AIRCRAFT SAT FOR 1 HR,ENG'S	 STARTED. LT ENG HAD VIBRATION HUMMING, RT ENG WAS STABLE.TAXIED OUT W/ANTI-ICE ON THRUOUT.  A/C TOOKOFF, IT SEEMED TO B	E SMOOTH ON THE ROLL AND INITIAL CLIMB, HOWEVER, OUT OF 10,000 FT LT ENG VIB WAS AROUND 1.5 MILS,ABNORMAL FOR THIS AIRPL	ANE. CREW ELECTED TO DIVERT (MAINT.BASE). LANDING WAS UNEVENTFUL. BOTH ENG'S HAD VISUAL CKS, NOTHING NOTED. CONCLUSION I	T MUST HAVE BEEN AN ICING/MELTING PROBLEM.		2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2007121400345	20071214	00345	EA  	2007	12	14	120507           	1	20071205	G	6310	A1902	V-BELT          			BLANCA	1413  	14132       	1201004	EA  										ENGINE TO TRANS	DISINTEGRATED   	C				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	19	413R	503  				1531				DURING IFR TRAINING FLIGHT WHILE IN CROSS COUNTRY CRUISE, LOUD NOISES FROM ENGINE AREA PROMPTED CREW TO MAKE UNSCHEDULED	 LANDING TO SAFE AREA OF FLORIDA STATE ROAD 80 MEDIAN TURN AROUND PAVEMENT. UPON LANDING FOUND AFT BELT OF MAIN DRIVE BE	LT HAD SHED ITS OUTER LAYER AND DISINTEGRATED, CAUSING DAMAGE ONLY TO THE FAN SHROUD BEHIND THE ENGINE OIL COOOLER, AND 	MINOR SKIN DENT BEHIND THE FUEL TANK IN OUTER SKIN. ONE MULTIFUNCTION ANTENNA RG58 TNC CONNECTOR DAMAGED. AIRCRAFT TRAIL	ERED TO HANGAR AND AFFECTED AREAS DISSASSEMBLED. REPLACEMANT SERVICABLE FAN SHROUD ASSEMBLY TO BE INSTALLED WITH NEW PAR	TS ORDERED FROM ROBINSON. NO ENGINE OR ROTOR OVERSPEED OCCURED. AUTOROTATION WAS NOT REQUIRED. PART 91 FLIGHT TRAINING O	1	L	7	1 	3O				A773    					 
2007121400347	20071214	00347	GL  	2007	12	14	15DR             	1	20070411	G	2421	BC4101	ALTERNATOR      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					NR 2	DESTROYED       	B			ODAR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	21	15DR					0394				OWNER REPORTED NR2 ALTERNATOR LIGHT ILLUMINATED.  REMOVED TOP COWLING TO INSPECT NR2 ALTERNATOR.  FOUND NR2 ALTERNATOR B	ROKEN OFF AT MOUNTING PLATE BY (3) STUDS.  ONE STUD STILL ATTACHED WITH NUT, BUT LOOSE.  REMOVED P/N BC410-1, S/N 092140	3.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007040200167	20070402	00167		2007	4	2	200345493        	1	20070316	G	7920	4012T16P01	OIL FILTER      																	OIL SYSTEM	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25										INTERNAL BORE TO EACH END OF THE OIL FILTER ASSEMBLIES ARE SHARP AND UNSMOOTH.  THIS CONDITION WAS NOTED ON 3 ADDITIONAL	 FILTERS IN OUR STOCK, LOT 583085.  THIS CONDITION CAUSES THE PACKINGS ON THE OIL FILTER BODY TO SHEAR UPON INSTALLATION	 OF THE FILTER ELEMENT AND COULD CAUSE OIL BYPASS TO OCCUR.  THIS FILTER ELEMENT IS USED.  (K)																	 
2007020100031	20070201	00031	SO  	2007	2	1	200600073        	1	20070131	G	5730		SKIN            			LKHEED	282   	C130A       	5262502	SO  										WING	CRACKED         	B			KGBR	K				NONE                    				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			NM	04	131HP	20233				56534				2EA CRACKS WERE DETECTED WHILE PERFORMING AD 2002-19-14, 1 CRACK EMANATING FROM A FASTENER HOLE LOCATED AT FS 543 RT CW 	STA 70 LOWER WING AND 1 CRACK EMANATING FROM A FASTENER HOLE AT  FS 569, LT CW STA 57, LOWER WING.  BOTH CRACKS ARE .125	0 INCH LONG.				2	H	7	4 	4T				A31NM   					 
2007020100015	20070201	00015	WP  	2007	2	1	200600083        	1	20070131	G	5711		SPAR CAP        			CVAC  	PB4Y2 	PB4Y2       	2421102	WP  	WRIGHT	R2600 	R260035     	67050	EA  	HAMSTD	23E	23E50       	NE  	WING	CRACKED         	B			KGBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	2872G	7162 				66300				WHILE PERFORMING THE REQUIREMENTS IN AD 2003-18-01, CRACKS WERE NOTED THRU-OUT THE WING.  THE MAJOR CRACK IS A 4-5 INCH 	CRACK IN THE FWD LT LOWER SPAR CAP AFT ANGLE AT THE WING ATTACH POINT TO THE BELT FRAME.  THE CRACK IS IN THE ANGLE (SPA	R CAP AFT LEG), DOUBLER AND SPAR WEB.  THERE ARE ALSO CRACKS .1250-.2500 INCH EMANATING FROM 3 OF THE 4 BELT FRAME CUTOU	TS ON THE LOWER WING.			2	H	7	4 	4R	4	R	RT	        	PAGE42	6	C	P603	 
2007110100188	20071101	00188	NM  	2007	11	1	200700026        	1	20071017	G	2797	WMBMS136OT7C4G20	WIRE            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					TE FLAPS	CHAFED          	C			SROM	O				OTHER                   				S			AFFECT SYSTEMS            			AP	APPROACH       	1			AL	03	733PA	38672				23466				TRAILING EDGE FLAPS ASYMMETRY LOCKOUT BETWEEN ZERO AND ONE DEGREE.  THERE IS A SPLIT IN T/E FLAP INDICATION, LT T/E FLAP	S INDICATE ONE DEGREE AND RT T/E FLAPS INDICATE ZERO.  FLIGHT CREW EXPERIENCED AN UNEVENTFUL LANDING AND NO UNCOMMANDED 	ROLL.  MAINTENANCE DISCOVERED RT T/E FLAP POSITION TRANSMITTER WIRE HARNESS HAD CHAFED WIRES.  REPLACED WIRE HARNESS FRO	M RT TRANSMITTER TO DISCONNECT STATION 720R CONNECTOR D4876P.			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007080700167	20070807	00167	SW  	2007	8	7	2007001          	1	20070717	G	5714		SPAR CAP        			CVAC  	P4Y   	P4Y2TRANSAIR	2421102	SW  	WRIGHT	R2600 	R260035     	67050	EA  	HAMSTD	23E	23E50       	NE  	CENTER WING	CRACKED         	B			KGBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	2872G	7162 				66300				WHILE PERFORMING AD 2003-18-01, CRACKS WERE FOUND UNDER THE LT LOWER, FWD, SPAR CAP DOUBLER IN THE CAP, SPAR WEB AND THE	 DOUBLER ITSELF.  CRACKS WERE ALSO FOUND IN THE WING SKIN CUTOUTS AT ALL 4 LOWER CENTER WING BELT FRAME CUT-OUTS. RT FWD	 LOWER SPAR CAP CRACKED IN (2) PLACES UNDER THE DOUBLER.				2	H	7	4 	4R	4	R		AR29    	PAGE42	6	C	P603	 
2007020100014	20070201	00014	WP  	2007	2	1	200700105        	1	20070131	G	5711		SPAR CAP        			CVAC  	PB4Y2 	PB4Y2       	2421102	WP  	WRIGHT	R2600 	R260035     	67050	EA  	HAMSTD	23E	23E50       	NE  	WING	CRACKED         	B			KGBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	2871G	7192 				66302				WHILE PERFORMING THE REQUIREMENTS IN AD 2003-18-01, CRACKS WERE NOTED THRU-OUT THE WING.  THE MAJOR CRACK IS A 1.5 INCH 	CRACK IN THE FWD LT LOWER SPAR CAP AFT ANGLE AT THE WING ATTACH POINT TO THE BELT FRAME.  THE CRACK IS IN THE ANGLE (SPA	R CAP AFT LEG), DOUBLER AND SPAR WEB.  THERE ARE ALSO CRACKS .1250-.2500 INCH EMANATING FROM THE 4 BELT FRAME CUTOUTS ON	 THE LOWER WING.			2	H	7	4 	4R	4	R	RT	        	PAGE42	6	C	P603	 
2007013100168	20070131	00168	EU  	2007	1	31	200700114        	1	20070130	G	5720	2121151091	STIFFENER       			CASA  	C212  	C212        	2410200	EU  	GARRTT	TPE331	TPE33110R   	0517	WP  	ROTOL	R334	R334482F13  	GL  	LT WING	CRACKED         	B			KGBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	515RL	5409 				405				WHILE PERFORMING CASA COM LETTER 212-224 AND CASA SB 212-57-57-30, A CRACK WAS NOTED FROM THE 4TH RIVET TO THE 5TH RIVET	 FROM THE BOTTOM, ON THE VERTICAL STIFFINER LOCATED ON THE LT WING AT STA 4700, AFT SPAR WEB.  THREE STIFFINERS NEXT TO 	THE ORIGINAL ARE CRACKED EXACTLY THE SAME, CRACKS ARE LOCATED INT HE SAME POSITIONS, BETWEEN THE 4TH AND 5TH RIVIT FROM 	THE BOTTOM.  THIS TOTALS 4EA CRACKED STIFFINERS.			2	H	7	2 	4T	4	T		A43EU   	E4WE	6	C	P61GL	 
2007022600165	20070226	00165	CE  	2007	2	26	2007001HAGGAN    	1	20070223	G	5740	2322330177	SUPPORT BRACKET 	GARKENYON   	26044       	LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ZONE 500	FAILED          	B			H51R	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			NM	03	252FX	5936 			0295	196				DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LEFT WING RIB SEGMENT.						2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007080700170	20070807	00170	WP  	2007	8	7	2007002          	1	20070717	G	5714		SPAR CAP        			CVAC  	PB4Y2 	PB4Y2       	2421102	WP  										CENTER WING	CRACKED         	B			KGBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	2871G	7192 				66302				WHILE PERFORMING AD 2003-18-01, CRACKS WERE FOUND UNDER THE LT LOWER, FWD, SPAR CAP DOUBLER IN THE CAP, SPAR WEB AND THE	 DOUBLER ITSELF.  CRACKS WERE ALSO FOUND IN THE WING SKIN CUTOUTS AT ALL 4 LOWER CENTER WING BELT FRAME CUT-OUTS. RT FWD	 LOWER SPAR CAP CRACKED IN ONE PLACE UNDER THE DOUBLER.				2	H	7	4 	4R			RT	        					 
2007040900153	20070409	00153	NE  	2007	4	9	200701           	2	20070328	G	7210	311300001	GEARBOX         			ACQCOR	F22   	F22         	8850908	EA  	PWA   	JT15  	JT15D4      	52112	NE  					ACCESSORY G/B	MISDRILLED      	B			LM1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09										ENGINE WAS ROUTED TO OUR FACILITY FOR OVERHAUL AND DURING A FLUSHING PROCESS WE DISCOVERED A WALL IN AN ACCESSORY GEARBO	X WITH A MISDRILLED OIL PASSAGE.  THE OIL PASSAGE DID SUPPLY OIL TO THE REQUIRED AREA BUT IT BROKE THROUGH THE WALL DURI	NG THE MANUFACTURING PROCESS RESTRICTING THE OIL SUPPLY. THE ENGINE HAS BEEN OPERATING WITH THIS CONDITION WITH NO APPAR	ENT EFFECT. THE AGB COMPONENTS WAS INSPECTED AND NO DAMAGE WAS FOUND AS A RESULT OF THIS CONDITION.			1	H	7	1 	3O	4	F	NC	1A9     	E1NE				 
2007012900391	20070129	00391	NE  	2007	1	29	20070125         	2	20070124	G	8520		GEAR            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	WORN            	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	622					10003	L2845148A			DURING INSPECTION OF THE ENGINE WHILE REPLACING THE CRANKSHAFT IAW SB 569A, IT WAS OBSERVED THAT (PN 13519647) CRANKSHAF	T GEAR WAS EXCESSIVELY WORN.  THE GEAR WAS REPLACED WITH A NEW PART.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110100185	20071101	00185	NM  	2007	11	1	20073            	1	20071016	G	6720	A3592	ATTACH BRACKET  			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320*       	41508	EA  					T/R PEDAL	CRACKED         	B			LJER	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			HO	HOVERING       	1			NM	09	721HH	12846				1484				TAIL ROTOR PEDALS JAMMED DURING FLARE TO A HOVER. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT TH	E TAIL ROTOR PEDAL BLOCK SUPPORT BRACKET ON THE RT SIDE HAD CRACKED AT THE AFT PEDAL BLOCK ATTACH POINT ALLOWING THE PED	AL BLOCK TO PIVOT DOWN AND JAM THE PEDALS. REPLACED BRACKET WITH NEW.				1	G	7	1 	3O	3	O		H10WE   	E274				 
2007090600021	20070906	00021	SO  	2007	9	6	2007ADP828001    	1	20070823	G	3230	159SCH1151	SELECTOR VALVE  			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  	ROTOL	R4304	R1844304    	EU  	RT MLG	BYPASSING       	C				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			SO	11	198PA		1253 			027				AIRCRAFT WAS ENROUTE, FLYING THE APPROACH FOR RUNWAY 03. ONCE THE CREW PERFORMED THE APPROACH CHECKLIST, AND GEAR DOWN W	AS SELECTED BEFORE LANDING CHECKLIST THEY GOT THE RT MAIN AND NOSE GEAR LIGHT ONLY. CREW TRY THE EMERGENCY PROCEDURES DE	SCRIBED ON CHECKLIST. THIS PROCEDURE DID NOT GET THE (3) GREEN GEAR LIGHTS.  AIRCRAFT LANDED WITH (2) GEARS DOWN ON RUNW	AY 21, AND SLID INTO THE GRASS.  NO INJURIES TO CREW OR PASSENGERS.			2	L	7	2 	4T	4	T		1A17    	E297	6	C	P899	 
2007082100203	20070821	00203	CE  	2007	8	21	2007AP080901     	1	20070809	G	5521	043200185	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RT ELEVATOR	CRACKED         	B			LJER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	48440	15375				15280910				RT ELEVATOR SPAR FOUND BROKEN/CRACKED AT OB ATTACH POINT. OB HINGE BRACKET PULLED AWAY FROM SPAR.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007082100209	20070821	00209	CE  	2007	8	21	2007AP081001     	1	20070810	G	2730	1016100190014	TORQUE TUBE     	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ELEVATOR	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	7166P	11959	11959		BB482	BB482				WHILE UNDERGOING A SCHEDULED INSPECTION, FOUND THE RT ELEVATOR HAD DEVELOPED VERTICAL PLAY WHEN GRASPED FROM THE TRAILIN	G EDGE. FOUND THE ELEVATOR TORQUE TUBE HAD ROTATIONAL WHERE THE 6 EACH OB BLIND RIVETS ATTACH THE TORQUE TUBE TO THE MOU	NT PLATE.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007083000020	20070830	00020	CE  	2007	8	30	2007AP0821001    	1	20070809	G	2497	36153	TERMINAL        			BEECH 	200   	B200        	1152922	CE  										RT GCU	BROKEN          	D				B	A			EMER. DESCENT           	UNSCHED LANDING         			B	G	H	SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   	CR	CRUISE         	1			CE	07	1925P	9715 				BB1094				WIRE NUMBER P73G16N AT RT ENGINE FIREWALL GROUND POINT GS15 SEPARATED FROM THE WIRE TERMINAL DURING CRUISE FLIGHT. THIS 	WIRE CONNECTS GROUND TO THE GCU PIN G. THE RT GENERATOR OUTPUT SPIKED AND OPENED THE 325 AMP RT BUSS CURRENT LIMITER, TH	E 50 AMP RT INVERTER CURRENT LIMITER, AND DAMAGED RADIOS, THE GCU AND SYSTEMS WIRED TO THE RT BUSS. UPON INSPECTION, THE	 INSULATION OF P73G16N WAS FOUND STRIPPED TOO FAR FROM THE WIRE END THEREBY GIVING NO SUPPORT OF THE WIRE INTO THE TERMI	NAL AT THE INSULATION CRIMP AREA.		1	L	7	2 	4T				A24CE   					 
2007091400201	20070914	00201	EU  	2007	9	14	2007F00052       	1	20070904	G	7714	AG34	TACH GENERATOR  			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE33110T   	 	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	LEFT ENGINE	FALSE INDICATION	E				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			EA	21	403VA					8171				LEFT RPM INDICATION ABNORMAL PERFORMED PRECAUTIONARY SHUTDOWN.  INSPECTION FOUND TACH GENERATOR SHAFT BROKEN.  REMOVED A	ND REPLACED TACH GENERATOR IAW AMM 77-11-03.  ENGINE GROUND PERFORMANCE RUN C/W AND PASSED.  ALL PARAMETERS NORMAL.  AIR	CRAFT APPROVED FOR RETURN TO SERVICE.				2	H	7	2 	4T	4	T	RT	A16EU   	E4WE	6	C	P40EA	 
2007113000144	20071130	00144	CE  	2007	11	30	2007F00064       	1	20071018	G	3220	13889	BEARING RACE    			BEECH 	100   	B100        	1152919	CE  										NLG	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	500KD	200  				BE79				FOUND BOTH NOSE WHEEL BEARINGS PN 13889, AND RACES, PN 13836 TO BE CORRODED.  CHANGED THESE SAME BEARINGS AND RACES AT L	AST INSPECTION DUE TO SAME PROBLEM.  BEARINGS HAVE 200 HOURS OR 4 MONTHS ON THEM.  NOSE WHEEL IS AN STC WHEEL AND BRAKE 	ASSEMBLY.  WE ALSO REPLACED THESE SAME BEARINGS AND RACES 1 YEAR PRIOR.  (K)				1	L	7	2 	4T				A14CE   					 
2007110500011	20071105	00011	SW  	2007	11	5	2007F00065       	1	20071016	G	6320	204040016005	TRANSMISSION    			BELL  	204   	UH1F        	1181411	SW  	GE    	T58   	T58GE3      	 	NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	4040P					657911				CRACK FOUND ON MAIN GEARBOX (TRANSMISSION IN VERTICAL CAST WEBBING ABOVE ENGINE TO TRANSMISSION DRIVE QUILL.  MILITARY T	ECHNICAL MANUAL ALLOWS .2500 INCH RADIUS/POLISH INTO WEBBING THIS CRACK HAS BEEN FOUND ON THREE (3 EACH) TRANSMISSIONS O	N OTHER AC WITH ONE PENETRATING THE GEARBOX AND LEAKING FLUID.  (K)				1	G	7	1 	4U	4	U		EXPA1G71	 				 
2007010800148	20070108	00148	CE  	2007	1	8	2007FA0000001    	1	20070102	G	2810	10092004115	LINE            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUEL SYSTEM	CHAFED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	155AV					BB1216				DURING A SCHEDULED PHASE INSPECTION P/N 100-920041-15 ALUMINUM MAIN FUEL LINE WAS FOUND CHAFED IN THE LT MAIN LANDING GE	AR WHEEL WELL WHERE IT ENTERS INTO THE BACK OF THE WING. THE EDGES OF THE HOLE THAT THE LINE PASSES THROUGH WAS PROTECTE	D WITH PLASTIC ANTI CHAFE MATERIAL THAT WE CALL TANK TRACKS, OR RAILROAD TRACK, AND HAS A PN MS21266-1N.  THIS ANTI CHAF	E MATERIAL WAS INSTALLED AT THE FACTORY. THIS ANTI CHAFE MATERIAL CAUSED P/N 100-920041-15 ALUMINUM MAIN FUEL LINE TO BE	 CHAFED ALMOST THROUGH ITS .030 INCH SIDEWALL THICKNESS.  THERE ARE OTHER AC THAT HAVE CHAFED FUEL LINES DUE TO THE CLOS	E TOLERANCE OF THE FUEL LINES PASSING THROUGH THE STRUCTURE IN THE MAIN LANDING GEAR WHEEL AREA.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007011600044	20070116	00044	EA  	2007	1	16	2007FA0000031    	2	20070103	G	8520	13B37024	CRANKSHAFT      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	CORRODED        	D			GICR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	5347M	2372 				2842136	L1949939A	A59073		THE ENGINE CURRENTLY UNDERGOING ITS FIRST OVERHAUL SINCE NEW.  THE CRANKSHAFT WAS CLEANED, URETHABOND 104 COATING REMOVE	D AND CORROSION PITTING WAS DISCOVERED BENEATH COATING.  THE PITTING EXCEEDED (SERVICEABLE LIMITS) AS STATED IN SB NR 50	5B.  THIS CAUSED THE CRANKSHAFT THE BE REMOVED     FROM SERVICE.  THE ENGINE AVERAGED 39.5 HOURS/ MONTH SINCE IT WAS NEW	.  MFG AD COVERS THIS SUBJECT WITH THE COMPLIANCE WITH FAR, BEING TERMINATING ACTION FOR THE REPETITIVE INSPECTION.  THE	 CRANKSHAFT (FROM THE FACTORY) HAD THE COATING AND (PID) STAMPING.  NOTE: DUE TO THE URETHABOND 104 COATING, THIS SHOULD	 HAVE PREVENTED THE CORROSION PITTING WHICH IS A CONCERN OF THIS AD.  THE ENGINE OVERHAULER STATED THE COATING WAS NOT W	1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007012500042	20070125	00042	SO  	2007	1	25	2007FA0000036    	2	20070102	G	8520		LIFTER          			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 6 CYLINDER	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	29114					U2061084	1683457			AFTER DRAINING OIL AND INSPECTING FILTER, LARGE FLAKES OF METAL WERE FOUND.  DISASSEMBLED VALVE TRAIN AND FOUND SPALLING	 ON CYLINDER NR 6 INTAKE LIFTER.  DAMAGE OCCURRED TO THE CORRESPONDING CAM LOBE AND CLYINDER NR 5 INTAKE LIFTER DUE TO D	ETERIORATION OF CYLINDER NR 6 INTAKE LIFTER.  UPON INSPECTION IT WAS DETERMINED THAT THE LIFTER HAS BAD METALLURGY.  ALL	 OTHER LIFTERS NOT NOTED, SHOWED PROPER WEAR, AND HARDNESS TESTING MARKS.  THE CAM SHOWED DAMAGE ON CORRESPONDING LOBE, 	NOT DETERIORATION, AND OTHER LOBES SHOWED PROPER WEAR.  THE ENGINE HAS 228.06 HOURS SINCE FACTORY REMANUFACTURE.  MFG WA	S CONTACTED ABOUT SITUATION, AND NO INTEREST WAS NOTED ON POSSIBLE PROBLEMS.  ENGINE WAS SENT TO LOCAL REPAIR STATION FO	1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007012500250	20070125	00250	EA  	2007	1	25	2007FA0000038    	1	20070115	G	3233	2953310095200	SEAL            	ROTOL       		CNDAIR	CL600 	CL6002B16   	1900305	EA  										ACTUATOR PISTON	POROUS          	B				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			GL	13					DCL28293					GREEN TWEED SEAL P/N 295-33100-952-0050 INSTALLED ON PISTON ASSEMBLY IN MFG SIDE BRACE ACTUATOR P/N: 6500-3 HAVE BEEN FO	UND WITH VOIDS ON THE INNER RAISED SURFACE CAUSING FLUID LEAK.  THESE VOIDS ARE UNDETECTED AT INSTALLATION OF NEW SEAL A	S THE VOIDS ARE NOT ON THE SURFACE AND DO NOT BECOME VISIBLE UNTIL AFTER MONTHS OF OPERATION.  SEAL CONDITION NOTED DURI	NG WARRANTY REPAIR.  SUBJECT ACTUATOR RETURNED FOR WARRANTY REPAIR AFTER 11 MONTHS OPERATION.			2	L	7	2 	4F			RT	A21EA   					 
2007012400183	20070124	00183	SO  	2007	1	24	2007FA0000039    	1	20070116	G	2497		WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					UNKNOWN	WORN            	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	456M					318152081				THE WIRING THAT PASSES THROUGH THE NOSE RIB GROMMETS HAVE WORN TO THE EXTENT THAT THE INSULATION IS GONE AT PLACES CAUSI	NG THE METAL CONDUCTOR TO SHOW THROUGH.  IT APPEARS THAT THIS IS WORSE WITH THE GREATER AMOUNT OF CABLES IN THE BUNDLE. 	 BUNDLES OF ONLY 2 WIRES DO NOT HAVE THIS PROBLEM. APPARENTLY THE BUNDLE IS (SLAPPED) UP AND DOWN WITH VIBRATION.  THIS 	IS CAUSE FOR CONCERN DUE TO SPARKING NEAR THE FUEL TANK.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007012900346	20070129	00346	SO  	2007	1	29	2007FA0000040    	1	20070116	G	3233	400872	CLEVIS BOLT     			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	SHEARED         	B				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			GL	21	289ND	4558 				2844039				DURING CRUISE FLIGHT, CREW REPORTED LOUD BANG FOLLOWED BY A NOSE GEAR DOWN AND LOCKED INDICATION. AIRCRAFT LANDED WITHOU	T INCIDENT. UPON INSPECTION BY MX PERSONNEL NOSE GEAR ACTUATOR ROD END CLEVIS BOLT (AN23-21A) MISSING WITH EVIDENCE OF B	OLT FAILURE.				1	L	7	1 	3O	3	O		2A13    	1E10				 
2007012600251	20070126	00251	SO  	2007	1	26	2007FA0000041    	1	20070116	G	3233	400872	CLEVIS BOLT     			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	SHEARED         	B			OG5R	A				UNSCHED LANDING         				F	D	J	FLT CONT AFFECTED         	INFLIGHT SEPARATION       	WARNING INDICATION        	CR	CRUISE         	1			GL	21	289ND	4558 				2844039				DURING CRUISE FLIGHT, CREW REPORTED LOUD BANG FOLLOWED BY A NOSE GEAR DOWN AND LOCKED INDICATION. AIRCRAFT LANDED WITHOU	T INCIDENT. UPON INSPECTION BY MX PERSONNEL NOSE GEAR ACTUATOR ROD END CLEVIS BOLT (AN23-21A) MISSING WITH EVIDENCE OF B	OLT FAILURE.				1	L	7	1 	3O	3	O		2A13    	1E10				 
2007012900347	20070129	00347	SO  	2007	1	29	2007FA0000042    	1	20070116	G	2497		WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ELECTRICAL SYS	CHAFED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	456M					318152081				THE WIRING THAT PASSES THROUGH THE NOSE RIB GROMMETS HAS WORN TO THE EXTENT THAT THE INSULATION IS GONE AT PLACES CAUSIN	G THE METAL CONDUCTOR TO SHOW THROUGH.  IT APPEARS THAT THIS IS WORSE WITH THE GREATER AMOUNT OF CABLES IN THE BUNDLE.  	BUNDLES OF ONLY 2 WIRES DO NOT HAVE THIS PROBLEM. APPARENTLY THE BUNDLE IS (SLAPPED) UP AND DOWN WITH VIBRATION.  THIS I	S CAUSE FOR CONCERN DUE TO SPARKING NEAR THE FUEL TANK.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007012600006	20070126	00006	CE  	2007	1	26	2007FA0000046    	1	20070105	G	5713	05112821	STRINGER        			CESSNA	170   	170B        	2072306	CE  	CONT  	O300  	O300*       	17022	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3436D	4200 				26979				CRACKED AT FORWARD END AND PROGRESSES AFT.  PROP STRIKE, OUT OF BALANCE PROP.  EXAMPLE FROM C-170B WITH THE ENGINE INSTA	LLED.  (K)					1	H	7	1 	3O	3	O		A799    	E253				 
2007012500346	20070125	00346	CE  	2007	1	25	2007FA0000047    	1	20070105	G	5713	0511282	STRINGER        			CESSNA	170   	170B        	2072306	CE  	CONT  	O300  	O300*       	17022	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3436D	4200 				26979				CRACKED AT FWD END AND PROGRESSES AFT.  PROP STRIKE, OUT OF BALANCE PROP?  AIRCRAFT HAS A HISTORY OF WING REPAIRS FROM G	ROUND LOOPS BUT HAS SINCE HAD A ENGINE UPGRADE TO MFG.  (K)					1	H	7	1 	3O	3	O		A799    	E253				 
2007012500347	20070125	00347	CE  	2007	1	25	2007FA0000048    	1	20070105	G	5713	0511282	STRINGER        			CESSNA	170   	170B        	2072306	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										CRACKED AT FORWARD END AND PROGRESSES AFT.  PROP STRIKE, OUT OF BALANCE PROP.  (K)						1	H	7	1 	3O				A799    					 
2007012500281	20070125	00281	EU  	2007	1	25	2007FA0000049    	1	20070104	G	4980	MY20240035005A3	SEAL            	MICROTURBO  		AMD   	FALC20	FALCON20F5  	2730105	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					APU EXHAUST	DETERIORATED    	B			JGVR	O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			CE	09	189RB	1673 			592	262				DETERIORATED APU EXHAUST DUCT SEAL BETWEEN THE DUCT FLANGE AND AIRCRAFT SKIN ALLOWED HOT EXHAUST GASSES TO ENTER THE TAI	LCONE AREA RESULTING IN HEAVY SOOT BUILDUP AND HEAT DAMAGE TO WIRE BUNDLES AND ELECTRICAL CONNECTORS AND STRUCTURAL COMP	ONENTS ADJACENT TO THE APU EXHAUST OPENING.  ULTRASOUND INSPECTION REVEALED HEAT DAMAGE TO THE AC SKIN ABOVE THE EXHAUST	 OPENING.  THE APU EXHAUST OPENING DOUBLER AND STRINGERS ADJACENT TO THE OPENING.  PERIODIC INSPECTION OF THE APU INSTAL	LATION, INCLUDING THIS SEAL, IS REQUIRED EVERY A-CHECK IAW MM.  (K)		2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2007012500197	20070125	00197	SO  	2007	1	25	2007FA0000050    	1	20070110	G	5521	510229615	ATTACH ANGLE    			AMRGEN	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320*       	41508	EA  					STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	9962U	3163 				AA5A0362				DURING INSPECTION, ANGLE PN 5102296-15 AND PN 5102296-16, WERE FOUND CRACKED IN THE UPPER END OF THE ANGLE AS INSTALLED.	  CAUSE OF CRACKING IS BELIEVED TO BE DUE TO HIGHT STRESS LOADS IN THIS AREA.  (K)					1	L	7	1 	3O	3	O		A16EA   	E274				 
2007012500198	20070125	00198	CE  	2007	1	25	2007FA0000051    	1	20070107	G	5230		DOOR            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					CARGO BAY	OPEN            	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	01	480DG	5294 				5600015	108029			RT BAGGAGE DOOR POPPED OPEN ON ROLLOUT WITHOUT WARNING.  COULD NOT DUPLICATE CIRCUMSTANCES, SUGGEST INSPECTING LATCHES A	ND DOOR WARNING.  ON A MORE REGULAR BASIS.  AIRCRAFT RETURNED WITHOUT PROBLEM.  (K)					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007012900355	20070129	00355	EU  	2007	1	29	2007FA0000054    	1	20070102	G	2435		BEARING         	LUCAS       	23080005    	BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					STARTER GEN	FAILED          	C				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	09	180NE		710  		95274	NA0401	P91312			FORWARD BEARING FAILED						2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007012500134	20070125	00134	SO  	2007	1	25	2007FA0000056    	1	20070110	G	5521	510229615	ATTACH ANGLE    			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360*       	41514	EA  					STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	11966	1190 				10121				DURING INSPECTION, ANGLE PN 5102296-15 AND PN 5102296-16, WERE FOUND CRACKED IN THE BEND RADIUS OF THE UPPER END OF THE 	ANGLE AS INSTALLED.  CAUSE OF CRACKING IS BELIEVED TO BE DUE TO HIGH STRESS LOADS IN THIS AREA.  (K)					1	L	7	1 	3O	3	O	NT	1L71    	E286				 
2007012500063	20070125	00063	GL  	2007	1	25	2007FA0000057    	1	20070105	G	5210		ATTACH FITTING  			DIAMON	DA40  	DA40        	2990002	GL  										AFT CABIN DOOR	BENT            	D			GO3S	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			NM	07	422FP	212  				40FC022				AFT CABIN DOOR ASSY SEPARATED FROM AC DURING FLIGHT.  CONTROL OF THE AC WAS MAINTAINED AND LANDED SAFELY AT DEPARTURE AI	RPORT.  DOOR WAS EVENTUALLY RECOVERED AND UPON VISUAL INSPECTION OF THE DOOR, THE AFT DOOR LATCH PIN WAS NOT ENGAGED.  T	HE FRONT DOOR LATCH PIN WAS PROPERLY ENGAGED AND THE DOOR LATCH WAS CLOSED.  NO (DOOR OPEN) ANNUNCIATION WAS INDICATED B	ECAUSE THE DOOR OPEN SWITCH IS ACTUATED FROM THE FRONT DOOR LATCH PIN.  UPON DISASSEMBLY OF THE DOOR, THE AFT DOOR LATCH	 ROD WAS DETACHED FROM THE LATCH MECHANISM.  THE ATTACHMENT CLIP, (PN AND NAME NOT GIVEN; NR 215 IN THE PARTS BOOK) WAS 	BENT ALLOWING THE ROD TO BECOME SEPARATED FROM THE LATCH.  A MUCH STRONGER MATERIAL IS RECOMMENDED FOR THE ATTACHMENT CL	1	L	7	1 	3O			NT	A47CE   					 
2007012500307	20070125	00307	EA  	2007	1	25	2007FA0000058    	2	20070105	G	8540	61098	GEARSHAFT       			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	SEIZED          	D			GO3S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	423FP	234  				40FC023	L4037236A			REMOVED VACUUM DRIVE ASSEMBLY AND FOUND DRIVE GEAR SHAFT SEIZED AND (3) TEETH BROKEN OFF OF DRIVE GEAR.  FURTHER INSPECT	ION REVEALED NO LUBRICATION PORT FOR PRESSURIZED ENGINE OIL TO LUBRICATE THE DRIVE GEAR SHAFT.  ALL (3) TEETH WER FOUND 	IN THE OIL PUMP INLET SCREEN.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2007012500138	20070125	00138	SO  	2007	1	25	2007FA0000059    	1	20070110	G	5521	510229615	ATTACH ANGLE    			AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360*       	41514	EA  					STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4521A	2194 				AA5B1070				DURING INSPECTION, ANGLE PN 5102296-15 AND PN 5102296-16, WERE FOUND CRACKED IN THE BEND RADIUS OF THE UPPER END OF THE 	ANGLE AS INSTALLED.  CAUSE OF CRACKING IS BELIEVED TO BE DUE TO HIGH STRESS LOADS IN THIS AREA.  (K)					1	L	7	1 	3O	3	O		A16EA   	E286				 
2007012500149	20070125	00149	CE  	2007	1	25	2007FA0000063    	1	20070110	G	5730	05230294	SKIN            			CESSNA	172   	172N        	2072434	CE  										RT WING	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	A5OR									DURING AN RECEIVING INSPECTION OF NEW RT OB LEADING EDGE SKIN, IT WAS FOUND TO HAVE BEEN DRILLED UP INCORRECTLY SINCE NO	NE OF THE NOSE RIBS WOULD LINE UP AND THE SET UP WOULD HAVE LT INSUFFICIENT EDGE DISTANCE ON THE LOWER MAIN WING SPAR RI	VET LINE.  THIS IS ZND TIME WE HAVE RECEIVED THIS SAME PART.  WE ASKED THAT THE PART NOT BE PUT BACK INTO MFG STOCK SINC	E PART IS NON-CONFORMING.  THE PART CAME WITH 8130-3 AIRWORTHINESS APPROVAL TAG.  RECOMMEND MFG PERFORM CLOSE CONFORMITY	 INSPECTION OF PARTS.  (K)		1	H	7	1 	3O			NT	3A12    					 
2007012500292	20070125	00292	SO  	2007	1	25	2007FA0000064    	1	20070109	G	3213	6531904	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG	DAMAGED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	15715	3501 				287325144				DURING AN ANNUAL INSPECTION FO THE LT MLG CYLINDER ASSY PN 6531904, IT WAS FOUND TO BE LOOSE IN THE MAIN WING SPAR.  THE	 LT MLG WAS REMOVED FOR FURTHER INSPECTION OF THE LT MAIN WING SPAR ASSY GEAR ATTACHING BOLT HOSES AND ATTACH POINTS.  C	LOSE INSPECTION FO THE WING SPAR SHOWED THAT THE LOWER (4) BOLTS HOLES HAD BEEN ELONGATED.  THE HOLES IN THE LT LANDING 	GEAR CYLINDER WERE FOUND TO BE ELONGATED ALSO.  IT APPEARED THAT ALL BOLTS WERE TIGHT AND THIS CONDITION HAD BEEN LOOSE 	FOR SOME TIME.  AIRCRAFT WING SPAR WS REPAIRED AND THE LT MLG CYINDER WAS REPLACE WITH A LATER MODEL CYLINDER ASSY FROM 	MFG SINCE THE ORIGINAL PART WAS NO LONGER AVAILABLE.  RECOMMEND CLOSE INSPECTION OF LANDING GEAR ATTACH POINTS DURING AL	1	L	7	1 	3O	3	O		2A13    	E274				 
2007013000176	20070130	00176	EU  	2007	1	30	2007FA0000065    	1	20070103	G	2742		ACTUATOR        			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1A    	41514	EA  					PITCH TRIM	SEIZED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	03	3832Q					274				(REF NR: PT202781) AIRCRAFT ARRIVED WITH PITCH TRIM ACTUATOR SEIZED IN FULL NOSE UP POSITION.  ACTUATOR IS DRIVEN BY TRI	M CABLE LOOPED OVER ACTUATOR PULLEY WITH NO MEANS OF PREVENTING CABLE FROM SLIPPING ON THE PULLEY.  IT IS POSSIBLE TO RU	N TRIM TO FULL TRAVEL ALLOWING ACTUATOR TO BIND.  WHEN TRIM CONTROL IS REVERSED THE CABLE CAN SLIP OVER PULLEY WITH OUT 	MOVING ACTUATOR IF PROPER CABLE TENSION IS NO PRESENT.  SUGGEST REVISION TO POH/AFM ADVISING CREW TO VISUALLY CHECK OPER	ATION OF PITCH TRIM SYSTEM PRIOR TO FLIGHT.  (K)		1	H	7	2 	3O	3	O		A31EU   	1E10				 
2007013100033	20070131	00033	CE  	2007	1	31	2007FA0000070    	1	20070108	G	2520	5514551129	ATTACH FITTING  	CESSNA      		CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					CABIN	CRACKED         	B			ESER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	117TW					5000059				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  CHAIR WAS REPAIRED IAW STC ST01042WI STRUCTURAL SEAT REP	AIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007020100001	20070201	00001	NE  	2007	2	1	2007FA0000071    	1	20070110	G	6220	7610208051105	TIE BOLT        			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6*        	52043	EA  					MAIN ROTOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	411JW	3392 				760357				WHILE PERFORMING A ROUTINE INSPECTION OF THE MAIN ROTOR SPINDLES, A SPINDLE TIE BOLT WAS FOUND BROKEN AT THE THREADED EN	D OF THE BOLT WHERE THE NUT ATTACHES.  THE NUT WAS FOUND INSIDE THE SPINDLE CUFF WHERE THE ROTOR BLADE IS ATTACHED.  A B	ROKEN SECTION OF THE BOLT WAS STILL THREADED INTO THE NUT.  IT IS UNCLEAR WHY THE BOLT BROKE.  THE BOLT AND SPINDLE HAVE	 BEEN REMOVED AND SENT TO MFG AIRCRAFT FOR FURTHER INVESTIGATION TO DETERMINE CAUSE OF FAILURE.  (K)			1	G	7	2 	4U	3	T		H1NE    	E2NE				 
2007012900120	20070129	00120	EU  	2007	1	29	2007FA0000072    	1	20070102	G	2435		BEARING         			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					STATER GEN	FAILED          	C				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	09	180NE		710  		95274	NA0401	P91312			FORWARD BEARING FAILED.						2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007012900357	20070129	00357		2007	1	29	2007FA0000073    	1	20070126	G	8011	ES6462751	STARTER         																	ENGINE	LEAKING         	C			WS9R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	07		2    								SUBMITTED TO SLC-FSDO BY (WS9R).  STARTER LEAKING OUT OF REAR OF STARTER PLATE.																			 
2007013100066	20070131	00066	SO  	2007	1	31	2007FA0000074    	1	20070123	G	5312	624403	BULKHEAD        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	7095W	4309 				28882	L148936C	15028K		THE BULKHEAD, BRACKETS, AND DOUBLERS AT STA. 228.3 WERE SEVERELY CORRODED. THIS BULKHEAD IS THE FRONT SUPPORT FOR THE VE	RTICAL STABILIZER/RUDDER ASSEMBLY. THE CORROSION COVERED AN AREA APPROXIMATE THE SIZE OF THE FRONT RUDDER ATTACHMENT BRA	CKET THAT IS PART OF THIS BULKHEAD ASSEMBLY. THE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION AND WAS ONLY VISIBLE, W	ITHOUT DISASSEMBLY, AS SLIGHT BUBBLING OF THE METAL ON THE BRACKETS FACING REARWARD THAT ARE ATTACHED TO THE AFORE MENTI	ONED BULKHEAD ASSEMBLY.		1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2007013100067	20070131	00067	SO  	2007	1	31	2007FA0000075    	1	20070123	G	5312	624403	BULKHEAD        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	7095W	4309 				28882	L148936C	15028K		THE BULKHEAD, BRACKETS, AND DOUBLERS AT STA. 228.3 WERE SEVERELY CORRODED. THIS BULKHEAD IS THE FRONT SUPPORT FOR THE VE	RTICAL STABILIZER/RUDDER ASSEMBLY. THE CORROSION COVERED AN AREA APPROXIMATE THE SIZE OF THE FRONT RUDDER ATTACHMENT BRA	CKET THAT IS PART OF THIS BULKHEAD ASSEMBLY. THE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION AND WAS ONLY VISIBLE, W	ITHOUT DISASSEMBLY, AS SLIGHT BUBBLING OF THE METAL ON THE BRACKETS FACING REARWARD THAT ARE ATTACHED TO THE AFORE MENTI	ONED BULKHEAD ASSEMBLY.		1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2007013100073	20070131	00073	SO  	2007	1	31	2007FA0000076    	1	20070117	G	2434	635796	COUPLING        	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ALTERNATOR	FAILED          	C				B				EMER. DESCENT           				H	G		ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          		CR	CRUISE         	1			GL	09	321AK	4479 	869  		B020128	3447021	811403R	960254		ALTERNATOR DRIVE COUPLING FAILED ON LT AND RT ALTERNATORS, IN IMC SIMULTANEOUSLY.  1 PIECE COUPLING WITH A RUBBER LORD B	USHING BONDED/INTERFERENCE FIT SLIPPED, CAUSING THE ALTERNATORS FAILURES.  PILOTS LOST ELECTRICAL AND DESCENDED THROUGH 	ICE, UNABLE TO SHED MODERATE TIME ICE ACCUMULATION. TOTAL COMM AND AVIONICS FAILURE, PARTIAL PANEL WITH NO PITOT HEAT AV	AILABLE.			1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2007013100075	20070131	00075	SO  	2007	1	31	2007FA0000077    	1	20070117	G	2434	635796	COUPLING        	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ALTERNTOR	FAILED          	C				B				EMER. DESCENT           				H	G		ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          		CR	CRUISE         	1			GL	09	321AK	4479 	869  		B020128	3447021	811403R	960254		ALTERNATOR DRIVE COUPLING FAILED ON LT AND RT ALTERNATORS, IN IMC SIMULTANEOUSLY.  1 PIECE COUPLING WITH A RUBBER LORD B	USHING BONDED/INTERFERENCE FIT SLIPPED, CAUSING THE ALTERNATORS FAILURES.  PILOTS LOST ELECTRICAL AND DESCENDED THROUGH 	ICE, UNABLE TO SHED MODERATE  RIME ICE ACCUMULATION. TOTAL COMM AND AVIONICS FAILURE, PARTIAL PANEL WITH NO PITOT HEAT A	VAILABLE.			1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2007013000179	20070130	00179	CE  	2007	1	30	2007FA0000081    	1	20070119	G	3245	850X1000	TUBE            			CESSNA	208   	208B        	2073701	CE  										TIRE	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	1293E	4    				208B0537				RIGHT MAIN GEAR TIRE REPORTED LOW.  REMOVED TIRE TO CHECK THE TUBE.  THE TUBE APPEARED TO LOOK OLD AND CHECKED.  TECHNIC	IAN REPLACED WITH NEW TUBE.  ONE WEEK LATER TIRE REPORTED LOW AGAIN ON SAME POSITION.  REMOVED THE TIRE AND INSPECTED TH	E TUBE.  THE TUBE LEAKING ON ONE SIDE AND ALMOST WORN THRU ON THE OPPOSITE SIDE.  AFTER FURTHER INVESTIGATION DETERMINED	 THAT THE STICKERS INSIDE THIS 8.50 X 10.00 FC III P/N 850T86-2 S/N 62570185 TIRE HAD CAUSED THE FAILURE.  THIS WAS THE 	SECOND FAILURE ON THE SAME GEAR POSITION WITH THE SECOND NEW TUBE WITHIN 7 WEEKS.  AFTER CONTACTING MANUFACTURER TIRE PR	ODUCT SUPPORT, SENT A NOTE AND PICTURES ABOUT THE PROBLEM AND THE FAA PMI FROM THE FARGO FSDO.  THE MANUFACTURER RESPOND	1	H	7	1 	3T				A37CE   					 
2007013100100	20070131	00100		2007	1	31	2007FA0000082    	2	20070119	G	7414	K3823	DISTRIBUTOR BLK 	SLICK       	6314        															MAGNETO	MELTED          	B				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			GL	21	408ND	493  			05100422					DURING TEARDOWN INSPECTION OF 2 SLICK 6314 MAGNETOS THE DISTRIBUTOR BLOCK AND GEAR ASSY PN K3823 WAS FOUND TO BE MELTED 	TO THE POINT OF EMANATE FAILURE. THE MAGS WERE FROM 2 SEPARATE AIRCRAFT BUT WITH NEAR IDENTICAL TOTAL TIMES ONE AT 493.3	 HRS AND THE OTHER AT 498.8.THE MANUFACTURE WAS CONTACTED AND THEY REQUESTED THE MAGS FOR EVALUATION.																	 
2007013100103	20070131	00103	CE  	2007	1	31	2007FA0000083    	1	20070123	G	7160	07520161011	SEAL            			CESSNA	180   	180J        	2072622	CE  										INTAKE	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	9986N					18052641				INTAKE SEALS FOUND MISSING. AD 77-04-05 PERTAINING TO THIS DEFECT HAD BEEN PREVIOUSLY ACCOMPLISHED IN 1977. DUE TO THE A	GE OF THE FLEET I BELIEVE THAT THE ONE TIME INSPECTION IAW THIS AD IS INSUFFICIENT. AS THIS IS NOT THE FIRST TIME I HAVE	 FOUND THE SAME CONDITION ON OTHER AIRCRAFT I WOULD CONSIDER UPDATING THE AD TO INCLUDE REPETITIVE INSPECTIONS AT ANNUAL	/100 HOUR INTERVALS.			1	H	7	1 	3O				5A6     					 
2007013100104	20070131	00104	CE  	2007	1	31	2007FA0000084    	1	20070119	G	3245	850X1000	TUBE            			CESSNA	208   	208B        	2073701	CE  										LANDING GEAR	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	1293E	4    				208B0537				RT MAIN GEAR TIRE REPORTED LOW. REMOVED TIRE TO CHECK THE TUBE. THE TUBE APPEARED TO LOOK OLD AND CHECKED. TECHNICIAN RE	PLACED WITH NEW TUBE. 1 WEEK LATER TIRE REPORTED LOW AGAIN ON SAME POSITION. WE REMOVED THE TIRE AND INSPECTED THE TUBE.	 THE TUBE LEAKING ON ONE SIDE AND ALMOST WORN THRU ON THE OPPOSITE SIDE.  AFTER FURTHER INVESTIGATION WE DETERMINED THAT	 THE STICKERS INSIDE THIS 8.50 X 10.00 FC III P/N 850T86-2 S/N 62570185 TIRE HAD CAUSED THE FAILURE. THIS WAS THE SECOND	 FAILURE ON THE SAME GEAR POSITION WITH THE SECOND NEW TUBE WITHIN 7 WEEKS.  AFTER CONTACTING MFG WHO GAVE ME AN E-MAIL 	FOR THEIR PRODUCT SUPPORT CONTACT WE GOT INFORMATION VERY QUICKLY. I SENT HIM A NOTE AND PICTURES ABOUT THE PROBLEM AND	1	H	7	1 	3T				A37CE   					 
2007013100106	20070131	00106	SO  	2007	1	31	2007FA0000085    	1	20070117	G	2434	635796	COUPLING        	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C509   	GL  	ALTERNATOR	FAILED          	C				B				EMER. DESCENT           				H	G		ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          		CR	CRUISE         	1			GL	09	321AK	4479 	869  			3447021	812128R	961321		ALTERNATOR DRIVE COUPLING FAILED ON LT AND RT ALTERNATOR, IN IMC SIMULTANEOUSLY. COUPLING FAILURE RESULTED IN TOTAL ELEC	TRICAL FAILURE, RT ENGINE.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2007013100107	20070131	00107	CE  	2007	1	31	2007FA0000086    	1	20070126	G	3260	1003810061	DOWNLOCK SWITCH 			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LANDING GEAR	FAILED          	E				A				UNSCHED LANDING         				N			FALSE WARNING             			LD	LANDING        	1			GL	07	200EW	7169 	70   			BB1163				NOSE LANDING GEAR DID NOT HAVE A DOWN AND LOCKED INDICATION GEAR WARNING SYSTEMS ACTIVATED (LIGHT IN SELECTOR HANDLE AND	 GEAR HORN). AN UNEVENTFUL LANDING HAS MADE VISUAL CHECK OF NOSE GEAR SHOWED TO BE IN THE DOWN AND LOCKED POSITION. SWIT	CH REMOVED AND REPLACED WITH A NEW UNIT AND THE SYSTEM CHECKED NORMAL.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007013100256	20070131	00256	CE  	2007	1	31	2007FA0000090    	1	20070102	G	2730	355246516	CONTROL CABLE   			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520*      	17032	SO  					ELEVATOR SYS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	767TM	2801 				D8556				FOUND BROKEN STRANDS ON ELEVATOR CABLE BEHIND INSTRUMENT PANEL ABOUT 10 INCHES ABOVE THE (PN 535521242-13) BOBWEIGHT.  (	K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007013100257	20070131	00257	EA  	2007	1	31	2007FA0000091    	2	20070118	G	7314	AC40295	PUMP            			AMRGEN	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320E2G     	41508	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	01	24AU		302  			AA50588				AT ANNUAL FUEL STAINS WERE FOUND ON ENGINE LOWER COWLING.  IN AN ATTEMPT TO FIND THE LEAK THE ELECTRIC FUEL PUMP WAS TUR	NED ON TO PRESSURIZE THE FUEL SYSTEM BUT NO LEAKAGE WAS FOUND.  WHILE TURNING ENGINE OVER BY HAND DURING THE COMPRESSION	 CHECK A LARGE FLOW OF GAS WAS FOUND LEAKING OUT THE SIDE OF THE FUEL PUMP ABOVE THE OUTLET PORT BETWEEN THE DIAPHRAGM A	ND PUMP CASTINGS.  REPAIR STATION WAS CONTACTED AND THY INDICATED THAT THE SCREWS THAT HOLD THE PUMP TOGETHER ARE ASSEMB	LED AT 25 INCH LBS TORQUE + OR - 5 INCH LBS .  PUMP SCREWS WERE CHECKED AND THEY WERE FOUND TO BE TIGHTENED TO ONLY 2-3 	INCH LBS OF TORQUE.  ALL OF THE SCREWS HAD TORQUE PUTTY ON THEM WHICH INDICATED THE SCREWS HAD NOT BACKED OUT.  GUESS IS	1	L	7	1 	3O	3	O		A16EA   	E274				 
2007021500169	20070215	00169	WP  	2007	2	15	2007FA0000092    	2	20070115	G	7250	31021069	TURBINE WHEEL   			GULSTM	690TP 	690B        	7630516	SW  	GARRTT	TPE331	TPE33110T   	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	DAMAGED         	B			IZ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	690LL	2245 				11544	P99112C	BVA7239		INSPECTION OF ENGINE REVEALED DAMAGE TO 3RD STAGE TURBINE ROTOR VISIBLE THROUGH ENGINE TAILPIPE.  ENGINE WAS REMOVED FRO	M AIRCRAFT AND THE TURBINE SECTION MODULE REMOVED TO INVESTIGATE FOR CAUSE OF DAMAGE.  UPON INSPECTION 4 EA PINS WERE FO	UND MISSING FROM 2ND STAGE TURBINE ROTOR ASSEMBLY CAUSING SIGNIFICANT DAMAGE TO VARIOUS TURBINE SECTION COMPONENTS, SEVE	RAL OTHER PINS WERE ALSO FOUND LOOSE AND DAMAGED.  SB ADDRESSES REMOVAL OF 2ND STAGE TURBINE ROTORS PN 310210610 UTILIZI	NG AN IMPROVED PIN DESIGN.  FURTHERMORE MFG HAS INDEPENDENT SERVICE CENTER SPECIAL PROGRAM IN PLACE TO COVER PIN REPLACE	MENT ON AFFECTED TURBINE ROTORS AT NO CHARGE, COVERING SECONDARY DAMAGE ON A PRORATED BASIS.  (K)	1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P15EA	 
2007021300165	20070213	00165	EA  	2007	2	13	2007FA0000095    	2	20070109	G	8520	AEL321031	CRANKSHAFT      			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	BROKEN          	B			VA1R	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			SW	19	15RA	410  				17259568	L2207127A			ENGINE BEGAN RUNNING ROUGH AND BECAME SMOOTH AGAIN DURING DESCENT.  TROUBLESHOOTING FIRST FOUND BRASS METAL PARTICLES IN	 AIR FILTER AND OIL.  CRANKSHAFT WAS APPARENTLY BROKEN OR CRACKED BUT STILL TOGETHER.  AFTER NUMEROUS GROUND RUSN AND KN	OCKING NOISES HEARD, THE CRANKSHAFT BROKEN AND ROD THROWN THROUGH CASE.  THE BREAK WAS BETWEEN NR 3 AND NR 4 ROD JOURNAL	S.  SENG BACK TO ENGINE COMPONENTS FOR WARRANTY AND ANALYSIS.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007021400083	20070214	00083	SO  	2007	2	14	2007FA0000096    	1	20070103	G	3230	455180	CONDUIT         			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					LT MLG PUSH PULL	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	63	6632P	3200 				241755				THE LT MAIN LANDING GEAR PUSH PULL CONDUIT SEPARATED AT THE BALL END WHERE IT IS ATTACHED TO THE SUPPORT STRUCTURE IN TH	E WHEEL WELL.  BELIEVE THIS FAILURE OCCURRED AT THE PREVIOUS LANDING GEAR RETRACTION.  (K)					1	L	7	1 	3O	3	O		1A15    	E295				 
2007021300176	20070213	00176		2007	2	13	2007FA0000101    	2	20070124	G	7414	6320	MAGNETO         																	ENGINE	FROZEN          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07										SHAFT IN MAGNETO FROZEN, WOULD NOT MOVE.  (K)																			 
2007021300189	20070213	00189	EA  	2007	2	13	2007FA0000102    	1	20070109	G	5755		BRACKET         			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343B1     	 	NE  					FLT SPOILER	CRACKED         	B			RO3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	684TS					5384				WHILE PERFORMING A 96 MONTH AIRFRAME INSPECTION, DISCOVERED THE LT FLIGHT SPOILER TRANSMITTER BRACKET WAS CRACKED.  UPON	 REMOVING BRACKET, DISCOVERED MATTING SURFACE WITH TRANSMITTER WAS CORRODED.  DECIDED TO REMOVE TO INSPECT RT TRANSMITTE	R BRACKET AND FOUND THE RT SIDE CORRODED AS WELL.  REMOVED AND REPLACED BOTH BRACKETS.  RT AND LT HAVE THE SAME PN.  (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007021300164	20070213	00164	EA  	2007	2	13	2007FA0000103    	1	20070109	G	5755	600913563	BRACKET         			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					RT FLT SPOILER	CRACKED         	B			RO3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	267DW					5391				RT FLIGHT SPOILER POSITION INDICATION WOULD NOT OPERATE PROPERLY.  UPON FURTHER INVESTIGATION, FOUND THE FLIGHT SPOILER 	TRANSMITTER BRACKET WAS CRACKED AND UNABLE TO HOLD POSITION TRANSMITTER.  REMOVED AND REPLACED BRACKET.  (K)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007020500043	20070205	00043	CE  	2007	2	5	2007FA0000104    	1	20070201	G	2710	S394	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  										AILERONS	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5275S	3179 	100  			172S9203				DURING A ROUTINE INSPECTION THE AILERON CONTROL DIRECT CABLE WAS FOUND SERIOUSLY WORN IN THE CABIN OVERHEAD AREA. THE AI	LERON BALANCE AND DIRECT CABLES ARE SEPARATED AND GUIDED BY 3 PULLIES, P/N-S394, INDEX NR 30, CHAPTER 27-10-00, FIG 3 IN	 THE CESSNA PARTS MANUAL. THE CENTER CABLE WAS WORN EXTENSIVELY AND HAD BROKEN STRANDS. THE WEAR IS CAUSED BY CONTACT WI	TH THE PULLEY. IT IS DIFFICULT TO SEE WITHOUT ROTATING THE CABLE AND EXPOSING THAT PORTION OF THE CABLE THAT CONTACTS TH	E PULLEY DURING LEVEL FLIGHT. THE CABLE AT FIRST APPEARS SHINY, BUT WITH THE AID OF A POWERFUL MAGNIFYING GLASS REVEALS 	MUCH MORE SERIOUS WEAR. OBVIOUSLY, THE FAILURE OF THIS CABLE WOULD LIKELY RESULT IN THE LOSS OF THE AIRCRAFT WITH LITTLE	1	H	7	1 	3O			NT	3A12    					 
2007020500030	20070205	00030	CE  	2007	2	5	2007FA0000105    	1	20070202	G	5711	51220311	SPAR CAP        			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520BB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	465DL	1132 				310R1622				LT TOP WING SPAR CAPS AND TOP SKINS SEVERELY CORRODED IN AREA OF FACTORY NACELLE FUEL BLADDERS.  LT-PN 5122031-1.						1	L	7	2 	3O	3	O		3A10    	E8CE	5	C	P22EA	 
2007021300174	20070213	00174	GL  	2007	2	13	2007FA0000106    	1	20070111	G	7603		FRICTION LOCK   			AMTR  	LANCAR	LANCAIR     	05616TS	GL  	WALTER	M601  	M601E       	 	EU  					POWER LEVER	INOPERATIVE     	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	750TL	154  				LIV555	913008			AIRCRAFT EXPERIENCED LOSS OF POWER DURING TAKEOFF AND LANDED WITH LANDING GEAR RETRACTED DEPARTING RUNWAY FROM WHICH TAK	EOFF WAS MADE.  INVESTIGATION REVEALED FRICTION LOCK WAS NOT EFFECTIVE.  (K)					1	L	7	1 	3O	3	T	RT	EXPA1L71	EXPE3T				 
2007021300063	20070213	00063	EU  	2007	2	13	2007FA0000107    	1	20070125	G	5210	333045181	SEAL            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN DOOR	LEAKING         	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	09	300XL	9015 				276				THE AIRCRAFT DEPARTED, CLIMBING THROUGH 30000.  THE CABIN ALT BEGAN TO CLIMB WITH THE AIRCRAFT.  THE PILOTS REQUESTED TO	 DESCEND.  CENTER DECLARED EMERGENCY AND GAVE CREW 12000 FT.  AIRCRAFT PRESSURIZED PROPERLY AT THAT ALT.  PILOT REQUESTE	D DEVIATION AND TO HAVE EMERGENCY CANCELED.  THIS WAS GRANTED BY CENTER.  AFTER LANDING, CREW LOOKED OVER THE AC AND COU	LD NOT FIND ANYTHING WRONG, PROCEEDED, AT 19000 FT.  AIRCRAFT PRESSURIZED PROPERLY.  IN MAINTENANCE CREW INSPECTED THE A	IRCRAFT AND PERFORMED NUMEROUS GROUND PRESSURIZATION RUNS AN COULD NOT DUPLICATE PROBLEM.  PILOT MADE STATEMENT THAT THE	 DOOR MAY NOT OF SEALED PROPERLY.  MAINTENANCE LOOKED AT THAT ASPECT AND FOUND THAT THE DOOR CAN BE CLOSED IN A MANOR TH	2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007021300060	20070213	00060	NE  	2007	2	13	2007FA0000108    	2	20070101	G	7200	CFM563B1	POWERPLANT      			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					OIL SYSTEM	CONTAMINATED    	B			UOXR	A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	NR	NOT REPORTED   	1			SO	19	XAMAA	44927	3514 				720721			ENGINE SUFFERED AN IFSD DUE TO POWER LOSS AND A COMMANDED ENGINE SHUTDOWN WAS CARRIED OUT.  ENGINE RESTART WAS ATTEMPTED	, UNSUCCESSFULLY.  FURTHER INVESTIGATION REVEALED THAT NR 10 STRUT ON FAN FRAME (9 O`CLOCK STRUT AFT LOOKING FWD) WHICH 	RADIAL DRIVE SHAFT IS LOCATED WAS PUNCTURED, BOTH ON UPPER AND LOWER SURFACES OF STRUT.  IT WAS AGREED TO CARRY OUT ENGI	NE REMOVAL AND RETURN ENGINE TO REPAIR FACILITY.  HYDRAULIC FLUID WAS FOUND IN OIL SYSTEM, AIR STARTER AND CSD OIL SUMPS	.  ALL OIL WETTED ITEMS REQUIRE INSP.  ENGINE HAD UNDERGONE TROUBLESHOOTING FOR HIGH OIL CONSUMPTION FOLLOWING REPORTS O	N 2 FLIGHTS AND RETURN ON DEC 22, 2006.  LEVELS OF 2.08 GALLON QUARTERS/HOUR WERE REPORTED AND AVERAGE OIL CON WAS 0.15 	2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007021300055	20070213	00055	CE  	2007	2	13	2007FA0000109    	1	20070131	G	2730	50524401	BELLCRANK       			BEECH 	90    	65A901      	1152901	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELEVATOR	FAILED          	C			NBFG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	87V					LM130				FOUND BROKEN FORK ON ELEVATOR BELLCRANK SUPPORT ARM AT FWD END OF ELEVATOR LT PUSHROD.  FOUND THE PUSH ROD FWD ATTACH BO	LT HAD BEEN OVER-TORQUED SO MUCH AS TO CREATE A 0.016 INCH -0.021 INCH DEPRESSION IN EACH (MAGNESIUM) FORK WHERE THEY PR	ESSED INTO THE ROD END BEARING.  MFG SB2231R2 INCLUDES: INSPECTION FOR CRACKS IN THIS AREA OF ELEVATOR BELLCRANK.  PROPE	R GAP BETWEEN ROD END AND SUPPORT ARM FORKS (0.00 INCH TO 0.01 INCH GAP) PROPER TORQUE OF PUSHROD ATTACH BOLT (70-108 IN	CH LBS)  RECOMMEND FOLLOWING PROPER INSPECTION, INSTALLATION AND TORQUE WHEN INSTALLING THE BELLCRANK AND PUSHRODS.  FOL	LOW THE INSTRUCTIONS IN THE MM AND SB2231R2.  (K)	1	L	7	2 	3T	3	T		3A20    	E2NE				 
2007020900036	20070209	00036	CE  	2007	2	9	2007FA0000112    	1	20070108	G	7160	1116	AIR FILTER      			CESSNA	172   	R172K       	2072431	CE  	CONT  	IO360 	IO360*      	17025	CE  						TWISTED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	758EJ					R1723034				DURING REMOVAL OF THE AIR FILTER THE CENTER WIRE MESH SCREEN WAS FOUND TWISTED AND BENT.  SOME OF THE WELDS WERE BROKEN.	  SCREEN DEFORMATION CAN LEAD TO UNFILTERED AIR AND FOD ENTERING THE ENGINE.  APPARENT CAUSE IS EITHER OVERTORQUEING WIN	G NUT AND/OR INSUFFICIENT STRENGTH OF SCREEN.  RECOMMEND UTILIZING A STRONGER MESH/PERFORATED SCREEN OR EVALUATING INSTA	LLATION INSTRUCTIONS/TORQUEING PROCEDURES.			1	H	7	1 	3O	3	O		3A17    	E1CE				 
2007021200156	20070212	00156	GL  	2007	2	12	2007FA0000113    	1	20070205	G	6500	E181150P	V-BELT          			AMTR  	ROTWAY	EXEC162F    	056037T	GL  										TAIL ROTOR	BROKEN          	G				R				AUTOROTATION            				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CE	07	113JD	80   				6107				V BELT PREMATURELY FAILED. THIS IS A 250 HOUR CHANGE OUT PART.						1	G	7	1 	3O			O	EXPA1G71					 
2007031200062	20070312	00062	SO  	2007	3	12	2007FA0000114    	1	20070206	G	2820	W70120TE	CONNECTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										FUEL LINE	LOOSE           	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	83M					557				FUEL LINE CONNECTOR IN MAIN WHEEL WELL COMING LOOSE, RESULTING IN FUEL LEAKING INTO WHEEL WELL.REFERENCE MFG ILLUSTRATED	 PARTS CATALOG; 28-26-00, FIGURE 5, PAGE 2, ITEM 205, PN W701-20TE.  WE ARE HAVING THIS PROBLEM ON MORE THAN ONE OF OUR 	AIRCRAFT.  THERE IS NO WAY TO SAFETY THIS FITTING.  THIS SITUATION COULD RESULT IN FUEL BEING SPRAYED ON A HOT BRAKE RES	ULTING IN A FIRE.			2	L	7	2 	4F			RT	A12EA   					 
2007022000010	20070220	00010	CE  	2007	2	20	2007FA0000115    	1	20070111	G	7120		MOUNT           			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  	MCAULY	3A32C	D3A32C*     	GL  	ENGINE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	1562F					E2857	687034	940159		PERFORMED ANNUAL INSPECTION ON ENGINE, FOUND BLACK (FRETTING) CORROSION BELOW CENTER 2 (LT AFT) ENGINE MOUNT BOLTS.  BOL	TS WERE LOOSE IN MOUNT, BUT THE NUTS WERE TIGHT ON BOLTS.  PROBLEM IS THAT THE BOLTS ARE A LITTLE TOO LONG AND THE NUTS 	WERE RUNNING OUT OF THREADS ON THE BOLTS.  SOLUTION WAS TO ADD ANOTHER WASHER BELOW THE NUTS, THEN RETORQUE BACK TO SPEC	S.  (K)			1	L	7	1 	3O	3	O		3A15    	E3SO	5	C	P21EA	 
2007051100144	20070511	00144		2007	5	11	2007FA0000119    	1	20070208	G	2435	23085001	STARTER GEN     																		OUT OF TOLERANCE	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	603W	36   	36   							S/G SUSPECTED TO HAVE IMPROPER DRIVE SHAFT INSTALLED. DRIVE SHAFT MEASURES LONGER THAN ANOTHER S/G WITH SAME PN. ENGINE 	HAVE THEIR STARTER MOUNT BEARING FAIL.																		 
2007021300067	20070213	00067	CE  	2007	2	13	2007FA0000120    	1	20070129	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					TAXI LIGHT	ODOR            	B			ODAR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			EA	21	321ME					172S8566				PILOT REPORTED TO APPROACH THAT THERE WAS AN ELECTRICAL SMELL IN CABIN.  AN EMERGENCY WAS DECLARED AND AIRCRAFT LANDED W	ITHOUT INCIDENT.  UPON INSPECTION, FOUND THE TAXI LIGHT CIRCUIT BREAKER/SWITCH WAS SLIGHTLY DISCOLORED, SMELLED BURNED A	ND IT WAS INOPERATIVE.  THERE WAS NO APPARENT OTHER DAMAGE TO CIRCUIT OR ANY OTHER PART.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007022000016	20070220	00016		2007	2	20	2007FA0000121    	4	20070130	G	3418	C528072	TRANSDUCER      			PIPER 	PA46  	PA46500TP   	7104622	SO  										STALL WARNING	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	5337N	320  				4697102				THIS UNIT WAS INSTALLED 12 MONTHS AGO.  THIS IS A TYPICAL LIFE SPAN.  CAUSE OF MALFUNCTION IS UNIT BEING OVERHEATED IN F	LIGHT.  THEY CAN`T TURN DOWN THE HEAT BECAUSE OF THE WAY IT WAS CERTIFIED.  MOST PILOTS DO NOT KNOW THIS UNIT IS INOPERA	TIVE.  THE STALL WARNING HORN WILL SOUND EVEN THOUGH THE UNIT IS BAD.  (K)				1	L	7	1 	3O			RT	A25SO   					 
2007021300057	20070213	00057	EA  	2007	2	13	2007FA0000122    	2	20070105	G	8530		NUT             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					ARM RETAINER	LOOSE           	B			ONFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	5123E	1788 				17271722	RL8312761			THE NR 3 CYLINDER EXHAUST ROCKER ARM RETAINING NUT BECAME LOOSE, REDUCING LIFT ON THE EXHAUST VALVE, NOT ALLOWING SUFFIC	IENT AIR TO EXIT THE CYLINDER.  PRESSURE IN THE CYLINDER EXCEDED THE STRENGTH OF THE INTAKE VALVE SYSTEM TO OPEN, CAUSIN	G THE INTAKE PUSHROD TO FALL (BEND).  RECOMMEND A SIMPLE LOCKPLATE BE ADDED UNDER THE ROCKER ARM RETAINING NUT WITH A LO	CK TAB TO ELIMINATE THIS POSSIBLE FAILURE.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007030900126	20070309	00126	CE  	2007	3	9	2007FA0000141    	1	20070205	G	2820	0500106326	FUEL LINE       			CESSNA	180   	180         	2072602	CE  										FUEL SYS	WORN            	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AL	05		4000 								FLAP CABLE WEARING INTO FUEL LINE.  FUEL LINE WAS INCORRECTLY ASSEMBLED.  VISUAL INSPECTION OF AREA AT ANNUAL OR 100 HR 	INSPECTIONS.  (K)					1	H	7	1 	3O			NC	5A6     					 
2007022600185	20070226	00185	SO  	2007	2	26	2007FA0000144    	1	20070205	G	3230	6741102	SWITCH          			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					MLG	FROZEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	1533E					347350050				UPON LANDING, GEAR EXTENSION, DURING APPROACH TO LANDING,  PILOT NOTED AN EXCEPTIONALLY LONG TIME BETWEEN GEAR SWITCH AC	TUATION AND INDICATION OF ALL DOWN AND LOCKED.  OUTSIDE TEMP +9 F.  BELIEVE THAT SWITCH ARM FOR DOWNLOCK HAD FROZEN IN P	LACE (UP) AND REQUIRED TIME TO ACTUATE.  (K)				1	L	7	2 	3O	3	O		A7SO    	1E10				 
2007022600076	20070226	00076	CE  	2007	2	26	2007FA0000145    	1	20070215	G	7810	02R3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		6162 	731  				PCE85441			WHILE PERFORMING SCHEDULED MAINTENANCE, REMOVED LT ENGINE EXHAUST STACKS TO FACILITATE INSPECTING THE EXHAUST DUCT.  FOU	ND A 14 INCH CRACK FOLLOWING THE CIRCUMFERENCE OF THE SKI SLOPE WITH A 3 INCHES CRACK PROPAGATING LONGITUDELY AT THE 10 	O'CLOCK POSITION FROM THE 14 INCHES CRACK. EXHAUST DUCT HAD PWA SB 3380 COMPLIED WITH 731 HOURS EARLIER. BECAUSE OF THE 	REMAINING ENGINE TIME, IT WILL BE PULLED FOR OVERHAUL.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007022300288	20070223	00288	CE  	2007	2	23	2007FA0000147    	1	20070201	G	2571		HOSE            			BEECH 	95    	B95         	1153404	CE  										BATTERY BOX	DISCONNECTED    	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	9631R					TD314				BATTERY ELECTROLYTE RESIDUE FOUND ON LEFT NOSE GEAR DOOR AND LOWER FORWARD FUSELAGE.  INSPECTION REVEALED BATTERY BOX DR	AIN HOSE DISCONNECTED AND HANGING IN LOWER NOSE STRUCTURE AREA BELOW THE BAGGAGE FLOOR.  ACCESS IS HINDERED BY NUMEROUS 	FASTENERS THAT ARE HARD TO REMOVE.  AT SOME TIME IN THE PAST THE ADF ANTENNA MAST, WHICH DOUBLED AS THE BATTERY DRAIN MA	ST, HAD BEEN REMOVED AND THE BATTERY DRAIN HOSE WAS NOT RECONNECTED TO A SUITABLE DRAIN.  THIS COULD CAUSE CORROSION DAM	AGE TO NOSE AREA LOWER STRUCTURE ON TRAVEL AIR AND BARON AIRPLANES, WHICH HAVE SIMILAR DESIGN.  BEECH MODEL 95 PARTS AND	 SHOP MANUALS CARRY NO REFERENCES ABOUT THE BATTERY DRAIN SYSTEM.  SUGGEST REVIEW OF ANY RAYTHEON SERVICE BULLETINS DISC	1	L	7	2 	3O				3A16    					 
2007030100236	20070301	00236	SO  	2007	3	1	2007FA0000148    	1	20070214	G	3234	761213	LEVER           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	BROKEN          	D			F7HS	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			WP	13	31PD	7657 				277654016				LANDING GEAR LEVER BROKE AT THE RIVET DURING TAKEOFF, AFTER RAISING LANDING GEAR LEVER UP TO RETRACT LANDING GEAR.  (K)						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2007030100201	20070301	00201		2007	3	1	2007FA0000149    	2	20070209	G	7414	6310	MAGNETO         																	ENGINE	MALFUNCTIONED   	B			WS9R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	07										MAGNETO IS MISSING AT HIGH ALTITUDE.  (K)																			 
2007030100202	20070301	00202		2007	3	1	2007FA0000150    	2	20070209	G	7414	6310	MAGNETO         																	ENGINE	MALFUNCTIONED   	B			WS9R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	07		2    								MAGNETO`S MISSING AT HIGH ALTITUDE.  (K)																			 
2007030900152	20070309	00152	SW  	2007	3	9	2007FA0000151    	1	20070214	G	5712		FASTENER        			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					WING	OUT OF POSITION 	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	5505N					126678				RIB NAILS PULLING OUT IN ALMOST EVERY RIB.  RT TIP RIB HAS ALL NAILS PULLED OUT AND A  SPACE BETWEEN RIBS AND SPARS, BOT	H FRONT AND REAR LOCATIONS.  LT WING HAS ONE NAIL THAT IS ABOUT TO FALL OUT AS IT IS PULLED/WORKED OUT .4375 INCH.  80 P	ERCENT OF RIBS HAVE AT LEAST ONE NAIL OUT OVER .1250 INCH, AND ONLY APPROX 10 PERCENT OF TOTAL NAILS ARE NOT MOVING.  HA	VE NOT DISASSEMBLE YET FOR SPAR DAMAGE, BUT HAVE SEEN A FEW NAILS THAT ARE (SMOKING) WHERE THEY CONTACT THE ALUMINUM RIB	.  ALL FOUND DURING ROUTINE INSPECTION AT ANNUAL IAW AD AND APPLICABLE SB`S IAW THE AD.  (K)		1	H	7	1 	3O	3	O		A759    	E223				 
2007030900114	20070309	00114	SO  	2007	3	9	2007FA0000155    	2	20070212	G	8530		CYLINDER        			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	4988F					U2060688				CRACKED CYLINDER HEAD BETWEEN 4TH AND 5TH FIN IB OF TOP SPARK PLUG.  CRACKS HEADED TOWARD VALVE SEAT.  (K)						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007032900296	20070329	00296	SO  	2007	3	29	2007FA0000156    	2	20070212	G	8530		CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7711D					U20603170				CRACKED CYLINDER LEAD BETWEEN 4TH AND 5TH FIN IB AT UPPER SPARK PLUG.  CRACK NOT VISIBLE INSIDE CYLINDER.  (K)						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007030900046	20070309	00046	SO  	2007	3	9	2007FA0000157    	2	20070212	G	8530	AEC63139	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7711D	10226				U20603170				CRACKED CYLINDER BETWEEN 2ND AND 3RD FIN IB OF UPPER SPARK PLUG ORIENTED DOWN SIDE OF CYL HEAD.  LARGE NEAR SEPARATION. 	 (K)					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007030900127	20070309	00127	SO  	2007	3	9	2007FA0000158    	2	20070212	G	8530	AEC631397	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7711D					U20603170				CYLINDER HEAD CRACKED AT UPPER SPARK PLUG HOLE THRU BEND TO EXHAUST SEAT.  (K)						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007030900303	20070309	00303	CE  	2007	3	9	2007FA0000162    	1	20070206	G	5511	233201015	SPAR CAP        	LEAR        		LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZ STAB	CORRODED        	C			BHKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	96FN	17284			1187	186				VISUAL CONDITION CHECK PERFORMED ON HORIZONTAL STABILIZER AFT SPAR CAP AND ELEVATOR HINGE BRACKETS FOR CORROSION, BROKEN	 FASTENERS, ETC.  FOUND SEVERE CORROSION ON UPPER SPAR CAP ASSEMBLY ALONG ENTIRE LENGTH.  THIS REQUIRED REMOVAL AND REPL	ACEMENT OF UPPER SPAR CAP.  CORROSION CAUSED BY OPERATING CONDITIONS, LACK OF CONSISTENT WASHING PROGRAM AND POSSIBLE EX	POSED, UNPROTECTED METAL.  RECOMMENDA CONSISTENT AIRCRAFT WASHING PROGRAM WHEN OPERATIONS ARE IN OR NEAR COSTAL REGIONS 	AND ENSURING ALL EXPOSED SURFACES ARE PROPERLY TREATED AND PAINTED.  (K)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007030900161	20070309	00161	SO  	2007	3	9	2007FA0000163    	1	20070201	G	8120		FITTING         			PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	TURBOCHARGER	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	05	8185Y		522  			328024018	L699564A	FM1408B		THIS PART IS BOLTED TO THE TURBOCHARGER ASSY BETWEEN THE HOT AND COLD SECTIONS.  THE HIGH PRESSURE OIL LINE CONNECTS TO 	THIS PART VIA A FITTING IN THE TOP OF THE PART.  AFTER AN ANNUAL INSP, THE ENG WAS RUN-UP AND SYSTEM CHECKED.  AN OIL SE	EP WAS NOTED IN THE TURBOCHARGER AREA.  THE HIGH PRESSURE OIL LINE AND FITTING WAS REMOVED.  PN LW 14465 WAS REMOVED AND	 CLEANED.  THE CRACK WAS NOTED. THE PART WAS REPLACED WITH NEW.  AFTER RESEARCHING THE AC RECORDS, IT WAS NOTED THAT EXH	AUST SYS, INCLUDING TURBOCHARGER WASTE GATE AND CONTROL ROD END WAS NOT OVERHAULED WITH THE ENGINE CORE AS REQUIRED BY M	FG.  TURBOCHARGER WAS REPLACED WITH NEW UNIT AT TIME OF O/H.  UNKNOWN IF PN LW-14465 WAS REPLACED AT THAT TIME.  PART IS	1	L	7	1 	3O	3	O		A3SO    	E14EA	5	C	P33EA	 
2007032900265	20070329	00265	EA  	2007	3	29	2007FA0000164    	2	20070206	G	8500		ENGINE          			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540A1A   	41532	EA  						MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3543B					T20608330	L1123761A			UNDER NORMAL CONDITIONS AND UNDER OIL SAMPLE PROGRAM, ENGINE HAS HAD (6) HIGH BAD SAMPLES, HIGH IRON, COPPER AND ALUMINU	M.  AC IS A PUBLIC USE AIRCRAFT WITH CUSTOMS AND BORDER PROTECTION, BUT AM REPLACING ENGINE WITH NEW/ OVERHAUL.  CONTACT	ED MFG ABOUT PROBLEM BUT WAS TOLD TO KEEP CHANGING OIL AND FILTERS.  RECOMMEND THA THIS TYPE ENGINE BE INVESTIGATED CLOS	ER.  THIS ENGINE WAS CHANGED IN 2005 DUE TO SIMILAR PROBLEM.  (K)			1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2007031200262	20070312	00262	CE  	2007	3	12	2007FA0000165    	1	20070206	G	5511	233201015	SPAR CAP        			LEAR  	35    	36LEAR      	5170601	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZ STAB	CORRODED        	C			BHKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	12FN	15719				016				VISUAL CONDITION CHECK PERFORMED ON HORIZONTAL STABILIZER AFT SPAR CAP AND ELEVATOR HINGE BRACKETS FOR CORROSION, BROKEN	 FASTENERS, ETC.  FOUND MODERATE CORROSION ON UPPER SPAR CAP ASSY AT LT OB ELEVATOR HINGE AREA.  THIS REQUIRED REMOVAL A	ND REPLACEMENT OF UPPER SPAR CAP.  CORROSION CAUSED BY OPERATING CONDITIONS, LACK OF CONSISTENT WASHING PROGRAM AND POSS	IBLE EXPOSED, UNPORTECTED METAL.  RECOMMEND A CONSISTENT AC WASHING PROGRAM WHEN OPERATIONS ARE IN OR NEAR COASTAL REGIO	NS AND ENSURING ALL EXPOSED SURFACES ARE PROPERLY TREATED AND PAINTED.  (K)		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007022600030	20070226	00030	EU  	2007	2	26	2007FA0000166    	1	20070223	G	6230	1090110677	FITTING         			AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	745HA		32   			7413				MAIN ROTOR DRIVELINK UPPER FITTING STEEL BUSHES (109-0110-70-1) AND UPPER SLEEVE (109-0110-69-1) SEVERELY WORN.  SLEEVE 	STEPPED TO LESS THAN HALF MANUFACTURED DIAMETER AT BOTH ENDS.  STEEL BUSHES WORN THROUGH COMPLETELY, WEAR EXTENDING INTO	 FITTING.  HOLE IN BOTH ENDS OF FITTING FOR STEEL BUSHES ELONGATED.  PHOTOGRAPHS AND DISCREPANT PARTS AVAILABLE IF REQUI	RED.  DEFECTIVE PARTS REPLACED.			1	G	7	2 	3U	3	U		H7EU    	E4CE				 
2007030900122	20070309	00122	SO  	2007	3	9	2007FA0000168    	1	20070206	G	5711		SPAR            			PIPER 	J3    	J3C65       	7100510	SO  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6609H	2884 				19808				DURING REMOVAL OF LT WING FOR INSTALLATION OF WING FUEL TANK, A QUESTIONABLE PREVIOUS REPAIR WAS FOUND AT THE FRONT WOOD	 SPAR ROOT.  FURTHER INVESTIGATION FOUND LONGNATUDINAL CRACKS OF THE LT AND RT, FOR AND AFT WOOD WING SPARS.  THESE CRAC	KS WERE VISIBLE WITH A BARE EYE WHEN THE FRONT SPAR CARRY ATTACH INSPECTION PANEL WAS REMOVED AND INSPECTED FROM THE FRO	NT CABIN AREA.  CRACKS ARE NOT UNCOMMON AFTER 60 YEARS OF HARD SERVICE AND NATURAL DEGRADATION OF THE WOOD.  (K)			1	H	7	1 	3O				A691    					 
2007022600170	20070226	00170	SO  	2007	2	26	2007FA0000169    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					RIGHT	MISREPAIRED     	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	07	576ER	3598 				4496152				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD	 LEAD TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI	GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  MFG 	HAS A HISTORY OF AILERON SKIN CRACKING.  (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM.)  O	NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURING SKIN 	REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE T/E TAKES ON A (FAT) CONDITION.  THIS LEADS	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007022700048	20070227	00048	CE  	2007	2	27	2007FA0000171    	1	20070220	G	3230	504501033	TORQUE TUBE     	CESSNA      		CESSNA	340   	340A        	2076405	CE  	CONT  	O550  	IO550*      	 	SO  					MLG	BINDING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15	467DB					340A0467				DURING REPLACEMENT OF ORIGINAL EQUIPMENT TORQUE TUBE (P/N 5045010-18/19) WITH MFG REPLACEMENT P/N 5045010-32/33 INTERFER	ENCE BETWEEN THE TORQUE TUBE AND AIRFRAME ATTACHMENT FITTING WAS DISCOVERED.  RIGGING THE MLG TO ACHIEVE A .1250 DROP OF	F WAS IMPOSSIBLE DUE TO THE INTERFERENCE BETWEEN THE TORQUE TUBE AND THE ATTACHMENT FITTING. DROP OFF IS ACHIEVED ONCE T	HE TORQUE TUBE ROTATES FAR ENOUGH OVER CENTER TO ALLOW THE GEAR TO DROP .1250 BACK DOWN FROM ITS MAXIMUM HEIGHT.  MFG TE	CHNICAL SUPPORT INDICATED THAT THE ORIGINAL TORQUE TUBE (-18/19) HAD A FLAT SPOT BETWEEN THE AFT HINGE ARMS DESIGNED TO 	CLEAR THE AIRCRAFT STRUCTURE. THIS FLAT SPOT WAS ORIENTED AT A 33 DEGREE OFFSET. THE TORQUE TUBES WERE REDESIGNED IN 197	1	L	7	2 	3O	3	O		3A25    	E3SO				 
2007022700051	20070227	00051		2007	2	27	2007FA0000173    	2	20070222	G	7414	6310	MAGNETO         																	ENGINE	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		2    								MAGNETO CAUSING HIGH ALTITUDE MIS-FIRE.																			 
2007022700087	20070227	00087	CE  	2007	2	27	2007FA0000174    	1	20070201	G	2432		HOSE            			BEECH 	95    	B95         	1153404	CE  	LYC   	O360  	O360*       	41514	EA  					BATTERY DRAIN	DISCONNECTED    	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	9631R					TD314				BATTERY ELECTROLYTE RESIDUE FOUND ON LT NOSE GEAR DOOR AND LOWER FORWARD FUSELAGE.  INSPECTION REVEALED BATTERY BOX DRAI	N HOSE DISCONNECTED AND HANGING IN LOWER NOSE STRUCTURE AREA BELOW THE BAGGAGE FLOOR.  ACCESS IS HINDERED BY NUMEROUS FA	STENERS THAT ARE HARD TO REMOVE.  AT SOME TIME IN THE PAST THE ADF ANTENNA MAST, WHICH DOUBLED AS THE BATTERY DRAIN MAST	, HAD BEEN REMOVED AND THE BATTERY DRAIN HOSE WAS NOT RECONNECTED TO A SUITABLE DRAIN.  THIS COULD CAUSE CORROSION DAMAG	E TO NOSE AREA LOWER STRUCTURE ON TRAVEL AIR AND BARON AIRPLANES, WHICH HAVE SIMILAR DESIGN.  PARTS AND SHOP MANUALS CAR	RY NO REFERENCES ABOUT THE BATTERY DRAIN SYSTEM.  SUGGEST REVIEW OF ANY MFG SB DISCUSSING BATTERY BOX DRAIN COMPONENTS, 	1	L	7	2 	3O	3	O		3A16    	E286				 
2007030200033	20070302	00033	CE  	2007	3	2	2007FA0000175    	1	20070216	G	1100	070507109	PLACARD         			CESSNA	206   	206CESSNA   	2073302	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	WING	FADED           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		150  				T20608291	L1083261A	002324		P/N 0705071-9) FUEL QUANTITY AND TYPE PLACARDS HAVE BEEN REPLACED ABOUT ONCE A YEAR DUE TO FADING.  THIS AIRCRAFT IS HAN	GARED.  THIS FADING HAS BEEN NOTED WITH OTHER MFG AIRCRAFT.  RETAIL COST LAST YEAR NR 50.00+.  THIS HAS NOW DOUBLED.  OW	NERS DON'T PLACARD IMPORTANCE FOR AIRWORTHINESS.				1	H	7	1 	3O	3	O		A4CE    	E14EA	5	C	P58GL	 
2007031200032	20070312	00032	CE  	2007	3	12	2007FA0000176    	1	20070222	G	2752	55651904	ROLL PIN        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SPROCKET	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	797CW	8177 	1200 			5500232				DURING A PHASE 5 INSPECTION THE FLAPS SEAMED TO BE SLOW AND BINDING. AT CLOSER INSPECTION IT WAS FOUND THAT THE ROLL PIN	 HAD BROKEN ALLOWING THE SPROCKET TO MOVE FWD. ON THE P/N 5565190-9 BRAZE ASSY-DRIVE THIS CAUSED BINDING AND ALLOWED THE	 SPROCKET TO EVEN DROP DOWN ON TO THE P/N 6565193-9 CHAIN GUARD-LOWER FWD. THIS IS A HARD AREA TO LOOK AT EVEN WITH A MI	RROR. A FEW MORE ACTIONS WITH THE FLAP WOULD HAVE LED TO TOTAL FAILURE OF THIS SYSTEM.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007030200034	20070302	00034	SO  	2007	3	2	2007FA0000177    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					WING	MISREPAIRED     	D				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	570ER	3583 				4496146				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD	 LEAD TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI	GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  MFG 	HAS A HISTORY OF AILERON SKIN CRACKING.  (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM).  O	NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURING SKIN 	REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION.  	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007030800056	20070308	00056	SO  	2007	3	8	2007FA0000178    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					WING	MISREPAIRED     	B				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	571ER	3801 				4496147				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD	 LEAD TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI	GHTS BOTH BY COMPANY PILOTS AND PIPER FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  PI	PER HAS A HISTORY OF AILERON SKIN CRACKING.  (IT HAS BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM).  ONCE THE C	RACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURING SKIN REPLACEME	NT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION.  THIS LEAD	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007030800057	20070308	00057	SO  	2007	3	8	2007FA0000179    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					WING	MISREPAIRED     	A				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	572ER	3160 				4496148				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD	 LEAD TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI	GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  MFG 	HAS A HISTORY OF AILERON SKIN CRACKING.  (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM.)  O	NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURING SKIN 	REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION.	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007030800058	20070308	00058	SO  	2007	3	8	2007FA0000180    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					WING	MISREPAIRED     	B				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	573ER	3969 				4496149				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD	 LEAD TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI	GHTS BOTH BY COMPANY PILOTS AND PIPER FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  MF	G HAS A HISTORY OF AILERON SKIN CRACKING.  (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM). 	 ONCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURING SKI	N REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION.	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007030800059	20070308	00059	SO  	2007	3	8	2007FA0000182    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O320  	O320*       	41508	EA  					WING	MISREPAIRED     	B				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	577ER	3881 				4496153				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD	 LEAD TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI	GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  MFG 	HAS A HISTORY OF AILERON SKIN CRACKING.  (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM.)  O	NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURING SKIN 	REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION.	1	L	7	2 	3O	3	O		A19S0   	E274				 
2007022700060	20070227	00060	EA  	2007	2	27	2007FA0000183    	2	20070211	G	8540	13S19646	GEAR            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	CRANKSHAFT	LOOSE           	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			GL	15	242SP	1855 				172S8226	L2830651A	SK039		DURING TAKEOFF AT 400 FT AGL ENGINE QUIT FORCING AN OFF AIRPORT EMERGENCY LANDING.  INITIAL INSPECTION FOUND NO MOVEMENT	 OF ACCESSORIES AND VALVE MOVEMENT.  REMOVED ACCESSORIES CASE AND FOUND DRIVE GEAR ON CRANKSHAFT MOUNT BOLT LOOSE AND PI	N SHEARED.  MARKS SHOW THAT BOLT AND GEAR WERE LOOSE FOR SOME TIME ALLOWING WEAR ON PIN UNTIL FAILURE. SUSPECT INCORRECT	 TORQUE OR INCORRECT SEATING OF GEAR TO FLANGE.  ALSO WITH GEAR LOOSE BOLT COULD BE TURNED IN LOCKING TAB. HOLE IN LOCKI	NG TAB TOO LOOSE ON BOLT.  ENGINE NEW FROM MFG. WITH 1855.3 HOURS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007032900295	20070329	00295	EA  	2007	3	29	2007FA0000185    	2	20070222	G	7414	ESIO357424	BUSHING         	BENDIX      		MOONEY	M20   	M20D        	5870210	SW  	LYC   	O360  	O360A1D     	41514	EA  					MAGNETO	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	6914U	31   			1060379	246				BRONZE BUSHING VERY LOOSE IN DISTRIBUTOR BLOCK AND MAG WOULD NOT OPERATE CORRECTLY.  AN EMERGENCY LANDING WAS MADE.  (K)						1	L	7	1 	3O	3	O		2A3     	E286				 
2007030900172	20070309	00172	SO  	2007	3	9	2007FA0000186    	2	20070222	G	7414		BUSHING         	BENDIX      		CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					MAGNETO	LOOSE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	2948U	194  				17250548				BRONZE BUSHING, VERY LOOSE IN DISTRIBUTOR BLOCK AND DISTRIBUTOR ARM WAS CONTACTING PINS IN BLOCK.  MAG WOULD NOT OPERATE	 CORRECTLY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2007030900140	20070309	00140	EU  	2007	3	9	2007FA0000187    	1	20070222	G	2910	285683	COUPLING        			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HYDRAULIC SYS	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	43EC	9017 				168				THIS COUPLING IS A QUICK-DISCONNECT TYPE FITTING THAT IS IN LINE OF THE ENGINE DRIVEN HYDRAULIC PUMP AND LOCATED IN THE 	ENGINE PYLON.  THERE IS ONLY ONE ON EACH ENGINE AND ONLY ON THE SUCTION LINE.  THESE FITTINGS HAVE NO TIME CHANGE REQUIR	EMENT.  WHEN THIS PART WAS CHANGED (DUE TO EXTERNAL LEAKAGE) IT WAS EXTREMELY DIFFICULT TO SEPARATE.  ONCE SEPARATED, TH	E LOCKING BALLS HAD DUG SO DEEPLY INTO THE LOCK RING THAT PARTIAL UNSEATING OF THE O-RING HAD OCCURRED.  THERE QUICK DIS	CONNECT COUPLINGS (LT AND RT) SHOULD BE REQUIRED TO BE INSPECTED AT EACH ENGINE REMOVAL AND REPLACED IF WEAR IS DETECTED	.  (K)	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2007032900294	20070329	00294	CE  	2007	3	29	2007FA0000188    	1	20070215	G	2510	551900922	SEAT            	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	404BS					5500403				UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  CHAI	R WAS REPAIRED IAW STC 01042WI STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007032600101	20070326	00101	CE  	2007	3	26	2007FA0000189    	1	20070226	G	2750	051010593	CONTROL CABLE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					TE FLAPS	FRAYED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	31SZ	13729	13729			17267732				PILOT REPORTED EXCESSIVE MOVEMENT IN LT FLAP DURING PRE-FLIGHT WALK AROUND OF AIRCRAFT.  INITIAL INVESTIGATION BY MAINTE	NANCE PERSONNEL CONFIRMED FINDINGS.  MAINTENANCE PERSONNEL DISCOVERED THAT CABLE P/N 0510105-93 HAD MULTIPLE BROKEN STRA	NDS/FRAYING NEAR THE TURNBUCKLE END.   SUSPECTED CAUSE OF DAMAGE TO CABLE IS DUE TO EXCESSIVE FLEXING BETWEEN TURNBUCKLE	 END AND FLAP POSITION INDICATOR CLAMP, P/N 0560037-1.  AD 80-06-03 HAD BEEN COMPLIED WITH ON 10/11/1982 BY INSTALLATION	 OF KIT SK172-60A.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007030100205	20070301	00205	GL  	2007	3	1	2007FA0000190    	3	20070221	G	6114	C4201C58	HUB             	MCAULY      												MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	B			LT4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					720009			720009		HUB RECEIVED DISASSEMBLED, CLEANED AND ANODIZED WITH NO CERTIVICATION.  BLADE RETENTION THREADS EDDY CURRENT INSPECTED. 	 NR 1 BLADE RETENTION THREAD, 4 THREADS IN AT APPROXIMATELY 6 O`CLOCK POSITION FOUND CRACKED.  HUB REMOVED FROM SERVICE.	  (K)														5	C	P3EA	 
2007030900119	20070309	00119	EU  	2007	3	9	2007FA0000191    	1	20070227	G	5730	S25WS3001	SKIN            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					RT WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	224EA	9121 				257088				RT WING LEADING EDGE(S) HAD SEVERE CORROSION WHERE THE TKS PANELS ATTACH.  AFTER COMPLETE DISASSEMBLY IT WAS DETERMINED 	TO BE BEYOND ECONOMICAL REPAIR.  RT WING LEADING EDGE HAD BEEN INSPECTED AT MFG 2.5 YEAR PRIOR TO THIS DISCOVERY.  (K)					2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2007032600144	20070326	00144	EU  	2007	3	26	2007FA0000192    	1	20070227	G	5754	S25WS3002	SKIN            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					RT WING LE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	224EA	9121 				257088				RT WING LEADING EDGE(S) HAD SEVERE CORROSION WHERE THE TKS PANELS ATTACH.  AFTER COMPLETE DISASSEMBLY, IT WAS DETERMNED 	TO BE BEYOND ECONOMICAL REPAIR.  RT WING LEADING EDGE HAD BEEN INSPECTED AT MFG 2.5 YEARS PRIOR TO THIS DISCOVERY.  (K)					2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2007040200170	20070402	00170		2007	4	2	2007FA0000193    	2	20070213	G	7414	6350	ROTOR           																	MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										ROTOR AT ROTOR GEAR AND BROKEN.  (K)																			 
2007030900133	20070309	00133	EU  	2007	3	9	2007FA0000194    	1	20070221	G	5512	25TP1001A	SKIN            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZ STAB	CORRODED        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	224EA	9121 				257088				LT AND RT HORIXONTAL STABILIZER LEADING EDGES HAD SEVERE CORROSION WHERE THE TKS PANELS ATTACH.  AFTER COMPLETE DISASSEM	BLY, IT WAS DETERMINED TO BE BEYOND ECONOMICAL REPAIR.  THIS AREA HAD BEEN INSPECTED AT MFG 2.5 YEARS PRIOR TO THIS DISC	OVERY.  (K)				2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2007032900299	20070329	00299	CE  	2007	3	29	2007FA0000195    	1	20070129	G	3233		LIMIT SWITCH    			CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG ACTUATOR	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	3091L					310J0091				UP LIMIT SWITCH FAILED ON LANDING GEAR ACTUATOR, CAUSING OVER EXTENSION OF NOSE GEAR SYSTEM.  THIS CAUSED THE INTERMEDIA	TE TORQUE TUBE TO BEND.  (K)					1	L	7	2 	3O	3	O		3A10    	E1CE				 
2007040200168	20070402	00168	WP  	2007	4	2	2007FA0000196    	2	20070220	G	7261	8961051	COVER           			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					LT ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	241CW					BE54	P27188			PILOT REPORTED HIGH OIL CONSUMPTION, INSPECTED LT ENGINE SCAVENGE PUMP AND FOUND THE PUMP COVER BROKEN AND MISSING PIECE	S.  ALSO FOUND THE SCAVENGE PUMP OIL TUBE COVER BROKEN AND CHAFING A HOLE THROUGH THE OIL TUBE.  RECOMMEND REMOVING EXHA	UST PIPE AT INSPECTIONS TO INSPECT PUMP COVER AND TUBE ASSY FOR DEFECTS.  (K)				1	L	7	2 	4T	4	T		A14CE   	E4WE				 
2007030900116	20070309	00116	CE  	2007	3	9	2007FA0000199    	1	20070301	G	2571	07120591P	SUPPORT         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					BATTERY BOX	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	3539G					18281039				FOUND BATTERY SUPPORT CRACKED.  TOTAL AIRFRAME TIME 1075.  THIS IS THE 3RD ONE THAT WE FOUND.  SUPPORTS NEED TO BE BEEFE	D UP, THEY ARE TOO LIGHT FOR THE APPLICATION.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007030900157	20070309	00157	CE  	2007	3	9	2007FA0000200    	1	20070301	G	2571	07120591P	SUPPORT         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					BATTERY BOX	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	65KC					18281015				FOUND BATTERY SUPPORT CRACKED.  TOTAL AIRFRAME TIME 1716.  THIS IS THE THIRD ONE THAT WE FOUND SUPPORTS NEED TO BE BEEFE	D UP, THEY ARE TOO LIGHT FOR THE APPLICATION.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007031200254	20070312	00254	EA  	2007	3	12	2007FA0000201    	2	20070221	G	8520	V53793493	CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CORRODED        	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	982BT	4744 	2196 			17280307	L1466351A			THIS CRANKSHAFT WAS LAST INSPECTED AND PID COATED AT THE FACTORY APRIL 23, 2002, YET 6 YEARS AND 2196 HOURS LATER, IT WA	S PITTED, AND REQURIED FURTHER MACHINING.  THE PID COATING DOES NOT SEEM TO HOLD UP, OR BLOCK THE CORROSION.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007031200253	20070312	00253	EA  	2007	3	12	2007FA0000202    	2	20070223	G	8520	V537925914	CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CORRODED        	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	988BC	4170 	2211 			17280472	L2494851A			DURING SCHEDULED OVERHAUL, THIS CRANKSHAFT WAS FOUND PITTED IN THE INNER BORE.  THIS ENGINE WAS A FACTORY OVERHAUL JULY 	2002, AND DID HAVE THE PID COATING.  THE COATING DOES NOT SEEM TO BLOCK THE CORROSION.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007030900154	20070309	00154	EU  	2007	3	9	2007FA0000203    	1	20070213	G	8120	LW18607	STRUT           			PARTEN	P68   	P68TCOBS    	6780108	EU  										TURBO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737					40004OTC	RL20464A			UPON REMOVING ENGINE FROM SHIPPING CRATE, FOUND (NEW) TURBO SUPPORT STRUT CRACKED.  THESE BRACKETS CRACK ALL THE TIME ON	 THE AIRPLANE.  VERY POOR DESIGN!  (K)					1	H	7	2 	3O			RT	A31EU   					 
2007030900155	20070309	00155	EU  	2007	3	9	2007FA0000204    	1	20070213	G	8120	LW18607	STRUT           			PARTEN	P68   	P68TCOBS    	6780108	EU  										TURBO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737					40004OTC	RL20364A			UPON REMOVING ENGINE FROM SHIPPING CRATE, FOUND (NEW) TURBO SUPPORT STRUT, CRACKED.  THESE BRACKETS CRACK ALL THE TIME I	N THE AIRPLANE.  VERY POOR DESIGN!  (K)					1	H	7	2 	3O			RT	A31EU   					 
2007032900292	20070329	00292	CE  	2007	3	29	2007FA0000205    	1	20070222	G	3610	1H1069	MIXING VALVE    			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					BLEED AIR SYS	INTERMITTENT    	C				A				UNSCHED LANDING         				J	B		WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			GL	11	500	83   				306				SHORTLY AFTER TAKEOFF, AIRCRAFT (L BLEED AIR) WARNING ILLUMINATED, AND (R BLEED AIR) WARNING ILLUMINATED APPROX 5 SEC LA	TER, SMELLED ODOR IN CABIN.  REDUCED POWER AND WARNING WENT OUT.  AIRCRAFT DIVERTED FOR MAINTENANCE.  UNABLE TO DUPLICAT	E MALFUNCTION ON GROUND RUN, LT MIXING VALVE WAS SUSPECTED, SO REPLACED.  PERFORMED GROUND RUN FUNCTIONAL TEST OF BLEED 	AIR SYSTEM, AND FLIGHT TEST.  NO FURTHER BLEED AIR WARNINGS.  (K)			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007030800083	20070308	00083	SO  	2007	3	8	2007FA0000206    	1	20070223	G	5751	86562025	AILERON         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					WING	MISREPAIRED     	B			BF8X	O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	575ER	3448 				4496151				DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AC WOULD SUDDENLY BREAK LEFT AND IF NOT IMMEDIATELY STOPPED COULD LEA	D TO A SPIN.  AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLIGHTS	 BOTH BY COMPANY PILOTS AND MFG TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET.  THIS MAKE OF AIR	CRAFT HAS A HISTORY OF AILERON SKIN CRACKING.  (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLE	M).  ONCE THE CRACK IS PAST A CERTAIN POINT , YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON.  DURI	NG SKIN REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE, THE TRAILING EDGE TAKES ON A (FAT) CON	1	L	7	2 	3O	3	O		A19S0   	E286				 
2007030900004	20070309	00004	CE  	2007	3	9	2007FA0000207    	1	20070301	G	2432	G35	BATTERY         			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470*       	17026	SO  						LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	9198C	34   				31297				BATTERY ACID LEAKED OR TRANSFERRED TO AFT, LOWEST CELL (AIRCRAFT TAIL WHEEL) AND SPILLED OUT.  CORRODED HOLE IN BATTERY 	BOX AND SPILLED INTO BELLY OF AIRCRAFT.					1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2007030900005	20070309	00005	CE  	2007	3	9	2007FA0000208    	1	20070301	G	2432	G35	BATTERY         			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470*       	17026	SO  						LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	9198C	34   				31297				BATTERY ACID LEAKED OR TRANSFERRED TO AFT, LOWEST CELL (AIRCRAFT TAIL WHEEL) AND SPILLED OUT.  CORRODED HOLE IN BATTERY 	BOX AND SPILLED INTO BELLY OF AIRCRAFT.					1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2007032200025	20070322	00025		2007	3	22	2007FA0000209    	4	20070306	G	2350	9903334446	AUDIO CONTROL   			GULSTM	G1159 	G1159       	3953505	SO  	PWA   	530   	PW530A      	 	NE  					COCKPIT	SHORTED         	C				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	21	685SF					94				UNIT WAS MANUFACTURED IN AUGUST 06 AND WAS INSTALLED IN DECEMBER 06. THE UNIT POPPED THE CIRCUIT BREAKER ON THE FIRST TR	IP. THE UNIT WAS SENT IN FOR REPAIR AND REINSTALLED IN FEBRUARY 07 AND FAILED AGAIN ON THE FIRST FLIGHT.					2	L	7	2 	4F	4	F	RT	A12EA   	E00053EN				 
2007030900041	20070309	00041	SO  	2007	3	9	2007FA0000210    	2	20070220	G	8530	639614639615	ROCKER          	CONT        	O300D       	CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	INCORRECT       	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	17	8848Z		110  		64805D6D	17255498	64805D6D			PILOT REPORTED LOSS OF POWER (600 RPM DROP) SIGNIFICANT ENGINE ROUGHNESS DURING CLIMB. ENGINE RECOVERED SHORTLY AFTERWAR	DS. PILOT ELECTED TO CONTINUE AND HAD SAME PROBLEM AGAIN DURING CRUISE FLIGHT. ENGINE RECOVERED ON ITS OWN ONCE AGAIN. P	ILOT SAID CARB HEAT DID NOT MAKE ANY IMPROVEMENT DURING BOTH OCCURRENCES. AIRCRAFT WAS TURNED OVER TO MAINTENANCE.  THE 	ONLY ABNORMALITY DISCOVERED WAS THAT THE EXHAUST VALVES ON 4 OF THE 6 CYLINDERS HAD INCORRECT ROCKER INSTALLED (639614, 	INTAKE ROCKER). PARTS MANUAL CALLS FOR 639615 (EXHAUST ROCKER) TO BE INSTALLED ON EXHAUST POSITION.		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2007030900073	20070309	00073	CE  	2007	3	9	2007FA0000214    	1	20070307	G	8011	85562020	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SPINNING        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	767CL	57   				172S9987				STARTER SPINS AND WILL NOT ENGAGE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007032200081	20070322	00081	CE  	2007	3	22	2007FA0000215    	1	20070301	G	3230	MS2764816	BEARING         			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					MLG	SEIZED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	19RK	9280 				LA12				PERFORMING A ROUTINE 6 YEAR LANDING GEAR OVERHAUL, THE LT LANDING GEAR GEARBOX-ACTUATOR TORQUE TUBE HAD A SEIZED MAIN SU	PPORT BEARING. THIS MADE THE TORQUE TUBE EXTREMELY HARD TO TURN. THE BEARING WAS FOUND TO BE RUSTED, AND SEIZED. BEARING	 WAS REPLACED WITH NEW.				1	L	7	2 	4T	4	T		A31CE   	E4EA				 
2007040200169	20070402	00169	EA  	2007	4	2	2007FA0000218    	2	20070202	G	8550	56G23399	BAFFLE          			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	TIO540AH1A  	42003	EA  					OIL SUMP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	447KC	85   				3255047	L1239361A			DURING ENGINE OIL CHANGE FOUND RIVET HEAD IN OIL SUMP SCREEN.  REMOVED ENGINE AND OIL SUMP ASSY.  FOUND OIL SUMP BAFFLE 	ASY RIVETS SHEARED OFF AND ATTACH HOLES BROKEN OUT AND BAFFLE ASSY CRACKED.  RETRIEVED RIVET STEMS AND HEADS.  REMOVED A	ND REPLACED OIL SUMP BAFFLE ASSY WITH NEW PART.  REASSEMBLED ENGINE AND REINSTALLED.  (K)				1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2007032900269	20070329	00269	EA  	2007	3	29	2007FA0000219    	2	20070302	G	7310		B-NUT           			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					FUEL SYSTEM	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	38AL					18281450	L2980148A			IN THIS CASE, FOUND THAT THE B-NUT CONNECTING TO THE FUEL CONTROL FROM THE SPIDER WAS LOOSE.  IT WAS NOT LEAKING, BUT RE	QUIRED A THIRD OF A TURN TO TORQUE DOWN TO PROPER TORQUE.  NO OTHER WORK HAS BEEN DONE TO THE SPIDER OR FUEL CONTROL BEC	AUSE I HAVE DONE THE WORK SINCE NEW ON THIS AIRCRAFT.  TT 228.8.  REMEMBER FINDING A LOOSE FIREWALL FITTING ON THE FIRST	 INSPECTION.  THIS IS THE SECOND INSPECTION DONE ON THIS AIRCRAFT.  IT WAS CERTIFIED 11/11/2004.  (K)			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007032900280	20070329	00280	CE  	2007	3	29	2007FA0000220    	1	20070223	G	2510	551900921	SEAT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	630CC					5500130				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  	CHAIR WAS REPAIRED IAW ST01042WI STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007040200237	20070402	00237	EA  	2007	4	2	2007FA0000221    	2	20070222	G	8520		CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CORRODED        	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2199 				L130951A			DURING NORMAL OVERHAUL, CRANKSHAFT FOUND PITTED IN THE INTERNAL BORE.  THIS ENGINE WAS LAST OVERHAULED BY THE FACTORY, J	ULY 2002..  THE PID COATING DOES NOT SEEM TO PREVENT PITTING OR CORROSION.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007050400165	20070504	00165	CE  	2007	5	4	2007FA0000222    	1	20070215	G	2821	99120154	FUEL FILTER     			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  					RT WING	SEPARATED       	D			J7BR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	409S	10045				5000238				THE RT FUEL FILTER ASSY SEPARATED FROM THE STANDPIPE DUE TO THE SNAP-RING BECOMING DISLOGED AND RESULTED IN A SUBSTANTIA	L FUEL LEAK.  (K)					1	L	7	2 	4F	4	F		A22CE   	E25EA				 
2007032900273	20070329	00273	EA  	2007	3	29	2007FA0000223    	2	20070124	G	7261		OIL FILTER      			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	COLLAPSED       	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99										OIL LEAK NOTED AFTER OIL CHANGE.  REMOVED OIL FILTER AND DISCOVERED PARTIAL COLLAPSE OF THE OIL FILTER ELEMENT.  IT WAS 	DETERMINED THAT THE ENGINE MOUNTED INTERNAL BY-PASS VALVES OPERATION.  PREVIOUS TO THIS OCCURRENCE THE SB MENTION HAD NO	T BEEN COMPLIED WITH.  AFTER THIS OCCURRENCE, SB WERE COMPLIED WITH AND A NEW OIL FILTER OF THE SAME MAKE AND MODEL WAS 	INSTALLED AND THE SYSTEM FUNCTIONED PROPERLY.  SUBMITTER SUGGESTS THAT DUE TO THE SIGNIFICANT NR OF OCCURRENCES OF THIS 	TYPE THAT SB SI-1442 AND 1453 BECOME MANDATORY THROUGH AD FOR ADDED SAFETY.  (K)		1	L	7	1 	3O	3	O		A3SO    	1E4				 
2007040200127	20070402	00127	CE  	2007	4	2	2007FA0000224    	1	20070215	G	2821	99120154	FUEL FILTER     	PUROLATOR   		CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  					RT WING	SEPARATED       	B			J7BR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	409S	10045				5000238	76509			THE RT FUEL FILTER ASSY SEPARATED FROM THE STANDPIPE DUE TO THE SNAP-RING BECOMING DISLODGED AND RESULTED IN A SUBSTANTI	AL FUEL LEAK.					1	L	7	2 	4F	4	F		A22CE   	E25EA				 
2007032900297	20070329	00297	SO  	2007	3	29	2007FA0000225    	1	20070215	G	2750	62679000	BRACKET         			PIPER 	PA28  	PA28*       	       	SO  										COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03										THIS BRACKET IS RIVETED IN THE CENTER TUNNEL AND ACCEPTS (2) BOLTS AT THE FORWARD SIDE OF THE FLAP HANDLE SUPPORT MOUNT.	  THIS IS A DIFFICULT AREA TO SEE, EVEN WITH A MIRROR.  WE HAVE FOUND (6) CRACKED BRACKETS SO FAR TO DATE.  SUSPECT FATI	GUE AND AIR LOADS CAUSING CRACKS.  (K)				1	L	7	1 	3O				2A13    					 
2007040200158	20070402	00158	SO  	2007	4	2	2007FA0000226    	2	20070220	G	8500		ENGINE          			CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  						FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	442EH					4040202	604103			THIS ENGINE FAILED TO THE TERMINOLOGY OF CATASTROPHIC AT THE NR 1 AND NR 2 CYLINDER CONNECTING ROD LOCATIONS DURING A MA	INTENANCE TEST FLIGHT WITHIN TEN MINUTES INTO THAT FLIGHT WITH A MECHANIC ON BOARD MONITORING THE ENGINE INSTRUMENTS.  T	HE OIL PRESSURE SUDDENLY DROPPED TO ZERO, THE PROPELLER STARTED TO FEATHER AND DURING SHUTDOWN AND SECURING, THE ENGINE 	LOCKED UP.  PRIOR TO THIS, THE OIL FILTER WAS REMOVED, CUT OPEN AND INSPECTED WITH NO DEFECTS NOTED.  AN OIL SOAP SAMPLE	 WAS TAKEN.  THE OIL PUMP AND AIRCRAFT OIL PRESSURE GAUGE WAS CHECKED FOR A POSITIVE OIL PRIME AND INDICATION.  AN EXTEN	DED ENGINE GROUND RUN WAS DONE AT LOW AND HIGH POWER SETTINGS WITH NO OIL PRESSURE DISCREPANCIES NOTED.  THESE CHECKS WE	1	L	7	2 	3O	3	O	RT	A25CE   	E7CE				 
2007031300197	20070313	00197	CE  	2007	3	13	2007FA0000227    	1	20070119	G	8011	85A34117	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	STUCK           	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	767CL	527  				172S9987				STARTER STUCK IN ENGAGED POSITION.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007050400138	20070504	00138	NM  	2007	5	4	2007FA0000228    	1	20070306	G	3260		SENSOR          			BOEING	747   	747230B     	1384889	NM  	GE    	CF6   	CF650*      	30018	NE  					MLG	MALFUNCTIONED   	B			GJPY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	33	760SA					21221				DURING TAKEOFF, THE LANDING GEAR HANDLE WILL NOT GO TO UP OR RETRACT POSITION.  AIRCRAFT RETURNED TO BASE.  PERFORMED TR	OUBLESHOOTING ON THE LANDING GEAR SYSTEM AND FOUND THAT LT WING GEAR TRUCK ROTATION SENSOR AT FAULT.  ADJUSTED THE LT WI	NG GEAR TRUCK ROTATION SENSOR IAW AMM 32-61-04.  PERFORMED LANDING GEAR SYSTEM EXTENSION AND RETRACTION SEVERAL TIMES IA	W AMM 32-32-00/501, TEST NORMAL.  (K)			2	L	7	4 	4F	4	F		A20WE   	E23EA				 
2007041200027	20070412	00027	EU  	2007	4	12	2007FA0000229    	1	20070308	G	2820	653014	VALVE           			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					RT LWR FUEL CELL	CRACKED         	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	328PC	8597 				328				CRACK IN INTERCONNECT VALVE MOTOR HOUSING.  FOUND DURING BAG REMOVAL AND REINSTALLATION.  CAUSE OF CRACK, UNKNOWN.  (K)						2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007032900293	20070329	00293	SO  	2007	3	29	2007FA0000230    	1	20070220	G	5521	4602003	RIB             			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					LT ELEVATOR	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	112ED					31T8020060				1 INCH CRACK NOTED ON LOWER SKIN THRU RIVET.  DRILLED OPEN SKIN AND FOUND 5 INCH OF RIB FLANGE BROKE OFF 2 INCHS FROM TR	AILING EDGE.  SKIN AND RIB HAVE TO BE REPLACED.  (K)					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2007032900298	20070329	00298	SO  	2007	3	29	2007FA0000231    	1	20070215	G	2910		HYDRAULIC LINE  			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					HYDRAULIC SYS	CHAFED          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	19	144CN	5200 				278054036				AIRCRAFT HYDRAULIC SYSTEM RT GEAR DOWN ALUMINUM LINE LOCATED UNDER COCKPIT FLOOR WAS CHAFING AGAINST CONTROL CABLE AND W	AS PENETRATED CAUSING LEAK AND DEPLETION OF HYDRO FLUID WHICH RESULTED IN AIRCRAFT LANDING WITH UNSAFE NOSE GEAR AND DAM	AGE TO AIRCRAFT NOSE SECTION.  THIS AREA SHOULD BE INSPECTED AT LEAST DURING ANNUAL INSPECTIONS.  (K)				1	L	7	2 	3O	3	O		1A10    	1E4				 
2007050700186	20070507	00186	SO  	2007	5	7	2007FA0000232    	1	20070305	G	2432	RG380E44	BATTERY         			LKHEED	1329  	1329*       	       	SO  	GARRTT	TFE731	TFE7313     	01518	WP  					MASTER	FAILED          	B			VXWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	58TS					5079	75238			THESE 2 EA PN RG-380E/44 MAIN SHIP BATTERIES WERE INSTALLED ON 10/30/2006.  THESE BATTERIES WERE REPLACEMENTS FOR 2 EA B	ATTERIES THAT HAD BEEN IN SATISFACTORY SERVICE IN THIS AC FOR APPROX 48 MONTHS BUT FAILED A CAPACITY CHECK DURING A REGU	LAR SCHEDULED INSPECTION.  LESS THAN 2 MONTHS AFTER INSTALLATION THE PILOTS WERE UNABLE TO START THE MAIN ENGINES USING 	THESE BATTERIES.  AT THIS TIME THE BATTERIES HAD A TOTAL FLIGHT TIME OF 16 HOURS AND HAD PERFORMED 26 MAIN ENGINE STARTS	 AND 8 APU STARTS.  THE MAIN ENGINES WERE STARTED USING A GROUND POWER UNIT.  ALL CHARGING AND ELECTRICAL OPERATIONS APP	EARED NORMAL.  THE BATTERIES WERE REMOVED AND GIVEN TO REPAIR STATION FOR TESTING.  BOTH BATTERIES WERE TESTED IAW (INST	2	L	7	4 	4J	4	F		2A15    	E6WE				 
2007032900290	20070329	00290	EA  	2007	3	29	2007FA0000233    	2	20070312	G	7414	M3081	SPRING          	SLICK       		CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540AK1A  		EA  					RT MAGNETO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	29	5198G	658  			66LC35SDNP	T18208150	L1121761A			NEW POINTS (PN M3081) WERE INSTALLED IN BOTH MAGNETOS AT THE ANNUAL INSPECTION ON 2/22/07, TT 649.2.  ON 3/10/07, TT 658	.2, PART TT - 9.0 HOURS, THE PILOT/OWNER PERFORMED MAG CHECK AND THE ENGINE QUIT.  A MECHANIC REMOVED THE RT MAG AND FOU	ND THAT THE SPRING THAT HOLDS HALF THE POINTS HAD SNAPPED OFF.  THE MECHANIC TOLD THE OWNER THAT HE HAD NEVER SEEN POINT	S FAIL LIKE THIS IN HIS 30 YEARS OF AC MAINTENANCE.  TOLD HIM THAT I HAD NEVER SEEN THIS TYPE OF MALFUNCTION IN MY 10 YE	ARS OF MAINTENANCE.  IT APPEARS THAT THE METAL SPRING THAT MAKES UP THE POINT KIT FAILED JUST AFT OF THE AREA WHERE THE 	METAL IS BENT ON BOTH EDGES FOR STRENGTHING PURPOSE.  THE BREAK IS IN A SEMICIRCLE FRO ONE SIDE TO THE OTHER.  THE METAL	1	H	7	1 	3O	3	O	NT	3A13    					 
2007040900162	20070409	00162	GL  	2007	4	9	2007FA0000234    	3	20070317	G	6111	F8483	BLADE           													HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	MISREPAIRED     	B			ME4R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	19								DY5121B		(REF NR: 38430A) 2 OF 3 PROPELLER BLADES WERE PREVIOUSLY REPAIRED USING AN UNAPPROVED WELD METHOD IN SEVERAL LOCATIONS O	N THE BLADE AIRFOIL.  THE BLADES HAVE BEEN SCRAPED PENDING DISPOSITION INSTRUCTIONS FROM MFG.  THE CUSTOMER HAS BEEN CON	TACTED FOR HISTORICAL RECORDS.  (K)														5	C	P25EA	 
2007050700183	20070507	00183	GL  	2007	5	7	2007FA0000235    	3	20070317	G	6111	F8483	BLADE           													HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	MISREPAIRED     	B			ME4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19								DY5121B		(REF NR 38430A)  2 OF 3 PROPELLER BLADES WERE PREVIOUSLY REPAIRED USING AN UNAPPROVED WELD METHOD IN SEVERAL LOCATIONS O	N THE BLADE AIRFOIL.  THE BLADES HAVE BEEN SCRAPED PENDING DISPOSITION INSTRUCTIONS FROM MFG.  THE CUSTOMER HAS BEEN CON	TACTED FOR HISTORICAL RECORDS. (K)														5	C	P25EA	 
2007032900284	20070329	00284	EU  	2007	3	29	2007FA0000236    	1	20070121	G	2434		TERMINAL        			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  					ALTERNATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	711RP					1081	L1813148A			FIELD WIRE TERMINAL END BROKEN AT ALTERNATOR TERMINAL LUG CAUSED FAILURE OF ALTERNATOR TO CHARGE BATTERY.  (K)						1	L	7	1 	3O	3	O	RT	A51EU   	1E4				 
2007040200214	20070402	00214	CE  	2007	4	2	2007FA0000237    	1	20070301	G	5610	10138402524	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	CRACKED         	B			AHTR	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			GL	11	200VC	728  				FL316				AT AN ALTITUDE OF 17,000 FT OAT -6 DEGREES C, THE RT WINDSHIELD CRACKED FROM THE CENTER OB FROM THE TOP TO THE BOTTOM AB	OUT 2 INCHES OB ON THE OUTER PANE.  RETURNED TO THE DEPARTING AIRPORT WITHOUT ANY PROBLEMS.  WINDSHIELD WAS REPLACED AND	 NO KNOWN CAUSE FOR THE WINDSHIELD TO CRACK. (K)				2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2007032200037	20070322	00037	CE  	2007	3	22	2007FA0000238    	1	20070316	G	3242	RA66109	BRAKE PADS      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	6440V	49   				172RG0701	L2783136A	951039		DURING A 50 HR OIL CHANGE AND INSPECTION, FOUND BOTH LT AND RT BRAKE PADS FALLING APART, SEVERELY CRACKED WITH LARGE PIE	CES MISSING.  BOTH SIDES WERE CHANGED AT THE PREVIOUS 100 HOUR INSPECTION.  THIS HAS BEEN A FREQUENT PROBLEM WITH THESE 	BRAKE PADS ON ALL OF OUR AIRCRAFT (2 C152, 1 C172, 1 C172RG), NEW PADS FAILING WITHIN 200 HOURS OR LESS SINCE WE STARTED	 USING THEM. PREVIOUSLY, WE USED OTHER MFG PADS WITH VERY FEW PROBLEMS.			1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007032200092	20070322	00092	CE  	2007	3	22	2007FA0000243    	1	20070226	G	5310	VP10	ANTENNA         			BEECH 	33    	35B33       	1151406	CE  	CONT  	O470  	IO470*      	17026	SO  					VHF SYSTEM	MISINSTALLED    	B				A				UNSCHED LANDING         				W	D		INADEQUATE Q C            	INFLIGHT SEPARATION       		CR	CRUISE         	1			CE	03	1768G	94   	94   			CD509				THE DOUBLER FOR THE VHF ANTENNA APPEARS TO HAVE BEEN TOO SMALL(SLIGHLY LARGER THAN THE BASE OF THE ANTENNA)AND WAS NOT R	IVITED TO THE FUSELAGE,ALLOWING THE ANTENNA TO FLUTTER WHILE AIRBORNE.ON POST FLIGHT INSPECTION THE PILOT DISCOVERED TEA	RING ON THREE SIDES ON TOP OF THE FUSELAGE AROUND THE BASE OF THE ANTENNA.NOTE THE TACH ONLY READS 94.5				1	L	7	1 	3O	3	O		3A15    	E1CE				 
2007032200093	20070322	00093	CE  	2007	3	22	2007FA0000244    	1	20070301	G	5551	071204221	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4640E					18503824				DURING A DETAILED INSPECTION OF THE EMPENAGE, THE RT HORIZONTAL STABILIZER HINGE BRACKET P/N 0712042-2 WAS FOUND CRACKED	 AND HAD (2) SHEARED RIVETS.  UPON DISASSEMBLY THE LT BRACKET P/N 0712042-1 WAS FOUND TO HAVE (2) SHEARED RIVETS.  THESE	 PARTS ARE IN THE MFG 180/185 IPC FIG 32 INDEX NR 36 AND NR 37.THERE IS NOTHING IN THE RECORDS THAT SHOW THESE PARTS CHA	NGED, HOWEVER THE RT BRACKET DID HAVE (2) NR 5 RIVETS WHERE ALL OF THE REST ON BOTH BRACKETS WERE NR 4S.  LEADING US TO 	BELIEVE THAT IT MAY HAVE BEEN REPLACED BEFORE.		1	H	7	1 	3O	3	O		3A24    	E5CE				 
2007032200098	20070322	00098	CE  	2007	3	22	2007FA0000246    	1	20070313	G	2820	050011849	LINE            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	CHAFED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	30LU	847  				17281257				DURING PREFLIGHT INSP. PILOT FOUND FUEL ON RAMP UNDER CENTER FUSELAGE  MECHANIC INVESTIGATED INSIDE COCKPIT FLOOR AND FO	UND ALUMINUM FUEL LINE CHAFING AGAINST RT STEERING TUBE, CAUSING THE FUEL LEAK. MECHANIC INSPECTED 6 OTHER 2005/2006 172	R AIRCRAFT IN OUR FLEET AND FOUND CHAFING IN (3) OTHER AIRCRAFT, WITH ANOTHER LEAK IMMINENT. ALL AC UNDER 900 HRS AFTT. 	OUR AIRCRAFT CAME FROM THE FACTORY WITH THIS FUEL LINE/STEERING TUBE CONFIGURATION. SUBMITTER SUGGESTS IMMEDIATE INSPECT	ION FOR THIS CONDITION. NOTE: FUEL WAS NOT SMELLED IN COCKPIT.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007032200140	20070322	00140	CE  	2007	3	22	2007FA0000247    	1	20070227	G	7160	11702	CLAMP           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520L    	17040	SO  					LT ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	25RL					TJ232	0			LT ENGINE REPORTED TO BE ROUGH RUNNING.  INDUCTION HOSE CLAMP(P/N-RAM 1170-2)FAILED; ALLOWING INDUCTION COUPLER(P/N-6323	23) TO SEPARATE FROM INDUCTION TUBE. THIS INDUCTION LEAK OCCURRED BETWEEN THE Y AND INTAKE TUBES TO CYLINDERS NR 2, NR 4	 AND NR 6.				1	L	7	2 	3O	3	O		A23CE   	E8CE				 
2007032600107	20070326	00107	CE  	2007	3	26	2007FA0000253    	1	20070307	G	2720	65651412	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR	BINDING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	797CW	8177 	300  			0232				WHILE REPLACING TRIM ACTUATOR P/N 6565141-2 WITH WHAT MFG SAID WAS AN APPROVED SUB PART P/N 5565450-92.   IT WAS FOUND T	HAT THE LOLLIPOPS (JACK SCREWS) WERE 5.5 INCHES LONG AND THE ORIGINAL LOLLIPOPS ARE 5.75 INCHES LONG. IF YOU LOOK AT THE	 COMPONENT MANUAL FOR THIS ACTUATOR 6565141-2 IT SHOWS 4 DIFF. DASH NUMBERS. -4 AT 5.5 INCHES, -7 AT 5.5 INCHES, -15 AT 	4.85 INCHES, AND -21 AT 5.75 INCHES ALL WHICH IS TO THE SAME LOLLIPOP P/N. THE -92 ACTUATORS FITS UNITS 692 TO 924, WHIL	E OUR UNIT IS 232. MFG NEEDS TO FIX THESE P/NS AND CLEAR THE WAY THESE MANUALS ARE WRITTEN FOR CLARITY. TO MANY ACTUATOR	S ARE TO ANOTHER P/N WITH INCORRECT JACKSCREW LENGTHS.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007032600116	20070326	00116	CE  	2007	3	26	2007FA0000256    	1	20070314	G	7810	655503011	DUCT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					EXHAUST ASSY	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13	797CW					5500232				DURING INSPECTION MULTIPLE PATCHES WERE FOUND ON EXHAUST DUCT ASSY P/N 6555030-11. A REPLACEMENT WAS ORDERED AND FOUND T	O HAVE 2 HOLES MISDRILLED BY 2 DEGREES. MFG WAS CONTACTED AS TO WHAT COULD BE DONE AND AFTER CONFIRMING THAT IN TRUTH 2 	HOLES WERE NOT PROPERLY PLACED WE WERE TOLD THAT IN FACT 4 DUCTS WERE FOUND NOT BUILT CORRECTLY AND 1 HAD GOTTEN TO THE 	FIELD. MFG HAS AGREED TO ACCEPT THE DUCT BACK FOR REPAIR BUT WANTS TO BILL US FOR THE FIX ON A NEW PART. AFTER REPAIR, W	E ARE TO SUBMIT FOR FINANCIAL REIMBURSEMENT FOR THERE ENGINEERING REPAIR.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007032600125	20070326	00125	EA  	2007	3	26	2007FA0000257    	2	20070224	G	8530		ROCKER SHAFT    			UNIVAR	108   	1081        	9230404	NM  	FRNKLN	6A4150	6A4150*     	27024	EA  					NR 3 CYLINDER	BROKEN          	G				B				EMER. DESCENT           				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	11	9088K					1082088				THE NR 3 CYLINDER ROCKER ARM SHAFT FAILED (BROKE) AT THE CENTER SUPPORT POSITION.  ADDITIONALLY, (2) OF THE (3) ROCKER A	RM BOSS SECURING BOLTS FAILED AND THE THIRD BOLT PULL OUT OF THE HEAD.					1	H	7	1 	3O	3	O		A767    	E238				 
2007032600127	20070326	00127	CE  	2007	3	26	2007FA0000258    	1	20070301	G	3210	MS2764816	BEARING         			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					LT MLG	SEIZED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	19RK	9280 				LA12				PERFORMING A ROUTINE 6 YEAR LANDING GEAR OVERHAUL, THE LT LANDING GEAR GEARBOX-ACTUATOR TORQUE TUBE HAD A SEIZED MAIN SU	PPORT BEARING. THIS MADE THE TORQUE TUBE EXTREMELY HARD TO TURN. THE BEARING WAS FOUND TO BE RUSTED, AND SEIZED. BEARING	 WAS REPLACED WITH NEW.				1	L	7	2 	4T	4	T		A31CE   	E4EA				 
2007032600128	20070326	00128	SO  	2007	3	26	2007FA0000259    	1	20070301	G	8000	PM1201	STARTER         			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  	HARTZL	HCF3Y	HCF3YK1     	GL  	ENGINE	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2177Z	28   	28   			287911154	L2117640A	CM288		THIS AIRCRAFT HAS HAD (5) PM1201 STARTERS INSTALLED SINCE 03-08-2004. THE STARTERS HAD TO BE REPLACED AT THE FOLLOWING I	NTERVAL: 58 HOURS TIME IN SERVICE, 18 HOURS TIME IN SERVICE, 11 HOURS TIME IN SERVICE, 5 HOURS TIME IN SERVICE, 28 HOURS	 TIME IN SERVICE.  ALL STARTERS SUFFER THE SAME PROBLEM. AFTER THE ENGINE IS STARTED AND THE AIRCRAFT HAS FLOWN FOR A SH	ORT PERIOD OF TIME, (LESS THAN ONE HOUR) THE BENDIX GEAR WILL BEGIN TO CREEP OUT AND TRY TO ENGAGE/RUB THE RING GEAR.  I	N FEW FLIGHT HOURS THE BENDIX GEAR WILL START SHOWING WEAR ON BOTH THE BENDIX GEAR AS WELL AS THE RING GEAR ON THE FLYWH	EEL.  ALL THE STARTERS WERE REPORTED TO HAVE HAD THE SAME PROBLEM.  THE OWNER DECIDED TO REMOVE THE STARTER FROM HIS AIR	1	L	7	1 	3O	3	O		2A13    	E295	5	C	P31EA	 
2007040300082	20070403	00082		2007	4	3	2007FA0000260    	3	20070219	G	6111	3BLADEWOOD68	PROPELLER       			AMTR  	KITFOX	KITFOX41200 	05626LB	GL  										PROPELLER	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	11	880BW	219  	6    			C96010137				OWNER REPORTED 5 MINUTES AFTER TAKEOFF AT 2500 ASL, ALL 3 PROPELLER BLADES DEPARTED.  THERE WAS ONE VIOLENT SHAKE AND TH	EN SMOOTH GLIDING TO SAFE LANDING OFF AIRPORT.  PRELIMINARY EXAM INDICATES ENGINE MOVED ENOUGH TO CAUSE CARBURETOR TO SE	PARATE PREVENTING OVERSPEED.  SEPARATED BLADES WERE NEVER LOCATED.  PROPELLER TO BE REPLACED BY OWNER, THIS IS AN EXPERI	MENTAL HOMEBUILT AIRCRAFT.			1	H	7	1 	3I			NC	EXPA1H71					 
2007032600060	20070326	00060	CE  	2007	3	26	2007FA0000261    	1	20070322	G	5210	99120754	SEAL            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN DOOR SEAL	MISMANUFACTURED 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	797CW	8177 	300  			5500232				WHILE INSTALLING THIS FACTORY NEW SEAL IT WAS NOTED THAT THE SEAL WAS VERY TIGHT GOING AROUND THE DOOR. UPON CABIN PRESS	 TEST THE SEAL WILL NOT INFLATE DUE TO BEING TO TIGHT.  (2) SEAL FROM STOCK WERE TRIED WITH THE SAME AFFECT. THE LAST SE	AL WAS INSTALLED AND INFLATED AS SHOULD BE. THE FACTORY NEEDS TO CHECK THERE SEALS CLOSER UPON RECEIPT FROM THERE VENDOR	S.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007032600085	20070326	00085	CE  	2007	3	26	2007FA0000262    	1	20070322	G	7810	655503011	DUCT            			CESSNA	500   	550         	2076604	CE  										ENGINE	UNKNOWN         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	797CW	8177 	300  			5500232				UPON RECEIVING THE NEW PART P/N 6555030-11 IT WOULD NOT FIT THE ENGINE. THE ORIGINAL DUCT IS 27 .2500 INCH OUTSIDE AND 2	5.5 INCH INSIDE. THE NEW UNIT IS A FULL .5 INCH SMALLER IN DIAMETER ALL AROUND. THIS IS THE SECOND ISSUE WITH THESE DUCT	S THE FIRST WERE MIS-DRILLED BY 2 DEGREES AT THE 1 AND 5 OCLOCK POSITION. THIS NEW DUCT IS NOT EVEN CLOSE TO FITTING.				1	L	7	2 	4F				A22CE   					 
2007040300037	20070403	00037	EU  	2007	4	3	2007FA0000263    	1	20070321	G	7600	L810BQ54	SOLENOID        			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					AUTO THROTTLE	UNSERVICEABLE   	B			N37R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	186AE	189  				3872	22484			(REF NR: 186AE-2007-I-0032) WHILE PERFORMING A CHECK OF THE TWIST GRIP SOLENOID, ENGAGED THE SOLENOID BY PLACING THE AUT	O/MAN SWITCH TO MAN  MODE FOR A TOTAL OF 10 MINUTES.  AFTER THE 10 MINUTE PERIOD HAD ELAPSED, RETURNED THE AUTO/MAN SWIT	CH TO AUTO.  AFTER 15 MINUTES MOVED AUTO/MAN SWITCH BACK TO MAN, THE PISTON FROM THE SOLENOID FAILED TO MOVE.  THE PISTO	N SHOULD HAVE RETRACED IMMEDIATELY.  PROBABLE CAUSE: SOLENOID OVERHEATING AND MALFUNCTIONING.  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				 
2007040200157	20070402	00157	SO  	2007	4	2	2007FA0000264    	1	20070306	G	5350	1159B541014	FAIRING         			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700715A130	 	NE  					FUSELAGE	DEPARTED        	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CE	07	401HF	1300 				5039				ON MARCH 6, 2007, DURING A FLIGHT, THE SUBJECT AIRCRAFT EXPERIENCED AN IAPPARENT IN-FLIGHT STRUCTURAL FAILURE OF THE RIG	HT WING-TO FUSELAGE FORWARD FAIRING.  THE INCIDENT OCCURRED AT FLIGHT LEVEL 400 AT 90 DME ON THE (LNK) VOR 220 RADIAL AT	 .85 MACH.  AFTER ONE HOUR AND 45 MINUTES INTO THE FLIGHT (APPROX 2115Z), THE CREW NOTED AN AUDIBLE (THUMP) FOLLOWED BY 	A (CHANGE IN WIND NOISE).  AS THE AIRCRAFT IS EQUIPPED WITH PROXIMITY CAMERAS, THE FIGHT CREW WAS ABLE TO SEE A (HOLE OF	 SIGNIFICANT SIZE) IN THE AREA OF THE SINGLE POINT REFUELING ACCESS DOOR USING THE LOWER AFT-FACING FUSELAGE CAMERA.  TH	E FLIGHT CREW NOTIFIED AND REQUESTED EMERGENCY LANDING, WHERE THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  THE FSDO WA	2	L	7	2 	4F	4	F	RT	A12EA   	E00061EN				 
2007040200134	20070402	00134	CE  	2007	4	2	2007FA0000265    	1	20070322	G	2910	270213	REGULATOR       			LEAR  	60    	60LEAR      	5170707	CE  										HYD SYS PRESSURE	LEAKING         	C				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	11	500	105  				306				IN-FLIGHT FAILURE OF BOTH ENGINE HYDRAULIC PUMPS, AND LOSS OF MAIN HYDRAULIC SYSTEM FLUID.  AC DIVERTED TO HOME BASE, DE	CLARED EMERGENCY LANDING, UNEVENTFUL.  FOUND PRESSURE HOSE ON R ENGINE HAD FAILED, DUE TO OVER-PRESSURE.  FOUND RESERVOI	R AIR-PRESSURE REGULATOR (PN 2702-12) HAD FAILED, CAUSING LOSS OF HEAD PRESSURE IN RESERVOIR, AND SUBSEQUENT PRESSURE SP	IKES IN ENGINE PUMPS, WHICH BURST FLEX LINE ON R ENGINE HYD PUMP, AND DAMAGED FLEX LINE ON L HYD PUMP AS WELL.  REPLACED	 L AND R ENGINE HYDRAULIC PUMPS, ALL FLEX PRESSURE LINES IN ENGINE HYDRAULIC CIRCUIT, HYDRAULIC FILTERS, RESERVOIR PRESS	URE REGULATOR, CHECK VALVE, AND FILTER. BLED AIR FROM HYDRAULIC SYSTEM, PERFORMED FUNCTIONAL TESTS AND GROUND RUN, REPL	2	L	7	2 	4F			RT	A10CE   					 
2007050700003	20070507	00003	CE  	2007	5	7	2007FA0000266    	1	20070315	G	5510		HINGE BRACKET   			BEECH 	23    	A23         	1151204	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	STABILATOR	CRACKED         	B			MS2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	3573R	3596 				M756	1002075A	8623		UPON REMOVAL OF THE HORIZONTAL STABILATOR FOR BEARING REPLACEMENT, A CRACK WAS NOTED COMING OUT FROM UNDER THE LEFT HING	E BRACKET THAT IS RIVETED TO THE SPAR OF THE HORIZONTAL STABILATOR.  (K)					1	L	7	1 	3O	3	O		A1CE    	E3CE	5	N	P88614	 
2007040200222	20070402	00222	EU  	2007	4	2	2007FA0000267    	1	20070228	G	8120	4066109031	BEARING         			SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					TURBOCHARGER	FAILED          	B			BNGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	189GT	685  				2022	21052261A			IN FLIGHT, DROP IN MANIFOLD PRESSURE, TROUBLESHOT, FOUND TURBOCHARGER BEARING FAILURE.  FOUND METAL IN OIL FILTER.  ENGI	NE REMOVED FOR REPAIR.  (K)					1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
2007032900291	20070329	00291	SW  	2007	3	29	2007FA0000268    	1	20070308	G	2910	20144	B-NUT           			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	TIO540A1A   	41532	EA  					LT MLG	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	280MB					3255				PILOT NOTICED A FLUCTUATION AND LOSS OF HYDRAULIC PRESSURE IN FLIGHT, AFTER INSPECTION THE FORWARD HYDRAULIC HOSE B-NUT 	ON THE LT GEAR ACTUATOR WAS FOUND TO BE LOOSE.  THE B-NUT WAS TIGHTENED AND TORQUE SEAL WAS PUT ON THE B-NUT.  SERVICED 	HYDRAULIC RESERVOIR WITH H-5606.  AC WAS TEST FLOWN AND LEAK CHECK GOOD.  (K)				1	H	7	2 	3O	3	O		6A1     	E14EA				 
2007040200129	20070402	00129	CE  	2007	4	2	2007FA0000269    	1	20070321	G	6100		NONE            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER	UNKNOWN         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	427DM					LJ804				AIRCRAFT  HAS RAISEBECK STC SA3593NM INSTALLED WHICH STATES THE PROPS ARE NOT TO BE OPERATED BELOW THE SET MINIMUM RPM. 	PRE PHASE INSPECTION RUNS REVEALED THIS CONDITION. IAW MFG SERVICE LETTER 61-254 THIS CAN CAUSE  NO REACTION MODE VIBRAT	ORY RESONANCE AND MAY RESULT IN HIGH STRESS IN THE BLADES. IT WAS RECOMMENDED THAT THE PROPELLERS BE REMOVED AND BE SENT	 TO A PROPELLER SHOP FOR INSPECTION.  CUSTOMER DECLINED RECOMMENDATION. NO FURTHER ACTION WAS TAKEN AT THIS INSPECTION. 	 BOTH THE LT AND RT PROPELLERS HAVE A TSO OF 957.9 AND A TT OF 2615.2		1	L	7	2 	3T	4	T		3A20    	E4EA	5	C	STC	 
2007040300049	20070403	00049	CE  	2007	4	3	2007FA0000270    	1	20070326	G	2710	35524314	CONTROL CABLE   			BEECH 	35    	N35         	1151528	CE  	CONT  	O470  	IO470*      	17026	SO  					AILERONS	WORN            	C				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	23	1363Z	7541 				D6787				(REF MODEL 35 SERIES IPC FIG. 27)  LT AILERON CABLE FOUND RIDING ON PROP CONTROL CABLE SHEATH, ABOUT 2 INCHES AFT OF FIR	EWALL.  AILERON CABLE WAS WORN ABOUT HALF THROUGH, AND THE PROP CABLE WAS WORN THROUGH THE SHEATH TO THE INNER STEEL CAB	LE. (VERY DIFFICULT TO ACCESS THIS AREA FOR VISUAL INSPECTION.)  NO INDICATION OF RUBBING OR DRAGGING DURING GROUND CONT	ROL SYSTEM CHECKS, OR IN FLIGHT.  IT IS RELATIVELY EASY TO HAVE THE PROP CONTROL CABLE DISPLACED INTO CONTACT WITH THE A	ILERON CABLE WHEN WORKING IN THIS AREA DURING, FOR EXAMPLE, PANEL MODIFICATIONS OR AVIONICS UPGRADES.  RECOMMEND VISUAL 	AND TACTILE INSPECTION IN THIS AREA TO CONFIRM CLEARANCE.  UPON REMOVAL OF CABLE ASSEMBLY FOR REPLACEMENT, FOUND ADDITIO	1	L	7	1 	3O	3	O		3A15    	E1CE				 
2007040300039	20070403	00039	CE  	2007	4	3	2007FA0000274    	1	20070322	G	2910	270213	REGULATOR       			LEAR  	60    	60LEAR      	5170707	CE  										HYD SYSTEM	LEAKING         	C				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	11	500	105  				306				IN-FLIGHT FAILURE OF BOTH ENGINE HYDRAULIC PUMPS, AND LOSS OF MAIN HYDRAULIC SYSTEM FLUID.  AIRCRAFT DIVERTED TO HOME BA	SE, DECLARED EMERGENCY LANDING, UNEVENTFUL.  FOUND PRESSURE HOSE ON R ENGINE HAD FAILED, DUE TO OVER-PRESSURE.  FOUND RE	SERVOIR AIR-PRESSURE REGULATOR (PN 2702-12) HAD FAILED, CAUSING LOSS OF HEAD PRESSURE IN RESERVOIR, AND SUBSEQUENT PRESS	URE SPIKES IN ENGINE PUMPS, WHICH BURST FLEX LINE ON R ENGINE HYD PUMP, AND DAMAGED FLEX LINE ON L HYD PUMP AS WELL.  RE	PLACED L AND R ENGINE HYDRAULIC PUMPS, ALL FLEX PRESSURE LINES IN ENGINE HYDRAULIC CIRCUIT, HYDRAULIC FILTERS, RESERVOIR	 PRESSURE REGULATOR, CHECK VALVE, AND FILTER. BLED AIR FROM HYDRAULIC SYSTEM, PERFORMED FUNCTIONAL TESTS AND GROUND RUN,	2	L	7	2 	4F			RT	A10CE   					 
2007040200160	20070402	00160	GL  	2007	4	2	2007FA0000276    	1	20070306	G	5551		BOLT            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	HORIZ STAB	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	921DA					C0395	650218	AG5429		AC, RETURN FROM FLIGHT WITH BOTH BOLTS BROKEN; ATTACHING THE FORWARD HORIZONTAL STABILIZER MOUNT BRACKETS.  ATT 1) GIVES	 FLIGHT INFO.  ATT 2 AND 3) SHOW THE IPB BRAKE DOWN OF THE BOLTS AND LOCATION FROM MFG PARTS BOOK.  ATT 4) PICTURES OF B	OLTS AND AIRCRAFT.  ATT 5) THE NTSB PAPERWORK.  ATT 6) IS SOME EMAIL TRAFFIC.  WE REMOVED THE RUDDER AND HORIZONTAL STAB	ILIZER TO INSPECT ENTIRE AREA. WE REPLACE THE AFT MOUNT PLATE AND FORWARD MOUNT BRACKET ALONG WITH ALL NEW BOLTS, WASHER	S AND NUTS.  WE ALSO INSPECTED OUR OTHER 9 AC AND REPLACED BOTH BOTH ON ALL 9 AC.  NO OTHER ISSUES WERE FOUND ON OUR OTH	ER AC.  MFG HAS BEEN BRIEFED AND IS WORKING WITH THE NTSB.  (K)	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007050700023	20070507	00023	SO  	2007	5	7	2007FA0000277    	2	20070322	G	8520	A049405N	CRANKSHAFT      								CONT  	O360  	TSIO360EB   	17025	SO  					ENGINE	FAILED          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19							A049405U			CRANKSHAFT FAILED NDI SB MSB96-10.  (K)											3	O			E9CE				 
2007040900058	20070409	00058	CE  	2007	4	9	2007FA0000279    	1	20070228	G	3220	45A3952211	UPLOCK          			BEECH 	MU300 	400A        	1155402	CE  										NLG	OUT OF ADJUST   	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	123QS	243  				RK486				FLIGHT CREW REPORTED RED LANDING GEAR HANDLE WARNING LIGHT STAYING ILLUMINATED AFTER GEAR RETRACTION.  LANDING GEAR CYCL	ED SEVERAL TIMES, HANDLE WARNING LIGHT STAYED ILLUMINATED.  FOUND NOSE LANDING GEAR UPLOCK NOT FULLY ENGAGING ADJUSTED N	OSE LANDING GEAR UPLOCK AS REQUIRED IAW THE MM.  LANDING GEAR RETRACT/ EXTENSION CHECKS OK, NO FAULTS NOTED.  HAVE NOTED	 THIS FAULT ON LOW TIME AC SEVERAL TIMES, PARTICULARLY DURING COLD WEATHER OPERATION UPLOCK ADJUSTMENT FAULTS USUALLY SH	OW UP DURING MM FUNCTIONAL TESTS DURING THE LOW PRESSURE/LOW FLOW TESTS.  (K)		2	H	7	2 	4F			RT	A16SW   					 
2007040200164	20070402	00164		2007	4	2	2007FA0000280    	1	20070312	G	3230	452552	BEARING         																	LANDING GEAR	INACCURATE      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03										PN 96522-00, CENTERING SPRING ASSY, HAS A ROD END BEARING ON THE END OF THE SHAFT, WHICH BOLTS TO THE IMOVABLE PORTION O	F THE NOSE GEAR.  ORIGINAL ROD END BEARING IS .375 INCH THICK WHERE BOLT GOES THRU.  NEW ROD END BEARING THAT COMES WITH	 PN 96522-00 ASSY, IS .433 INCH THICK AND RELOCATES CLEVIS BOLT PN AN24-20A .0625 INCH DOWNWARD (UNFAVORABLE) AND CONTRA	DICTS REQUIREMENTS OF MFG MSB 893.  (K)																 
2007050400162	20070504	00162	CE  	2007	5	4	2007FA0000284    	1	20070317	G	5740	NAS1738B	ATTACH FITTING  			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					WING	LOOSE           	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	1525C	5500 				FL88				MANY OF THE BLIND RIVETS, PN NAS1738B6, ATTACHING THE WING SKIN TO THE LOWER FORWARD WING ATTACHMENT FITTING WERE FOUND 	TO BE LOOSE.  CONDITION EXISTED ON BOTH WINGS.  CONDITION ALSO FOUND ON AC SN FL59 (8100 HRS).  (K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007050400205	20070504	00205	GL  	2007	5	4	2007FA0000285    	2	20070319	G	7323	23065121	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FROZEN          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	CGPHC		293  			180257D				DURING AN INSPECTION IT WAS NOTED THAT THE BEAING RETAINING WASHER FOR THE ROD END WAS INCORRECT.  AFTER THE BOLT WAS RE	MOVED IT WAS THEN DISCOVERED THAT THE THROTTLE ARM WAS SEIZED UP ON THE GOVERNOR, REPLACED GOVERNOR.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007040200159	20070402	00159	GL  	2007	4	2	2007FA0000286    	1	20070322	G	7120	11925003	MOUNT           			CIRRUS	SR    	SR20        	05628AJ	GL  										ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	155CD	2058 				1058				ENGINE MOUNT RT FRONT CROSSOVER TUBE BETWEEN LT AND RT ENGINE SUPPORTS FOUND BROKEN AT THE WELD RT SIDE.  ENGINE WAS CHA	NGED ABOUT 250 HRS AGO, NO MENTION OF ENGINE MOUNT DAMAGE.  COULD HAVE BEEN A HARD LANDING, BUT NO OTHER SIGNS WERE NOTE	D.  CONTACT WITH MFG SAYS NO OTHER REPORTS HAVE BEEN FILLED.  (K)				1	L	7	1 	3O			NT	A00009CH					 
2007040200166	20070402	00166	SW  	2007	4	2	2007FA0000287    	1	20070322	G	7110		RIVET           			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					COWLING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	9156X					243253				OWNER BROUGHT COWLINGS IN FOR REPAIR BECAUSE THE THROUGH SKIN RIVETS WERE CORRODING AND SHEARING OFF AT THE MFG HEAD AS 	EXHIBITED BY BLISTERING PAINT AT THE RIVET LOCATIONS.  INSPECTION REVEALED MOST OF THE AD TYPE RIVETS WERE SEVERELY CORR	ODED BECAUSE THE COWLINGS WERE CONSTRUCTED WITH A HYBRID COMPOSITE LAMINATE OF E-GLASS AND CARBON GRAPHITE PLIES.  IT IS	 STANDARD INDUSTRY PRACTICE TO USE CORROSION RESISTANT FASTENERS SUCH AS RIVETS THROUGH CARBON GRAPHITE STRUCTURE AND IT	 IS UNKNOWN WHY ALUMINUM RIVETS ARE USED IN THIS CASE.  AFFECTED AREAS: UPPER COWL/ OIL DOOR CUTOUT DOUBLER RIVETS COOLI	NG AIR INLET AFT EDGE RIVETS.  LOWER COWL/ BOTH UPPER CAMLOCK RECEPTACLE GANG STRIPS (SEVERELY CORRODED AND CONCEALED BY	1	L	7	1 	3O	3	O		2A3     	1E10				 
2007040300032	20070403	00032	SO  	2007	4	3	2007FA0000288    	1	20070402	G	5321	37829007	FLOOR PANEL     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					FUSELAGE	DEBONDED        	D			IBIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	682JK	968  				3449154	322291			FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR 	PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM.  THE SEAT MOUNTING BR	ACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE.  CALLED MFG FOR GUIDANCE, BUT HAVE NOT HEAR	D ANYTHING AS YET.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007040300033	20070403	00033	SO  	2007	4	3	2007FA0000289    	1	20070402	G	5321	37829007	FLOOR PANEL     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					ZONE 100	DEBONDED        	D			IBIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	682JK	968  				3449154	322291			FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING.  THE FLOOR	 PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM.  THE SEAT MOUNTING B	RACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE.  CALLED MFG FOR GUIDANCE, BUT HAVE NOT HEA	RD ANYTHING AS YET.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007040300034	20070403	00034	SO  	2007	4	3	2007FA0000290    	1	20070402	G	5321	37829007	FLOOR PANEL     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					ZONE 100	DEBONDED        	D			IBIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	682JK	968  				3449154	322291			FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR 	PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM.  THE SEAT MOUNTING BR	ACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE.  HAVE CALLED MFG FOR GUIDANCE, BUT HAVE NOT	 HEARD ANYTHING AS YET.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007040300035	20070403	00035	SO  	2007	4	3	2007FA0000291    	1	20070402	G	5321	37829007	FLOOR PANEL     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					ZONE 100	DEBONDED        	D			IBIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	682JK	968  				3449154	322291			FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING.  THE FLOOR	 PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM.  THE SEAT MOUNTING B	RACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE.  HAVE CALLED MFG FOR GUIDANCE, BUT HAVE NO	T HEARD ANYTHING AS YET.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007040300036	20070403	00036	SO  	2007	4	3	2007FA0000292    	1	20070402	G	5321	37829007	FLOOR PANEL     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					ZONE 100	DEBONDED        	D			IBIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	682JK	968  				3449154	322291			FLOORPANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING.  THE FLOOR 	PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM. THE SEAT MOUNTING BRA	CKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE.  HAVE CALLED MFG FOR GUIDANCE, BUT HAVE NOT 	HEARD ANYTHING AS YET.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007050400135	20070504	00135	CE  	2007	5	4	2007FA0000293    	1	20070322	G	7830		LINK            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					THRUST REVERSER	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	413LC	6894 				5600003	PCE108003			ALL DRIVE LINK PIVOT BOLTS AND OVER CENTER LINKS SEVERELY CORRODED AND WORN.  PROBABLE CAUSE IS INADEQUATE LUBE.  MANUAL	 STATES TR`S MUST BE TORN DOWN AND LUBED UPON ASSEMBLY AT SPECIFIC INTERVALS.  ENGINEERING STATES THAT TEARDOWN IS NOT N	ECESSARY AND ON WING LUBRICATION IS ADEQUATE.  THESE FINDINGS INDICATE OTHERWISE.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007050400141	20070504	00141	CE  	2007	5	4	2007FA0000294    	1	20070222	G	3610	1H1069	MIXING VALVE    			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					LT ENGINE	INTERMITTENT    	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	500	83   				306				SHORTLY AFTER TAKEOFF, AIRCRAFT (LT BLEED AIR) WARNING ILLUMINATED, AND (RT BLEED AIR) WARNING ILLUMINATED APPROX 5 SEC 	LATER, SMELLED ODOR IN MAINTENANCE.  UNABLE TO DUPLICATE MALFUNCTION ON GROUND RUN; LT MIXING VALVE WAS SUSPECTED, SO RE	PLACED.  PERFORMED GROUND RUN FUNCTIONAL TEST OF BLEED AIR SYSTEM, AND FLIGHT TEST.  NO FURTHER BLEED AIR WARNINGS.  (K)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007040600160	20070406	00160	CE  	2007	4	6	2007FA0000295    	1	20070320	G	8120		BEARING         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					TURBOCHARGER	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	3247M	1031 			FKL00044	414A0828				FAILURE OF RT TURBOCHARGER SEAL AND CENTER BEARING CAUSED SMOKE OUT OF EXHAUST AND SQUEALING NOISE RESULTING IN THE FLIG	HT CREW TO FEATHER PROPELLER AND SHUTDOWN THE ENGINE.  CAUSE OF FAILURE DO TO WEAR. (K)					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007040900008	20070409	00008	SW  	2007	4	9	2007FA0000297    	1	20070305	G	6410	HAC473	BLADE           			BELL  	47    	47G5        	1181032	SW  	LYC   	O435  	VO435*      	41516	EA  					TAIL ROTOR	DAMAGED         	B			ECGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1202W					7857				THE STAINLESS STEEL ABRASION STRIP ON THE LEADING EDGE OF THE COMPOSITE TAIL ROTOR BLADE SEPARATED FROM BLADE IN FLIGHT.	  PILOT NOTED A VIBRATION IN A SPRAY TURN AND ELECTED TO LAND; AND LANDED SAFELY (NO INJURIES).					1	G	7	1 	3O	3	O		2H3     	E279				 
2007050400145	20070504	00145	SO  	2007	5	4	2007FA0000298    	1	20070320	G	2400	100201021346	INVERTER        			GULSTM	GVSP  	GVSPG550    	3980203	SO  	GE    	CF34  	CF343A      	30066	NE  						SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	05	5PG	1383 				5046				WHEN TURNING MAIN BATTERY SWITCHES ON, MECHANIC HEARD A LOUD POPPING SOUND, FOLLOWED BY THE AROMA OF SMOKE IN THE ENTRAN	CE AREA OF THE AIRCRAFT.  THE FLOORBOARD WAS REMOVED AND FOUND THAT WATER FROM THE FORWARD LAVATORY AREA HAD BEEN RUNNIN	G ONTO THE TOP OF THE EMERGENCY INVERTER CAUSING H2O AND AC VOLTAGE TO MEET (H2O WON).  THE LAV AREA ON BOTH OF OUR AC W	ERE INSPECTED FOR LEAKS AND FOUND AREAS WHERE WATER HAD BEEN SITTING, EVEN THROUGH THERE WERE NO LEAKS.  IT IS POSSIBLE 	THAT WHEN STOWING THE SINK (HINGED AND FOLDS UP INTO A CLOSEOUT) RESIDULE WATER IS DUMPING INTO THE CLOSEOUT.  THE INVER	TER WAS REPLACED AND WE SHUT THE WATER SUPPLY OFF FOR THE FORWARD LAY SINK ON BOTH.  THERE IS NO PREFLIGHT OR SCHEDULED	2	L	7	2 	4F	4	F	RT	A12EA   	E15NE				 
2007050400148	20070504	00148	CE  	2007	5	4	2007FA0000299    	1	20070326	G	2820	050011849	LINE            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	2470N	400  				172S10070				FOUND FUEL LINE PN 05001( 8-49, FUEL RETURN  LINE TO RESERVOIR WORN BY RUBBING ON NOSE STEERING ROD JUST BEHIND FIREWALL	.  INSTALLED NEW LINE SO AS NOT TO RUB ON STEERING.  INSTALLED SPIRAL WRAP ON AREA WHERE RUBBING HAD OCCURRED.  NOTE: FU	EL LINE WAS WORN TO POINT OF LEAKING.  RECOMMEND INSPECTING NEW AC FOR PROPER LINE INSTALLATION.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007050400144	20070504	00144	CE  	2007	5	4	2007FA0000300    	1	20070327	G	3240	16011800	HOUSING         	CLEVELAND   		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	BRAKE CALIPER	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	PKMPS				017	208B0656	PCEPC0548	001276		THE MAIN CASTING, WHICH HOUSES THE BRAKE CALIPER PISTONS LEAKS FLUID UNDER NORMAL BRAKING PRESSURE.  THE LEAKS ARE FROM 	EXCESSIVE POROSITY IN THE CASTING.  CASTING  THIS IS THE SECOND OCCURRENCE IN OUR OPERATIONS.  THE FIRST WAS NOT REPORTE	D.  (K)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2007040600163	20070406	00163	CE  	2007	4	6	2007FA0000301    	1	20070406	G	1400		NUT             			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  						MISMANUFACTURED 	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	949SP					172S8145				WHILE INSTALLING KIT MK172-25-10C TO COMPLY WITH SB 04-25-01 R4 AND AD 2007-05-10, ONE OF THE PARTS IN THE KIT WAS MACHI	NED IMPROPERLY. THE HEIGHT ADJUSTING NUT HAD THE THRU HOLE FOR THE ULTRALOC WITH MIS FORMED THREADS. THE MINOR DIAMETER 	OF THE THREAD WAS GREATER THAN THE MAJOR DIAMETER OF THE THREADS ON THE ULTRALOC. THE CROSS HOLE FOR MOUNTING WAS INCORR	ECTLY LOCATED WITH INSUFFICIENT EDGE DISTANCE, AND THE PILOT HOLE WAS OFFSET GIVING AN EGG SHAPED HOLE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007040900036	20070409	00036	CE  	2007	4	9	2007FA0000302    	1	20070403	G	2731	65651412	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR TRIM	BINDING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	5314J	5592 	300  			5500663				AFTER A PHASE 1-4 INSPECTION THE ELEVATOR TRIM WAS FOUND TO BE BINDING. INSPECTION OF THIS SYSTEM FOUND THAT THE WILKIE 	BUTTON IN THE BACK OF THE ACTUATOR TRIM JACK SCREWS HAD COME OUT AND WAS BINDING THE TRIM CHAIN AND SPROCKETS. WHEN THE 	ACTUATORS ARE LUBED THE WILKIE BUTTONS HAVE A TENDENCY TO POP OUT OF THERE PLACE IF YOU DONT LOOK CLOSELY AFTER LUBING T	HESE ACTUATORS THE GREASE PUSHES THESE PLUGS OUT AND THEY STICK TO THE INTERCONNECT CHAIN CAUSING A BINDING CONDITION. T	HIS COULD ALSO HAPPEN IN FLIGHT CAUSING A LIKE CONDITION WITH MORE DIRE PROBLEMS. I THINK MFG SHOULD REMOVE THIS PLUG OR	 MORE SECURELY FIX THIS PLUG IN PLACE.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007040900037	20070409	00037	CE  	2007	4	9	2007FA0000303    	1	20070403	G	2731	65651412	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ZONE 200	BINDING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	5314J	5592 	300  			5500663				AFTER A PHASE 1-4 INSPECTION THE ELEVATOR TRIM WAS FOUND TO BE BINDING. INSPECTION OF THIS SYSTEM FOUND THAT THE WILKIE 	BUTTON IN THE BACK OF THE ACTUATOR TRIM JACK SCREWS HAD COME OUT AND WAS BINDING THE TRIM CHAIN AND SPROCKETS. WHEN THE 	ACTUATORS ARE LUBED THE WILKIE BUTTONS HAVE A TENDENCY TO POP OUT OF THERE PLACE IF YOU DONT LOOK CLOSELY AFTER LUBING T	HESE ACTUATORS THE GREASE PUSHES THESE PLUGS OUT AND THEY STICK TO THE INTERCONNECT CHAIN CAUSING A BINDING CONDITION. T	HIS COULD ALSO HAPPEN IN FLIGHT CAUSING A LIKE CONDITION WITH MORE DIRE PROBLEMS. I THINK MFG SHOULD REMOVE THIS PLUG OR	 MORE SECURELY FIX THIS PLUG IN PLACE.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007040900020	20070409	00020	CE  	2007	4	9	2007FA0000308    	1	20070402	G	3211	508103437	PIN             			BEECH 	200   	B200        	1152922	CE  										LT MLG	BROKEN          	E				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	05	65TW	6551 	6551 			BB902				UPON EXTENDING THE LANDING GEAR, THE PILOTS GOT A RED GEAR UNSAFE LIGHT IN THE HANDLE, AND THE LT DOWN AND LOCKED LIGHT 	WAS NOT LIT UP. THE PILOTS TRIED TO EXTEND THE GEAR MANUALLY, BUT THE HANDLE WOULD NOT EXTEND THE GEAR ANY FURTHER, THE 	PILOTS RETRACTED THE GEAR AND THE RED LIGHT STAYED ILLUMINATED, THE GEAR WAS EXTENDED AGAIN, STILL THE LT DOWN AND LOCKE	D LIGHT WAS OFF AND THE RED LIGHT IN THE HANDLE WAS ON. THE PILOTS DECLARED AN EMERGENCY AND LANDED THE AIRCRAFT, WITH N	O OTHER EVENTS. THE AIRCRAFT WAS JACKED UP, AND THE LANDING GEAR WAS INSPECTED. THE LT MAIN DOWN LOCKING ASSY PIN WAS FO	UND TO BE BROKEN AND HANGING OUT OF THE LOCK HOLES, PREVENTING THE GEAR FROM FULLY EXTENDING AND RETRACTING. THE PIN WAS	1	L	7	2 	4T				A24CE   					 
2007040900021	20070409	00021	CE  	2007	4	9	2007FA0000309    	1	20070402	G	3210	508103437	PIN             			BEECH 	200   	B200        	1152922	CE  										ZONE 700	BROKEN          	E				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	05	65TW	6551 	6551 			BB902				UPON EXTENDING THE LANDING GEAR, THE PILOTS GOT A RED GEAR UNSAFE LIGHT IN THE HANDLE, AND THE LT DOWN AND LOCKED LIGHT 	WAS NOT LIT UP. THE PILOTS TRIED TO EXTEND THE GEAR MANUALLY, BUT THE HANDLE WOULD NOT EXTEND THE GEAR ANY FURTHER, THE 	PILOTS RETRACTED THE GEAR AND THE RED LIGHT STAYED ILLUMINATED, THE GEAR WAS EXTENDED AGAIN, STILL THE LT DOWN AND LOCKE	D LIGHT WAS OFF AND THE RED LIGHT IN THE HANDLE WAS ON. THE PILOTS DECLARED AN EMERGENCY AND LANDED THE AIRCRAFT, WITH N	O OTHER EVENTS. THE AIRCRAFT WAS JACKED UP, AND THE LANDING GEAR WAS INSPECTED. THE LT MAIN DOWN LOCKING ASSY PIN WAS FO	UND TO BE BROKEN AND HANGING OUT OF THE LOCK HOLES, PREVENTING THE GEAR FROM FULLY EXTENDING AND RETRACTING. THE PIN WAS	1	L	7	2 	4T				A24CE   					 
2007040900032	20070409	00032	CE  	2007	4	9	2007FA0000310    	1	20070406	G	1400	07900072	NUT             			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					KIT	MISMANUFACTURED 	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	07	949SP					172S8145				WHILE INSTALLING KIT MK172-25-10C TO COMPLY WITH SB 04-25-01 R4 AND AD 2007-05-10, ONE OF THE PARTS IN THE KIT WAS MACHI	NED IMPROPERLY. THE HEIGHT ADJUSTING NUT HAD THE THRU HOLE FOR THE ULTRALOC WITH MALFORMED THREADS. THE MINOR DIAMETER O	F THE THREAD WAS GREATER THAN THE MAJOR DIAMETER OF THE THREADS ON THE ULTRALOC. THE CROSS HOLE FOR MOUNTING WAS INCORRE	CTLY LOCATED WITH INSUFFICIENT EDGE DISTANCE, AND THE PILOT HOLE WAS OFFSET GIVING AN EGG SHAPED HOLE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007040900022	20070409	00022	NE  	2007	4	9	2007FA0000311    	2	20070305	G	7314		REGULATOR       			NAMER 	T6    	AT6D        	6400416	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	FUEL PUMP	STUCK           	P				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			NM	03	8541B									THE PRESSURE REGULATOR (IN THE WOBBLE PUMP) STUCK IN THE (BYPASS) POSITION CAUSING LOSS OF FUEL PRESSURE AND POWER LOSS 	DUE TO LACK OF FUEL.					1	L	7	1 	3R	3	R		A2575   	5E2	5	C	P257	 
2007040900081	20070409	00081	WP  	2007	4	9	2007FA0000313    	2	20070330	G	7210	31030351	BEARING         								GARRTT	TPE331	TPE33110U   	01514	WP  					IDLER GEAR	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07			723  				P44218C			SUBASSEMBLY BEARINGS TO 2ND IDLER GEAR ASSEMBLED BACKWARDS, CAGE FAILED.											4	T			E4WE				 
2007040900028	20070409	00028	CE  	2007	4	9	2007FA0000315    	1	20070402	G	3610	1H1068	MIXING VALVE    			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					LT BLEED AIR SYS	OUT OF TOLERANCE	B				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			GL	09	706CR					168				DURING TAKEOFF ROLL CREW EXPERIENCED A RUSH OF WARM OILY SMELLING AIR IN THE COCKPIT. CREW ABORTED TAKEOFF AND RETURNED 	TO BASE. MAINTENANCE CREW RAN AIRCRAFT AND DUPLICATED PROBLEM FINDING THE DUCT OVRHT LIGHT AND LT BLEED LIGHT ON AT FULL	 POWER. FURTHER TROUBLESHOOTING FOUND THAT THE LT BLEED AIR MIXING VALVE WAS ALLOWING MORE THAN 200PSI OUT PUT OF AIR. L	T BLEED AIR MIXING VALVE WAS REPLACED WITH A SERVICEABLE INSPECTED VALVE AND OPS CHECKED GOOD.			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007041000035	20070410	00035		2007	4	10	2007FA0000316    	4	20070406	G	2200	0111	TRANSDUCER      			CESSNA	180   	180         	2072602	CE  										AUTO PILOT	MALFUNCTIONED   	D				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			WP	28		460  								ALTITUDE HOLD WAS INOP.  WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTAIN ALTI	TUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC OF TESTING.	 BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCER WITH A	 KNOWN GOOD PART AND PROBLEM WAS SOLVED.  STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULD NOT FIND THE PROBLEM!			1	H	7	1 	3O			NC	5A6     					 
2007041000036	20070410	00036		2007	4	10	2007FA0000317    	4	20070406	G	2200	0111	TRANSDUCER      	STEC        		CESSNA	180   	180         	2072602	CE  										AUTO PILOT	MALFUNCTIONED   	D				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			WP	28		460  								ALTITUDE HOLD WAS INOPERATIVE.  WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTA	IN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FOR 	TESTING. BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCE	R WITH A KNOWN GOOD PART AND PROBLEM WAS SOLVED.STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULDN'T FIND THE PROBLEM!			1	H	7	1 	3O			NC	5A6     					 
2007041000037	20070410	00037		2007	4	10	2007FA0000318    	4	20070406	G	2215	0111	TRANSDUCER      	STEC        		CESSNA	180   	180         	2072602	CE  										ZONE 200	MALFUNCTIONED   	D				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			WP	28		460  								ALTITUDE HOLD WAS INOP.  WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMEDIATLEY, OR THE A/C WOULD MAINTAIN ALTIT	UDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FO TESTING. 	BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCER WITH A 	KNOWN GOOD PART AND PROBLEM WAS SOLVED.STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULDN'T FIND THE PROBLEM!			1	H	7	1 	3O			NC	5A6     					 
2007041000038	20070410	00038		2007	4	10	2007FA0000319    	4	20070406	G	2215	0111	TRANSDUCER      	STEC        		CESSNA	180   	180         	2072602	CE  										ZONE 200	MALFUNCTIONED   	D				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			WP	28		460  								ALTITUDE HOLD WAS INOPERATIVE.  WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTA	IN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FOR 	TESTING. BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCE	R WITH A KNOWN GOOD PART AND PROBLEM WAS SOLVED.STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULDN'T FIND THE PROBLEM!			1	H	7	1 	3O			NC	5A6     					 
2007050400155	20070504	00155	GL  	2007	5	4	2007FA0000321    	2	20070401	G	7412	6870885	EXCITER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	INOPERATIVE     	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	CGBUY					6109580	CAE833577			PILOT WENT TO START THE AIRCRAFT AND THERE WAS NO IGNITION.  FOUND IGNITION EXCITER INOPERATIVE, REPLACED.  (K)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007050400152	20070504	00152	SO  	2007	5	4	2007FA0000322    	1	20070330	G	5730	427	SKIN            			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY511*    	54523	EU  					RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	300WY					427				DURING A WING NDT INSPECTION OF THE UPPER RT WING PLANK AT FS 452 AND BL 33, CORROSION WAS NOTED IN THIS AREA.  ENGINEER	ING HAS DETERMINED THIS CORROSION IS EXCESSIVE ENOUGH TO REQUIRE ACCOMPLISHMENT OF ASC 229, WHICH REMOVES THE CORROSION 	ON THE PLANK AND INSTALLS A DOUBLER PLATE AND A NEW STYLE WING ATTACH PIN AS A CORRECTIVE ACTION.  (K)				2	L	7	2 	4F	4	F		A12EA   	E2EU				 
2007050700006	20070507	00006	SO  	2007	5	7	2007FA0000323    	1	20070301	G	3220	95829000	DRAG LINK       			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	JAMMED          	G			R2LS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	15338					347350051				THE NOSE GEAR LINK ASSEMBLY JAMS INTERMITTENTLY, KEEPING THE FWD AND AFT NOSE GEAR DRAG LINKS FROM LOCKING COMPLETELY.  	REFER TO SB NR 1123B.  (K)					1	L	7	2 	3O	3	O		A7SO    	1E10				 
2007050400140	20070504	00140	GL  	2007	5	4	2007FA0000324    	1	20070317	G	3240		PLATE           			TCRAFT	BC    	BC12D       	8850316	GL  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100*      	GL  	LT BRAKE	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	43336	1669 				6995	666377A	G1885		WHEN BRAKES WERE APPLIED AFTER LANDING.  IT APPEARS THAT THE PINS HOLD THE BACK PLATE ALLOW IT TO SHIFT ENOUGH TO HAVE P	OSSIBLY MADE CONTACT WITH THE BRAKE ACCUATOR ARM AND NOT ALLOW IT TO RELEASE.  (K)					1	H	7	1 	3O	3	O		A696    	E252	5	N	P918	 
2007042500263	20070425	00263	CE  	2007	4	25	2007FA0000325    	1	20070325	G	7810		EXHAUST PIPE    			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	RT EXHAUST	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	5848B					33848	668686L	891146		RT EXHAUST BROKE AT ELBOW, PART HAD BEEN REPAIRED 544 HRS AGO.  DID NOT SHOW ANY CRACK 50 HRS EARLIER.  DO NOT REPAIR EX	HAUST PARTS THAT HAVE 1000 HRS ON THEM.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2007042500255	20070425	00255	EU  	2007	4	25	2007FA0000328    	1	20070406	G	5554	T700A5340023100	FITTING         			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  	HARTZL	HCE4N	HCE4N3      	NE  	RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	704QD					188	PCEPM0073	HH463		DURING A 6000HR/10 YEAR CORROSION INSPECTION AD2007-06-11 WAS BEING COMPLIED IAW AD AND MANDATORY SB70-=104, AMENDMENT 2	.  AFTER COMPLETING THE PENETRANT INSPECTION NO CRACKS WERE DETECTED IN THE SPECIFIED AREAS HOWEVER THE FITTINGS LISTED 	IN BLOCK 5 WERE REMOVED FROM SERVICE FOR LIGHT PITTING CORROSION.  RECENTLY IN OUR FACILITY, THERE WAS A LEVEL 3 NDT REC	URRENT COURSE BEING GIVEN AND THE REMOVED FITTINGS WERE CRACK CHECKED USING A ROTARY TOOL FOR BOLT HOLE EDDY CURRENT SET	 UP ON .030 CORNER EDM NOTCH AS A REFERENCE STANDARD.  AT THIS TIME THERE WERE CORROSION PITTING CRACKS DETECTED IN BOTH	 FITTINGS.  THE INSPECTION CRITERIA STATED IN AD AND SB ARE INSUFFICIENT FOR CRACK DETECTION IN THIS AREA.  POSSIBLY THE	1	L	7	1 	3T	4	T	RT	A60EU   	E4EA	5	C	P10NE	 
2007050400168	20070504	00168	EU  	2007	5	4	2007FA0000329    	1	20070406	G	5510	T700A5530072102	FITTING         			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  	HARTZL	HCE4N	HCE4N3      	NE  	STABILIZER	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	704QD	5980 				188	PCEPM0073	HH463		DURING A 6000HR/10 YEAR CORROSION INSPECTION AD2007-06-11 WAS BEING COMPLIED IAW AD AND MANDATORY SB70-104, AMENDMENT 2.	  AFTER COMPLETING THE PENETRANT INSPECTION, NO CRACKS WERE DETECTED IN THE SPECIFIED AREAS HOWEVER THE FITTINGS LISTED 	IN BLOCK 5 WERE REMOVED FROM SERVICE FOR LIGHT PITTING CORROSION.  RECENTLY IN OUR FACILITY, THERE WAS A LEVEL 3 NDT REC	URRENT COURSE BEING GIVEN AND THE REMOVED FITTINGS WERE CRACK CHECKED USING A ROTARY TOOL FOR BOLT HOLE EDDY CURRENT SET	 UP ON /030 CORNER EDM NOTCH AS A REFERENCE STANDARD.  AT THIS TIME THERE WERE CORROSION PITTING CRACKS DETECTED IN BOTH	 FITTINGS.  THE INSPECTION CRITERIA STATED IN AD AND SB ARE INSUFFICIENT FOR CRACK DETECTION IN THIS AREA.  POSSIBLY THE	1	L	7	1 	3T	4	T	RT	A60EU   	E4EA	5	C	P10NE	 
2007050400171	20070504	00171	GL  	2007	5	4	2007FA0000330    	2	20070403	G	7240	23031260	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	CGPHC					180257D	CAE831562			PILOT NOTICED CRACK IN COMBUSTION CAN ON PREFLIGHT CHECK REPLACED UNIT.  (K)						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007050400190	20070504	00190	SO  	2007	5	4	2007FA0000331    	2	20070404	G	7200	629340	ROD BOLT        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  					LT ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	2641D	740  				310R1678	829015R			PRELIMINARY INSPECTION FINDINGS:  IN FLIGHT, LT ENGINE FAILURE ON CLIMB OUT.  LT ENGINE HAD 737.1 HOURS AND PUT IN SERVI	CE 05/2003.  LARGE HOLE IN CASE AROUND NR 5 AND 6 CYLINDER.  NR 5 ROD SEPARATED FROM CRANK AND BROKEN IN TWO PIECES A FE	W INCHES FROM PISTON PIN.  SUBSEQUENT FINDINGS FROM ENGINE TEARDOWN REPORT PERFORMED BY MFG.  THE SIGNATURES PRESENT ON 	THE NR 5 CYLINDER BORE AND THE DAMAGE TO THE NR 5 CONNECTING ROD ARE CONSISTENT WITH A HYDROSTATIC LOCK EVENT.  PRELIMIN	ARY INFORMATION WAS BASED ON A SB CE-00-07, AND SDR REPORTS ISSUED BETWEEN 1995 AND PRESENT, ON SAME MODEL ENGINE WITH S	IMILAR BOLT FAILURES.  (K)	1	L	7	2 	3O	3	O		3A10    	E5CE				 
2007050400198	20070504	00198	SO  	2007	5	4	2007FA0000332    	2	20070401	G	8500		SNAP RING       			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	IO470*      	17026	SO  					ENGINE	MISMANUFACTURED 	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	4145					32840	CS76646PF			SNAP RING USED TO RETAIN PLATE PN 643629 AND COUNTERWEIGHT PIN 643626-101 WAS BEING INSTALLED IN COUNTERWEIGHT.  UPON IN	STALLING, THE LAST SNAP RING, IT WAS NOTICED THAT THE SNAP RING DID NOT HAVE ANY RETAINING PROPERTIES.  IT LACKED TEMPER	 TO SPRING BACK AND COULD BE FORMED INTO ANY POSITION WHICH COULD HAVE ALLOWED THE PLATE AND PIN TO FALL OUT OF THE COUN	TERWEIGHT CAUSING ENGINE FAILURE..  THE SNAP RING WAS PURCHASED ON 12 MARCH, 2007.  THE BATCH NR LISTED FOR THE SNAP RIN	G WAS 0000070137 UNDER API`S PO NR 4500018586.  (K)		1	H	7	1 	3O	3	O		5A6     	E1CE				 
2007050400137	20070504	00137	EA  	2007	5	4	2007FA0000333    	2	20070406	G	8530	LW15014	ROCKER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE CYLINDER	BROKEN          	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	2994E					17271398	L717976T			THE STAMPED EXHAUST STEEL ROCKER ARM WAS FOUND BROKEN THROUGH AT PUSH ROD, AND THE INTAKE ROCKER ARM WAS CRACKED, AND TH	E PUSH ROD WAS BENT BADLY.  THE ENGINE HAD 120 HR TSO AND NEW FACTORY CYLIDERS WERE INSTALLED.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007042500258	20070425	00258	CE  	2007	4	25	2007FA0000334    	1	20070402	G	5312	07126161	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	42053	4571 				18258832				SMALL CRACK AT RUDDER CABLE CUTOUT IB, APPROX .2500 INCH, NO CAUSE.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007042500257	20070425	00257	EA  	2007	4	25	2007FA0000335    	2	20070417	G	7414		SPRING          	SLICK       		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					IMPULSE COUPLING	BROKEN          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			NE	05		1603 	38   							PILOT STARTED AIRCRAFT NORMALLY AND DID RUN UP WITH A BAD MAGNETO CHECK. PILOT DID NOT FLY AIRCRAFT AND RETURNED TO HANG	ER. AIRCRAFT WOULD NOT RESTART. IMPULSE COUPLE DID NOT MAKE ANY NOISE, TIMING WAS WAY OFF. FOUND IMPULSE COUPLE SPRING B	ROKEN A TURN AND A HALF FROM OUTER END.				1	L	7	1 	3O	3	O		2A13    	E286				 
2007042500273	20070425	00273		2007	4	25	2007FA0000336    	4	20070416	G	2312	0464105430	RADIO           			BOLKMS	117   	BK117A1     	5626010	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2 COMM	SHORTED         	E			BAQR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			AA	AIR AMBULANCE  	1			EA	03	952CJ					S7052				WHILE SHUTTING DOWN AIRCRAFT THE CREW NOTED A WHIFF OF SMOKE AND ELECTRICAL SMELL IN THE COCKPIT.  FOUND THE NR (2) COMM	 RADIO INTERNALLY SHORTED.					1	G	7	2 	3U	3	U		H13EU   	E5NE				 
2007042500247	20070425	00247	GL  	2007	4	25	2007FA0000337    	1	20070418	G	2710		CONTROL SYSTEM  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					AILERON SYS	OUT OF RIG      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	636ST					2153				DURING INSPECTION, FOUND AILERON RUDDER INTECONNECT OUT OF RIG AND CAUSING INTERFERENCE BETWEEN RUDDER AND AILERON. THIS	 IS THE FOURTH AIRCRAFT WE'VE FOUND WITH THIS PROBLEM AND ONE ACTUALLY HAD THE RUDDER AND AILERON LOCK IN FULL OPPOSITE 	DEFLECTIONS JUST PRIOR TO TAKEOFF.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007042400085	20070424	00085	GL  	2007	4	24	2007FA0000339    	1	20070419	G	2720		ARM             			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					RUDDER	MISRIGGED       	B			LC1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	927SE					2238				EACH AC THAT CAME INTO THE SHOP WAS INSPECTED FOR THE SAME CONDITION WITH THE AILERON/RUDDER INTERFERENCE. INSPECTION FO	UND RUDDER/AILERON INTERCONNECT MISRIGGED RESULTING IN THE BOLT CONNECTING THE BUNGEE TO THE RUDDER/AILERON INTERCONNECT	 ARM HITTING THE  FORWARD CABLE CLAMP AND DEFLECTING THE RT AILERON CABLE. THE CONTROLS DID NOT LOCK BUT THERE WAS DEFIN	ITE INTERFERENCE. IN THE NEUTRAL POSITION, THE DISTANCE FROM THE C/L OF THE ARM IS SUPPOSED TO BE 4.5 INCHES. ON THIS AI	RPLANE IT ABOUT 3.75 INCHES. THERE WAS NO EVIDENCE OF ANYONE MOVING THE CLAMP OR THE CLAMP SLIDING. RECORDS SHOW THAT TH	ERE WAS NO FLIGHT CONTROL RIGGING DONE SINCE THE AIRCRAFT LT THE FACTORY.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007042400083	20070424	00083	GL  	2007	4	24	2007FA0000340    	1	20070419	G	2720		ARM             			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O550  	IO550N      	17042	SO  					RUDDER	MISRIGGED       	B			LC1R	D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			EA	07	636ST					1720				PILOT WAS TURNING ONTO RUNWAY IN CROSSWIND WITH FULL OPPOSITE AILERON AND RUDDER CONTROLS. CONTROLS LOCKED IN CROSSED PO	SITION AND WOULD NOT RETURN TO NEUTRAL. PILOT RETURNED TO RAMP. INSPECTION FOUND RUDDER/AILERON INTERCONNECT MISRIGGED R	ESULTING IN THE BOLT CONNECTING THE BUNGEE TO THE RUDDER/AILERON INTERCONNECT ARM LOCKING OVER THE BOLT GOING THROUGH TH	E FORWARD CABLE CLAMP. IN THE NEUTRAL POSITION, THE DISTANCE FROM THE C/L OF THE ARM IS SUPPOSED TO BE 4.5 INCHES. ON TH	IS AIRPLANE IT WAS JUST OVER 3 INCHES. THERE WAS NO EVIDENCE OF ANYONE MOVING THE CLAMP OR THE CLAMP SLIDING. RECORDS SH	OW THAT THERE WAS NO FLIGHT CONTROL RIGGING DONE SINCE THE AIRCRAFT LEFT THE FACTORY.	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007042500246	20070425	00246	GL  	2007	4	25	2007FA0000341    	1	20070416	G	2750		RELAY           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					T/E FLAP	FAILED          	P				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SW	01	105SR					1866				DURING A TRAINING FLIGHT, THE FLAPS BECAME STUCK IN THE DOWN POSITION.  THE AIRCRAFT RETURNED TO THE AIRPORT WITHOUT INC	IDENT AND THE AIRCRAFT WAS SENT TO MAINTENANCE FOR TROUBLESHOOTING.  MAINTENANCE DISCOVERED THE FLAPS DOWN RELAY FAILED.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007042500259	20070425	00259	SO  	2007	4	25	2007FA0000342    	2	20070421	G	8520	655910	CONNECTING ROD  	CONT        	TSIO520E    	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF34C	3AF34C*     	GL  	RT ENGINE	FAILED          	E				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			NM	05	8FB				176257	402B1372	176257			DURING CLIMB AFTER THE POWER HAD BEEN REDUCED FROM THE TAKEOFF SETTING, THE RT ENGINE STARTED TO VIBRATE.  THE PILOT COU	LD SEE OIL SPLASHING FROM AROUND THE OIL ACCESS DOOR AND RUNNING BACK ON THE TOP COWLING.  THE PILOT SHUTDOWN THE ENGINE	 AND FEATHERED THE RT PROPELLER.  THE PILOT RETURNED TO THE DEPARTURE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.  UPON	 INITIAL INVESTIGATION, A LARGE HOLE WAS FOUND IN THE CRANKCASE ABOVE THE NR 4 ROD JOURNAL.  THE NR 4 CONNECTING ROD WAS	 SEPARATED FROM THE CRANKSHAFT AND PROTRUDING FROM THE HOLE IN THE CASE.  THE NR 4 CONNECTING ROD CAP WAS ALSO SEPARATED	 FROM THE CONNECTING ROD AND WAS STICKING UP OUT OF THE HOLE.	1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2007050400146	20070504	00146	WP  	2007	5	4	2007FA0000343    	2	20070411	G	7261	31080261	SCAVENGE PUMP   			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					LT ENGINE	FLUCTUATES      	B				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	25	835MA					4410343	P77725			COMMANDED IN-FLIGHT SHUTDOWN OF LT ENGINE DUE TO FLUCTUATING OIL PRESSURE.  UNEVENTFUL SINGLE ENGINE LANDING.  ENGINE LO	ST OIL.  OIL EXITED ENGINE FROM TURBINE AIR/OIL SEAL AS A RESULT OF TURBINE SCAVENGE PUMP FAILURE.  RECOMMEND COMPLIANCE	 WITH SB 72-2074R1.  (K)				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2007050400173	20070504	00173	EA  	2007	5	4	2007FA0000344    	2	20070323	G	7320	25765362	SERVO           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE FUEL	WORN            	B			HUNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	9522S	1938 				17280432	RL30493351A	SF010		PILOT REPORTS THAT ENGINE DIED ON FINAL APPROACH.  ADJUSTED IDLE STOP SLIGHTLY AND MIXTURE SLIGHTLY.  RAN ENGINE AND FOU	ND THAT SLIGHT ADJUSTMENTS MADE TO FUEL SERVO CREATED LARGE CHANGES IN THE ENGINE OPERATION.  UNABLE TO ADJUST THE FUEL 	SERVO TO MEET PERFORMANCE REQUIREMENTS STATED IN AD2001-06-17, (D)(2).  THIS IS THE SECOND ATTEMPT TO ADJUST THE FUEL SE	RVO.  THE FUEL SERVO WAS REMOVED FROM THE AIRCRAFT AND FORWARDED FOR REPAIR UNDER THEIR W/O NR 07-00900.  ORIGINAL FUEL 	SERVO, PN 25765362, SN 70148401, REINSTALLED ON AC UPON COMPLETION OF REPAIR, WITH REFERENCE TO MM, CHAP 73.  IDLE AND M	IXTURE ADJUSTMENT COMPLETED WITH REFERENCE TO MM, CHAP 73.  OPERATIONAL/LEAK CHECK GOOD AT THIS TIME.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007050400204	20070504	00204		2007	5	4	2007FA0000345    	4	20070117	G	3417	702490031304	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT AVIONICS BAY	MALFUNCTIONED   	B				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	07	700SJ					082				WHILE ENROUTE, THE PILOTS ALTIMETER (FROZE UP) AT ABOUT 8000 FT AND THE OVERSPEED HORN WENT OFF.  THE PILOT RECYCLED THE	 ADC AND ITS OPERATION WAS RESTORED.  THE ADC WAS TESTED AND NO DEFECTS WERE FOUND.  THERE WAS NO EVIDENCE OF WATER OR M	OISTURE IN OR AROUND THE ADC.  THE ADC WAS REPLACED AND TESTED.  THERE HAS BEEN NO PREVIOUS REPORTED FAILURES OF THIS SY	STEM IN THIS AIRCRAFT.  (K)			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007042600267	20070426	00267		2007	4	26	2007FA0000346    	4	20070122	G	3417	702490031304	ADC             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  						MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	813AS					167				DURING PRE-FLIGHT, THE CREW NOTED THAT THE PILOTS ALTIMETER AND ALTITUDE ALERTER WERE FLAGGED.  ATTEMPTS TO RECYCLE THE 	SYSTEM WERE NOT SUCCESSFUL.  THE CREW GROUNDED THE AIRCRAFT.   AN AVIONICS TECH WAS DISPATCHED TO THE AIRCRAFTS LOCATION	 AND DETERMINED THAT THE ADC HAD FAILED.  THE ADC WAS REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY	 WITH FAR 91.411, PART 43 AND TO REMAIN RVSM COMPLIANT.  (K)			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007050400186	20070504	00186	CE  	2007	5	4	2007FA0000348    	1	20070330	G	3240		LINE            			CESSNA	170   	170B        	2072306	CE  	CONT  	C145  	C145*       	17012	SO  					BRAKE	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	4696C	2611 				25640				DURING AN ANNUAL INSPECTION, THE RT BRAKE SUPPLY LINE WAS FOUND CHAFED BY THE ELEVATOR CONTROL CABLE.  THE CHAFING OCCUR	RED WHEN THE ELEVATOR IS OPERATED NEAR THE (UP) LIMIT OF TRAVEL.  THE LOCATION OF CHAFE IS VIEWED DIRECTLY BELOW THE ELE	VATOR TRIM WHEEL, LOOKING SLIGHTLY FORWARD.  THE BRAKE TUBE WAS NOT SUPPORTED BY ANY CLAMPING MEANS TO SECURE THE TUBE. 	 A REPLACEMENT TUBE WAS FABRICATED AND INSTALLED WITH ADEQUATE CLAMPING TO INSURE NO FURTHER CHAFING ACTION.  THE BRAKE 	WAS SERVICED AND A SATISFACTORY LEAK CHECK WAS ACCOMPLISHED.  THE ELEVATOR CONTROL CABLE WAS CHECKED FOR DAMAGE AND IS A	CCEPTABLE FOR SERVICE.  PHOTOS DETAILING THE CHAFED AREA AND MFG IPC FOR INSTALLATION DETAIL. (K)	1	H	7	1 	3O	3	O		A799    	E253				 
2007050400172	20070504	00172	SO  	2007	5	4	2007FA0000349    	1	20070401	G	5753	3087B	SPAR            			MAULE 	M4    	M4210C      	5460112	SO  	CONT  	IO360 	IO360*      	17025	CE  					RT FLAP	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	9810M	5341 				1020C				DURING AN ANNUAL INSPECTION, THE RT FLAP IB HINGE/CONTROL BRACKET WAS FOUND TO BE LOOSE.  FURTHER INSPECTION REVEALED TH	AT THE FLAP SPAR WAS CRACKED AT THE UPPER RIVET ATTACH POINTS.  THE CRACK IS 3.5 INCH LONG AND EXTENDS PAST THE RIVET HO	LES IN BOTH DIRECTIONS.  ADDITIONALLY, BOTH CLOSURE RIBS, AT THEIR ATTACH ANGLES TO THE SPAR.  THE SPAR PN IS 3078B, RIB	 PNS 3046-2 AND 3046-1, RIVET PNS SS/SS 34D AND SS/SS 32D (MFG SUPPLIED).   THE FLAP SPAR AND RIBS WERE REPLACED AND THE	 AIRCRAFT RETURNED TO SERVICE.  (K)		1	H	7	1 	3O	3	O		3A23    	E1CE				 
2007050400149	20070504	00149	NE  	2007	5	4	2007FA0000350    	2	20070401	G	7250	1767M75G03	SHAFT           	GE          		BOEING	777   	777224      	1385225	NM  	GE    	GE90  	GE9090B     	 	NE  					LPT FAN	UNSERVICEABLE   	B			QEMY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	78017	36785			T900253	31679	900238			AIRCRAFT TAKEOFF WAS ABORTED, A 147 KNOTS AFTER ENGINE LOST POWER.  AC WAS STOPPED SAFELY AND ALL PASSENGERS AND CREW DE	PLANED SAFELY.  UPON INSPECTION OF THE ENGINE, THE FAN ROTATED FREELY, BUT THE LPT DID NOT ROTATE.  BS1 OF THE ENGINE SH	OWED THAT THE HPT WAS CLEAN, BUT THE LPT WAS HEAVILY DAMAGED.  THE ENGINE WAS SHIPPED TO MFG.  INITIAL INSPECTIONS SHOWE	D THAT THE FAN MID SHAFT WAS SEPARATED IN THE AXIAL PLANE OF THE HPC S3 DISC.  THE CENTER VENT TUBE WAS SEPARATED IN 3 P	LACES ALL AFT OF FMS SEPARATION. AND INVESTIGATION IS ON GOING.  (K)		2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
2007050700051	20070507	00051	NE  	2007	5	7	2007FA0000351    	2	20070424	G	8560	230319303	THRUST BEARING  								LYC   	LF507 	LF5071F     	 	NE  					SUPERCHARGER	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07							LF07712			NR 8 THRUST BEARING FAILURE RESULTED IN FAN AND SUPERCHARGER ROTORS TO SHIFT FORWARD CAUSING DAMAGE TO SUPERCHARGER 2ND 	DISK TO CONTACT THE STATORS MACHINING THROUGH THE 2ND SUPERCHARGER DISK WEB,  RESULTING IN  IN-FLIGHT SHUTDOWN OF NR 1 E	NGINE.  OPERATIONAL DESCRIPTION OF EVENT DID NOT INDICATE LOW OIL PRESSURE PRIOR TO THE FAILURE.  WARNING SEQUENCE WAS D	ESCRIBED AS (1) SMELL IN THE CABIN, HIGH VIBRATIONS WARNING AND VISUAL SPARKES COMING FROM ENGINE, THEN SHUT-DOWN.  BEAR	ING APPEARS TO BE STARVED OF OIL UPON DISASSEMBLY, ALONG WITH VERY LOW OIL CONTENT IN ADJACENT NR 9 BEARING AND PLANETAR	Y REDUCTION GEAR CARRIER.  CURRENTLY INVESTIGATING CAUSE OF OIL STARVATION.  LUBE PUMP IS FROZEN, BUT ENGINE NR 2 AND NR						4	F			E6NE				 
2007050100116	20070501	00116	SO  	2007	5	1	2007FA0000352    	2	20070424	G	7322	3801552	CARBURETOR      								CONT  	A65   	A65*        	17003	SO  					ENGINE	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										CARBURETOR WAS SENT IN FOR AN OVERHAUL BECAUSE IT WOULD NOT ACCEPT THROTTLE.  THERE WAS VERY LITTLE TIME ON THE CARBURET	OR SINCE IT'S LAST OVERHAUL.  UPON DISASSEMBLY, IT WAS FOUND THAT THE CARBURETOR HAD THE WRONG VENTURI INSTALLED AND THE	RE WAS OLD CORROSION IN THE FLOAT CHAMBER THAT WAS NOT REMOVED DURING THE PREVIOUS OVERHAUL.  IT HAD THE WRONG SEAT INST	ALLED FOR THE TYPE NEEDLE THAT WAS BEING USED.  IT WAS OBVIOUS THAT SOMEONE WHO THOUGHT THEY KNEW CARBURETORS HAD ATTEMP	TED TO OVERHAUL THE UNIT UNSUCCESSFULLY.							3	O			E205				 
2007050400199	20070504	00199	CE  	2007	5	4	2007FA0000354    	1	20070402	G	2697	MS24266R12B12SN	CONNECTOR       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					FIRE DETECTION	CORRODED        	D			GONR	A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	01	200VU	3534 				BB1393				THE AIRCRAFT WAS FLYING THROUGH IMC, WITH ALOT OF RAIN ON THEIR WAY TO DESTINATION.  AS THE CREW WAS LETTING DOWN TO LAN	D THE LT ENGINE FIRE LIGHT LIT UP.  THE CREW SCANNED ALL THE GAGES, AND DETERMINED THAT THIS WAS A FALSE LIGHT.  THE AC 	LANDED WITHOUT COMPLICATION.  UPON INSPECTION OF THE LT ENGINE FIRE DETECT SYSTEM, THE TECH FOUND SOME VERY LIGHT CORROS	ION AND MOISTURE ON THE J102 CONNECTOR PLUG, LOCATED ON THE LT ENGINE FIRE WALL.  THE MOISTURE AND CORROSION WAS REMOVED	 AND THE FIRE DETECT SYSTEM TESTED PROPERLY, THE AC WAS RETURNED TO SERVICE.  APPLING A THIN COATING OF DC-4 GREASE IN T	HE CONNECTOR PLUG WOULD PREVENT MOISTURE FROM ENTERING THE PLUG AND THEREFORE KEEP THE CORROSION OUT.  (K)	1	L	7	2 	4T	3	T		A24CE   	E2NE				 
2007050700005	20070507	00005	CE  	2007	5	7	2007FA0000355    	1	20070417	G	7810	265401416	EXHAUST DUCT    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	4365U					208B0253				CRACKING OCCURRED IN A SHORT TIME SPAN, DURING NORMAL OPERATION.  CRACKS WERE OVER AN AREA APPROX 7 INCHES X 7 INCHES.  	ONE PIECE APPROX 3 INCHES X 3 INCHES SEPARATED FROM THE PART.  AFTER CRACKING, DEFORMATION OF LOWER TRAILING EDGE OCCURR	ED BECAUSE IT WAS NO LONGER RIGID.  IF THIS PROBLEM HAD GONE UNNOTICED, HEAT DAMAGE WOULD PROBABLY HAVE OCCURRED TO ADJA	CENT PARTS.  MATERIAL OR MFG PROCESS COULD BE SUSPECT.  RECENT MFG BULLETIN CAB 07-2 AFFECTS SOME PRIMARY EXHAUST DUCTS 	DUE TO IMPROPER MFG, BUT IT DOES NOT APPLY TO THIS ONE.  (MFG HAS BEEN MADE AWARE OF THIS PROBLEM, PART WAS RETURNED TO 	THEM ON REQUEST FOR EVALUATION).  (K)	1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007050700185	20070507	00185	SO  	2007	5	7	2007FA0000356    	2	20070418	G	8530	FRCN68OACA01	CYLINDER HEAD   			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					NR 1	SEPARATED       	D			FO7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	5162D	145  				51262				PERFORMED CYLINDER COMPRESSION TEST AND FOUND NR 1 CYLINDER READING 0 PSI AND FOUND LEAKING AROUND CYLINDER HEAD AND BAR	REL FINS.  UPON REMOVAL THE HEAD IS COCKED SIDEWAYS ON THE BARREL.  THE HEAD WAS SEPARATING FROM BARREL.  THE CYLINDER P	N FRCN68.  OACA/01 CL68 CERMINIL FREEDOM.  CYLINDER ONLY HAD 145.6 HRS TIME IN SERVICE OVERHAUL IN DEC 2003.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007042700004	20070427	00004	CE  	2007	4	27	2007FA0000357    	1	20070425	G	3220		LANDING GEAR    			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NOSE	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	09	757CM	10768				15279633	RL2072615	770307		NOSE LANDING GEAR BROKE AT HARD NOSE LANDING, NO EVIDENCE OF PREVIOUS CRACKS.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007050400154	20070504	00154	CE  	2007	5	4	2007FA0000359    	1	20070403	G	5510	12320131	FITTING         			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C401   	GL  	STABILIZER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	803AN	11657				20700570	248811R	765815		FWD RT STABILIZER FITTING CRACKED.  FOUND CRACKED FITTING UPON ANNUAL INSPECTION OF EMPENNAGE.  (K)						1	H	7	1 	3O	3	O		A16CE   	E8CE	5	C	P47GL	 
2007050400212	20070504	00212	EU  	2007	5	4	2007FA0000360    	1	20070407	G	5340	N325400A	BRACKET         			SNIAS 	350   	AS350B3     	8680954	EU  										FUSELAGE	BROKEN          	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	C6YPN	480  				3688				DURING 100 HR INSPECTION, THE MECHANIC REACHED TO UNSCREW THE OIL FILTER AND THE BRACKET BROKE OFF IN HIS HAND.  REPLACE	D UNIT, THE ENTIRE BREAK LOOKED FRESH EVEN WITH 10X MAGNIFICATION.  IT IS A POT METAL BRACKET.  (K)					1	G	7	1 	3U				H9EU    					 
2007050400229	20070504	00229	CE  	2007	5	4	2007FA0000361    	1	20070419	G	2420		COUPLING        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ALTERNATOR	WORN            	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	63332					15077241	250316			ALTERNATOR DRIVE COUPLING WAS WORN AND SEVERELY LOOSE WITH EXCESSIVE PLAY DUE TO SOFT, UNDERCUT BUSHINGS PN 632050.  IN 	ADDITION, THE DRIVE HUB KEY WAY WAS SEVERELY WORN CAUSING EXCESSIVE PLAY OF THE HUB ON THE SHAFT.  CONTINUED OPERATION W	OULD RESULT IN DRIVE COUPLING RETAINER PN 352030 FAILING AND POTENTIALLY CAUSING CATASTROPHIC ENGINE FAILURE.  THE CURRE	NT RUBBER BUSHINGS ARE SOFT AND ALLOW THE DRIVE GEAR TO CRUSH AND DEFORM THEM WHICH REDUCES SHOCK ABSORPTION AND LEADS T	O DRIVE COUPLING FAILURE WHEN DRIVE GEAR BEGINS TO CONTACT THE RETAINER CUP DIRECTLY.  THIS IS A RECURRING PROBLEM AS FO	UND ON OTHER ALTERNATORS USING THIS TYPE OF DRIVE COUPLING AS LISTED IN SB 95-3B.  (K)	1	H	7	1 	3O	3	O		3A19    	E252				 
2007050400225	20070504	00225	CE  	2007	5	4	2007FA0000362    	1	20070419	G	2910	98811281	POWERPACK       			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					HYD SYSTEM	MISREPAIRED     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	413EB					172RG0113				INSTALLED A NEWLY OVERHAULED COMPLETE HYDRAULIC POWER PACK UNIT AS RECEIVED.  AFTER INSTALLING THE UNIT IN THE AIRCRAFT 	AND PERFORMING A RETRACT TEST THE NEW OVERHAULED GEAR MOTOR WAS JERKY AND ACTING LIKE IT WAS SHORTING OUT.  REMOVED MOTO	R AND INSTALLED ANOTHER NEW OVERHAULED MOTOR AND SYSTEM WORKED FINE.  (K)				1	H	7	1 	3O	3	O		3A17    	E286				 
2007050400233	20070504	00233	CE  	2007	5	4	2007FA0000363    	1	20070411	G	3210	05412024	BUSHING         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					RMLG	UNSERVICEABLE   	B			NU7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	106RA	3586 				172S8241				BUSHING LINER SEPARATED FROM METAL SHELL, SLID OUT OF SHELL CAUSING AC TO LEAN RT WING TIP LOW.  BETTER BONDING ADHESIVE	 FOR LINER TO SHELL.  NEED TO GO TO A TIME SCHEDULE FOR INSPECTION.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007050700182	20070507	00182	CE  	2007	5	7	2007FA0000364    	1	20070420	G	3230		LANDING GEAR    			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  						MALFUNCTIONED   	B			EBVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	32TX					S5500026				EMERGENCY LANDING GEAR DEPLOYMENT SYSTEM INSPECTED DURING ROUTINE PHASE INSPECTION.  EMERGENCY GEAR CABLES CHECKED FOR C	ORRECT RIGGING, AND EMERGENCY GEAR SYSTEM FUNCTION TESTED WITH AIRCRAFT ON JACKS.  SYSTEM FUNCTION TESTED PROPERLY.  PIL	OT ELECTED TO PERFORM IN FLIGHT CHECK OF SAME SYSTEM AND FOUND THAT MAIN GEAR WOULD NOT DEPLOY.  PILOT EXTENDED GEAR USI	NG NORMAL HYDRAULIC SYSTEM OPERATION AND LANDED WITHOUT INCIDENT.  AC WAS FLOWN TO SERVICE CENTER FOR EVALUATION.  (K)			1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2007050400213	20070504	00213	CE  	2007	5	4	2007FA0000366    	1	20070412	G	7921	652065	GASKET          			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					OIL COOLER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	42776	322  				421B0394	607077			AIRCRAFT DEPARTED ON A CHARTER , PILOT WAS OVER LAKE WHEN HE NOTICED ENGINE OIL COMING OUT OF TOP ENGINE COWLING COOLING	 LOUVERS.  PILOT NOTIFIED CONTROL HE WAS LOSING OIL.  FEATHERED THE RT ENGINE AND DIVERTED .  PILOT MADE UNEVENTFUL SING	LE ENGINE LANDING AND TAXIED TO MAINTENANCE HANGAR.  DISCOVERED THE ENGINE WAS SEIZED AND THE COWLING AND NACESSE BOTTOM	 COVERED WITH OIL.  STARTED DISASSEMBLY AND FOUND THE OIL COOLER GASKET, PN 652065, HAD .1250 INCH SECTION MISSING FROM 	THE UPPER FORWARD AREA OF THE GASKET.  (K)		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007050400214	20070504	00214	CE  	2007	5	4	2007FA0000367    	1	20070420	G	5100	6213011139	DOUBLER         			CESSNA	650   	650         	2076802	CE  										UNKNOWN	FATIGUED        	B			CNQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07										THE 6213011139 LT DOUBLER AND THE 6213011140 RT DOUBLER FATIGUE CRACKING ON BOTH.  THE 6213011139 LT DOUBLER AND THE 621	3011140 RT DOUBLER, ON MODEL 650 IS PART OF THE NOSE WHEEL WELL ASSY, HAS BEEN FOUND WITH FATIGUE CRACKING ON MULTIPLE S	N.  CURRENTLY THE PART IS BEING REMOVED AND REPLACED AS NEEDED AND A SERVICE CONDITION REPORT (SCR) HAS BEEN SUBMITTED T	O ENGINEERING FOR REVIEW.  (K)			2	L	7	2 	4F				A9NM    					 
2007050400227	20070504	00227	CE  	2007	5	4	2007FA0000368    	1	20070420	G	5310	6213011140	DOUBLER         			CESSNA	650   	650         	2076802	CE  										FS 92-94	FATIGUED        	D			CNQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07										THE 6213011-139 LT DOUBLER AND THE 6213011-140 RT DOUBLER FATIGUE CRACKING ON BOTH.  THE 6213011-139 LT DOUBLER AND THE 	6213011-140 RT DOUBLER, ON MODEL 650 IS PART OF THE NOSE WHEEL WELL ASSY, HAS BEEN FOUND WITH FATIGUE CRACKING ON MULTIP	LE SN.  CURRENTLY THE PART IS BEING REMOVED AND REPLACED AS NEEDED, AND A SERVICE CONDITION REPORT (SCR) HAS BEEN SUBMIT	TED TO ENGINEERING FOR REVIEW.  (K)			2	L	7	2 	4F				A9NM    					 
2007050400223	20070504	00223	CE  	2007	5	4	2007FA0000369    	1	20070404	G	3210	084100097	LANDING GEAR    			CESSNA	310   	310D        	2074212	CE  	CONT  	O470  	IO470*      	17026	SO  					LT MLG	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	6981T					39281				THE PILOT NOTED THAT SOMETHING WAS HANGING DOWN UNDER THE AC IN CRUISE FLIGHT AND THAT THE AC WAS NOT GOING AS FAST AS I	T NORMALLY DID.  ANOTHER AC NOTED THAT THE GEAR WAS UP, BUT THAT THE LEFT IB GEAR DOOR WAS HANGING DOWN PART WAY.  THE T	OWER CONFIRMED THAT THE GEAR APPEARED TO BE DOWN AND LOCKED, BUT THAT THE LT IB GEAR DOOR WAS PART WAY DOWN.  ALL INDICA	TIONS OF THE GEAR IN THE AC WERE NORMAL AND THE GREEN LIGHT WAS ON WHEN THE AC LANDED.  THE AIRCRAFT LANDED NORMALLY AND	 ROLLED ABOUT 800 FT DOWN THE RUNWAY WHEN THE LEFT MAIN GEAR BROKE OUT OF THE WHEEL WELL.  IT WENT STRAIGHT BACK BEHIND 	THE WING AND THE AC WENT AROUND TO THE LEFT AND OFF THE RUNWAY.  THE LT IB DOOR WILL MOVE SOME BY HAND AND SEEMED TO OPE	1	L	7	2 	3O	3	O		3A10    	E1CE				 
2007050400133	20070504	00133		2007	5	4	2007FA0000370    	4	20070427	G	2562	MN1300	BATTERY         	ACK         		PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ELT	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01			12   		020150	28791146	L2113440A	CM285		BATTERIES LEAKED ACID/ALKALII, CORRODING CONTACTS SERVERLY AND RENDERING ELT INOPERABLE.  BATTERIES WERE INSTALLED IN 20	06. SHELF DATE ON BATTERIES WERE MAR 2011. ELT WAS NOT FOUND ACTIVATED. THIS IS THE THIRD CASE OF THIS I HAVE SEEN IN 20	06/2007 AND THERE HAVE BEEN SEVERAL OTHERS IN THE PAST 5 YEARS.  IN ALL CASES THE BATTERIES RENDERED THE ELT INOP PRIOR 	TO THE REPLACEMENT DATE (HALF OF SHELF LIFE IAW FAR 91.207 (C)). ALL PROBLEMS WERE DETECTED DURING ANNUAL INSPECTIONS OF	 ELT IAW FAR 91.207 D.		1	L	7	1 	3O	3	O		2A13    	E295	5	C	P27EA	 
2007050400134	20070504	00134		2007	5	4	2007FA0000371    	4	20070427	G	2562	MN1300	BATTERY         	ACK         		PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ELT	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01			12   		020150	28791146	L2113440A	CM285		BATTERIES LEAKED ACID/ALKALII, CORRODING CONTACTS SERVERLY AND RENDERING ELT INOPERABLE.BATTERIES WERE INSTALLED IN 2006	. SHELF DATE ON BATTERIES WERE MAR 2011. ELT WAS NOT FOUND ACTIVATED. THIS IS THE THIRD CASE OF THIS I HAVE SEEN IN 2006	/2007 AND THERE HAVE BEEN SEVERAL OTHERS IN THE PAST 5 YEARS. IN ALL CASES THE BATTERIES RENDERED THE ELT INOP PRIOR TO 	THE REPLACEMENT DATE (HALF OF SHELF LIFE I/A/W FAR 91.207 (C)). ALL PROBLEMS WERE DETECTED DURING ANNUAL INSPECTIONS OF 	ELT I/A/W FAR 91.207 D.		1	L	7	1 	3O	3	O		2A13    	E295	5	C	P27EA	 
2007050400153	20070504	00153		2007	5	4	2007FA0000372    	4	20070502	G	2562	MN1300	BATTERY         	AMERIKING   		CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					ELT	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01		12   	12   		353328	01165				BATTERIES LEAKED INSIDE ELT UNIT PREVENTING ELT OPERATION AND DESTROYING CONTACTS INSIDE UNIT. THIS IS ONE OF SEVERAL TI	MES THIS PROBLEM HAS BEEN SEEN IN THE NEWER OR MORE RECENTLY MANUFACTURED BATTERIES THIS PARTICULAR SET HAD AN EXPIRATIO	N OF 2012 AND HAD ONLY BEEN INSTALLED IN THE UNIT FOR ONE YEAR.  RECOMMEND BAT REPLACEMENT EVERY 6 MONTHS UNTIL THIS PRO	BLEM IS ADDRESSED BY ELT MANUFACTURES OR THE BATTERY COMPANY NOTE OLDER BATTERIES DID NOT EXHIBIT THIS PROBLEM.			1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2007050400161	20070504	00161	GL  	2007	5	4	2007FA0000375    	1	20070427	G	2720		CONTROL CABLE   			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					AILERONS	INTERFERENCE    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	220SR					0391				DURING INSPECTION FOUND INTERFERENCE BETWEEN RUDDER/AILERON INTERCONNECT SYSTEM AND RT AILERON CABLE. CHECKED RIGGING AN	D FOUND CABLE CLAMP ON RT AILERON CABLE OUT OF POSITION. VISUAL INSPECTION INDICATES NO MOVEMENT BETWEEN CABLE AND CLAMP	 AND RECORDS REVIEW INDICATE THAT NO RIGGING HAS TAKEN PLACE SINCE THE AIRPLANE LEFT THE FACTORY.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007050400170	20070504	00170	CE  	2007	5	4	2007FA0000377    	1	20070426	G	3232		ROD             	GARKENYON   		LEAR  	60    	60LEAR      	5170707	CE  	WRIGHT	R3350 	R3350*      	67040	EA  					ACTUATOR	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	09	718A				0290	065				WHEN LANDING GEAR WAS CYCLED DOWN, THE RT RED IB GEAR DOOR OPEN LIGHT WOULD NOT EXTINGUISH. GEAR DOWN LOCK LIGHTS WERE G	REEN. NORMAL LANDING. INSPECTION REVEALED THAT THE ACTUATOR SHAFT HAD UNSCREWED FROM THE PISTON NOT ALLOWING THE DOOR TO	 CLOSE. FURTHER EXAMINATION REVEALED THAT THE ROLL PIN SECURING THE SHAFT TO THE PISTON WAS SHEARED.  THE LT ACTUATOR WA	S INSPECTED AND THE ACTUATOR ROD WAS FOUND TO BE 2.5 TURNS FROM DISENGAGING FROM THE PISTON. 6-7 TURNS BOTTOMS THE ROD I	N THE PISTON. REPLACED BOTH DOOR ACTUATORS.		2	L	7	2 	4F	4	R	RT	A10CE   	E272				 
2007050400188	20070504	00188	CE  	2007	5	4	2007FA0000378    	1	20070426	G	3232	66000858	ACTUATOR        			LEAR  	60    	60LEAR      	5170707	CE  	WRIGHT	R3350 	R3350*      	67040	EA  					MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	09	718A	4200 				065				WHEN LANDING GEAR WAS CYCLED DOWN, THE RT RED IB GEAR DOOR OPEN LIGHT WOULD NOT EXTINGUISH.  GEAR DOWN LOCK LIGHTS WERE 	GREEN. NORMAL  LANDING. INSPECTION REVEALED THAT THE ACTUATOR SHAFT HAD UNSCREWED FROM THE PISTON NOT ALLOWING THE DOOR 	TO CLOSE. FURTHER EXAMINATION REVEALED THAT THE ROLL PIN SECURING THE SHAFT TO THE PISTON WAS SHEARED. THE LT ACTUATOR W	AS INSPECTED AND THE ACTUATOR ROD WAS FOUND TO BE 2.5 TURNS FROM DISENGAGING FROM THE PISTON. 6-7 TURNS BOTTOMS THE ROD 	IN THE PISTON. REPLACED BOTH DOOR ACTUATORS.		2	L	7	2 	4F	4	R	RT	A10CE   	E272				 
2007050400206	20070504	00206	CE  	2007	5	4	2007FA0000381    	1	20070404	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		13510	514  				PCE81382			WHILE PREFORMING 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 SB 3380 COMPLIED WITH 514 HOURS EARLIER.POWER 	SECTION WAS REMOVED AND SENT FOR REPAIR.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007050400215	20070504	00215	SO  	2007	5	4	2007FA0000383    	1	20070430	G	5520	2039700	HORN            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					STABILIZER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5977P	6000 				241070				FOUND STABILATOR HORN P/N 20397-00 SEVERELY CRACKED FROM THE INSIDE WHERE THE ATTACH BOLTS CONNECT THE BALANCE WEIGHT TU	BE P/N 20398-02 AND STABILATOR TORQUE TUBE ASSEMBLY P/N 20203-03.					1	L	7	1 	3O	3	O		1A15    	E295				 
2007061300266	20070613	00266		2007	6	13	2007FA0000385    	2	20070501	G	7320		FADEC           			DIAMON	DA40  	DA40        	2990002	GL  											MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		103  								THE ECU WARNING LIGHTS HAVE COME ON MULTIPLE TIMES NOW.  ACCRODING TO THE MANUFACTURER, EACH TIME THESE ANNUNCIATORS COM	E ON THE AIRCRAFT MUST BE SERVICED BY AN APPROVED MECHANIC. BY THIELERTS EXPLANATION, IF THE AIRCRAFT GOES INTO A STEEP 	BANK OR UN-COORDINATED TURN THAN AN AIR BUBBLE CAN GET INTO THE FUEL LINE AND CAUSE UNEVEN PRESSURES BETWEEN THE TWO ENG	INES.  THE FADEC SENSES THIS AS A PROBLEM AND THE ECU WANRINGS TRIP.  ACCORDING TO THIELERT THIS HAS BEEN HAPPENING FREQ	UENTLY ON AIRCAFT WITH THEIR FADEC ENGINES.  THREE TIMES ALREADY ON OUR WITHIN 100 HOURS.  IT IS A NUISANCE BECAUSE AN A	IRCRAFT CAN EASILY BE STRANDED IN A LOCATION WITHOUT A THIELERT APPROVED MECHANIC. OR WORSE, IF A GENUINE PROBLEM EXISTE	1	L	7	1 	3O			NT	A47CE   					 
2007050700184	20070507	00184		2007	5	7	2007FA0000386    	2	20070501	G	7320		FADEC           			DIAMON	DA40  	DA40        	2990002	GL  											MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03		103  								THE ECU WARNING LIGHTS HAVE COME ON MULTIPLE TIMES NOW.  ACCORDING TO THE MANUFACTURER, EACH TIME THESE ANNUNCIATORS COM	E ON THE AIRCRAFT MUST BE SERVICED BY AN APPROVED MECHANIC. BY THIELERTS EXPLANATION, IF THE AIRCRAFT GOES INTO A STEEP 	BANK OR UN-COORDINATED TURN THAN AN AIR BUBBLE CAN GET INTO THE FUEL LINE AND CAUSE UNEVEN PRESSURES BETWEEN THE TWO ENG	INES.  THE FADEC SENSES THIS AS A PROBLEM AND THE ECU WARNINGS TRIP.  ACCORDING TO MANUFACTURE THIS HAS BEEN HAPPENING F	REQUENTLY ON AIRCRAFT WITH THEIR FADEC ENGINES.  THREE TIMES ALREADY ON OUR WITHIN 100 HOURS.  IT IS A NUISANCE BECAUSE 	AN AIRCRAFT CAN EASILY BE STRANDED IN A LOCATION WITHOUT A THIELERT APPROVED MECHANIC. OR WORSE, IF A GENUINE PROBLEM EX	1	L	7	1 	3O			NT	A47CE   					 
2007052100146	20070521	00146	CE  	2007	5	21	2007FA0000388    	1	20070413	G	3233	99101368	ACTUATOR        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT MLG	CORRODED        	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	61	6672C	7623 				414A0053				LT LANDING GEAR ACTUATOR FAILED WHILE TAXING.  COLLAPSED LT WING.  DAMAGED LT PROP AND WING TIP.  ACTUATOR INSPECTED AND	 FOUND WATER INSIDE.  ACTUATOR OVERHAULED AND REINSTALLED NOSE AND RT LG ACTUATOR REMOVED FOR INSPECTION AND CHECKED GOO	D.  (K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007052100114	20070521	00114	EA  	2007	5	21	2007FA0000389    	2	20070420	G	8530	5L32006WA1	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	4801D	1400 				17272362				CRACK FROM EXH STUD AROUND CYLINDER TO UPPER SPARK PLUG.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007051400210	20070514	00210	GL  	2007	5	14	2007FA0000390    	2	20070412	G	7323	369A7701	BRACKET         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					GOVERNOR	DAMAGED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING A PREFLIGHT, THE PILOT NOTICED THE GOVENOR BELCRANK HAD SOME SLOP SUBSEQUENT INSPECTION DISCLOSED THAT THE BELCRA	NK PIVOT BOLT WAS MOVING  IN THE BRACKET BECAUSE THE HOLE WAS ELONGATED, REPLACED BRACKET.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007052100147	20070521	00147	SO  	2007	5	21	2007FA0000391    	2	20070411	G	7414	6310	MAGNETO         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					LEFT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	11BX	26   				CE388	814263R			DURING NORMAL FLIGHT, VFR CONDITIONS, LT MAGNETO FAILED TO CONTINUE FIRING.  AC LANDED WITHOUT INCIDENT.  UPON TROUBLESH	OOTING LT MAGNETO FOUND TO ONLY FIRE ON ONE LEAD.  MAGNETO REPLACED WITH NEW UNIT.  DEFECTIVE MAGNETO FOUND TO HAVE LOOS	E PARTS RATTLING INSIDE AFTER REMOVAL FROM ENGINE.  MAGNETO NOT DISASSEMBLED DUE TO WARRANTY STATUS OF MAGNETO.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007051400183	20070514	00183		2007	5	14	2007FA0000392    	1	20070301	G	1430		TAB             																		CRACKED         	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19										WHEN TECH WENT TO BEND THE TAB ATTACHED TO THE WASHER AT THE RADIUS OF THE BEND, THEY WOULD CRACK.  (K)																			 
2007052100084	20070521	00084	CE  	2007	5	21	2007FA0000393    	1	20070409	G	7921	LW10025	OIL COOLER      			BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					LT ENGINE	CRACKED         	G				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	09	1873W		142  			P231				ON APRIL 9, 2007, MADE A PRECAUTIONARY LANDING, AL (TCL) DUE TO LOW OIL PRESSURE ON THE LEFT ENGINE.  MAINTENANCE PERSON	NEL REPORTED THAT THE OIL COOLER HAD FAILED DUE TO CRACKS, THE OIL LEVEL WAS DOWN (4) QUARTS, AND THE OIL FILTER WAS INS	PECTED WITH NO CONTAMINATION FOUND.  ENGINE MAINTENANCE LOG RESEARCH SHOWED THE FAILED OIL COOLER WAS OVERHAULED AND INS	TALLED BY FIREWALL FORWARD.  THE COOLER WAS REPLACED WITH A NEW PART ON 4/13/2007 AT 1770.6 HOBBS.  THE FAILED OIL COOLE	R HAD 142.1 HOURS SINCE OVERHAUL.  NO DETERMINATION COULD BE MADE OF OIL COOLER TOTAL TIME. (K)		1	L	7	2 	3O	3	O		A12CE   	E10EA				 
2007051400208	20070514	00208	CE  	2007	5	14	2007FA0000394    	1	20070406	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LT MLG	CRACKED         	D			H2US	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	11	9353D					172RG1131	L1868036A	801202		PILOT REPORTED LOUD POP JUST BEFORE INTERING THE PATTERN AT M89.  WHEN HE EXTENDED THE GEAR THE GREEN GEAR DOWN LIGHT WO	ULD NOT COME ON.  FLY BY REVEALED THE LEFT GEAR WAS IN TRANSIENT.  GEAR UP LANDING FOLLOWED.  INSPECTION OF LT MAIN GEAR	 ACTUATOR REVEALED THE ACTUATOR HOUSING WAS CRACKED ACROSS THE FORWARD ATTACH BOLT HOLE.  THE CRACKED HOUSING ALLOWED TH	E PISTON RACK TO JUMP GEARS ON THE PINION GEAR ATTACHED TO MAIN GEAR LEG.  THIS AREA IS INSPECTED EACH 100 HR FOR CRACKS	 AND DEFECTS VERY CAREFULLY WITH LIGHTS AND INSPECTION MIRROWS.  TIME SINCE LAST INSPECTION WAS 25 HRS.  AD 2001-06-06 W	AS CW 8-13-2001 TACH 497, TOTAL TIME 4516 WITH NO DEFECTS FOUND.  (K)	1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007051400224	20070514	00224	CE  	2007	5	14	2007FA0000395    	1	20070423	G	3246	13685	BEARING         			BEECH 	1900  	1900D       	1154162	CE  										MLG	LACK OF LUBE    	B			HY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	733DC	360  				UE307				WHILE PERFORMING ROUTINE PREVENTATIVE MAINTENANCEON THE RT IB WHEEL AND TIRE ASSEMBLY (TO CHANGE A WORN TIRE) ONE OF THE	 WHEEL BEARING ROLLERS CAME OUT OF THE OUTER WHEEL BEARING ONCE THE WHEEL BEARING WAS REMOVED FROM THE WHEEL ASSEMBLY.  	THE WHEEL BEARING CAGE WAS FOUND TO BE DEFORMED WITH ONE PART OF THE CAGE BROKEN ALLOWING THE ROLLER TO FALL OUT.  PIECE	S OF METAL WERE FOUND IN THE BEARING SEAL.  THE BEARING APPEARS TO HAVE BEEN OVERHEATED.  PROPER LUBRICATION WOULD HAVE 	PREVENTED THIS BEARING FROM OVERHEATING.  IT IS IMPERATIVE THAT EACH OPERATOR BE AWARE THAT THE INSPECTION AND LUBRICATI	ON REQURIEMENT/INTERVAL FOR THE WHEEL BEARINGS MAY BE LESS THAN THE MFG RECOMMENDATIONS BASED ON THE OPERATORS OWN SPECI	2	L	7	2 	4T			RT	A24CE   					 
2007051400182	20070514	00182		2007	5	14	2007FA0000396    	4	20070430	G	3400	593250101	SWITCH          			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	STUCK           	B			YLMR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	42SG	2972 				4140927				AVIONICS MASTER SWITCH STUCK IN THE ON POSITION AD 2005-20-25 WAS PREVIOUSL COMPLIED WITH AND DID NOT APPLY.  DATE CODE 	OF THE SWITCH WAS 7647.  THERE WAS NO BURNING SMELL WHEN THE SWITCH BECAME STUCK.  (K)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2007052100141	20070521	00141	SO  	2007	5	21	2007FA0000397    	1	20070331	G	3210		BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	AEIO540*    		EA  					MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	61	7178P					242347	L259640			BEARING ROD END BROKEN AT THREAD EXP BEARING (452377) CONDUIT BENT. CONTROL ASSY (455180).						1	L	7	1 	3O	3	O		1A15    	1E4				 
2007052100075	20070521	00075	SO  	2007	5	21	2007FA0000398    	2	20070418	G	7414	6320	MAGNETO         			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	CORRODED        	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	13	5361Y	525  				21064183	517975	871106		EMERGENCY RETURN TO FIELD:  INSPECTION REQUIREMENTS FOR MAGNETO (PN 6320) ARC NOT ADEQUATE TO INSURE PROPER VENTING (PRE	SSURIZED MAG).  SB 2-80C SPECIFIES ONLY EXTERNAL INSPECTION IS REQUIRED EVERY 100 HOURS AND AN INTERNAL INSPECTION AFTER	 500 HOURS.  THE SUBJECT MAGNETOS WITH 525 AND 438 CONTAINED MOISTURE AND EXCESSIVE CORROSION INTERNALLY BECAUSE THE PRE	VIOUS REQUIREMENTS TO TEST PRESSURIZED MAGNETOS CONTAINED IN SB 1-88A DO NOT APPLY TO THE 6300 SERIES MAGNETOS.  (K)			1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL	 
2007052100115	20070521	00115	SO  	2007	5	21	2007FA0000399    	2	20070418	G	7414	6320	MAGNETO         			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	CORRODED        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5361Y	438  				21064183	517975	871106		EMERGENCY RETURN TO FIELD:  INSPECTION REQUIREMENTS FOR MAGNETO (PN 6320) ARC NOT ADEQUATE TO INSURE PROPER VENTING (PRE	SSURIZED MAG).  SB2-80C SPECIFIES ONLY EXTERNAL INSPECTION IS REQUIRED EVERY 100 HOURS AND AN INTERNAL INSPECTION AFTER 	500 HOURS.  THE SUBECT MAGNETOS WITH 525 AND 438 CONTAINED MOISTURE AND EXCESSIVE CORROSION INTERNALLY BECAUSE THE PREVI	OUS REQUIREMENTS TO TEST PRESSURIZED MAGNETOS CONTAINED IN SB 1-88A DO NOT APPLY TO THE 6300 SERIES MAGNETOS.  (K)			1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL	 
2007051400200	20070514	00200	GL  	2007	5	14	2007FA0000400    	2	20070425	G	7230		BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			EOOR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	03	511SB	504  				1090592D	CAE830001			DURING FLIGHT THE UPPER CHIP PULL ILLUMINATED, IT WAS CLEANED IAW MM AND RETURNED TO SERVICE.  A COUPLE OF HOURS LATER, 	A SECOND LIGHT ILLUMINATED.  FOUND LOTS OF FINE CHIPS.  REPLACED ENGINE.  FOUND NR 1 BEARING BAD.  (K)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007061500173	20070615	00173		2007	6	15	2007FA0000401    	1	20070521	G	5100	31699042	HOUSING         																	UNKNOWN	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										CRACK IN PART ID.																			 
2007061500174	20070615	00174	CE  	2007	6	15	2007FA0000402    	1	20070522	G	2750		CONTROL CABLE   			SYMPHO	SA160 	SA160       	05619SU	CE  										TE FLAPS	CHAFED          	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										DURING PREFLIGHT INSPECTION, FOUND FLAP CONTROL CABLES CHAFING ON THE FLAP TRACK.  DEPTH OF INTERFERENCE BETWEEN CABLE A	ND TRACK WAS ABOUT THE DIAMETER OF THE CABLE.					1	H	7	1 	3O			NT	A46CE   					 
2007061500175	20070615	00175	CE  	2007	6	15	2007FA0000403    	1	20070522	G	5750		CONTROL CABLE   			SYMPHO	SA160 	SA160       	05619SU	CE  										TE FLAPS	CHAFED          	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										DURING PREFLIGHT INSPECTION, FOUND FLAP CONTROL CABLES CHAFING ON THE FLAP TRACK.  DEPTH OF INTERFERENCE BETWEEN CABLE A	ND TRACK WAS ABOUT THE DIAMETER OF THE CABLE.					1	H	7	1 	3O			NT	A46CE   					 
2007061500176	20070615	00176	EU  	2007	6	15	2007FA0000404    	1	20070522	G	5330		SKIN            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	600NY					231				FOUND SEVERE PITTING CORROSION ON BOTH THE LT AND RT SIDES BETWEEN FRAME, STATIONS 184 AND 194 BELOW EMERGENCY ESCAPE DO	ORS.  BELIEVE THIS IS DUE TO WATER LEAKING AROUND THE EMERGENCY ESCAPE DOORS AND SOAKING THE SOUND DAMPENING INSULATION.	  THE PITTING WAS SO BAD IT CORRODED THROUGH THE SKIN ON THE RT SIDE.  THIS CORROSION WAS FOUND DURING AN RVSM INSTALLAT	ION WHILE WE WERE MARKING OUT THE CRITICAL REGION AROUND THE STATIC PORTS.  WE REPAIRED THE DAMAGE FOLLOWING APPROVED DA	TA FROM A STRUCTURAL ENGINEER AND RETURNED TO SERVICE IAW FAA FORM 8110-3.		2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007061500177	20070615	00177	EU  	2007	6	15	2007FA0000405    	1	20070522	G	5330		SKIN            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	600NY					231				FOUND SEVERE (PITTING CORROSION) ON BOTH THE LT AND RT SIDES BETWEEN FRAME, STATIONS 184 AND 194 BELOW EMERGENCY ESCAPE 	DOORS.  THIS IS DUE TO WATER LEAKING AROUND THE EMERGENCY ESCAPE DOORS AND SOAKING THE SOUND DAMPENING INSULATION.  THE 	PITTING WAS SO BAD IT CORRODED THROUGH THE SKIN ON THE RT SIDE.  THIS CORROSION WAS FOUND DURING AN RVSM INSTALLATION WH	ILE WE WERE MARKING OUT THE CRITICAL REGION AROUND THE STATIC PORTS.  REPAIRED THE DAMAGE FOLLOWING APPROVED DATA FROM A	 STRUCTURAL ENGINEER AND RETURNED TO SERVICE IAW FAA FORM 8110-3.		2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007061400237	20070614	00237	CE  	2007	6	14	2007FA0000410    	1	20070110	G	3245	0923540	TUBE            			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985*       	52008	NE  					TIRE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	500MK	50   								THIS IS THE THIRD NEW MFG INNER TUBE THAT HAS SPLIT ALONG CIRCUMFERENTIAL WELDED SEAMS.						1	L	7	2 	3R	3	R		A765    	5E1				 
2007061500171	20070615	00171	EU  	2007	6	15	2007FA0000411    	1	20070515	G	3210	5321012110	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LANDING GEAR	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	624AF	1576 			AM090	624	PR0499	KX227		DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF	 THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12.	205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERMI	NE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING G	EAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061500192	20070615	00192	EU  	2007	6	15	2007FA0000412    	1	20070515	G	3210	5321012110	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LANDING GEAR	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	624AF	1576 			AM090	624	PR0499	KX227		DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF	 THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12.	205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERMI	NE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING G	EAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061500193	20070615	00193	EU  	2007	6	15	2007FA0000413    	1	20070515	G	3210	5321012110	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ZONE 700	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	624AF	1576 			AM090	624	PR0499	KX227		DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF	 THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12.	205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERMI	NE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING G	EAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061500194	20070615	00194	EU  	2007	6	15	2007FA0000414    	1	20070515	G	3210	5321012110	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ZONE 700	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	624AF	1576 			AM090	624	PR0499	KX227		DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF	 THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12.	205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED.  THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERM	INE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING 	GEAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000002	20070530	00002	EA  	2007	5	30	2007FA0000416    	2	20070415	G	7322	103103	CARBURETOR      			AMTR  	VAN   	HATZVAN     	0561383	GL  	LYC   	O235  	O235C1      	41505	EA  	SNSNCH	76AM	M76AM       	EA  	ENGINE	CONTAMINATED    	C				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			GL	15	899P					313	335915	12242		DURING INSPECTION OF THE CARBURETOR, DISCOVERED FLAKES OF WHAT APPEARS TO BE METAL IN THE GASCOLATOR SCREEN.  ALSO, OBSE	RVED SOME SPECS OF RED MATERIAL ABOUT THE SIZE OF PEPPER. WHEN WE PULLED THE CARB APART WE OBSERVED A LINE ON THE BOTTOM	 OF THE BOWL WHERE SEDIMENT HAD PREVIOUSLY SETTLED IN THE BOWL. HOWEVER, NOTHING SIGNIFICANT WAS NOTED IN THE BOWL DURIN	G OUR INSPECTION.  FURTHER INSPECTION REVEALED THAT ONCE THE NEEDLE VALVE WAS SEATED BY LIGHTLY PRESSING THE FLOAT UPWAR	D, IT WOULD THEN REMAIN SEATED EVEN IF AIR WAS BLOWN IN THE FUEL INLET  PORT. HOWEVER, IF THE FLOAT WAS MANIPULATED UP A	ND DOWN A FEW TIMES, THE NEEDLE VALVE WOULD THEN NOTICEABLY POP FREE. AND ALTHOUGH NO OBVIOUS DEBRIS WAS NOTED UPON DISA	1	H	7	1 	3O	3	O		EXPA1H71	E223	5	N	1P210	 
2007061500195	20070615	00195	CE  	2007	6	15	2007FA0000417    	1	20070511	G	5711		SPAR            			BBAVIA	11    	11AC        	0191102	CE  	LYC   	O235  	O235*       	41505	EA  	SNSNCH	76AK	M76AK       	EA  	LT WING	DELAMINATED     	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	3581E					11AC1813	108715	11544		DELAMINATION OCCURRING AT LT FRONT WING SPAR / STRUT LOCATION.  CRACK AT BOTTOM EDGE, AT WING ROOT FITTING.  POSSIBLE AG	E OF SPAR CAUSING DELAMINATION.  LONGITUDINAL CRACK AT WING ROOT POSSIBLE EARLIER DAMAGE.  REPLACED WITH NEW WOOD SPAR P	/N 5146L.				1	H	7	1 	3O	3	O		A761    	E223	5	N	1P210	 
2007061300214	20070613	00214	CE  	2007	6	13	2007FA0000419    	1	20070410	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		13510	365  							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 365 HOURS PRIOR.POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300205	20070613	00205	SO  	2007	6	13	2007FA0000420    	1	20070510	G	2571	352020035201	BATTERY BOX     			PIPER 	PA28  	PA28181     	7102807	SO  											BROKEN          	B			LC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	6151H					287890211				PLASTIC BATTERY BOX BROKE INTO SEVERAL PIECES. LID WOULD NO LONGER HOLD SECURLY ON THE BOX ALLOWING BATTERY TO BE UNSECU	RED IN THE AIRCRAFT. PIPER REPIORTED THAT P/N 35201-00 LID AND 35202-00 WAS NO LONGER AVAILABLE. INSTALLED STC'D BATTERY	 BOX TO REPLACE THE DAMAGED ONE.				1	L	7	1 	3O				2A13    					 
2007061500197	20070615	00197	CE  	2007	6	15	2007FA0000425    	1	20070515	G	5511	0432001466	RIB             			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2586J	8600 				15061086				DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRD STRIKE FOUND BOTH IB LEADING EDGE RIBS PN 0	432001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FO	RWARD SPAR. BIRD STRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDE	NCE OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR.			1	H	7	1 	3O	3	O		3A19    	E252				 
2007061500198	20070615	00198	CE  	2007	6	15	2007FA0000426    	1	20070515	G	5511	0432001466	RIB             			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	2586J	8600 				15061086				DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRD STRIKE FOUND BOTH IB LEADING EDGE RIBS PN 0	432001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FO	RWARD SPAR. BIRDSTRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDEN	CE OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR.			1	H	7	1 	3O	3	O		3A19    	E252				 
2007061500199	20070615	00199	CE  	2007	6	15	2007FA0000427    	1	20070515	G	5511	0432001466	RIB             			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2586J	8600 				15061086				DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRDSTRIKE FOUND BOTH IB LEADING EDGE RIBS PN 04	32001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FOR	WARD SPAR. BIRDSTRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDENC	E OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR.			1	H	7	1 	3O	3	O		3A19    	E252				 
2007061500200	20070615	00200	CE  	2007	6	15	2007FA0000428    	1	20070515	G	5511	0432001466	RIB             			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2586J	8600 				15061086				DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRDSTRIKE FOUND BOTH IB LEADING EDGE RIBS PN 04	32001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FOR	WARD SPAR. BIRDSTRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDENC	E OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR.			1	H	7	1 	3O	3	O		3A19    	E252				 
2007061500202	20070615	00202	CE  	2007	6	15	2007FA0000429    	1	20070515	G	7820	E477001	MUFFLER         			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2586J	3128 				15061086				PILOT REPORTED FATIGUE WHILE FLYING. NO OBVIOUS EXTERNAL SIGNS OF MUFFLER FAILURE WERE FOUND, SHROUD REMOVAL REVEALED A 	TIGHT CRACK FROM NR 2 RISER INTO BODY, 3 INCHES LONG THAT LEFT VERY LITTLE STAINING ON INSIDE OF SHROUD. MUFFLER BODY WA	S DEFORMED WHERE RISER IS WELDED INTO BODY, NEW MUFFLER HAD NO DEFORMATION IN THIS AREA.				1	H	7	1 	3O	3	O		3A19    	E252				 
2007061500201	20070615	00201	CE  	2007	6	15	2007FA0000434    	1	20070515	G	7820	E477001	MUFFLER         			CESSNA	150   	150E        	2071812	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	2586J	3128 				15061086				PILOT REPORTED FATIGUE WHILE FLYING. NO OBVIOUS EXTERNAL SIGNS OF MUFFLER FAILURE WERE FOUND, SHROUD REMOVAL REVEALED A 	TIGHT CRACK FROM NR 2 RISER INTO BODY, 3 INCHES LONG THAT LT VERY LITTLE STAINING ON INSIDE OF SHROUD.  MUFFLER BODY WAS	 DEFORMED WHERE RISER IS WELDED INTO BODY, NEW MUFFLER HAD NO DEFORMATION IN THIS AREA.				1	H	7	1 	3O	3	O		3A19    	E252				 
2007061300225	20070613	00225	CE  	2007	6	13	2007FA0000435    	1	20070209	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		13502	422  							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE. EXHAUST DUCT SB HAD BEEN COMPLIED WITH 422 HOURS PRIOR. POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007053000005	20070530	00005	SO  	2007	5	30	2007FA0000436    	2	20070410	G	8530	649169	CYLINDER        								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17										PARTIAL HEAD AND BARREL SEPARATION. LARGE CRACK STARTING AT THE FUEL INJECTOR PORT RUNNING INTO THE CYLINDER HEAD COMBUS	TION CHAMBER, THROUGH THE INTAKE SEAT BOSS AND CONTINUING AROUND TO THE LOWER SPARK PLUG BOSS.										3	O			E5CE				 
2007061500204	20070615	00204	EU  	2007	6	15	2007FA0000437    	1	20070522	G	5330		SKIN            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	600NY					231				FOUND SEVERE PITTING CORROSION ON BOTH THE LT AND RT SIDES BETWEEN FRAME STATIONS 184 AND 194 BELOW EMERGENCY ESCAPE DOO	RS.  THIS IS DUE TO WATER LEAKING AROUND THE EMERGENCY ESCAPE DOORS AND SOAKING THE SOUND DAMPENING INSULATION.  THE PIT	TING WAS SO BAD IT CORRODED THROUGH THE SKIN ON THE RT SIDE.  THIS CORROSION WAS FOUND DURING AN RVSM INSTALLATION WHILE	 WE WERE MARKING OUT THE CRITICAL REGION AROUND THE STATIC PORTS.  REPAIRED THE DAMAGE FOLLOWING APPROVED DATA FROM A ST	RUCTURAL ENGINEER AND RETURNED TO SERVICE IAW FAA FORM 8110-3.		2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007061500205	20070615	00205	GL  	2007	6	15	2007FA0000443    	3	20070525	G	6110		ROD             			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09								001922		RECEIVED PROPELLER FOR OVERHAUL. DURING PREFUNCTION TEST FOUND BLADE NR 1 WAS NOT LINKED TO THE PITCH CHANGE ROD. AFTER 	DISASSEMBLY OF PROPELLER FOUND NR 1 BLADE ACTUATING PIN PN B5072-1 DISCONNECTED FROM BLADE. ACTUATING PIN ATTACHMENT SCR	EWS WERE SAFETIED AND HAD ANTISABOTAGE ON THE SCREW HEADS. THE THREADS HAD BEEN PULLED OUT OF THE BLADE. THERE WAS NO OB	VIOUS SIGNS OF SUDDEN STOPPAGE OR A STRIKE. ALL BLADES SHOWED SIMILAR EROSION FROM ROCK DAMAGE. BLADE TRACK WAS .0625 IN	CH PLUS OR MINUS AND DIAMETER WAS 106 INCHES.IAW THE RECORD, THIS WAS THE FIRST OVERHAUL EVENT. MANUFACTURE HAS REQUESTE	D BLADE, ACTUATING PIN AND LINK BE RETURNED TO THEM FOR EVALUATION.	1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
2007061800104	20070618	00104		2007	6	18	2007FA0000444    	2	20070421	G	8500	12501	ENGINE          																		MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	620TS					20				AIRCRAFT ECU WARNING LIGHT COME ON FREQUENTLY.  WE SPOKE WITH THIELERT ABOUT THE PROBLEM AND THEY SAY THAT DURING STEEP 	BANKS OR YAW THE FUEL PRESSURE CAN BE DIFFERENT BETWEEN THE RAILS ON EACH ENGINE.  THE ECU CAN INTERPRET THIS AS A PROBL	EM AND TURN ON THE ANNUNCIATOR.  THIS IS MOSTLY A NUISANCE BECAUSE EVERYTIME THE AN ANNUNCIATOR TURNS ON WE MUST BRING T	HE AIRCRAFT TO A MECHANIC WHO MUST CLEAR THE PROBLEM FORM THE COMMPUTER.  WHILE THE ANNUNCIATOR IS ON WE HAVE NO WAY OF 	KNOWING IF A REAL PROBLEM DEVELOPS BECAUSE THE ANNUCIATOR IS STILL ON. IN ADDITION AS A FLIGHT SCHOOL IT COSTS US SIGNIF	ICANT AMOUNTS OF LOST REVENUE EVERY TIME THAT WE MUST TAKE THE AIRPLANE OFF-LINE UNTIL OUR MECHANICE CAN INSPECT IT.   O														 
2007060100116	20070601	00116	EU  	2007	6	1	2007FA0000447    	1	20070508	G	2150	5700700A	HOSE            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					A/C SYSTEM	BURST           	D				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			EA	01	849BP					3554	22310			HIGH PRESSURE AIR CONDITIONER HOSE BURST.						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007053000016	20070530	00016	EA  	2007	5	30	2007FA0000450    	2	20070328	G	8530	LW19279	CYLINDER        			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					ENGINE	SCRATCHED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28		1023 	1023 			T20608350	172S08719			SET OF 6 CYLINDERS CAME IN WITH 2 BROKEN CONTROL RINGS. CYLINDERS HAD RING STEPS ON TOP AND BOTTOM OF CYLINDER BARRELS. 	CORROSION WAS PRESENT IN BARRELS FROM THE MIDDLE UP TO THE HEAD OF THE CYLINDERS. EXHAUST GUIDES WERE FAR OUT OF LIMITS 	AND DIFFICULT TO REMOVE RESULTING IN HAVING TO OVERSIZE 3 BOSSES TO P05 GUIDES AND THE OTHER 3 TO P10. 2 EXHAUST SEATS F	ELL OUT DURING THE HEAT SOAK FOR INSTALLING THE EXHAUST GUIDES. BROKEN RINGS DAMAGED 2 PISTONS WHICH HAD TO BE REMOVED F	ROM SERVICE. 4 OTHER PISTONS WERE DAMAGED IN THE PISTON PIN BOSSES. THE BROKEN RINGS ALSO CAUSED MODERATE SCRATCHING TO 	THE BARREL OF THE CYLINDERS WHICH WAS REMOVABLE BY POWER HONING. 2 CYLINDERS HAD TO BE OVERSIZED FROM THE CORROSION AND 	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2007061300167	20070613	00167	EA  	2007	6	13	2007FA0000451    	2	20070328	G	8530	LW19279	CYLINDER        			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					ENGINE	SCRATCHED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07		1023 	1023 			T20608350	172S08719			SET OF 6 CYLINDERS CAME IN WITH 2 BROKEN CONTROL RINGS. CYLINDERS HAD RING STEPS ON TOP AND BOTTOM OF CYLINDER BARRELS. 	CORROSION WAS PRESENT IN BARRELS FROM THE MIDDLE UP TO THE HEAD OF THE CYLINDERS. EXHAUST GUIDES WERE FAR OUT OF LIMITS 	AND DIFFICULT TO REMOVE RESULTING IN HAVING TO OVERSIZE 3 BOSSES TO P05 GUIDES AND THE OTHER 3 TO P10. 2 EXHAUST SEATS F	ELL OUT DURING THE HEAT SOAK FOR INSTALLING THE EXHAUST GUIDES. BROKEN RINGS DAMAGED 2 PISTONS WHICH HAD TO BE REMOVED F	ROM SERVICE. 4 OTHER PISTONS WERE DAMAGED IN THE PISTON PIN BOSSES. THE BROKEN RINGS ALSO CAUSED MODERATE SCRATCHING TO 	THE BARREL OF THE CYLINDERS WHICH WAS REMOVABLE BY POWER HONING. 2 CYLINDERS HAD TO BE OVERSIZED FROM THE CORROSION AND 	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2007060700007	20070607	00007	SO  	2007	6	7	2007FA0000453    	1	20070407	G	5610	1159SCB31023	WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					COCKPIT	FAILED          	B			JUOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	495RS	2735 				1161				CREW REPORTS WINDSHIELD FAILURE DURING PART 91 MAINTENANCE POSITIONING FLIGHT.  EMERGENCY DECLARED WITH UNEVENTFUL LANDI	NG.  AIRCRAFT CONTINUED TO DESTINATION AIRPORT UNDER CDL RESTRICTIONS.  UNKNOWN CAUSE.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007060100107	20070601	00107	SO  	2007	6	1	2007FA0000454    	2	20070501	G	7414		BRUSHES         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					MAGNETO	WORN            	B			YYBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	154WF	423  				1638	360136			THIS MAGNETO WAS MISFIRING, AND APPEARS TO HAVE CAUSED DETONATION IN THE NR 5 CYLINDER.  PISTON MATERIAL WAS FOUND IN TH	E OIL FILTER AND OIL COOLER.  ENGINE HAD TO BE REMOVED, INSPECTED, AND REPAIRED DUE TO THE DETONATION.  THE MAGNETO WAS 	FOUND TO HAVE A SEVERELY WORN BRUSH (K3215), THE BRUSH BLOCK WAS MELTED (K3823), THE COIL WAS BURNED CLOSE TO THE BRUSH 	CONTACT POINT (K3975), AND THE POINTS WERE BADLY BURNED (M3081).  THIS IS THE (3RD) OCCURRENCE FOUND WITH THIS SAME PROB	LEM.  (K)		1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2007060100112	20070601	00112	CE  	2007	6	1	2007FA0000455    	1	20070505	G	3230	08940002	GEARBOX         			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	2745F					340A0949				GEAR MOTOR, REDUCTION GEAR BOX AND GEAR TRANSMISSION WERE REMOVED AND SENT OUT TO FOR INSPECTION.  WHEN THEY OPENED GEAR	 REDUCTION BOX, THEY DISCOVERED THAT ONE OF THE MOUNTING BOLTS HAVE BEEN OF THE IMPROPER LENGTH CAUSING THE THREAD PATTE	RN.  TBOLT SHOWS SLIGHT WEAR WHERE IT TOUCHED THE GEAR SYSTEM.  ACCORDING TO MFG THERE WAS ONLY A SLIGHT TRANSFER TO GEA	R, WHICH THEY FEEL WOULD NOT HAVE CAUSED A PROBLEM.  CANNOT DETERMINE HOW LONG THIS CONDITION EXISTED.  THE BOLTS LOOK T	O BE OLD AND THE INTERNAL GEAR BOX SEEMS ALSO TO BE OLD.  THE INSTALLATION CALLED FOR A .8750 INCH BOLT FOR THIS MOUNTIN	G HOLE, AND REMOVED A 1 INCH BOLT.  THE CORRECTIVE ACTION IS TO INSTALL THE REPAIRED GEAR BOX AND THE CORRECT MOUNTING H	1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007060700031	20070607	00031	GL  	2007	6	7	2007FA0000456    	3	20070516	G	6110	B24573	FORK            			BNORM 	BN2   	BN2         	1520202	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PITCH CHANGE	UNSERVICEABLE   	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19								AU9949B		STEEL FATIGUE CRACK NDT (MAGNETIC PARTICLE) DETECTED.  PROPELLER ASSY RECEIVED FOR STANDARD OVERHAUL AND DEFECT FOUND IN	 PROPELLER ASSY (PN C2K00500, DESCRIPTION HC-C2YK-2CUF/FC8477A-4, SN AU9949B), UNDER WO NR 38425A.					1	H	7	2 	3O				A17EU   		5	C	P920	 
2007060700009	20070607	00009	GL  	2007	6	7	2007FA0000457    	3	20070516	G	6111	F8468A6R	BLADE           			PZLWAR	WILGA 	PZL104W35A  	7360104	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	CRACKED         	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	424HD					00030015		DY2965A		ALUMINUM FATIGUE CRACK VISUALLY AND NDT DETECTED.  PROPELLER ASSY RECEIVED FOR OVERHAUL AND BLADE NR 2 OF 3 REMOVED FROM	 PROPELLER ASSY (HC-C3YR-1RF/ F8468A-6R, UNDER WO NR 38598A.  NOTE: MANDATORY OVERHAUL REQUIRED DUE TO GROUND STRIKE, HO	WEVER, BLADE SUBMITTED WAS NOT BENT AND LEAST DAMAGED.  (K)				1	H	7	1 	3R	3	O	NC	EXPA1H71	1E4	5	C	P25EA	 
2007060100113	20070601	00113	WP  	2007	6	1	2007FA0000458    	2	20070502	G	7321	307080026	FUEL CONTROL    			AMD   	FALC90	FALCON900B  	2730171	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	FAULTY          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	4MB	5476 	1861 			146	P101199			PILOTS REPORTED THAT ENGINE THAT THIS FUEL CONTROL UNIT WAS INSTALLED ON COULD NOT BE CONTROLLED BY NORMAL COMPUTER MODE	, AND THAT WHEN THEY WENT TO MANUAL MODE THAT THEY COULD NOT CONTROL ENGINE SPEED FUNCTIONS EITHER.  IT SEEMS THAT THIS 	FUEL CONTROL HAS SOME INTERNAL FAULT.  REPLACEMENT FUEL CONTROL RESOLVED THIS PROBLEM.  (K)				2	L	7	3 	4F	4	F	RT	        	E6WE				 
2007060600001	20070606	00001	CE  	2007	6	6	2007FA0000459    	1	20070404	G	2720	04140161532	BRACKET         			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300*       	17022	SO  					RUDDER CONTROL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	8879U	2961 				17252796				DURING ANNUAL INSPECTION BRACKET (PN 04140616-1-532).  FOUND BROKEN AND CRACKED IN OTHER LOCATIONS.  LOCATED UNDER FLOOR	 CENTER SECTION AT FLIGHT CONTROL BELL CRACK.  REPLACED WITH NEW PART.  REQUEST INSPECTORS CHECK THIS AREA OF THE FLIGHT	 CONTROLS CAREFULLY DURING 100/ANNUAL INSPECTION. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2007060100115	20070601	00115	CE  	2007	6	1	2007FA0000460    	1	20070430	G	3297	D3899924WD19	CONNECTOR       			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ44        	66000	GL  					ANTI SKID SYS	FAULTY          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	972PF	976  				RB38				TROUBLESHOT INTERMITTENT ANTI-SKID SYSTEM FAIL ANNUNCIATION, CABIN DOOR SEAL STAYING INFLATED ON GROUND, AND LIFT DUMP H	ANDLE OPERATION.  FOUND BAD CRIMP ON PIN (L) FOR WIRE G117B24 IN LT MLG SQUAT SWITCH CONNECTOR.  FUNCTIONAL CHECKS OK.  	(K)				1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2007060100114	20070601	00114	SO  	2007	6	1	2007FA0000461    	2	20070309	G	7414	1051324	SPRING          	CONT        		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					MAGNETO	BROKEN          	E			MKWA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	7293R	827  			F02CA139R	TH590	824323R			WHILE TROUBLESHOOTING ENGINE RUNS ROUGH AND WONT RUN AT ALL OVER 1200 RPM.  WE DISCOVERED THE IMPULSE COUPLING SPRINGS 	ON BOTH MAGS WERE BROKEN.  (IMPULSE COUPLING , PN 10-400309)  (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2007060700033	20070607	00033	SO  	2007	6	7	2007FA0000462    	2	20070309	G	7414	1051324	SPRING          	CONT        		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	7293R	827  			F02CA164R	TH590	824323			WHILE TROUBLESHOOTING ENGINE RUNS ROUGH AND WON`T RUN AT ALL OVER 1200 RPM.  WE DISCOVERED THE IMPULSE COUPLING SPRINGS 	ON BOTH MAGS WERE BROKEN.  (IMPULSE COUPLING PN 10400309) (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2007060600002	20070606	00002	CE  	2007	6	6	2007FA0000463    	1	20070514	G	5711		SPAR            			BBAVIA	11    	11BC        	0191106	CE  	LYC   	O235  	O235*       	41505	EA  	SNSNCH	76AK	M76AK       	EA  	LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	3581E					11AC1813	108715	11544		DELAMINATION OCCURRING AT WING STRUT ATTACH LOCATION.  CRACK AT BOTTOM EDGE AT ROOT FITTING.  POSSIBLE AGE OF SPAR CAUSI	NG DELAMINATION.  LONGITUDINAL CRACK AT WING ROOT POSSIBLE EARLIER DAMAGE REPLACE WITH NEW WOOD SPAR (PN 5146L).  (K)					1	H	7	1 	3O	3	O		A761    	E223	5	N	1P210	 
2007061500103	20070615	00103		2007	6	15	2007FA0000464    	1	20070430	G	6100		BOLT            								LYC   	O360  	O360*       	41514	EA  	MCAULY	1A200	1A200*      	GL  	PROPELLER	SHORT           	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AL	05	866MM	400  						YI46003		INSPECTING PROPELLER DURING ANNUAL, FOUND PROPELLER BOLTS 0.25 IN SHORT OF BACK SIDE OF FLANGE INSERTS.  ALL BOLT THREAD	 ENGAGEMENT WAS FORWARD OF INSERT BOSS.  AFT .2500 INC OF INSERT, MATERIAL BEHIND CRANK FLANGE, HAD NO THREAD ENGAGEMENT	.  WRONG BOLTS INSTALLED, CORRECTED BY INSTALLING PROP BOLT KIT (PN 76EM8) WHICH PROVIDED (2) THREADS THROUGH INSERT WHE	N TROQUED.  (K)								3	O			E286	5	N	P874	 
2007060700014	20070607	00014	EU  	2007	6	7	2007FA0000465    	1	20070509	G	3411		PITOT LINE      			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 2	LOOSE           	B			EBVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	160FJ					160				WHILE TROUBLESHOOTING A LEAK IN NR 2 STATIC SYSTEM, THE RT SIDE STATIC PLATE HAD TO BE TAKEN LOOSE.  UPON REMOVAL OF THE	 PLATE, SILICONE RTV WAS FOUND ON THE FITTING FOR THE NR 1 STATIC SYSTE.  WHEN THE FITTING WAS LOOSENED, FOUND A LAGRE A	OUNT OF TEFLON PIPE TAPE WRAPPED AROUND THE NIPPLE OF THE STATIC PLATE, AND THE FLARE OF THE ALUMINUM HARD LINE GOING TO	 THE STATIC PLATE WAS BROKEN OFF AND LAYING LOOSE IN THE ASSY.  A TECH IN THE PAST HAD POSSIBLY EXPERIENCED A LEAK ON TH	IS SYSEM, AND LOADED THE NIPPLE WITH TEFLON TAPE AND RTV TTO GET THE SYSTEM TO SEAL, INSTAD OF REPAIRING THE HARD LINE. 	 THESE LINES SHOULD BE REPAIRED IAW STANDARD PRACTICE TO PREVENT PREMATURE FAILURE.  (K)	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2007060500272	20070605	00272	CE  	2007	6	5	2007FA0000466    	1	20070201	G	3310		LIGHT           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COMPASS	FIRE            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	340JH					340A0771				COMPASS LIGHT/SOCKET OVERHEATED DURING TAXI AND CAUGHT FIRE BEFORE THE CIRCUIT BREAKER TRIPPED.  PILOT EXTINGUISHED FIRE	 WITH HANDKERCHIEF.  CAUSE UNKNOWN, NO DAMAGE TO AIRCRAFT INTERIOR OR STRUCTURE.  (K)					1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007060700035	20070607	00035	CE  	2007	6	7	2007FA0000467    	1	20070316	G	5532		SKIN            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A6       	52043	EA  					VERTICAL STAB	DAMAGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	135YV					UE135				VERTICAL STABILIZER LEADING EDGE SKIN ATTACH RIVETS WORKING.  FOUND THAT THE ORIGINAL UNIVERSAL HEAD RIVETS WERE REPLACE	D WITH FLUSH RIVETS.  THE SKIN WAS COUNTERSUNK TO ACCOMMODATE THE RIVETS, HOWEVER THE SKIN WAS TOO THIN TO COUNTERSINK A	ND EVENTUALLY WORKED LOOSE.  SKIN WAS REPAIRED IAW DER ENGINEERING REPORT AND CORRECT RIVETS INSTALLED.  STRICT ADHERENC	E TO PUBLISHED DATA WOULD HAVE PREVENTED DAMAGE.  (K)			2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2007060700034	20070607	00034	EU  	2007	6	7	2007FA0000468    	1	20070501	G	5610	D25W343001009	WINDSHIELD      			ISRAEL	1125  	ASTRASPX    	4500205	EU  										COCKPIT	CRACKED         	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	411MM					080				THE WINDSHIELD ON THE PILOT`S SIDE CRACKED DURING FLIGHT AT F/L 41,000 FT ON 4/24/2007.  THE WINDSHIELD HAD 3104.6 TT.  	(K)					2	L	7	2 	4F			RT	A16NM   					 
2007060700026	20070607	00026	CE  	2007	6	7	2007FA0000469    	1	20070227	G	3220	C611300518	LINK            			BEECH 	90    	F90         	1152909	CE  										NLG	DAMAGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	189JR					LA61				THIS REPORT IS A RESULT OF REPLACEMENT OF THE FORWARD NOSE GEAR RETRACT CHAIN.  TO REPLACE OR TO REINSTALL THIS CHAIN, A	 NEW PN C-6113005-18, CONNECTING LINK MUST BE USED.  A NEW LINK SHOULD HAVE FIVE PIECES.  ONE LINK ASSY WITH (2) SHAFTS 	SWAGED INTO AN END PLATE, TWO CENTER PLATES THAT SHOULD SLIP ONTO THE SHAFTS, ONE END PLATE, AND ONE SPRING CLIP RETAINE	R.  THE END PLATE SHOULD HAVE SMALLER HOLES IN IT AND REQUIRE PRESSING FOR PROPER ASSY.  THIS PRESSED FIT REQUIRES DISTR	UCTION OF THE LINK DURING ASSY.  WHEN INSTALLING THE NEW CHAIN AND INSTALLING THE NEW LINK, FOUND THAT ALL THREE PLATES 	HAD THE HOLE SIZE THAT WOULD ALLOW THEM TO BE SLIPPED ONTO THE SHAFTS WITHOUT PRESSING.  CHECKED ANOTHER NEW LINK ASSY. 	1	L	7	2 	4T				A31CE   					 
2007060500273	20070605	00273	CE  	2007	6	5	2007FA0000470    	1	20070226	G	2170	1013840245	EVAPORATOR      			BEECH 	200   	B200        	1152922	CE  										AIR CONDITIONER	UNSERVICEABLE   	D			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03										AFT CABIN AIR CONDITIONER EVAPORATOR RECEIVED FROM VENDER IN OVERHAULED CONDITION.  INITIAL INSPECTION REVEALED HARD LIN	E.  WHICH SHOULD RUN PARALLEL TO HEAT EXCHANGER, WAS INSTALLED APPROXIMATELY 25 DEGREES TO HEAT EXCHANGER.  THE EVAPORAT	OR COULD NOT HAVE BEEN INSTALLED WITHOUT STRESSING AIRCRAFT HARD LINES.  THIS LINE HAD BEEN REPAIRED (BY WELDING?) HOWEV	ER, THE INSIDE SURFACE STILL SHOWED SEVERE PITTING.  THE UNIT WAS RETURNED TO VENDER AS WELL AS VENDER SHOULD HAVE CAUGH	T THESE DEFECTS.  (K)		1	L	7	2 	4T				A24CE   					 
2007060700032	20070607	00032	SW  	2007	6	7	2007FA0000471    	1	20070404	G	3213	12984	LOCK NUT        			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O290  	O290*       	41506	EA  					MLG LEG	STRIPPED        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	6096F	1642 				7ECA352				LOCK NUT THREADS FAILED, MLG STRUT EXTENDED ON TAKEOFF ALLOWING MLG TO SWING FREE.  DURING LANDING, MLG WAS UNDER FUSELA	GE CAUSING DAMAGE TO LOWER LONGERONS, CONDITION OF THREADS CANNOT BE DETERMINED WITHOUT DISASSEMBLING THE MLG STRUT ASSY	.  THEREFORE, THE THREADS MAY DETERIORATE SIGNIFICANTLY WITHOUT DETECTION.  SUGGEST SPECIAL EMPHASIS INSPECTION ROUTINE 	AT (5) YEAR INTERVALS TO INCLUDE DISASSEMBLY OF MLG STRUT ASSY.  (K)			1	H	7	1 	3O	3	O		A759    	E229				 
2007060400015	20070604	00015		2007	6	4	2007FA0000472    	2	20070510	G	7322	105018	BOWL            																	CARBURETOR	DAMAGED         	B			NE2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07					A44695					RECEIVED CARBURETOR FROM CUSTOMER WITH THE REQUEST (PLEASE INSPECT UNIT FOR PROPER OPERATION, AIRCRAFT ON GROUND.  HAVE 	BEEN BOMBARDED WITH SERIOUS PROBLEMS TO JUST ABOUT EVERY CARBURETOR WE HAVE) PILOT STATED THAT HE ALMOST CRASHED HELICOP	TER DUE TO LACK OF ENGINE RESPONSIVENESS AFTER ROLLING THROTTLE IN AFTER TEST AUTO ROTATION.  INSPECTION OF CARBURETOR R	EVEALED VENT PORTS IN BOWL AND THROTTLE BODY WERE NOT IN THE NORMAL POSITION NOR THE NORMAL SIDE FOR THIS CARBURETOR MOD	EL.  COULD NOT POSITIVELY IDENTIFY THE IDLE TUBE AND NOZZLE AS OEM PARTS.  THE ACCELERATOR PUMP DISCHARGE CHECK VALVE DI	D NOT FUNCTION IN THE MANNER NORMALLY SEEN BY THIS REPAIR STATION.  THROTTLE BODY HAS ECONOMIZER JET INSTALLED WHICH IS 														 
2007060600003	20070606	00003	EU  	2007	6	6	2007FA0000473    	1	20070511	G	6210	1090103019	BLADE           			AGUSTA	A109  	A109        	0260109	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			NM	01	109CJ	2031 				7280				SKIN CRACKS WERE DISCOVERED IN THIS BLADE UPON INVESTIGATION OF AN UNUSUALLY HIGH VIBRATION LEVEL AS REPORTED BY THE PIL	OT.  THE ONE-PER-REV VERTICAL VIBRATION WAS ESPECIALLY NOTICEABLE DURING THE LANDING PHASE OF FLIGHT.  INSPECTION OF THI	S BLADE REVEALED CORD-WISE CRACKS IN THE TOP AND BOTTOM SKINS WHICH EXTEND FROM THE TRAILING EDGE AT STA 3135 TO THE AFT	 EDGE OF THE SPAR AT STA 3123.  THE CRACKS THEN EXTEND SPAN-WISE FROM STA 2940 TO STA 3225.  THE CRACK IN THE LOWER SKIN	 BISECTS A SKIN REPAIR AT STA 3130, APPROXIMATELY 2 INCHES FORWARD OF THE TRAILING EDGE.  THIS REPAIR WAS ACCOMPLISHED W	ITH AD 2000-15-20 AND BT 109-111 UNDER WO NR 8-080132-84, DATED 4/24/2006.  BT 109-50, PART I REQUIRES DAILY VISUAL INSP	1	G	7	2 	3U	3	U		H7EU    	E4CE				 
2007060600004	20070606	00004	NE  	2007	6	6	2007FA0000474    	2	20070507	G	7420		IGNITION LEAD   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT ENGINE	OUT OF POSITION 	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	25	228PC					5600310				WHILE DEPARTING, ENCOUNTERED A  75 PERCENT THROTTLE SPLIT WITH THE LEFT ENGINE ACHIEVING ONLY 93 PERCENT N1.  A MFG PHAS	E B INSPECTION WAS PERFORMED ON THE AIRCRAFT ON 5/5/2007.  WHILE PERFORMING THE PHASE B INSPECTION ITEM B742001, TASK 74	-31-00-210 (ENGINE IGNITERS OPERATIONAL TEST), IT WAS DETERMINED THAT THE RT IGNITER LEAD ON THE LT ENGINE WAS RE-INSTAL	LED IN A POSITION THAT AFFECTED THE THROTTLE LINKAGE AND PREVENTED FULL TRAVEL OF THROTTLE LEVER IN THE FLIGHT DECK.  FU	RTHER INVESTIGATION REVEALED THAT THERE IS NO REFERENCE OR PRECAUTIONS IN THE MM AS TO THE RE-INSTALLATION POSITION OF T	HE LEAD UPON REMOVAL AND RE-INSTALLATION OF THE IGNITER PLUG.  INSTALLING THE IGNITER LEAD END TO THE IGNITER WITH A 90 	2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007060700003	20070607	00003	EU  	2007	6	7	2007FA0000475    	1	20070430	G	2520	4311935	HOUSING         			AMD   	FALC50	FALCON900   	2730160	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					SEAT ROLLER	MISMANUFACTURED 	B			UO2R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	19	678CH					47				(8) SEATS, MODEL 5004 (SINGLE) WERE PURCHASED.  THE SEATS HAVE (3 FT) ON EACH CORNER (12 TOTAL) THAT ARE TO FIT INTO THE	 SEAT RAIL.  SAID PURCHASED SEATS DID NOT FIT INTO THE EXISTING MFG SEAT RAIL.  MFG WAS CONTACTED.  IT WAS DETERMINED BY	 THE MFG THAT THE (3 FEET) BY THE MFG THAT THE (3 FEET) ON EACH CORNER (12 TOTAL) WERE BEING MFG INCORRECTLY.  THE SEATS	 ARE DESIGNED TO FIT INTO (2 TRACKS).  THE FRONT 3 AND BACK 3 FEET ON THE LT SIDE OF THE CHAIR ARE PART OF A (ROLLER HOU	SING).  EACH CHAIR HAS (2) ROLLER HOUSINGS.  MFG IS PROVIDING 16 REPLACEMENT ROLLER HOUSINGS (PN 431193-5). (K)		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2007061300166	20070613	00166	GL  	2007	6	13	2007FA0000476    	1	20070504	G	7160	BA24	AIR FILTER      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE INTAKE	DEBONDED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	711KW					1348	917594	FP3492B		APPEARS THAT THE FOAM AIR FILTER ELEMENT, THAT IS CYLINDER SHAPED AND BONDED TOGETHER, DID NOT HAVE SUFFICIENT GLUEUU OR	 CAME UNBONDED AND WAS ALLOWING UNFILTERED AIR TO ENTER THE ENGINE INTAKE.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2007061300168	20070613	00168	GL  	2007	6	13	2007FA0000477    	1	20070507	G	2720		BUNGEE          			CIRRUS	SR    	SR22        	2130001	GL  										RUDDER	MISRIGGED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	519SR					2072				DURING INSPECTION FOUND RUDDER AILERON INTERCONNECT BUNGEE MISRIGGED AND INTERTFERING WITH THE AILERON CONTROLS. THERE I	S NO EVIDENCE THAT THIS AIRCRAFT HAS HAD ANY MAINTENANCE TO THIS SYSTEM SINCE LEAVING THE FACTORY. ANOTHER AIRCRAFT WITH	 THIS CONDITION HAD THE CONTROL SYSTEM JAM WITH FULL OPPOSITE RUDDER AND AILERON. IT APPEARS THAT THIS CONDITION IS CAUS	ED BY IMPROPER RIGGING OF THE INTERCONNECT SYSTEM AT THE FACTORY.			1	L	7	1 	3O			NT	A00009CH					 
2007061300204	20070613	00204	EA  	2007	6	13	2007FA0000478    	2	20070510	G	8530	LW12987	CYLINDER        								LYC   	O540  	IO540*      	41532	EA  					ENGINE	ERODED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17										AFTER REMOVAL OF THE CYLINDER BARREL FROM THE CYLINDER HEAD, SEVER ERROSION WAS NOTED JUST ABOVE THE SEAL BAND AREA. IF 	THE BARREL HAD NOT BEEN REMOVED, THIS ERROSION WOULD HAVE BEEN UNDETECTED AND WOULD HAVE CAUSED A HEAD AND BARREL SEPERA	TION.									3	O			1E4				 
2007061800105	20070618	00105	CE  	2007	6	18	2007FA0000479    	1	20070516	G	2510	04101342	SEAT            			CESSNA	150   	150F        	2071814	CE  	CONT  	E185  	E185*       	17014	SO  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	8095S					15061695				SEAT PAN WAS FOUND CRACKED AT THE FORWARD END OF PILOTS OB SEAT RAIL STIFFENER, APPROXIMATELY 1 NR LONG ACROSS SCREW HOL	ES. STIFFENER PN 0411546-1 WAS ALSO CRACKED AT CUTOUT FOR FUEL LINE. TOTAL AIRFRAME TIME UNKNOWN, BUT GREATER THAN 1300 	HOURS. THESE CRACKS ARE SOMEWHAT COMMON ON 3000 TO 5000 HOUR AIRPLANES.				1	H	7	1 	3O	3	O		3A19    	E246				 
2007061500224	20070615	00224	SO  	2007	6	15	2007FA0000480    	1	20070523	G	5711	6707003	SPAR CAP        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					RT WING	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4579R	3465 				2821321				FUEL TANK REMOVED DUE TO LEAKING VENT LINES. UPON REMOVAL, DISCOVERED RT WING UPPER SPAR CAP SEVERLY CORRODED. MAJOR EXF	OLIATION TO THE SPAR CAP AT THE OB SECTION OF THE FUEL TANK OPENING.					1	L	7	1 	3O	3	O		2A13    	E274				 
2007061800106	20070618	00106	CE  	2007	6	18	2007FA0000481    	1	20070523	G	5311	051212497	SPAR            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUSELAGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5145U	14529	100  			172RG0258	L2767336A	961976		FOUND SMOKING RIVETS ON TOP OF FUSELAGE IN AREA OF THE REAR CENTER SECTION SPAR.  REMOVED RIVETS (APPROX. EIGHT ON EACH 	END OF SPAR) AND FOUND RIVET HOLES SEVERELY ELONGATED.  FACTORY ORIGINAL RIVETS WERE .1250 INCH DIA. AND SEVERAL HAD BEE	N REPLACED IN THE FIELD WITH .1562 INCH RIVETS.  ALL OF THE AFFECTED RIVET HOLES HAD BECOME OVERSIZED TO AN EXTENT THAT 	RENDERED THE SPAR AND OVERLAPPING FUSELAGE SKINS UNSERVICEABLE.			1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007061500213	20070615	00213	SO  	2007	6	15	2007FA0000482    	1	20070523	G	5711	6205401	SPAR            			PIPER 	PA28  	PA28R180    	7102809	SO  										RT WING	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	3208R	14400				28R3113				RT WING REMOVED DUE TO DAMAGE. WING WAS SCRAPPED AND DEALER WANTED STEEL FITTINGS REMOVED. UPON REMOVAL OF REAR SPAR ATT	ACH PLATE, SEVERE CORROSION WAS FOUND ON THE SPAR UNDER THE PLATE. CONDITION WAS VERY SERIOUS AND COULD HAVE LEAD TO AN 	INFLIGHT FAILURE.				1	L	7	1 	3O				2A13    					 
2007061500214	20070615	00214	CE  	2007	6	15	2007FA0000483    	1	20070525	G	2400		UNKNOWN         			BEECH 	35    	K35         	1151524	CE  	CONT  	O470  	IO470N      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  		UNKNOWN         	C				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CE	07	6061E					D5996	096827R	7710181		LOST ELECTRICAL POWER.						1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
2007061500216	20070615	00216	EA  	2007	6	15	2007FA0000484    	2	20070525	G	7322	MA45	CARBURETOR      			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	WORN            	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			EA	23	7204P	748  	748  			242374				THE ACCELERATOR PUMP IN THE CARBURETOR FAILED.  INSPECTION SHOWED THAT THE PUMP HEAD GLAND HAD SHRUNK, SO THAT IT DID NO	T PROVIDE A SEAL BETWEEN THE CARBURETOR BODY AND THE PUMP ITSELF.  THE RESULT WAS THAT ADVANCING THE THROTTLE DID NOT CA	USE FUEL TO BE SQUIRTED FROM THE PUMP EXIT ORIFICE.  REPLACEMENT OF THE PUMP RESOLVED THE PROBLEM.				1	L	7	1 	3O	3	O		1A15    	E286				 
2007061500210	20070615	00210	EU  	2007	6	15	2007FA0000486    	1	20070530	G	2752	1391T1008	ACTUATOR        			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					FLAP	MISALIGNED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	27TZ					213				INSTALLED REBUILT FLAP ACTUATOR IN RT OB POSITION; PN 1391T100-8, SN 387AB.  FLAP OPERATION WAS NORMAL.  WHILE CHECKING 	AILERON TRAVELS IT WAS DISCOVERED THAT AILERON TRAVELS WERE LIMITED BY THE REBUILT FLAP ACTUATOR.  A COVER PLATE ON THE 	FLAP ACTUATOR HAD BEEN INDEXED INCORRECTLY AND WAS INTERFERING WITH THE AILERON BELLCRANK.  PROBABLE CAUSE WAS INCORRECT	 ASSEMBLY OF FLAP ACTUATOR.			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007061500211	20070615	00211	EU  	2007	6	15	2007FA0000487    	1	20070530	G	2752	1391T1008	ACTUATOR        			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					FLAP	MISALIGNED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	27TZ					213				INSTALLED REBUILT FLAP ACTUATOR IN RT OB POSITION; PN 1391T100-8, SN 387AB.  FLAP OPERATION WAS NORMAL.  WHILE CHECKING 	AILERON TRAVELS IT WAS DISCOVERED THAT AILERON TRAVELS WERE LIMITED BY THE REBUILT FLAP ACTUATOR.  A COVER PLATE ON THE 	FLAP ACTUATOR HAD BEEN INDEXED INCORRECTLY AND WAS INTERFERING WITH THE AILERON BELLCRANK.  PROBABLE CAUSE WAS INCORRECT	 ASSEMBLY OF FLAP ACTUATOR.			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007061800108	20070618	00108		2007	6	18	2007FA0000489    	2	20070530	G	7414		CAPACITOR       																	MAGNETO	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										IN READING AN ALERT FROM APRIL 2007 REFERRING TO SLICK MAGNETO CAPACITOR FAILURE PN M-3984 STATES THAT OIL/DIELECTRIC FL	UID LEAKED FROM THE CAPACITOR.  THAT IS A DRY CAPACITOR AND CONTAINS NO FLUID. HAVE CUT OPEN SEVERAL FOR TRAINING AIDS A	ND NO LIQUID EXISTS IN THAT PART.																	 
2007061500218	20070615	00218	SO  	2007	6	15	2007FA0000490    	2	20070525	G	8520	IO240A	CRANKSHAFT      								CONT  	O240  	IO240B      	17063	SO  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17										CRANKSHAFT  HAD A VERY LARGE, DEEP FORGING LAP ON THE NR 3 CRANK CHEEK. AN EFFORT WAS MADE TO REMOVE THE LAP BY LOCALIZE	D GRINDING BUT THE IT WAS TOO DEEP TO REMOVE. CRANKSHAFT WAS DETERMINED UNAIRWORTHY BY ENGINEERING.										3	O			E7SO				 
2007061500221	20070615	00221		2007	6	15	2007FA0000491    	4	20070429	G	2215	065001790100	SERVO           			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					AILEONS	BINDING         	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SW	09	9875F	1056 				18280141				PILOT/OWNER REPORTED TO MX THAT ON APPROACH AFTER DISENGAGING AUTOPILOT, AILERONS WERE DIFFICULT TO MOVE. NO WINDS AND S	TABLE APPROACH MINIMIZED PROBLEM. MX NOTED AILERONS WERE EXTREMELY DIFFICULT TO MOVE, AND FURTHER MOVEMENT COULD HAVE CA	USED EVEN GREATER DIFFICULTY OR COMPLETE IMMOBILIZATION OF THE AILERONS. AILERON SERVO WAS REMOVED AND SENT OUT FOR EXCH	ANGE. IT WAS NOTED ON REMOVAL THE OUTPUT SHAFT SUPPORT BEARING WAS LOOSE AND BINDING.			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007061500222	20070615	00222	CE  	2007	6	15	2007FA0000492    	1	20070531	G	5753	07620382	BELLCRANK       			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					TE FLAPS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9875F	1056 				18280141				DURING ANNUAL INSPECTION, IT WAS NOTED THAT THE (BELLCRANK ASSY) ON THE FLAP FEEDBACK LEVER, BEHIND THE INSTRUMENT PANEL	, WAS BROKEN IN TWO, IT CONSIST OF A PLASTIC BLOCK WITH A SLOT IN IT WHICH MOVES THE MICROSWITCH ASSY TO ACTIVATE, OR DE	ACTIVATE THE FLAP DRIVE MOTOR. THE BLOCK IS ATTACHED WITH 2 RIVETS OF SOME TYPE. THE END OF THE BLOCK IS CRACKED COMPLET	ELY THROUGH ALLOWING SEPARATION OF THE UPPER AND LOWER HALVES. THIS ALSO STRESSED THE ATTACHING RIVETS CAUSING CRACKS, A	ND EXCESSIVE MOVEMENT.  (PICS ARE AVAILABLE)  IF PART COMPLETELY FAILED IT COULD ALLOW COMPLETE UNCOMMANDED FLAP DEPLOYM	ENT OR INABILITY TO RETRACT FLAPS, SUCH AS A BALKED LANDING.	1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007061500223	20070615	00223		2007	6	15	2007FA0000493    	2	20070530	G	7414	M3984	CAPACITOR       																	MAGNETO	NONE            	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										IN READING AN ALERT FROM APRIL 2007 REFERING TO SLICK MAGNETO CAPACITOR FAILURE PART NR  M-3984 STATES THAT OIL/DIELECTR	IC FLUID LEAKED FROM THE CAPACITOR.  THAT IS A DRY CAPACITOR AND CONTAINS NO FLUID.  I HAVE CUT OPEN SEVERAL FOR TRAININ	G AIDS AND NO LIQUID EXSISTS IN THAT PART.																	 
2007061800211	20070618	00211		2007	6	18	2007FA0000494    	4	20070604	G	2216	6565001197	CABLE           			CESSNA	500   	550         	2076604	CE  										AUTOPILOT	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4614N	7737 	300  			5500659				WE HAVE FOUND THE ELEVATOR CABLE AT THIS SERVO P/N 4006719-904 SHOWING EXCESSIVE WEAR ON AIRCRAFT UNDERGOING PHASE 1-4 A	ND ALSO PHASE 5 INSPECTIONS. THE CABLE WAS FOUND WHERE IT PASSES THROUGH AT FS. 428.50 AND IS DIFFICULT TO SEE. THIS CAB	LE HAD APROX. 3 STRANDS TO GO TO TOTAL FALURE. THE IPC REFERENCE FOR THE CABLE IS 22-10-00, FIGURE 1, PAGE 3, ITEM 85				1	L	7	2 	4F				A22CE   					 
2007061800222	20070618	00222	NM  	2007	6	18	2007FA0000495    	1	20070606	G	3060	SMR2263	HEATER          	HARTZL      		LANCAR	LC40  	LC40550FG   	5150000	NM  	CONT  	O550  	TSIO550C    		SO  					PROP BLADES	DEBONDED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1439C	226  			LX197B	41618	914411			INBOARD PORTION OF ALL THREE PROP DEICE BOOTS DEBONDED AGAIN.  ON THIS PROP, NEW BLADES WERE SENT FROM HARTZELL DUE TO D	EBOND OF PREVIOUS BOOTS AT 28.4 HRS TT AND AGAIN AT 28.9 HRS TT.  RETAINER STRAP AND BOOT DEBONDS DUE TO CENTRIFUGAL FOR	CE PULLING DEICE BOOT LEAD ON EACH PROP BLADE.  THIS HAS HAPPENED ON FIVE OR MORE LANCAIR COLUMBIA AIRCRAFT.  THE SEALIN	G PROCESS FOR THE RETAINER STRAP IS LACKING.  SMR TECHNOLOGIES AND HARTZELL NEED A BETTER STRAP OR A GOOD TY-RAP.			1	L	7	1 	3O	3	O	RT	A00003SA	E5SO				 
2007061800224	20070618	00224	SO  	2007	6	18	2007FA0000496    	2	20070530	G	8500		STUD            								CONT  	O520  	TSIO520*    	17040	SO  					ENGINE CASE	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99							532343			DURING BUILD UP OF A NEW ENGINE FOR INSTALLATION, IT IS ROUTINE FOR US TO R&R THE OIL COOLER TO INSTALL THE GASKET WITH 	SEALANT AND TO INSPECT THE ADAPTER PLATE MOUNTING STUD HEIGHT.  ON THIS PARTICULAR ENGINE, ALL OF THE STUDS WERE INSTALL	ED TOO HIGH, SO THAT THEY PROTRUDED ABOVE THE GASKET MOUNTING SURFACE.  TWO OF THEM HAD MADE IMPRESSIONS IN THE COOLER S	EALING SURFACE.   								3	O			E8CE				 
2007061800265	20070618	00265	SO  	2007	6	18	2007FA0000497    	2	20070607	G	8530	EC646144CN	CYLINDER        			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGING	DAMAGED         	G				A				UNSCHED LANDING         				A			FLAME/FIRE                			CL	CLIMB          	1			WP	21	3622Y		501  			21058122	CS1024292S			CYLINDER HEAD DETACHED FROM CYLINDER BARREL CAUSING INJECTOR FUEL LINE TO RUPTURE.  A INFLIGHT FIRE OCCURED CAUSING DAMA	GE TO WIREING, MAG.,AND OTHE ENGINE COMPONENTS. 					1	H	7	1 	3O	3	O		3A21    	3E1				 
2007061800266	20070618	00266	CE  	2007	6	18	2007FA0000498    	1	20070527	G	5610		WINDSHIELD      			CESSNA	421   	421C        	2076016	CE  										COCKPIT	BROKEN          	G				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	15	237SM					421C0237				MAJOR PORTION OF RT WINDSHIELD SEPARATED FROM AIRCRAFT.						1	L	7	2 	3O				A7CE    					 
2007061800267	20070618	00267	EA  	2007	6	18	2007FA0000501    	2	20070607	G	8520	LW13683	MAIN BEARING    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	DELAMINATED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		1100 				318052122	L110868A			CUSTOMER FOUND METAL IN FILTER DURING ROUTINE MAINTENANCE. TOOK ENG. APART AND FOUND 2 CENTER MAIN BRGS. WHERE DELAMINAT	ED.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007062700015	20070627	00015	NM  	2007	6	27	2007FA0000503    	1	20070618	G	6510	A04111	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320*       	41508	EA  					DRIVESHAFT	ROUGH           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	461H	161  				1460				PILOT REPORTS GRINDING NOISE FROM TAIL ROTOR DRIVESHAFT. REMOVED DRIVESHAFT ASSY AND DISCOVERED ROUGH A041-11 DAMPER BEA	RING. REPLACED BEARING ASSY.  CLOSER EXAMINATION SHOWED PAINT USED DURING DRIVESHAFT ASSEMBLY ON LIP OF SEAL. OVER TIME 	THIS DAMAGED THE LIP OF THE SEAL AND ALLOWED GREASE TO PURGE FROM BEARING. THIS IS THE SECOND OCCURRENCE OF THIS IN THE 	PAST 12 MONTHS. MFG NOTIFIED EACH TIME. SUGGEST BETTER QC DURING DRIVESHAFT BUILD UP AT MFG.			1	G	7	1 	3O	3	O		H10WE   	E274				 
2007071100021	20070711	00021	CE  	2007	7	11	2007FA0000505    	1	20070504	G	5340	24130023	ATTACH FITTING  			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	NLG ACTUATOR	CRACKED         	B			BGSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	169EC	1345 				172RG0515	L2843836A	804955		L/W SEB 93-8 ON NOSE GEAR ACTUATOR ATTACH FITTING AND SOUND CRACK ON LT, LOWER, IB BOLT HOLE OF FITTING.  ALSO, BOLT HOL	ES IN LOWER SKIN WERE IN EXCESS OF .030.  REPLACED ATTACH FITTING, LOWER SKIN AND DOUBLER IAW SK 172-142 AND SK 172-159.					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007071100022	20070711	00022	CE  	2007	7	11	2007FA0000506    	1	20070517	G	5753	95160000XX	SKIN            			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					LT TE FLAP	CRACKED         	B			HSRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	06	837RJ	5859 				P355				BOTH FLAPS CRACKED AT ACTUATOR ATTACH POINT.  LT FLAP SKIN AND RIB CRACKED.  RT FLAP RIB CRACKED.  RIGGING WAS OK, PROBA	BLY AN OPERATOR INDUCED PROBLEM.  BELIEVE THE FLAPS HAVE BEEN LOWERED AT TOO HIGH AN AIRSPEED.  (K)					1	L	7	2 	3O	3	O		A12CE   	E10EA				 
2007071100029	20070711	00029	CE  	2007	7	11	2007FA0000507    	1	20070515	G	2130	AN8186D	NUT             	BEECH       		BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					TUBE	LOOSE           	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	132QS					RK427				CREW REPORTED PRESSURIZATION CONTROL INEFFECTIVE, CABIN RATE CLIMBING AND DESCENDING, WHILE DESCENDING IN AUTOMATIC MODE	.  STABILIZED BRIEFLY WHILE IN MANUAL MODE.  TROUBLESHOT IAW FIM 21-30-00, EXCESSIVE LEAK RATE NOTED AT TEST PORT 2.  FO	UND LOOSE (B) NUT ON CONTROL LINE TUBE ASSY.  AT TEE FITTING FOR MANUAL CONTROL VALVE.  CORRECTED LOOSE FITTING AND SYST	EM TESTS OK.  RESTORED AC TO NORMAL CONFIGURATION, PRESSURIZATION SYSTEM TESTS SATISFACTORY ON GROUND RUN-UP.  UNKNOWN I	F PREVIOUS MAINTENANCE PERFORMED IN THIS AREA.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007062700007	20070627	00007	WP  	2007	6	27	2007FA0000510    	1	20070618	G	6520	269A6029	LOCK NUT        			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360*     	41514	EA  					T/R GEARBOX	BACKED OUT      	B				C				ABORTED TAKEOFF         				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	09	27YS	1573 								DURING GROUND RUNUP, PILOT NOTICED TAIL ROTOR NOT SPINNING. AIRCRAFT SHUTDOWN AND RETURNED TO HANGER. UPON DISASSEMBLY I	T WAS NOTED THAT THE NUT PN 269A6029 THAT ATTACHES THE DRIVE COUPLING TO THE GEARBOX HAD BACKED OUT COMPLETELY AND WORN 	A HOLE THROUGH THE ALUMINUM BUMPER PN 269A5712 THAT IS INSIDE THE TAIL ROTOR DRIVESHAFT. THREADS INSIDE THE TAIL ROTOR G	EARBOX INPUT SHAFT PN 269A5626-5 WERE ALSO DAMAGED. PARTS WERE FORWARDED TO MFG FOR EVALUATION.			1	G	7	1 	3O	3	O		4H12    	1E10				 
2007071100062	20070711	00062	CE  	2007	7	11	2007FA0000511    	1	20070530	G	5730	552275563	PANEL           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					WING	DELAMINATED     	B			H00R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	100DS	4430 				5500639				DURING COMPLETION OF MFG PROGRAM PHASE 5 INSPECTION, NOTICEABLE DEPRESSION WAS OBSERVED IN UPPER SURFACE OF LT AND RT WI	NG SKINS IN AREA OF MLG UPLOCK HOOK ASSY ATTACHMENT.  DURING COMPLETION OF LANDING GEAR OPERATIONAL CHECK, IT WAS NOTED 	THAT DEPRESSION AREA SIZE GREW WHILE MLG WAS IN UP AND LOCKED POSITION.  USING THE COIN TAP TEST METHOD CONFORMATION WAS	 MADE THAT BOTH BONDED PANELS WERE DELAMINATED.  IAW TECH SUPPORT, NO DELAMINATION IS ALLOWED ON THESE PANELS.  OPTIONS 	AVAILABLE FOR REMEDY WERE REMOVED AND REPLACED, POSSIBLE REPAIR DEFINITION AND ASSOC 8110FORM, OR POSSIBLE TEMPORARY REP	AIR WITH FLIGHT EXTENSION.  (K)	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007071100063	20070711	00063	CE  	2007	7	11	2007FA0000512    	1	20070530	G	5730	552277564	PANEL           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT WING	DELAMINATED     	B			H00R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	100DS	4430 				5500639				DURING COMPLETION OF MFG PROGRAM PHASE 5 INSPECTION, NOTICEABLE DEPRESSION WAS OBSERVED IN UPPER SURFACE OF LT AND RT WI	NG SKINS IN AREA OF MLG UPLOCK HOOK ASSY ATTACHMENT.  DURING COMPLETION OF LANDING GEAR OPERATIONAL CHECK, IT WAS NOTED 	THAT DEPRESSION ARE SIZE GREW WHILE MLG WAS IN UP AND LOCKED POSITION.  USING THE COIN TAP TEST METHOD.  CONFORMATION WA	S MADE THAT BOTH BONDED PANELS WERE DELAMINATED.  IAW TECH SUPPORT, NO DELAMINATION IS ALLOWED ON THESE PANELS.  OPTIONS	 AVAILABLE FOR REMEDY WERE REMOVED AND REPLACED, POSSIBLE REPAIR DEFINITION AND ASSOC 8110 FORM, OR POSSIBLE TEMPORARY R	EPAIR WITH FLIGHT EXTENSION.  (K)	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007062500003	20070625	00003		2007	6	25	2007FA0000513    	4	20070608	G	2562	E0109	CONNECTOR       	ACK         	E01ELT      	PIPER 	PA16  	PA16        	7101602	SO  										ELT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	5834H	1277 	87   		021767	16453				DURING 100 HOUR INSPECTION IT WAS NOTED THAT THE BNC CONNECTOR ATTACHED TO THE ELT PORTABLE ANTENNA WAS MISSING. AN IN-D	EPTH SEARCH OF THE AIRCRAFT BELLY FAILED TO TURN UP THE CONNECTOR. THE CONNECTOR IS ATTACHED TO THE PORTABLE COLLAPSIBLE	 ANTENNA BY A 6-32 SCREW IN THE BOTTOM OF THE ANTENNA. THERE IS NO PROVISION TO LOCK THIS THREADED ATTACHMENT.				1	H	7	1 	3O				1A1     					 
2007062500006	20070625	00006	GL  	2007	6	25	2007FA0000516    	1	20070612	G	5753	13431004	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FLAP	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	122GH	543  				0175				FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGE JUST BELOW THE BOTTOM WING SKIN ABOVE T	HE HINGE FAIRING.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2007062500007	20070625	00007	GL  	2007	6	25	2007FA0000517    	1	20070612	G	5753	13432002	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FLAP	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	122GH	543  				0175				FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGE JUST BELOW THE BOTTOM WING SKIN ABOVE T	HE HINGE FAIRING.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2007062500025	20070625	00025	SO  	2007	6	25	2007FA0000524    	2	20070511	G	8500		ENGINE          			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					RIGHT	FAILED          	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			J	Y	T	WARNING INDICATION        	ENGINE STOPPAGE           	ENGINE CASE PENETRATION   	CR	CRUISE         	1			SO	11	814JG		14   			E2622	675591			ON MAY 11, 2007 AT APPROXIMATELY 1815 EST, 2205Z, A BEECH BE-36-A36 BONANZA, N814JG, S/N E-2622, AT CRUISE HAD A DECREAS	E IN ENGINE CYLINDER TEMPERATURE, FOLLOWED BY A LOSS OF OIL PRESSURE AND ENGINE POWER WITH SUBSEQUENT ENGINE FAILURE. TH	E AIRCRAFT MADE AN EMERGENCY LANDING. PILOT WALKED AWAY FROM THE AIRCRAFT WITH NO INJURIES. A VISUAL INSPECTION OF THE A	IRCRAFT REVEALED A HOLE IN THE UPPER RIGHT HAND ENGINE COWLING APPROXIMATELY 3 INCHES IN DIAMETER WHICH WAS LIMITED TO S	HEET METAL DAMAGE. UPON INSPECTION OF THE ENGINE COMPARTMENT THE FORWARD UPPER CASE OF THE ENGINE WAS HEAVILY DAMAGED RE	VEALING SEVERAL DAMAGED PISTONS, PISTON CONNECTING RODS BROKEN AND NR 6 CONNECTING ROD MISSING, ALONG WITH SEVERAL CRANK	1	L	7	1 	3O	3	O		3A15    	E3SO				 
2007062500027	20070625	00027	EA  	2007	6	25	2007FA0000525    	2	20070615	G	7414	M3548	ROTOR           	SLICK       	4370        	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAGNETO	SHEARED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01		335  	335  		06052245					RIGHT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE MAGNETO CAM.  SECOND IDENTICAL FAILURE IN 335 HRS ON THE AIRCRAFT.  AIRCR	AFT DYNAMIC PROP BALANCE WAS CHECKED AFTER THIS FAILURE AND CHECKED EXCELLENT.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007062500028	20070625	00028	SO  	2007	6	25	2007FA0000526    	1	20070615	G	2420		TERMINAL        	CHRYSLER    		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ALTERNATOR	LOOSE           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01					F082472					217 HOURS AFTER OVERHAUL, THE  OUTPUT TERMINAL BECAME LOOSE IN THE BUSS STRAP INSIDE THE ALTERNATOR, CAUSING COMPLETE FA	ILURE.  LIKELY THIS FIT (NORMALLY A PRESS FIT) WAS NOT AS TIGHT AS IT NEEDED TO BE WHEN THIS UNIT LEFT KELLY.					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2007071100061	20070711	00061	GL  	2007	7	11	2007FA0000530    	1	20070622	G	3222	11907005	STRUT           			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O550  	IO550N      	17042	SO  					NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	961CD	623  				1610				NOSE LANDING GEAR STRUT HAS A CRACK AT THE TOP. THE STRUT COMES UP TO A Y FOR MOUNT. AT THE YOKE OF THE Y IS A WELDED RE	INFORCEMENT, AND THE CRACK IS AT THE TOP WHERE THIS REINFORCEMENT MEETS THE LEGS OF THE Y ON BOTH SIDES.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007062700020	20070627	00020	EU  	2007	6	27	2007FA0000531    	1	20070615	G	2750	9450202205	FLEX DRIVE      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	BROKEN          	B				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			EA	65	591AF	2329 				591	PR0454	KX164		DURING APPROACH WHEN THE FLAPS WERE SELECTED TO 15 DEGREES THE FLAPS FAILED TO EXTEND AND A FLAP CAUTION ANNUNCITOR WAS 	DISPLAYED ON THE CAWS PANEL. THE FLIGHT CREW FOLLOWED THE APPROPRIATE POH PROCEDURES AND LANDED UNEVENTFULLY. INVESTIGAT	ION INTO THE FLAP PROBLEM AFTER THE AIRCRAFT LANDED DETERMINED THAT THE LT IB FLAP FLEX DRIVE PN 945.02.02.205, SN S2532	, HAD BROKEN JUST IB OF THE LT IB FLAP ACTUATOR.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007071100023	20070711	00023		2007	7	11	2007FA0000532    	1	20070620	G	3220	608200185	TORQUE KNEE     	BEECH       	T34         															NLG	MISMANUFACTURED 	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09					GL210					PURCHASED BRAND NEW PART. DURING ASSEMBLY IT WAS FOUND THAT THE TORQUE ARM PIN LUGS ARE OF DIFFERENT THICKNESSES.  THEY 	ARE SUPPOSED TO BE THE SAME.  THIS DEFECT CAUSED THE HOLES IN THE HOUSING AND THE TORQUE PIN TO NOT ALIGN.																		 
2007071100059	20070711	00059	GL  	2007	7	11	2007FA0000533    	1	20070622	G	3222	11907004	STRUT           			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	217JH	562  				1320				NOSE LANDING GEAR STRUT HAS A CRACK AT THE TOP. THE STRUT COMES UP TO A Y FOR MOUNT. AT THE YOKE OF THE Y IS A WELDED RE	INFORCEMENT, AND THE CRACK IS AT THE TOP WHERE THIS REINFORCEMENT MEETS THE LEGS OF THE Y.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2007062700019	20070627	00019	CE  	2007	6	27	2007FA0000534    	1	20070619	G	3246	D30257	HUB             			CESSNA	206   	U206F       	2073333	CE  										WHEEL	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	1191V				D30	U20602506				WHEEL-BROKE AT CENTER, CASTING FAILED AT BOLT HOLES-8:00X6 TIRES AND TUBES 190-200" NRS AT CAP SCREWS INSTALLED 7-23-03 	TACH 1709 CURRENT TACH 2052.					1	H	7	1 	3O				A4CE    					 
2007071100073	20070711	00073	EU  	2007	7	11	2007FA0000535    	2	20070501	G	7314	AN9113D	NIPPLE          			NANCNG	CJ6A  	CJ6A        	056183N	WP  	VEDENY	      	M14P        	 	EU  	MUHBR	MTV	MTV9*       	EU  	FUEL PUMP	UNKNOWN         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	552CY	20   				4332008	KR822009			FUEL INJECTION FUEL SUPPLY FROM FUEL PUMP FITTING THAT COMES OUT OF PUMP.  FIX WOULD BE CHANGE TO STEEL AND SUPPORT LINE	 WITH BRACKET OR CHANGE TO FIREWALL MOUNT OF FUEL PRESSURE TRANSDUCER.  (K)					1	L	7	1 	3R			RT	EXPA1L71	USSR	5	C	P24NE	 
2007071100088	20070711	00088	CE  	2007	7	11	2007FA0000536    	1	20070530	G	3500	510010746	LINE            			CESSNA	441   	441         	2076020	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					OVERHEAD CABIN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	377CA	5341 				4410289				DURING INSPECTION, HEARD A FAINT GAS LEAK IN OVERHEAD.   PULLED O2 OUTLETS IN SUSPECTED AREA, AND CHECKED B-NUTS, ALL SE	CURE.  PULLED HEADLINER FOR A CLOSER INSPECTION.  FOUND O2 LINE JUST FWD OF THE CABIN DOOR CORRODED AND LEAKING.    CORR	OSION ON THE LINE OCCURRED WHERE THE DUCTING PASSED UNDER IT.    EVERYWHERE THIS DUCTING TOUCHED AN O2 LINE THERE WAS CO	RROSION.    THE LINES & FLEX DUCTING WAS REPLACED WITH NEW.   (K)			1	L	7	2 	3T	3	O	RT	A28CE   	E7CE				 
2007071100092	20070711	00092	NE  	2007	7	11	2007FA0000537    	2	20070531	G	7321	312064401	FCU             	PWA         		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LT ENGINE	MALFUNCTIONED   	B			VG4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	609BG	403  	234  		PCEPK0709	FL468	PCEPK0709			ENGINE POWER LOSS AT ALTITUDE.  ENGINE ROLLED BACK FROM 50 PERCENT.  MFG TECH SUPPORT RECOMMENDS FCU REPLACEMENT.  CAUSE	 UNKNOWN AT THIS TIME. (K)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2007071100093	20070711	00093	CE  	2007	7	11	2007FA0000538    	1	20070604	G	5320		FLOOR SUPPORT   			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FS 151	CRACKED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	905CW	9359 				5500072				CABIN FLOOR SUPPORT WEB CRACKED AND BROKEN, FUSELAGE STATION 151.  FOUND CRACK DURING PHASE INSPECTION.   UNABLE TO FIND	 PN IN MFG PARTS CATALOG.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007071100094	20070711	00094	EU  	2007	7	11	2007FA0000539    	1	20070530	G	2752	1391T1008	ACTUATOR        			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					TE FLAPS	MISALIGNED      	D			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	27TZ					213				INSTALLED REBUILT FLAP ACTUATOR IN RT OB POSITION; PN 1391T1008, SN 387AB.  FLAP OPERATION WAS NORMAL.  WHILE CHECKING A	ILERON TRAVELS IT WAS DISCOVERED THAT AILERON TRAVELS WERE LIMITED BY THE REBUILT FLAP ACTUATOR.  A COVER PLATE ON THE F	LAP ACTUATOR HAD BEEN INDEXED INCORRECTLY AND WAS INTERFERING WITH THE AILERON BELLCRANK.  PROBABLE CAUSE; INCORRECT ASS	Y OF FLAP ACTUATOR.  (K)			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007071100098	20070711	00098	SO  	2007	7	11	2007FA0000540    	1	20070625	G	7500	M1213400	RING            	ALIDSG      		GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY*       	 	NE  					PRECOOLER	MISSING         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	2NA					309				THE COMPONENT OEM (REPORT 4-193), THE MM (CHAPTER 36-02-00), IPC (CHAPTER 36-10-00) AND THE CMP WORK CARDS (364040, 3640	45) ARE MISSING THE REQUIREMENT TO INSPECT AND INSTALL GAMMA RING (PN) M1213-400 DURING THE INSTALLATION OF THE PNEUMATI	C SYSTEM PRECOOLER. FAILURE TO INSTALL THE GAMMA RING COULD CAUSE THE HIGH PRESSURE DUCT TO SEPARATE FROM THE PRECOOLER 	AND CAUSE SIGNIFICANT HEAT DAMAGE TO THE AIRCRAFT SKIN AND STRINGERS.			2	L	7	2 	4F	4	T		A12EA   	E2EU				 
2007071100082	20070711	00082	SO  	2007	7	11	2007FA0000543    	2	20070625	G	7322		NEEDLE VALVE    			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					CARBURETOR	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99			51   							AT THE END OF THE FLIGHT, PILOT REPORTED THAT THE ENGINE WOULD NOT IDLE.  DURING INSPECTION OF THE CARBURETOR,  MECHANIC	 FOUND THE MIXTURE ADJUSTMENT NEEDLE VALVE MISSING.  CARBURETOR WAS REMOVED AND SENT BACK FOR REPAIR.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007071100026	20070711	00026	EU  	2007	7	11	2007FA0000547    	1	20070620	G	2760	69023617	PULLEY BRACKET  			GLASFL	H301  	H301LIBELLE 	3800337	EU  	CONT  	O360  	TSIO360E    	17025	SO  					SPOILER	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	301Q	2343 				35				ROLL SPOILER CABLE PN:S3779-4P233.7M WAS ROUTED INCORRECTLY OVER LOW FRICTION PULLEY P/N:S3504-4.5  (THROUGH A TOOLING H	OLE) IN PULLEY BRACKET P/N:6960236-17.  THIS CAUSED AN INTERFERENCE AND WEAR IN THE PULLEY BRACKET, AND FLAT AREAS TO TH	E CABLE.  CABLE AND BRACKET WERE REPLACED WITH NEW.				1	K	0	0 	  	3	O		G12EU   	E9CE				 
2007071100027	20070711	00027	CE  	2007	7	11	2007FA0000548    	1	20070620	G	2760	S37794P2337M	CONTROL CABLE   			CESSNA	680   	680CE       	2076811	CE  										SPOILER	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	301QS	2343 				6800010				ROLL SPOILER CABLE P/N S3779-4P233.7M WAS ROUTED INCORRECTLY OVER LOW FRICTION PULLEY. CABLE WAS FOUND ROUTED THROUGH TO	OLING HOLE IN BRACKET P/N 6960236-17 RATHER THAN ENGAGING PULLEY.  THE BRACKET TOOLING HOLE EXHIBITED WEAR FROM THE CABL	E RIDING (CUTTING) INTO THE TOOLING HOLE.				2	L	7	2 	4F			RC	T00012WI					 
2007071100043	20070711	00043	CE  	2007	7	11	2007FA0000550    	1	20070621	G	3230	50410015	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520*      	17032	SO  					ZONE 700	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	19	1771G					310R0040				LT MAIN GEAR BELLCRANK ASSY BROKE IN MARCH OF 2007. THE PART WAS REPLACED BY A USED SERVICABLE PART WHICH LASTED APPROXI	MATLY 58 HRS. THEN FAILED  AT THE SAME LOCATION ON THE PART.					1	L	7	2 	3O	3	O		3A10    	E5CE				 
2007071100052	20070711	00052	SO  	2007	7	11	2007FA0000552    	1	20070622	G	2910	177662	HOSE            			PIPER 	PA31T 	PA31T       	7103124	SO  										HYD SYSTEM	RUPTURED        	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	27	970PS	6349 				31T8020023				LT MLG IB GEAR DOOR ACTUATOR HYDRAULIC HOSE, HAD A PRESSURE FAILURE, THUS DRAINING HYDRAULIC FLUID IN FLIGHT, RESULTING 	IN FAILURE OF PROPER GEAR EXTENSION, EMERGENCY GEAR EXTENSION, AND CAUSING AIRCRAFT GEAR UP LANDING.  HYDRAULIC HOSE P/N	 17766-2 AND PIPER P/N 465-138.  HOSE IS ORIGINAL EQUIPMENT INSTALL.				1	L	7	2 	3T				A8EA    					 
2007071100116	20070711	00116	WP  	2007	7	11	2007FA0000553    	2	20070626	G	7200	30751604	ENGINE          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 2	BINDING         	C				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	07		1781 				258593	P107918			IFSD OCCURRED ON JUNE 21ST 2007.  AN EMERGENCY WAS DECLARED WHEN THE NR 2 ENGINE ITT CLIMBED TO 1066C FOR 5 SECONDS AT F	L 260 AND A HIGH VIBRATION WAS FELT.  THE PILOT SHUTDOWN THE ENGINE.  ALL PARAMETERS WERE FINE UNTIL THIS EVENT.  AN OVE	RWEIGHT LANDING INSPECTION WAS PERFORMED ON THE AIRCRAFT WITH NO ABNORMALITIES REPORTED.  DISASSEMBLY FINDINGS OF THE EN	GINE REVEALED LPC2 DISC POST SEPARATIONS AS LISTED IN SB TFE731-72-3711.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007071100127	20070711	00127		2007	7	11	2007FA0000554    	4	20070628	G	3457	12744001	ANTENNA         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					GPS	DISCONNECTED    	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	07	5959A	127  				1526				WHILE IN CRUISE FLIGHT THE NR 1 GPS STOPPED RECEIVING A SIGNAL. AFTER LANDING, REMOVED THE MFD AND FOUND THE GLUE HOLDIN	G THE VELCRO TO THE GPS ANTENNA HAD COME UNDONE. BOTH GPS ANTENNAS ARE HELD IN PLACE WITH VELCRO STRIPS AND IN THE HEAT 	OF SUMMER, THE GLUE SOFTENS AND COMES UNDONE.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2007071200120	20070712	00120	EA  	2007	7	12	2007FA0000555    	2	20070616	G	8530		EXHAUST VALVE   			AMERAC	S1    	S1AAMERAC   	       	WP  	LYC   	O235  	O235C2C     	41505	EA  	MCAULY	1A105	1A105SCM    	GL  	ENGINE	BENT            	G				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			GL	03	5651L	1749 	1749 			AA10051	L961915	52473		EXHAUST VALVE WAS FOUND STUCK IN THE OPEN POSITION ON TEARDOWN OF THE ENGINE.  VALVE STEM HAD A SLIGHT BEND.  ENGINE TEA	RDOWN WAS DUE TO AN AIRCRAFT ACCIDENT.					1	L	7	1 	3R	3	O		ATC521  	E223	5	N	P918	 
2007071100140	20070711	00140	EU  	2007	7	11	2007FA0000556    	1	20070628	G	6320	305A32031002	GEARBOX         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  						UNKNOWN         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	17	808CP	161  				4151	23335			MGB CHIP LIGHT CAME ON IN FLIGHT. INSPECTED CHIP PLUGS IAW AEC MWC AND SPM. NO FURTHER ACTION REQUIRED.						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007071100141	20070711	00141	EU  	2007	7	11	2007FA0000557    	1	20070628	G	6320	305A32031002	GEARBOX         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  						UNKNOWN         	B			PN1R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	17	808CP	161  				4151	23335			MGB CHIP LIGHT CAME ON IN FLIGHT. INSPECTED CHIP PLUGS IAW AEC MWC AND SPM. NO FURTHER ACTION REQUIRED.						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007071100150	20070711	00150	CE  	2007	7	11	2007FA0000558    	1	20070510	G	3240		LINE            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					BRAKE	LOOSE           	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	13	4845E					18503887				RT MAIN BRAKE FAILED ON AIRCRAFT ROLLOUT OF NORMAL CROSSWIND LANDING.  BRAKE LINE B-NUT FOUND COMPLETELY LOOSE.  (K)						1	H	7	1 	3O	3	O		3A24    	E5CE				 
2007071100152	20070711	00152	CE  	2007	7	11	2007FA0000559    	1	20070525	G	5280	45A303794	DOUBLER         			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  					MLG DOOR	CRACKED         	B			E81R	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	03	406TS					RJ6				FLIGHT CREW REPORTED RED GEAR UNSAFE INDICATION LIGHT AFTER GEAR EXTENSION FOR APPROACH, ALL (3) LANDING GEARS INDICATIN	G DOWN AND LOCKED.  PERFORMED ALTERNATE GEAR EXTENSION IAW CHECKLIST.  AIRCRAFT FERRIED WITH LANDING GEAR DOWN IAW PERMI	T TO FACILITY FOR REPAIRS.  AFTER NORMAL LANDING, RT MLG FUSELAGE DOOR UNLATCHED AND DRAGGED ON TAXIWAY DURING TAXI-IN. 	 FOUND DOUBLER UNDER RT FUSELAGE DOOR FORWARD HINGE BRACKET CRACKED, ALSO CRACK IN PN 45A30314-6 FRAME ( U-CHANNEL) AT F	ORWARD HINGE AREA.  SUSPECT CRACKED AREA ALLOWED ENOUGH PLAY IN DOOR ASSY FOR DOOR UPLOCK NOT TO FULLY ENGAGE.  DOOR ASS	Y APPEARS TO HAVE BEEN REPAIRED PREVIOUSLY.  (K)	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007071100192	20070711	00192	EU  	2007	7	11	2007FA0000560    	1	20070521	G	5302		STRUCTURE       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TAIL BOOM	CRACKED         	B			QS7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	352EV	2542 				2555				A CRACK APPROXIMATELY 170 MM LONG WAS FOUND ON THE LEADING EDGE, AFT OF FWD MOUNT POINT.  (K)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007071100196	20070711	00196	WP  	2007	7	11	2007FA0000561    	1	20070525	G	7600		BUSHING         			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					THROTTLE LINKAGE	WORN            	B			NTBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	1666S	192  				S1898	L3316351A			ENGINE MOUNTED THROTTLE LINKAGE BUSHINGS WORN.  FOUND ON INSPECTION WITH EXCESSIVE PLAY.  PROBABLY OCCURRED DUE TO EXCES	SIVE VIBRATION OR LACK OF SUBRICATION.  RECOMMENDATION TO PREVENT WOULD BE TO LUBRICATE MORE FREQUENTLY OR DIFFERENT DES	IGN OF LINKAGE.  (K)				1	G	7	1 	3O	3	O		4H12    	1E10				 
2007071100198	20070711	00198	EA  	2007	7	11	2007FA0000562    	2	20070629	G	8550	AE3663162J0230	LINE            			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540A1A   	41532	EA  					ENGINE OIL	CRACKED         	B			LJER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1328N					T18208403	L1196661A			30 DEGREE FITTING HAS CRACK ON WRENCH FLAT.  (K)						1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2007071100201	20070711	00201	EA  	2007	7	11	2007FA0000563    	1	20070507	G	3240		SHAFT           			SCWZER	G164  	G164A       	3952704	EA  										BRAKE	ROUGH           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5149					1123				ON DISASSEMBLY, THE SHAFT WAS FOUND TO BE QUIET ROUGH, WHERE THE PARKING BRAKE TAB LEVER 149-1 ENGAGES WITH THE SHAFT.  	THIS IS NOT APPARENT UNTIL IT IS REMOVED AND TAKEN APART, AS SPRING 02-9 OBSCURES THE NEW OF IT.  TO PREVENT REOCCURRED 	THE SHAFT SHOULD BE CHECKED AND SMOTHERED OR REPLACED.  (K)				1	Q	7	1 	3R				1A16    					 
2007071100202	20070711	00202	CE  	2007	7	11	2007FA0000564    	1	20070519	G	7400	4370	ARM             			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					POINTS	BROKEN          	D			M90R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	61953	133  				17264910	L4116127A			POINTS ARM BROKE IB OF POINTS AFTER ONLY 133.1, TIME SINCE INSTALLATION.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007071100204	20070711	00204	CE  	2007	7	11	2007FA0000565    	1	20070606	G	2910	41344	VALVE           			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ44        	66000	GL  					HYD SYSTEM	LEAKING         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CE	07	301PG					525A0301				PERFORMED AN EMERGENCY LANDING DUE TO LOSS OF HYDRAULIC PRESSURE.  THE EMERGENCY BOTTLE WAS USED TO LOWER THE GEAR AND L	AND WITHOUT INCIDENT.  THE CAUSE HAS BEEN DETERMINED TO BE THE HYDRAULIC LOADING VALVE (PN 4134-4, SN 781) FAILING IN CL	OSED POSITION, RESULTING THE HYDRAULIC FLUID IN THE SYSTEM TO BE DUMPED OUT THE VENT TUBE CAUSING THE LOSS OF HYDRAULIC 	PRESSURE.  IT IS ALSO SUSPECTED THAT THE LOADING VALVES FAILURE, CAUSED THE PCB N2108 (CIRCUIT BOARD) TO FAIL AS WELL.  	THE PCB 2108 WAS REPLACED.  THE AIRCRAFT HYDRAULIC SYSTEM HAS BEEN LEAK CHECKED, OPS CHECKED AND HAS BEEN RETURNED TO SE	RVICE WITH NO FURTHER INCIDENTS.	1	L	7	1 	4F	4	F	RT	A1WI    	E3GL				 
2007071100209	20070711	00209	CE  	2007	7	11	2007FA0000566    	1	20070608	G	2800		FUEL            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  						CONTAMINATED    	C				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	65	41YP					5250122				PERFORMED AN EMERGENCY LANDING, DUE TO A FUEL BYPASS LIGHT COMING ON IN FLIGHT.  THE AIRCRAFT LANDED AND TAXIED TO THE S	ERVICE CENTER WITHOUT INCIDENT.  THE CAUSE OF THE LIGHT HAS BEEN DETERMINED TO BE THE FUEL ITSELF.  THE FUEL IS CONTAMIN	ATED WITH VISIBLE DEBRIS AND HAS A CLOUDY TINT TO IT.  THE CAUSE OF THE BYPASS LIGHT IS FROM THE PARTICLES IN THE FUEL C	LOGGING THE ENGINE FILTERS.  THE FUEL FILTERS ON BOTH THE LT AND THE RT ENGINES HAVE BEEN REPLACED IAW MM.  THE AIRCRAFT	 HAS BEEN RETURNED TO SERVICE.  NOTE: THE FUEL WAS NOT PURCHASED FROM SERVICE CENTER.  (K)		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2007071100210	20070711	00210	CE  	2007	7	11	2007FA0000567    	1	20070629	G	6100	9696001123	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					PROPELLER	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	658RA	1501 				TH1892				BAD OIL LEAK:  DETERMINED METAL ID PLATE ON MP HOSE WORE HOLE INTO PROP UNFEATHERING ACCUMULATOR TUDE.  NOTE: THIS IS TH	E SUBJECT OF AD 2007-06-07 AND MANDATORY SB 61-3806 BUT DOES NOT COVER THIS AC SN.  (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2007071100212	20070711	00212	CE  	2007	7	11	2007FA0000568    	1	20070629	G	3260	602EN6026	UPLOCK SWITCH   			CESSNA	650   	650         	2076802	CE  										NLG	DEFECTIVE       	B			EWCR	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			EA	39	750CK					6507015				GEAR SELECTED UP AFTER TAKEOFF.  UNSAFE LIGHT WOULD NOT GO OUT AND AIR NOISE FROM NOSE GEAR DOORS OPEN.  2 GEAR CYCLE AT	TEMPTS WITH NO CHANGE.  RETURNED TO GSO (PTI) AIRPORT, LANDED WITH NORMAL GREEN LIGHTS.  AIRCRAFT TURNED OVER TO MFG SER	VICE CENTER FOR REPAIR.  NOSE GEAR UPLOCK SWITCH FOUND DEFECTIVE.  REPLACED SWITCH OPERATION CHECKED NORMAL.  (K)				2	L	7	2 	4F				A9NM    					 
2007071100214	20070711	00214	EU  	2007	7	11	2007FA0000569    	1	20070517	G	7700	642795431	TRANSMITTER     			AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE73160    	 	NE  					ENGINE	READS LOW       	B			UO2R	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			GL	19	127SF	5144 				013	P112149			THE AIRCRAFT WAS CLIMBING AND THE NR 3 ENGINE OIL PRESSURE INDICATION STARTED TO DROP.  AT 46 PSI IT WENT RED AND THE PI	LOT SHUTDOWN THE ENGINE  AND LANDED THE AIRCRAFT.  THE OIL LEVEL WAS IN LIMITS AND NO EXTERNAL LEAKS WERE FOUND.  A DIRE	CT READING PRESSURE GAGE WAS INSTALLED AND SHOWED GOOD OIL PRESSURE AND THAT THE INDICATOR WAS READING LOW.  A NEW OIL P	RESSURE TRANSMITTER WAS INSTALLED AND CORRECTED THE LOW READING PROBLEM.  (K)			2	L	7	3 	4F	4	F	RT	A46EU   	E1NM				 
2007071100215	20070711	00215	CE  	2007	7	11	2007FA0000570    	1	20070529	G	5311	5511118200	FRAME           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUSELAGE	DAMAGED         	C			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	905CW	9359 				5500072				FUSELAGE FRAME WEB DAMAGED BY DRILL BIT FROM THE BEND RADIUS OF THE OUTER (SKIN) FLANGE.  REPLACEMENT REQUIRED SRM, CHAP	TER 53-12-27.  PROBABLE CAUSE:  INCORRECTLY DRILLED AT AIRCRAFT MFG.  (K)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007071100218	20070711	00218	SO  	2007	7	11	2007FA0000571    	1	20070531	G	3220	67107000	BRACKET         			PIPER 	PA28  	PA28R200    	7102811	SO  	CONT  	IO360 	IO360*      	17025	CE  					NOSE GEAR	FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	33	56066					28R7335346				THE PILOT STATED NOSE GEAR COLLAPSED ON LANDING.  AFTER AIRCRAFT REMOVED FROM RUNWAY AND PUT ON JACKS.  THE NOSE GEAR WO	ULD NOT EXTEND OR RETRACT.  THE GEAR WAS EXTENDED BY EMERGENCY EXTENSION.  THE NOSE GEAR ALIGNER BRACKET FELL OFF THE GE	AR.  AGAIN THE NOSE GEAR WAS EXTENDED AND RETRACTED SEVERAL TIMES. THE TT OF THE NOSE GEAR ALIGNER BRACKET COULD NOT BE 	DETERMINED.  (K)			1	L	7	1 	3O	3	O		2A13    	E1CE				 
2007071100219	20070711	00219	CE  	2007	7	11	2007FA0000572    	1	20070525	G	2720	S16751	BEARING         			CESSNA	210   	T210M       	2073451	CE  										RUDDER PEDAL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	808FS	2721 				21061586				WHILE PERFORMING RUN UP OF AIRCRAFT DURING ANNUAL INSPECTION IT WAS NOTICED THAT PILOT RT RUDDER PEDAL HAD AN UNUSUAL FE	EL WHILE BRAKING.  DURING THE INSPECTION OF THE RUDDER PEDALS IT WAS FOUND THT THE EACH OF THE PILOT SIDE S1675-1 RUDDER	 IB BEARING HALF HAD BROKEN INTO SEVERAL PARTS.  THE S1675-1 BEARING HALFS ARE CONSTRUCTED OF PLASTIC, AND THE LIKELY RE	ASON FOR BREAKING WOULD BE DUE TO THE AGING AND EMBRITTLEMENT OF THE PLASTIC.  I WOULD RECOMMEND THAT THE BEARINGS BE CO	NSTRUCTED OF A MATERIAL OTHER THAN PLASTIC, OF HAVE A PART REPLACEMENT INTERVAL BEFORE BREAKAGE COULD OCCUR.  (K)		1	H	7	1 	3O				3A21    					 
2007071100220	20070711	00220	CE  	2007	7	11	2007FA0000573    	1	20070606	G	2720	25137911	PIN             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					RUDDER PEDAL	UNSERVICEABLE   	B			ES4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4365U	18129				208B0253				ON A ROUTINE INSPECTION, A MECHANIC FOUND THAT THE PILOTS RT RUDDER PEDAL PIN WAS ABOUT TO FALL OUT OF THE RUDDER PEDAL.	  FURTHER INSPECTION FOUND THAT THE ROLL PIN PN: NAS561C318 HAD FALLEN OUR OF ITS HOLE CAUSING THE RUDDER PEDAL PIN TO M	IGRATE FROM ITS POSITION.  INSPECTION OF RUDDER PEDAL ASSY FOUND THAT THE ROLL PIN HOLE IN THE RUDDER PEDAL HAD BECOME E	NLARGED, DUE TO AN UNKNOWN REASON.  RECOMMENDATION TO PREVENT RECURRENCE:  ATTENTION TO ROLL PIN INSTALLATION FOR ADEQUA	TE PRESS FIT AND ADDITIONAL ATTENTION OF ROLL PIN ON ROUTINE INSPECTION.  (K)		1	H	7	1 	3T	3	T		A37CE   	E2NE				 
2007071100221	20070711	00221	CE  	2007	7	11	2007FA0000574    	1	20070629	G	3244	265F868	TIRE            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6*        	52043	EA  					NLG	UNBALANCED      	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	5XM	408  				FL115				PILOT REPORTED A NOSE SHIMMY, UPON INVESTIGATION IT WAS DETERMINED THAT THE MFG BALANCE WEIGHT HAD COME LOOSE.  THIS IS 	THE SECOND OCCURRENCE OF THIS TYPE FOR THE OPERATOR. (K)					2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2007071100222	20070711	00222	NE  	2007	7	11	2007FA0000575    	2	20070602	G	7321	0292858360	HMU             			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	151AC	1609 				3732	23065			THE PILOT REPORTED A LOUD THUD AND A SUBSEQUENT YAWING OF THE AC, WITH CONTINUED YAWING OF THE AC, AND NO INDICATION ON 	THE COCKPIT INSTRUMENTATION THAT HE NOTICED.  THE PILOT DECLARED AN EMERGENCY AND PERFORMED AN AUTORATATIVE LANDING AT T	HE AIRPORT.  THE VEHICLE AND ENGINE MULTIFUNCTION DISPLAY, DISPLAYED FAILURE OF CHANNEL A.  THE EC130 IS EQUIPPED WITH A	 DUAL CHANNEL FADEC SYSTEM WITH A MECHANICAL BACKUP.  IN THE FOLLOWING TROUBLESHOOTING PROCESS IT WAS FOUND THAT THE RES	OLVER MOTOR ON THE FUEL CONTROL (HMU)  HAD A RESISTANCE VALUE THAT WAS OUT OF TOLERANCE.  A FIELD TECH WAS BROUGHT IN FR	OM MFG TO PERFORM FURTHER TESTING, SINCE THE FAILURE OF ONE CHANNEL OF THE FADEC AND THE SUBSEQUENT SWITCHING TO THE OTH	1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2007071100232	20070711	00232	CE  	2007	7	11	2007FA0000576    	1	20070611	G	5300		STRUCTURE       			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FUSELAGE	MISINSTALLED    	B			BWVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	7262U					FL532				THE AIRCRAFT ARRIVED NEW FROM THE FACTORY FOR AVIONICS MODIFICATIONS AND DURING OUR INCOMING INSPECTION A TECH NOTED MIS	SING RIVETS IN (2) STRINGER CLIPS.  THE CLIPS ARE LOCATED AT FS 386 ON THE RT NR3 AND RT NR 5 STRINGERS AS NOTED USING T	HE UPPER CENTERLINE STRINGER AS STRINGER NR 1.  EACH CLIP WITH (6) RIVETS EACH WERE EITHER MISSING RIVETS AND/OR THE RIV	ETS WERE NOT BUCKED SITTING IN THE HOLES.  ADVISED MFG OF DISCREPANCY.  (K)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2007071100233	20070711	00233	SO  	2007	7	11	2007FA0000577    	1	20070512	G	3220	6715003	DOWNLOCK        			PIPER 	PA28  	PA28R200    	7102811	SO  	CONT  	IO360 	IO360*      	17025	CE  					NLG	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	5094S	3220 				28R7135094				THE LOWER LATCH HOOK WAS BROKEN OFF ALLOWING THE NOSE GEAR TO COLLAPSE.  (K)						1	L	7	1 	3O	3	O		2A13    	E1CE				 
2007071100246	20070711	00246	CE  	2007	7	11	2007FA0000578    	1	20070605	G	5343	FMI32345010B	BUSHING         			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					TRUNNION	GOUGED          	B			NOZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	22NG					7500204				BUSHINGS WHERE OLEO ATTACHES TO TRUNNION.  OLEO ATTACH BOLT WAS SEIZED AND HARD TO REMOVE.  INNER BORE OF BUSHINGS WERE 	GOUGED.  NO MEANS TO LUBRICATE THESE BUSHINGS EXCEPT AT ASSY.   SUGGEST USE OF ANT SEIZE COMPOUND DURING ASSY INSTEAD OF	 AEROSHELL 17.  (K)				2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007071100247	20070711	00247	CE  	2007	7	11	2007FA0000579    	1	20070605	G	5343	67410261	TRUNNION        			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					MLG	MISALIGNED      	B			NOZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	22NG					7500204				AFT TRUNNION ATTACH PIN LOCK PIN HOLE MISALIGNED.  LOCK PIN HOLES DRILLED IN TRUNNION DO NOT LINE UP WITH HOLE DRILLED I	N MOUNTING PIN.  (K)					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007071100249	20070711	00249	CE  	2007	7	11	2007FA0000580    	1	20070427	G	8011	MHB4016R	STARTER         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	182MS					18200791				REMOVED THIS STARTER FROM AIRCRAFT DUE TO BENDIX FAILURE.  TIME ON THIS STARTER IS UNKNOWN.  (K)						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2007071100257	20070711	00257	CE  	2007	7	11	2007FA0000581    	1	20070518	G	8011	MHB4016R	STARTER         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					ENGINE	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	182MS	62   				18200791				REMOVED THIS STARTER FROM SAME AIRCRAFT FOR THE 3RD TIME WITH 62.3 HRS SINCE OVERHAUL.  STARTER BENDIX WOULD NOT ENGAGE 	ANYMORE DURING START UP.  NO PROBLEM COULD BE FOUND WITH AIRCRAFT ELECTRICAL SYSTEM.  (K)					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2007071100258	20070711	00258	CE  	2007	7	11	2007FA0000582    	1	20070430	G	8011	MHB4016R	STARTER         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	182MS					18200791				REMOVED THIS STARTER WITH 3.3 HOURS SINCE OVERHAUL.  STARTER BENDIX STAYED ENGAGED DURING START UP.  NO PROBLEM COULD BE	 FOUND WITH AIRCRAFT ELECTRICAL SYSTEM.  (K)					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2007071100259	20070711	00259	CE  	2007	7	11	2007FA0000583    	1	20070524	G	8011	MHB4016R	STARTER         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					ENGINE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	182MS					18200791				REMOVED THIS STARTER FROM SAME AIRCRAFT FOR THE 4TH TIME WITH 11.3 HOURS SINCE OVERHAUL.  STARTER BENDIX WOULD NOT ENGAG	E ANYMORE DURING STARTUP.  NO PROBLEM COULD BE FOUND WITH AIRCRAFT ELECTRICAL SYSTEM.  INSTALLED ON ANOTHER AIRCRAFT TO 	VERIFY PROBLEM AND FOUND THAT THE STARTER WAS DEFECTIVE.  (K)				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2007071100265	20070711	00265	CE  	2007	7	11	2007FA0000584    	1	20070521	G	3231	HM4	ROD END         			CESSNA	310   	310P        	2074238	CE  	CONT  	O470  	IO470*      	17026	SO  					NOSE GEAR DOOR	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	5918M					310P0218				ROD END FAILED, ALLOWING NOSE GEAR DOOR TO PARTIALLY CLOSE IN FLIGHT.  WHEN GEAR WAS RETRACTED, JAMMED NOSE GEAR ASSY AL	ONG WITH GEAR DOOR UP IN GEAR WELL.  (K)					1	L	7	2 	3O	3	O		3A10    	E1CE				 
2007071100266	20070711	00266	EA  	2007	7	11	2007FA0000585    	1	20070507	G	5100	AN837A	BOLT            			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					UNKNOWN	BROKEN          	C				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	15	5149					1123				THE BOLTS FAILED DUE TO LANDING WITH WHEEL LOCKED.  THINK THE BOLTS WERE FINE BEFORE THIS INCIDENT.  (K)						1	Q	7	1 	3R	3	R		1A16    	5E2				 
2007071100268	20070711	00268	NM  	2007	7	11	2007FA0000588    	1	20070413	G	3240		BRAKE DISC      			BOEING	727   	727200      	138407E	NM  										LT MLG	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	HP161					20780				(REG NR: HP1610)  DURING PREFLIGHT INSPECTION, FOUND MAIN TIRE NR 2 WITH FLAT SPOT.  ON THIS AIRCRAFT OP SPECS APPROVED 	BY THIS DGAC, OPERATING BY DHL OF GUATEMALA UNDER THEM.  REMOVED AND REPLACED MWA AND BRAKE ASSY.  NR 2 DUEL TO DAMAGED 	, ALSO MAIN WHEEL ASSY NR 1 WAS REPLACED , BECAUSE IT RAN WITH THE TIRE NR 2 DEFLATED.  (K)				2	L	7	3 	4F			RT	A3WE    					 
2007071200121	20070712	00121		2007	7	12	2007FA0000589    	2	20070622	G	7414	1068256013	GEAR            																	MAGNETO	DAMAGED         	G				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CE	01			720  							REPAIR STATION RECEIVED MAGNETO FOR REPAIR. WHEN THE UNIT WAS DISASSEMBLED IT WAS NOTED BOTH DISTRIBUTOR GEARS TCM PN 10	-682016 WERE MISSING TEETH. IT WAS NOTED THAT A PATTERN OF TEETH THAT WERE MISSING COULD BE SEEN. A TOTAL OF 5 TEETH WER	E MISSING FROM BOTH GEARS. WHAT SEEMS TO HAPPEN IS WHEN THE IMPULSE SNAPS THE IMPULSE SNAPS THAT TOOTH OFF THE GEAR? WHE	N ASSEMBLED TO VIEW THE GEAR POSITION IT WAS NOTED THAT ONE TOOTH WAS MISSING WITH FIVE EACH OF THE SIX TOTAL ENGAGEMENT	S OF THE IMPULSE. ITEMS THAT COULD CONTRIBUTE TO THIS PROBLEM CAN BE FOUND IN SB658. IT IS RECOMMENDED TO FOLLOW SB658 A	ND TO INSPECT THE DISTRIBUTOR GEARS ON ALL IMPULSE D-3000 OR D-2000 UNITS FOR WEAR AT EVERY 100 HRS BY REMOVING THE MAGN														 
2007071200122	20070712	00122	SO  	2007	7	12	2007FA0000590    	2	20070527	G	7414	10382585	CONTACTOR       		D4LN2021    						CONT  	O360  	IO360A      	17025	SO  					MAGNETO	MELTED          	D				E	B	A		ENGINE SHUTDOWN         	EMER. DESCENT           	UNSCHED LANDING         		G	Y		MULTIPLE FAILURE          	ENGINE STOPPAGE           		CR	CRUISE         	1			NM	03	134DC	114  			R2388K		L1176351A			AIRCRAFT HAD DEPARTED FOR A SIGHT SEEING TRIP. ON THE RETURN, ALL ENGINE POWER WAS LOST, THE AIRCRAFT WAS LANDED IN A ME	ADOW WITH MINIMAL DAMAGE TO THE AIRCRAFT.  UPON INSPECTION OF THE ENGINE, FOUND THAT THE MFG DUAL MAGNETO  D4LN-2021 WAS	 NOT FUNCTIONAL ON EITHER MAG. UPON FURTHER INVESTIGATION IT WAS DETERMINED THAT THE CAM FOLLOWERS OF THE POINTS HAD GOT	TEN TOO HOT AND MELTED TO A POINT THAT RENDERED THE CONTACT ASSEMBLY  INOPERATIVE, CAUSING A DUAL FAILURE OF THE MAG. IT	 WAS NOTED THAT THE SCREW THAT HOLDS THE POINTS CAM IN PLACE HAD A TORQUE CHECK  PAINTED ON IT AND HAD TURNED BLACK FROM	 HEAT. DUE TO THE FACT THAT THE DUAL MAG HAS MORE POSSIBILITIES TO PRODUCE MORE HEAT JUST FROM THE ELECTRICAL PART OF MA						3	O			E1CE				 
2007071200125	20070712	00125	SO  	2007	7	12	2007FA0000592    	2	20070703	G	8530	SA10203	CYLINDER        			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	NR 5	SEPARATED       	G				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			EA	63	5436T	850  				17251336	34640D6D	78634		CYLINDER BARREL SEPARATED APPROXIMATELY 2 NR ABOVE THE CYLINDER BASE FLANGE.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2007071200132	20070712	00132	NM  	2007	7	12	2007FA0000593    	1	20070703	G	5751	25W171124	SUPPORT FITTING 			ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE731*     	01518	WP  					AILERONS	DAMAGED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	49MN	7037 				019				AFTER REMOVAL OF AILERON AND SERVICE SUPPORT FITTING AT BL 9R FUSELAGE STATION 199.579.  FOUND SEVERAL MISSED DRILLED/EL	ONGATED /FILLED FASTENER HOLES IN  T CASTING P/N:25W17124, ANGLE P/N:25W171126 AND AILERON AND SERVICES SUPPORT FITTING 	CASTING P/N:25W353216				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2007071700012	20070717	00012	NM  	2007	7	17	2007FA0000594    	1	20070703	G	5751	25W171124	SUPPORT FITTING 			ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE731*     	01518	WP  					AILERON	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	49MN	7037 				019				AFTER REMOVAL OF AILERON AND SERVICE SUPPORT FITTING AT BL 9R FUSELAGE STATION 199.579. FOUND SEVERAL MISSED DRILLED/ELO	NGATED /FILLED FASTENER HOLES IN T CASTING P/N:25W17124, ANGLE P/N:25W171126 AND AILERON AND SERVICES SUPPORT FITTING CA	STING P/N:25W353216				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2007071800219	20070718	00219	EU  	2007	7	18	2007FA0000599    	1	20070616	G	2701	103B4411	CONTROL COLUMN  			GROB  	103TWN	G103ATWINII 	1660206	EU  										COCKPIT	FRACTURED       	D				B	A			EMER. DESCENT           	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			NM	07	4446Y	2650 				3825				ON SECOND FLT OF DAY, & WHILE STILL ON AERO-TOW, PILOT WHO WAS FLYING FROM THE REAR SEAT WITH A NON-PILOT PASSENGER IN F	RONT,  NOTICED THAT IT REQUIRED APPROXIMATELY 20 DEGREES OF RT-STICK CORRECTION TO MAINTAIN LEVEL FLT. PILOT ALSO OBSERV	ED AILERONS TO BE IN A NEUTRAL POSITION WITH THIS RT-STICK CORRECTION. PILOT RELEASED FROM TOW, & RETURNED TO AIRPORT & 	EXECUTED A SUCCESSFUL, UNEVENTFUL LANDING USING MINIMAL, LIGHT CONTROL STICK INPUTS. POST FLT INSPECTION OF AFT CONTROL 	STICK REVEALED CONTROL COLUMN BASE UNIT TUBING STUB OVER WHICH DETACHABLE REAR CONTROL STICK MOUNTS, TO BE FRACTURED, AP	PROXIMATELY 80 PERCENT OF ITS TOTAL CIRCUMFERENCE. IT REQUIRED ONLY MINIMUM FURTHER (BENDING) OF THE CONTROL STICK TO AC	1	K	0	0 	3O			0	G39EU   					 
2007071800235	20070718	00235	SO  	2007	7	18	2007FA0000601    	1	20070710	G	2910	MS21911D6	FITTING         			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD LINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT 	THE MALE END WHERE END AND TEE BODY COME TOGETHER.  REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK	 WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071800237	20070718	00237	SO  	2007	7	18	2007FA0000602    	1	20070710	G	2910	MS21911D6	FITTING         			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD LINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT 	THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK 	WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071800238	20070718	00238	SO  	2007	7	18	2007FA0000603    	1	20070710	G	2910	MS21911D6	FITTING         			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD LINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILLIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT	 THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK	 WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071700013	20070717	00013	SO  	2007	7	17	2007FA0000604    	1	20070710	G	2910	MS21911D6	TEE FITTING     			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD SYSTEM	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT 	THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK 	WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071700014	20070717	00014	SO  	2007	7	17	2007FA0000605    	1	20070710	G	2910	MS21911D6	TEE FITTING     			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD SYSTEM	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE.  CRACK WAS FOUND AT	 THE MALE END WHERE END AND TEE BODY COME TOGETHER.  REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHEC	K WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071700018	20070717	00018	EU  	2007	7	17	2007FA0000606    	1	20070712	G	2913	350A35109221	SHAFT           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					HYD PUMP	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	186AE	545  				3872	22484			DURING DAILY INSPECTION DISCOVERED EXCESSIVE PLAY IN HYDRAULIC PUMP DRIVE PULLEY. HYDRAULIC PUMP DRIVE WAS THEN REMOVED 	FOR FURTHER INSPECTION. IT WAS DISCOVERED THAT THE DRIVE PULLEY SHAFT HAD WORN EXCESSIVELY WHERE THE DRIVE BEARING HAD B	EEN SPINNING AROUND IT. THE DRIVE BEARING APPEARED TO BE FINE WITH NO BINDING NOTICED. IT APPEARS THAT THE FIT OF THE BE	ARING ONTO THE PULLEY WAS NOT TIGHT ENOUGH TO KEEP THE BEARING RACE FROM SPINNING.			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007071700019	20070717	00019	EU  	2007	7	17	2007FA0000607    	1	20070712	G	2913	350A35109221	PULLEY          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					HYD PUMP	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	186AE	545  				3872	22484			DURING DAILY INSPECTION DISCOVERED EXCESSIVE PLAY IN HYDRAULIC PUMP DRIVE PULLEY. HYDRAULIC PUMP DRIVE WAS THEN REMOVED 	FOR FURTHER INSPECTION. IT WAS DISCOVERED THAT THE DRIVE PULLEY SHAFT HAD WORN EXCESSIVELY WHERE THE DRIVE BEARING HAD B	EEN SPINNING AROUND IT. THE DRIVE BEARING APPEARED TO BE FINE WITH NO BINDING NOTICED. IT APPEARS THAT THE FIT OF THE BE	ARING ONTO THE PULLEY WAS NOT TIGHT ENOUGH TO KEEP THE BEARING RACE FROM SPINNING.			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007071700015	20070717	00015	SO  	2007	7	17	2007FA0000608    	1	20070710	G	2910	MS21911D6	TEE FITTING     			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD SYSTEM	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT 	THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK 	WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071700016	20070717	00016	SO  	2007	7	17	2007FA0000609    	1	20070710	G	2910	MS21911D6	TEE FITTING     			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD SYSTEM	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE.  CRACK WAS FOUND AT	 THE MALE END WHERE END AND TEE BODY COME TOGETHER.  REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM.  OP'S CHE	CK WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071700017	20070717	00017	SO  	2007	7	17	2007FA0000610    	1	20070710	G	2910	MS21911D6	TEE FITTING     			GULSTM	G1159 	GIV         	3980115	SO  										HYD SYSTEM	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT 	THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK 	WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F			RT	A12EA   					 
2007071800239	20070718	00239	SO  	2007	7	18	2007FA0000611    	1	20070710	G	2910	MS21911D6	FITTING         			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD LINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	177BB					1073				FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT 	THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK 	WAS GOOD, NO LEAKS NOTED.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007071800246	20070718	00246	EU  	2007	7	18	2007FA0000612    	1	20070711	G	2741	EM40112	ACTUATOR        			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					PITCH TRIM	FAILED          	C				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			WP	15	5166P	61   				1129				ON APPROACH PITCH TRIM ACTUATOR FAILED TO MOVE.  AIRCRAFT LANDED WITH PARTIAL FLAPS WITHOUT FURTHER INCIDENT.  ONE HOUR 	LATER TRIM ACTUATOR GROUND TESTED REVEALING NO DEFECTS.  ACTUATOR SENT TO MFG FOR INVESTIGATION.					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2007071800270	20070718	00270	CE  	2007	7	18	2007FA0000613    	1	20070713	G	3350		BATTERY         			BEECH 	B300  	B300        	1159232	CE  										EMERGENCY LIGHT	MELTED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NE	05	122RG					FL448				AIRCRAFT WAS IN MAINTENANCE FOR AN INSPECTION AND 12 MONTH EMERGENCY LIGHT BATTERY CHANGE.  FOUND BATTERIES SEVERELY COR	RODED AND HEAT DAMAGED.  BATTERIES INSTALLED WERE  P/N MN1400. THESE BATTERIES HAVE A TEST STRIP EFFECTIVELY SHORTS THE 	BATTERY TO CHECK THE CHARGE CONDITION.  THE BATTERY HOLDER IN THE EMERGENCY LIGHT ASSEMBLY CLAMPS THE BATTERY. THE BATTE	RIES WERE INSTALLED SO THE TEST STRIP WAS CLAMPED SHORTING THE BATTERIES CAUSING THE BATTERIES TO MELT AND CORROD IN THE	 HOLDERS, DESTROYING THE LIGHT ASSEMBLIES. THE P/N FOR THE BATTERIES FOR THE EMERGENCY LIGHT IS 14A, BATTERIES WHICH HAV	E NO TEST STRIP.   USE THE CORRECT P/N BATTERIES.	2	L	7	2 	4T			RT	A24CE   					 
2007071900120	20070719	00120	CE  	2007	7	19	2007FA0000617    	1	20070718	G	2731	556545098	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT STAB	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	26494	9131 	1200 			0605				AT THE PHASE 5 INSPECTION THE ELEVATOR FAILED THE FREE PLAY CHECK. A OVERHAULED UNIT P/N 5565450-98 S/N 0320-63 WAS INST	ALLED AND COULD NOT GET THE UP AND DOWN LIMITS TO COME IN TO SPECS. ON CLOSER INSPECTION IT WAS FOUND THAT THE PRIMARY D	RIVE GEAR HAS 16 TEETH AND THE ORIGINAL UNIT HAS 14 TEETH. THIS UNIT WAS OVERHAULED 6/8/2007. AS OF THIS WRITING WE ARE 	IN THE PROCESS OF INSTALLING ANOTHER UNIT WITH THE CORRECT NUMBER OF TEETH.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007071900142	20070719	00142	CE  	2007	7	19	2007FA0000618    	1	20070717	G	2700	07136242	ANCHOR          	CESSNA      		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	MASTER CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SO	09		3140 				172S9480	L1306651A	XB23004		ANCHOR PN 0713624-2, FOUND WORN ALMOST THROUGH BY THE STEEL PIN USED TO HOLD MASTER CYLINDER. ANCHOR IS ALUMINUM WHICH W	AS QUICKLY WORN OUT BY THE STEEL PIN.  IF PIN BREAKS FREE FROM THE ANCHOR THE MASTER CYLINDER CAN STOP MOVEMENT OF THE R	UDDER PEDAL.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007071900144	20070719	00144	NM  	2007	7	19	2007FA0000619    	1	20070717	G	5714	F13147LR	SKIN            			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					CENTER WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2048H	2500 	10   			2671				(5) MISSING AN426-3 RIVET HEADS ON LOWER CENTER SECTION SKINS PN F13147-L/-R PROMPTED INSPECTION HOLE INSTALLATION IAW S	B-31 FOR REPAIR ACCESS. LIGHT SURFACE CORROSION WAS FOUND ON LOWER SKINS AND STIFFENERS. BOTH SIDES WERE CLEANED AND TRE	ATED FOR CORROSION.  DURING CLEANING FOUND A 2 INCH SKIN CRACK IN AFT SECTION OF F13147-L AND A .5 INCH CRACK AT THE LOW	ER FWD TAB OF RIB PN F13016L, BOTH REPAIRED IAW AC 43.13-1B GUIDELINES. FUEL TANKS WERE REMOVED IAW SB-31 REQUIREMENTS A	ND 4 SMALL PATCHES OF LIGHT SURFACE CORROSION WERE FOUND ON THE RT OB END OF FWD FACE OF MAIN SPAR. CORROSION CLEANED AN	D TREATED. INSPECTION HOLE INSTALLATION ALLOWS MUCH BETTER VISUAL ACCESS FOR THE INSPECTION OF THE CENTER SECTION THAN W	1	L	7	1 	3O	3	O		A718    	E213				 
2007071900149	20070719	00149	SO  	2007	7	19	2007FA0000620    	1	20070525	G	2820	MILH25579	LINE            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	IO360E1A    	41514	EA  					FUEL SYSTEM	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	13	255ER	5    				448195004	L47872T			HOSE LEAK, ENGINE CAUGHT FIRE NOT DUE TO HOSE.  FUEL FED FIRE OFTEN STARTING AT NR 1 EXHAUST PORT.  (K)						1	L	7	2 	3O	3	O		A19S0   	1E10				 
2007071900150	20070719	00150	WP  	2007	7	19	2007FA0000621    	2	20070611	G	7261	31011607	SEAL            			SCWZER	G164  	G164B       	3952802	EA  	GARRTT	TPE331	TPE33143    	01514	WP  					COMPRESSOR	LEAKING         	B			G6CR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	48429					19B				THE COMPRESSOR SEAL WAS LEAKING AND THE REAR SCAVENGE PUMP GEAR SHEARED OFF CAUSING IT TO FAIL.  THIS CAUSED MAJOR OIL L	OSS AND THE PROP TO FEATHER.  HAVE REPLACED THE COMPRESSOR SEAL AND REAR PUMP TO PREVENT RECURRENCE.  (K)					1	Q	7	1 	3R	4	T		1A16    	E2WE				 
2007071900125	20070719	00125	WP  	2007	7	19	2007FA0000622    	2	20070611	G	7261		GEAR            			SCWZER	G164  	G164B       	3952802	EA  	GARRTT	TPE331	TPE33143B   	01514	WP  					SCAV PUMP	SHEARED         	B			G6CR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	48429					19B	P80151			THE COMPRESSOR SEAL WAS LEAKING AND THE REAR SCAVENGE PUMP GEAR SHEARED OFF CAUSING IT TO FAIL.  THIS CAUSED MAJOR OIL L	OSS AND THE PROP TO FEATHER.  HAVE REPLACED THE COMPRESSOR SEAL AND REAR PUMP TO PREVENT RECURRENCE.  (K)					1	Q	7	1 	3R	4	T		1A16    	E2WE				 
2007071900266	20070719	00266	SO  	2007	7	19	2007FA0000623    	1	20070616	G	2810		FUEL            			PIPER 	PA25  	PA25        	7102502	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	UNKNOWN	CONTAMINATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	6195Z					25229		A61128		WATER IN FUEL.  (K)						1	L	7	1 	3O	3	O		2A10    	E274	5	N	P88614	 
2007071900148	20070719	00148	CE  	2007	7	19	2007FA0000625    	1	20070622	G	3230	08421022	BELLCRANK       			CESSNA	310   	T310Q       	2074244	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	FAILED          	B			MYNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	372CC	4771 				310Q1071				FAILED DUE TO MECHANICAL OVERLOAD, NOSE GEAR JAMMED.  (K)						1	L	7	2 	3O	3	O		3A10    	E8CE				 
2007071900152	20070719	00152	CE  	2007	7	19	2007FA0000626    	1	20070606	G	2910	EM9159REVC	VALVE           			RAYTHN	390   	390         	7150030	CE  										HYDRAULIC SYS	STICKING        	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	18RF	85   				RB127				PILOT REPORTED RT HYDRAULIC SHUTOFF VALVE INITIALLY STUCK DURING PREFLIGHT TEST, THEN OPENED.  REPLACED VALVE WITH NEW U	NIT, FUNCTIONAL TESTS, OK.  REMOVED VALVE ASSY, PN 39045AS65014-003, MANUFACTURED 11/2005.  (K)					1	L	7	2 	3F			RT	A00010WI					 
2007071900154	20070719	00154	SO  	2007	7	19	2007FA0000627    	1	20070606	G	3230	455180	CONDUIT         			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  					RT MLG	SEPARATED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	61	7178P					242347	L359640			RT MLG EXTEND/RETRACT CONDUIT PUSH-PULL TUBING SEPARATED AT THE SWEDGE CONNECTION JUST OB OF THE LANDING GEAR CONTROL SU	PPORT BRACKET.  THERE WERE NO INDICATIONS OF IMPROPER INSTALLATION.  (K)					1	L	7	1 	3O	3	O		1A15    	E295				 
2007080700156	20070807	00156	CE  	2007	8	7	2007FA0000628    	1	20070718	G	5711		NUT PLATE       			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					SPAR	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	345BK					340A0113				WHILE UNDERGOING A ANNUAL INSPECTION INVESTIGATION OF NOISE COMPLAINT FROM THE LANDING GEARBOX IT WAS DISCOVERED THAT TH	E FOUR AN3-6A BOLTS THAT ATTACH THE PART 5011013-3 (BRACKET ACUATOR MOUNTING) & GEARBOX TO THE FRONT SPAR WAS LOOSE.  AN	 ATTEMPT AT TIGHTEN THEM REVEALED THAT THE NUT PLATES BUILT INSIDE THE SPAR WERE STRIPPED.  ALLOWED THE GEARBOX TO MOVE 	BACK FROM THE SPAR BY 1/8" AND REAR BULKHEAD FLEXING THE 1/8". (FS152.75)			1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007071900117	20070719	00117	CE  	2007	7	19	2007FA0000629    	1	20070718	G	5340		NUT PLATE       			CESSNA	340   	340A        	2076405	CE  										SPAR	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	60WH					340A0083				WHILE UNDERGOING A ANNUAL INSPECTION INVESTIGATION OF NOISE FROM THE LANDING GEARBOX, IT WAS DISCOVERED THAT THE (4) AN3	-6A BOLTS THAT ATTACH THE PN 5011013-3 (BRACKET ACTUATOR MOUNTING) AND GEARBOX TO THE FRONT SPAR WAS LOOSE.  AN ATTEMPT 	AT TIGHTEN THEM REVEALED THAT THE NUT PLATES BUILT INSIDE THE SPAR WERE STRIPPED.  ALLOWED THE GEARBOX TO MOVE BACK FROM	 THE SPAR BY .1250 INCH AND REAR BULKHEAD FLEXING THE .1250 INCH.			1	L	7	2 	3O				3A25    					 
2007080700159	20070807	00159	EU  	2007	8	7	2007FA0000630    	1	20070524	G	7921	369D25830101	BLOWER          			HUGHES	369   	369FF       	4470709	EU  	ALLSN 	250C  	250C30      	03013	GL  					OIL COOLER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	97FF	475  				0097F				OIL COOLER BLOWER APPEARS TO BE FOD`D OUT.  ONE BLADE WAS FOUND ENABLED IN THE HOUSING.  THE OUT OF BALANCE SITUATION BR	OKE ALL (4) BEARING CARRIER LEGS.  DAMAGED BLOWER WAS REPLACED AND AC WAS RETURNED TO SERVICE.  (K)					1	G	7	1 	3U	3	U		H3WE    	E1GL				 
2007080700162	20070807	00162	SW  	2007	8	7	2007FA0000631    	1	20070628	G	5711	5262	SPAR            			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320A2B     	41508	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	11666					23572	L31251278			(2) LONGITUDINAL CRACKS AT SPAR HINGE FITTING.  SHAKING AND EXPANDING OF WOOD FIBERS DUE TO MOISTURE OR LACK OF.  RECOMM	END USING ALUMINUM SPARS OF SUFFICIENT SIZE AND STRENGTH.  (K)					1	H	7	1 	3O	3	O		A759    	E274				 
2007080700164	20070807	00164	CE  	2007	8	7	2007FA0000632    	1	20070629	G	7830	545300319	LINK ROD        			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					THRUST REVERSER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	245SM					258567				PERFORMED EDDY CURRENT INSPECTION OF 8 EA THRUST REVERSER LINK ROD.  FOUND A CRACK IN (1) LINK ROD.  VERIFIED FINDING US	ING MAGNETIC PARTICLE INSP METHOD.  DURING MP INSP, NOTED ANOTHER CRACK, NOT DETECTED USING EDDY CURRENT.  DECIDED TO PE	RFORM MP INSP OF ALL RODS AND FOUND 3 MORE CRACKED.  CRACKS APPEAR TO BE ON THE INNER SURFACE AND WOULD NOT BE DETECTABL	E WITH NDT INSP PRESCRIBED IN THE MM.  CURRENT INSPECTION REQUIREMENTS ARE NOT ADEQUATE FOR FINDING THESE TYPES OF DEFEC	TS.  CRACKS IDENTIFIED ARE ORIENTED LONGITUDINALLY O THE RODS AND VARY IN LENGTH FROM .500 IN TO 3.0 INCH.  IT SHOULD BE	 NOTE THAT MAG PARTICLE INSP IS NOT A REQUIREMENT OF AIR FRAME MFG.  (K)	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007080700169	20070807	00169	CE  	2007	8	7	2007FA0000634    	1	20070520	G	7160	0750288	SUPPORT         			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470R       	17026	SO  					AIRBOX	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	2803Y					18253803				MECH DISCOVERED ON A 50 HR INSP, THE SUPPORT COLLAR ON THE AIRBOX MOUNTED TO THE CARBURETOR WAS CRACKED.  THIS COULD LEA	D TO THE SEPARATION OF THE AIRBOX FROM THE CARBURETOR AND LOSS OF POWER.  PN 0750288 WAS REPLACED WITH NEW SUPPORT COLLA	R PN 0750288-1 IAW SRM.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007080700171	20070807	00171	GL  	2007	8	7	2007FA0000635    	1	20070629	G	2420	646843	ALTERNATOR      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	FAILED          	B			T9ZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	769PC					1619		FP3952B		UPON RECEIPT OF CURRENT ALTERNATOR, NOTICED THAT SLIP-RING HOUSING WAS CLOCKED 180 DEGREES OUT OF ALIGNMENT OUT OF THE B	OX.  THIS PLANE HAS HAD SEVERAL REPAIRED ALTERNATORS INSTALLED ON IT.  THE MOST RECENT ALTERNATOR HAD ONLY 131.1 HOURS B	EFORE IT FAILED AND THE ONE PREVIOUS TO THAT ONE HAD 67.2 HOURS ON IT BEFORE IT FAILED.   (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2007080700172	20070807	00172	SW  	2007	8	7	2007FA0000636    	1	20070701	G	6410	206016201127M	BLADE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250B  	250B*       	 	GL  					TAIL ROTOR	DEPARTED        	D				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	15	357DC					1803				THE CENTER TIP WEIGHT SLUNG OUT OF SUBJECT TAIL ROTOR BLADE DURING FLIGHT, CAUSING A VIOLENT VIBRATION.  THE VIBRATION C	AUSED (3) OF THE TAIL ROTOR GEAR BOX STUDS TO SHEAR BEFORE THE AIRCRAFT COULD AUTO ROTATE TO THE GROUND.  IF THE HELICOP	TER HAD NOT MADE IT TO THE GROUND WHEN IT DID THE OTHER STUD WOULD HAVE SHEARED AND THE TAIL ROTOR GEAR BOX WOULD HAVE L	EFT THE AIRCRAFT AND THE RESULTS WOULD HAVE BEEN DISASTROUS.  RECOMMEND THE TIP BLOCKS BE MFG FROM MATERIAL THAT CAN WIT	HSTAND THE CENTRIFUGAL FORCES THAT ARE APPLIED TO THE TIP WEIGHTS DURING FLIGHT. RECOMMEND THAT HELICOPTER TAIL ROTOR BL	ADE TIPS BE INSPECTED AS SOON AS POSSIBLE AND EVERY 100 HR INSPECTION.  (K)	1	G	7	1 	3U	3	T		H2SW    	E10CE				 
2007080700173	20070807	00173	SO  	2007	8	7	2007FA0000637    	2	20070613	G	8520	SA640518	PISTON          			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	NR1 CYLINDER	FRACTURED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	1858X				4765K06552	18255958	1308944R	733700		AFTER INSTALLING NEW CYLINDER ASSY SA47006S-A20P WITH NEW PISTON ASSY PN SA640518, WE WERE PERFORMING BREAK IN RUN AT LO	W POWER, FIRST AT 800 RPM FOR 2 MIN.  SHUTDOWN ENGINE, CLEANED FOULED PLUGS DUE TO OIL IN CYLINDER FROM ASSY.  RAN ENGIN	E AT 1000 RPM FOR 3 MIN.  SHUTDOWN AND CLEANED SPARK PLUGS AGAIN.  RESTARTED ENGINE AND ADVANCED TO 1200 RPM, THE CYLIND	ER CLEARED OUT AND THEN STOPPED AFTER A FEW SECONDS.  AFTER REMOVING THE OIL PAN AND NR 1 CYLINDER THE PISTON APPEARED T	O HAVE FRACTURED ALONG A CASTING FAULT IN THE PISTON PIN BOSS.  THE RESULTING DEBRIS BENT THE CAM SHAFT, BROKE BOTH CRAN	KSHAFT HALVES.  (K)	1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2007080700174	20070807	00174	NE  	2007	8	7	2007FA0000638    	2	20070625	G	7250		BLADES          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	DAMAGED         	B			HDNR	A				UNSCHED LANDING         				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CR	CRUISE         	1			SW	03	911SV					0015	BB0113			DURING FLIGHT, A LOUD BANG WAS HEARD AND THEN ALL ENGINE INSTRUMENTS SHOWED AN INDICATION OF A TOTAL ENGINE FAILURE.  TH	E ENGINE WAS SECURED AND A SINGLE ENGINE LANDING WAS INITIATED WITHOUT INCIDENT.  UPON INSPECTION, IT WAS NOTICED THAT T	HE EXHAUST AREA OF THE ENGINE, THERE WERE PT ROTOR BLADES MISSING OR DAMAGED.  THE ENGINE WILL BE SENT BACK TO THE MFG F	OR EVALUATION.  (K)			1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2007080700175	20070807	00175	CE  	2007	8	7	2007FA0000639    	1	20070507	G	3233	12810013	HOUSING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG ACTUATOR	CRACKED         	C				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	09	4604V					172RG0337	L2232D38A	801046		ON A DUAL TRAINING FLIGHT, STUDENT AND INSTRUCTOR HEARD A NOISE WHEN LANDING GEAR WAS RETRACTED.  LT LANDING GEAR REMAIN	ED IN A PARTIALLY RETRACTED/ EXTENDED POSITION, UNABLE TO ACTUATE UP OR DOWN.  THE LT LANDING GEAR ACTUATOR BODY HAD FAI	LED (CRACKED) AT THE FWD MOUNTING BOLT HOLE, ALLOWING THE ACTUATOR BORE TO OPEN ENOUGH SO THAT  PISTON WOULD NOT ENGAGE 	THE LANDING GEAR PIVOT SECTOR GEAR SUFFICIENTLY TO MOVE THE LANDING GEAR.  (K)			1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007080700176	20070807	00176	SW  	2007	8	7	2007FA0000640    	1	20070702	G	3250		SOLENOID VALVE  			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					NLG STEERING	FAILED          	B			O9IR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	749L					T306				THE NOSE WHEEL STEERING WAS TESTED PRIOR TO FLIGHT, AD TESTED SATISFACTORY.  AT AROUND 60 TO 70 KNOTS DURING THE TAKEOFF	 ROLL, THE AC STEERING FAILED IN A MANOR THAT RESULTED IN THE AC PULLING HARD TO THE LEFT.  USING HARD RT BRAKE AND RT R	EVERSE THRUST THE AC WAS STOPPED BEFORE RUNNING OFF THE RUNWAY.  WHEN THE SPEED LEVER WAS RETARDED THE STEERING , RE-ENG	AGED, AS IT SHOULD HAVE, AND THE AC OPERATED NORMALLY.			2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
2007080800015	20070808	00015	CE  	2007	8	8	2007FA0000641    	1	20070706	G	2820	16864	LINE            			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					FUEL SYSTEM	MISMANUFACTURED 	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	13	4631C	394  				21063582				NEW FUEL INJECTOR LINE NR 5 CYL RAM PMA REPLACEMENT.  INSTALLED ON ENGINES, WELD DEFECT ALLOWED DEVIPER END BAIL TO COME	 LOOSE FROM LINE.  NOTED FUEL LEAN ON TOP OF ENGINE AT ANNUAL 100 HR INSP.  (K)					1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007080800016	20070808	00016	CE  	2007	8	8	2007FA0000642    	1	20070703	G	2820	L2891948A	LINE            			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	818CP	923  				18281258	L2891948A			FOUND HEAVY FUEL STAIN FROM OIL COOLER NR 5 INTAKE PIPE AND ON FIREWALL APPROVED TO BE NR 5 INTAKE PIPE.  FURTHER INSPEC	TION FOUND NR 5 FUEL INJECTION LINE LOOSE AT INJECTOR.  FOUND AND SNUGGED SEVERAL OTHER INJECTOR LINES AT INJECTOR AND F	LOW DIVIDER AD-02-01, AD LAST C/W 5-3-07. (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007080800017	20070808	00017	CE  	2007	8	8	2007FA0000643    	1	20070613	G	3246	G129	WHEEL           			CESSNA	172   	R172K       	2072431	CE  										NLG STRUT	MISREPAIRED     	G				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			GL	13	736MV	120  				R1722642				DURING TAKEOFF FROM A GRASS STRIP AS THE AIRCRAFT APPROACHED 30 TO 40 KNOTS, BOTH NOSE WHEELS INSTALLED ON THE FLOATS FA	ILED, CAUSING THE AIRCRAFT TO FLIP ON TO ITS BACK.  UPON EXAMINATION OF THE FLOAT NOSE WHEEL STRUTS THE FAILURE OCCURRED	 AT THE WELD JOINT OF BOTH LT AND RT WHEEL STRUTS.  IT APPEARS THAT THE WELDS DID NOT HAVE ADEQUATE PENETRATION.  INVEST	IGATION OF MFG IN PROCESS.  (K)			1	H	7	1 	3O				3A17    					 
2007080700163	20070807	00163	CE  	2007	8	7	2007FA0000646    	1	20070719	G	2710	05232182	PUSHROD         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERON	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	2277T					172S9958				AILERON PUSHROD WAS FOUND BENT DURING PREFLIGHT.  REMOVED PUSHROD AND WENT TO INSTALL NEW ROD AND FOUND THAT ALL FOUR RO	DS IN STOCK HAD BAD THREADS- PD WAS OVERSIZED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007080800010	20070808	00010	EA  	2007	8	8	2007FA0000647    	2	20070720	G	8520	AE75089	PISTON          			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  					NR 2 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	20858	1522 				17263857	L4988127A			PISTON SKIRT CRACKED ON 2 CYLINDERS.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2007080800026	20070808	00026		2007	8	8	2007FA0000648    	4	20070720	G	3457	GNS530W	DISPLAY         			CESSNA	414   	414A        	2075907	CE  										GPS	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	05		25   								SETTING AN EVENT IN THE AUX PAGE FOR A FUTURE TIME CAUSES AUX EVENTS PAGE TO NO LONGER FUNCTION.  SELECTING THIS PAGE CA	USES THE NAV6, GPS SATELLITE STATUS PAGE TO DISPLAY FOR 1 SECOND, THEN NAV2 PAGE(MAP) TO BE SELECTED.  AS A SIDE EFFECT,	 THE FLIGHT TIMER IS RESET EVERY TIME THE AUX PAGE IS ATTEMPTED TO BE SELECTED.  IT APPEARS THAT THE FIRMWARE BECOMES LO	ST, BUT RECOVERS.			1	L	7	2 	3O				A7CE    					 
2007080800027	20070808	00027	CE  	2007	8	8	2007FA0000651    	1	20070722	G	2810		FUEL CAP        			CESSNA	185   	185F        	2072820	CE  	CONT  	O520  	IO520D      	17032	SO  					WING	LEAKING         	P				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	13		5    				18503193				FUEL LEAKING FROM BASE OF NEWLY INSTALLED PREMIUM FUEL CAPS. LOCATION ON WINGS IRRELEVANT. LEAK FROM BOTH IB AND OB CAPS	. COMPLIED WITH MFG INSTRUCTIONS IAW VENT LOCATION WITHOUT EFFECT.  EVIDENTLY NOT UNCOMMON PROBLEM, AS BLOGS ON MFG CLUB	 FORUM AND PILOTS ASSOC. FORUM WILL ATTEST. MFG SENT NEW O-RINGS, BUT HAVEN'T TRIED THEM. NEVERTHELESS, CAPS SHOULD BE F	OOL-PROOF FROM FACTORY. HARDLY AN IMPROVEMENT OVER MY OLD MFG RAISED INLET CAPS.			1	H	7	1 	3O	3	O		3A24    	E5CE				 
2007080800049	20070808	00049	SO  	2007	8	8	2007FA0000657    	1	20070629	G	2720	480572	ROLL PIN        			PIPER 	PA42  	PA421000    	7104225	SO  										RUDDER PEDAL	SHEARED         	B			GW1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	411BG	5362 				425527004				PILOTS RT RUDDER PEDAL ROLL PINS SHEARED.  REFERENCE IPC PN 761792, FIG. 103, INDEX 14, PN 480572.  FAILURE MAY CAUSE LO	SS OF DIRECTIONAL CONTROL OR BRAKING ACTION DURING GROUND OPERATION.  (K)					1	L	7	2 	4T			RT	A23SO   					 
2007080800050	20070808	00050	CE  	2007	8	8	2007FA0000658    	1	20070612	G	2820	052355912	VENT            	CESSNA      		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					LT WING TANK	OBSTRUCTED      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	52119	9458 			0301	17274418	L1058239A			ENGINE QUIT IN FLIGHT WITH HALF TANK OF FUEL REMAINING.  UPON VISUAL INSPECTION OF LT WING, FOUND THE FUEL VENT LINE PN 	052355912 OBSTRUCTED WITH INSET REMAINS (WASP).  PHYSICALLY REMOVED OBSTRUCTION AND OPS TESTED ENGINE ON ALL TANK SETTIN	GS.  UPON SUCCESSFUL OPS CHECK OF FUEL SYSTEM, MADE LOG ENTRY AND RETURNED THE AIRCRAFT TO SERVICE.  AIRCRAFT HAS SUCCES	SFULLY FLOWN 50 HRS SINCE 6/12/07 WITH NO FURTHER INCIDENT.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007080800051	20070808	00051	CE  	2007	8	8	2007FA0000659    	1	20070712	G	3230	HMXL6G	ROD END         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG	UNSERVICEABLE   	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	820GW					TH13				DURING EXAMINATION OF AIRCRAFT POST INCIDENT, IT WAS DISCOVERED THAT ROD END (PN HMXL6G) ATTACHED TO THE NOSE GEAR RETRA	CT ARM (PN 35825172-2) WAS SHEARED OFF BELOW THE BEARING.  IT APPEARS THE FAILURE STARTED IN A CRACK IN THE THREADS.  TH	IS MOST LIKELY RELEASED THE OVER CENTER TENSION ON THE NOSE GEAR DOWNLOCK ALLOWING THE NOSE GEAR TO RETRACT AND SUBSEQUE	NTLY THE MAIN LANDING GEAR.  RECOMMEND ANNUAL PENETRANT INSPECTION OF ALL LANDING GEAR RETRACTION ROD ENDS.  (K)			1	L	7	2 	3O	3	O		3A16    	E5CE				 
2007080800052	20070808	00052	EA  	2007	8	8	2007FA0000660    	2	20070526	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					NR 4 CYLINDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	7342J	3339 	941  			2824671	L2283027A			NR 4 EXHAUST VALVE BROKE DURING FLIGHT, DAMAGING PISTON CAUSING OIL TO LEAK OUT EXHAUST PORT CREATING OIL SMOKE.   (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2007080800057	20070808	00057	SO  	2007	8	8	2007FA0000661    	1	20070701	G	1210		FUEL            			MAULE 	M5    	M5210C      	5460134	SO  	CONT  	O360  	IO360A      	17025	SO  						CONTAMINATED    	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			AL	05	62045		3    			6078C				WHILE PERFORMING BI-ANNUAL REVIEW.  ON LAST TAKEOFF, THE ENGINE BEGAN TO RUN ROUGH.  ENGINE DRIVEN FUEL PUMP FAILED AND 	INSTALLED A FRESHLY OVERHAULED PUMP.  ATTEMPTED A RUN UP WITH THE SECOND PUMP AND FOUND THE COVER PLATE AT THE MIXTURE C	ONTROL LEVER TO BE LEAKING.  REMOVED SECOND PUMP.  OVERHAUL SHOP  FOUND EVIDENCE OF WATER IN THE FUEL SYSTEM, LIGHT RUST	 IN THE ORIGINAL PUMP BODY, AND A WHITE FILM UNDER THE PRESSURE VALVE SEAT THAT DISINTEGRATED INTO A WHITE POWDER WHEN I	T DRIED.  THE PUMP WAS NOT ABLE TO PRODUCE THE PROPER PRESSURE WITH THIS FILM HOLDING THE VALVE OPEN.  DECIDED TO FLUSH 	THE FUEL SYSTEM AND TRY TO DETERMINE THE SOURCE OF CONTAMINATION.   FLUSHED ALL OF THE FUEL LINES.     THERE WAS LIGHT S	1	H	7	1 	3O	3	O		3A23    	E1CE				 
2007080800058	20070808	00058		2007	8	8	2007FA0000662    	1	20070628	G	8011	MZ422	STARTER         																		BURNED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										STARTER BURNED UP ON TEST CELL RUN.  (K)																			 
2007080800061	20070808	00061	CE  	2007	8	8	2007FA0000664    	1	20070628	G	3213	07416302	SPRING ASSY     			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  					AXEL FITTING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5544N	14045				18267782				DURING NDI OF MAIN LANDING GEAR SPRING ASSY, THE RT FITTING WAS FOUND CRACKED.  DURING WFPT FOR ASTM E1417.  PART WAS RE	PLACED WITH A SERVICEABLE UNIT.  SUSPECT CRACK WAS DUE TO CORROSION BETWEEN THE SPRING AND ALUMINUM FITTING.  (K)					1	L	7	1 	3O	3	O	NT	3A13    	E273				 
2007080800064	20070808	00064	CE  	2007	8	8	2007FA0000665    	1	20070726	G	1100		PLACARD         			CESSNA	172   	172S        	2072439	CE  										CABIN	INCORRECT       	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07										AIRCRAFT WITH AVIONICS: LOCATION OF INTERIOR ELT PLACARD IN BAGGAGE COMPARTMENT INDICATES THAT THE ELT IS BEHIND THE LOW	ER ACCESS PANEL TO THE AFT FUSELAGE.  THAT IS INCORRECT.  THE ELT ACCESS IS FROM THE UPPER PANEL.  REMOVED PLACARD AND F	ABRICATED NEW PLACARD AND PLACED IT ON THE UPPER ACCESS PANEL.				1	H	7	1 	3O			NT	3A12    					 
2007080800066	20070808	00066	EA  	2007	8	8	2007FA0000667    	2	20070726	G	8530	AEL85099	CYLINDER HEAD   			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					NR 2 CYLINDER	SEPARATED       	B				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	27	2021G	1046 				0095	L3725036A			NR 2 CYLINDER HEAD SEPARATED FROM CYLINDER BARREL IN FLIGHT.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2007080800068	20070808	00068	EU  	2007	8	8	2007FA0000669    	2	20070710	G	7200	DN3351053050	DAMPER          								CFMINT	CFM56 	CFM563C1    	13802	EU  					ENGINE	FAILED          	B			UOXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19							ESN725219			WAS NOTIFIED BY TEST CELL OPERATOR THAT DAMPER ASSY PN DN335-105-305-0 CAME APART DURING ENGINE TEST CELL OPERATIONS OF 	ENGINE DURING ENGINE TEST AND AFTER POST ENGINE ADJUSTMENT.  THE DAMPER ASSY WAS DISCOVERED IN THE ENGINE INLET AREA. (K	)									4	F			E21EU				 
2007080800069	20070808	00069	CE  	2007	8	8	2007FA0000670    	1	20070309	G	2460	IN31X100050CM358	MASTER SWITCH   			CESSNA	402   	402C        	207590R	CE  											FAILED          	C				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	99	J8VBL					0640				LOST POWER TO THE AVIONICS BUSS.  CARRIED OUT THE REQUIRED CHECKS AND TRIED REPEATEDLY TO RESTORE POWER TOT THE AVIONICS	 BUSS VIA THE EMERGENCY AVIONICS BUSS SWITCH, TO NO AVAIL.  LANDED, CONTACTED MAINTENANCE, WHO CONFIRMED THE AVIONICS BU	SS FAILURE.  (K) INVESTIGATE AVIONICS BUSS SYS FAILURE AND FOUND AVIONICS MASTER SWITCH DEFECTIVE.  MASTER SWITCH REMOVE	D AND REPLACED WITH NEW ITEM IAW MEB 05-1.  FUNCTION CHECK OF MASTER AVIONICS SWITCH AND EMERGENCY AVIONICS BUSS SWITCH 	CARRIED OUT SATISFACTORY.  (K)		1	L	7	2 	3O				A7CE    					 
2007080700033	20070807	00033	EU  	2007	8	7	2007FA0000671    	1	20070727	G	5310	A741210N	BRIDGE          			LET   	L23   	L23         	1360308	EU  											CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	431BA	1693 				029013				DURING A ROUTINE DYE-PENETRANT INSPECTION ON TG-10B CRACKS WERE DISCOVERED AT SEVERAL WELDS ON THE A741 210N BRIDGE ASSE	MBLY.    A REPLACEMENT BRIDGE ASSY CANNIBALIZED FROM ANOTHER TG-10B IN AN EFFORT TO PLACE THE FIRST NOTED AIRCRAFT BACK 	IN SERVICE.  AS A PRECAUTIONARY STEP, DECIDED TO DYE-PENETRANT THE CANNIBALIZED ASSEMBLY AND DISCOVERED IT TOO WAS CRACK	ED.   DECIDED TO INSPECT THE REST OF THE ACFT.  12 OUT OF 12 ACFT REVEALED CRACKS.			1	K	0	0 	  			RC	G24EU   					 
2007080800093	20070808	00093	EU  	2007	8	8	2007FA0000672    	1	20070727	G	5101	A741210N	BRIDGE          			LET   	L23   	L23         	1360308	EU  										ZONE 100	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	431BA	1693 				029013				ON JULY 23, 2007 DURING A ROUTINE DYE-PENETRANT INSPECTION ON TG-10B (L-23 SUPER BLANIK, S/N 029013) CRACKS WERE DISCOVE	RED AT SEVERAL WELDS ON THE A741 210N BRIDGE ASSEMBLY.  IT IS A MAINTENANCE MANUAL REQUIREMENT THAT THIS PART BE DYE-PEN	ETRANT INSPECTED EVERY 1000 HOURS.  A REPLACEMENT BRIDGE ASSEMBLY WAS CANNIBALIZED FROM ANOTHER TG-10B (L23, S/N 029015)	 IN AN EFFORT TO PLACE THE FIRST NOTED AIRCRAFT BACK IN SERVICE.  AS A PRECAUTIONARY STEP, WE DECIDED TO DYE-PENETRANT T	HE CANNIBALIZED ASSEMBLY AND DISCOVERED IT TOO WAS CRACKED.  AT THIS POINT IT WAS DECIDED TO INSPECT THE REST OF THE AIR	CRAFT HERE AT USAFA.  12 OUT OF 12 AIRCRAFT REVEALED CRACKS.	1	K	0	0 	  			RC	G24EU   					 
2007080800096	20070808	00096	CE  	2007	8	8	2007FA0000674    	1	20070717	G	2910	SA7670024001	LINE            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										HYD SYSTEM	RUPTURED        	C				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			EA	27	50AE	1848 				258650				FLEXIBLE HYDRAULIC LINE TO THE RT MAIN GEAR IB DOOR ACTUATOR RUPTURED IN FLIGHT. CREW EXTENDED LANDING GEAR AND FLAPS US	ING THE AUXILIARY HYDRAULIC SYSTEM AND LANDED WITHOUT INCIDENT. DURING INSPECTION BY MAINTENANCE DEPARTMENT NO APPARENT 	CAUSE WAS DETERMINED FOR THE LINE FAILURE. MFG HAS BEEN ADVISED OF THE DEFECT. NEW HYDRAULIC LINE WAS INSTALLED, SYSTEM 	WAS SERVICED WITH FLUID AND BLED, AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4F			RT	A3EU    					 
2007080800113	20070808	00113	CE  	2007	8	8	2007FA0000675    	1	20070712	G	5730	08220009	SKIN            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8647K	6580 				340A0605				CRACK IN THE TOP SKIN OF THE LT WING AT THE LANDING GEAR SIDE BRACE ATTACHMENT LOCATION, APPROXIMATELY WS 63.45.  THE SK	IN IS 2024-T63 ALUMINUM, .032 THICK.  THE CRACK IS ABOUT 3 INCHES LONG OR LONGER.  CANNOT DETERMINE THE TOTAL LENGTH OF 	THE CRACK.  (K)				1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007080800111	20070808	00111	EA  	2007	8	8	2007FA0000677    	2	20070715	G	8530	AEL85099IR	CYLINDER HEAD   			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	SEPARATED       	G				A				UNSCHED LANDING         				E	D	K	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	FLUID LOSS                	CL	CLIMB          	1			WP	27	2021G	1046 	1046 			0095	L3725036A			2 NR CYLINDER HEAD ASSEMBLY APPEARS TO HAVE FAILED DURING FLIGHT RESULTING IN A SEVERE ENGINE VIBRATION AND A FORCED LAN	DING. EXAMINATION OF UPPER HALF OF FAILED CYLINDER ASSEMBLY REVEALS THAT A CRACK OCCURRED AND PROPAGATED SYMMETRICALLY A	ROUND THE CYLINDER APPROXIMATELY .3750 BENEATH WHERE THE CYLINDER BARREL MEETS THE CYLINDER HEAD. NO INTERNAL CYLINDER /	PISTON DAMAGE WAS VISUALLY OBSERVED.			1	G	7	1 	3O	3	O	O	4H12    	E286				 
2007080800110	20070808	00110	GL  	2007	8	8	2007FA0000678    	1	20070624	G	3230	1956750	SHUTTLE VALVE   			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	MLG	MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	01	8847V	1527 	4    			30359				THE AIRCRAFT LOST ELECTRICAL POWER AND PILOT TRIED TO EXTEND THE LANDING GEAR USING THE EMERGENCY LEVER.  THE EMERGENCY 	LOWERING OF THE LANDING GEAR DID NOT TAKE PLACE AND THE PILOT HAD TO LAND THE AIRCRAFT WITH THE LANDING GEAR IN THE FULL	 UP POSITION.  DAMAGE; PROP STRIKE, LOWER FUSELAGE SKIDDING DAMAGE, LOWER FUSELAGE FUEL DRAIN GROUND OFF, SUDDEN STOPPAG	E OF THE ENGINE.			1	L	7	1 	3O	3	O		A18CE   	E5CE	5	C	P25EA	 
2007082100024	20070821	00024	SW  	2007	8	21	2007FA0000680    	1	20070729	G	7933	35C155103	SENSOR          			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  			PW610FA     							OIL TEMP	FAULTY          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	27	116DJ	32   				000021	LA0009			RT ENG HIGH OIL TEMPERATURE CAS MESSAGE UPON LANDING. EXCEEDANCE (OIL TEMP) AFTER LANDING-ENGINE SHUTDOWN DURING TAXI. F	OUND FAULTY MOT/MOP SENSOR REPLACED WITH NEW UNIT AND OPERATIONALLY CHECKED SATISFACTORY IAW EMM 79-30-04.					1	L	7	2 	4J			RT	A00002AC					 
2007080800109	20070808	00109	NE  	2007	8	8	2007FA0000681    	2	20070731	G	8560	13814	SEAL            								PWA   	R1340 	R1340AN1    	52016	NE  					SUPERCHARGER	LEAKING         	B				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	15										DISASSEMBLY OF THE ENGINE AND OR REAR SECTION AFTER CUSTOMERS REPORTED SMOKING AND INCREASE IN OIL CONSUMPTION. DURING T	HE DISASSEMBLY IT WAS FOUND THAT BLOWER SEALS HAVE FAILED AND BEEN LEAKING.										3	R			5E2				 
2007082100064	20070821	00064	CE  	2007	8	21	2007FA0000683    	1	20070712	G	5730	08220009	SKIN            			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	5152J					3400542				CRACK IN THE TOP SKIN OF THE RT WING AT THE LANDING GEAR SIDE BRACE ATTACHMENT LOCATION, APPROX WS 63.45.  THE SKIN IS 2	024-T3 ALUMINUM, .032 THICK.  THE CRACK IS ABOUT 4.5 INCHES LONG.  (K)					1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007082100065	20070821	00065	EA  	2007	8	21	2007FA0000684    	2	20070712	G	8520		CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CORRODED        	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	175AF	4363 				17281175	L3097351A			FOUND CRANKSHAFT TO BE PITTED, LAST INSPECTION WAS DONE BY MFG (4) YEARS AGO.  THIS ENGINE HAD HIGH UTILIZATION AND FREQ	UENT OIL CHANGES.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007082100067	20070821	00067	SO  	2007	8	21	2007FA0000685    	2	20070712	G	8550	ES48109	OIL FILTER      								CONT  	O520  	IO520M      	17032	SO  					ENGINE	CONTAMINATED    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11							560171			THE ENGINE OIL SYSTEM WAS CONTAMINATED BY OIL FILTER SEAL DEBRIS. (K) ON DISASSEMBLY OF THE ENGINE RUBBER DEBRIS WAS FOU	ND:  IN THE OIL PASSAGE THAT FEEDS THE STARTER ADAPTER WITH THE ADAPTER PILOT BEARING PLUGGED.  UPON SPLITTING OF THE EN	GINE CASE DEBRIS WAS FOUND IN THE OIL PASSAGE TO THE NR 3 MAIN BEARING.  BOTH OIL COOLING JETS TO NR 3 MAIN BEARING WERE	 PLUGGED WITH RUBBER DEBRIS.  THE RIGHT WAS PLUGGED WITH A PIECE .6250 INCH LONG AND THE LT WITH A PIECE .1875 INCH LONG	.  ONE PIECE OF RUBBER DEBRIS WAS LOCATED IN THE OIL PASSAGE TO THE NR 5 BEARING.  (K)							3	O			E5CE				 
2007082100068	20070821	00068	CE  	2007	8	21	2007FA0000686    	1	20070713	G	5510	45A2110422	RIB             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	52AW	4500 				RK115				HORIZONTAL STABILIZER LEADING EDGE IB RIBS ARE CRACKED AT THE ROLLER BRACKET ATTACHMENT POINTS.  SAFETY COMMUNIQUE NR 70	 IS ONLY PUBLISHED CRITERIA CONCERNING THIS PROBLEM.  (K)					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007082100070	20070821	00070	GL  	2007	8	21	2007FA0000687    	1	20070724	G	3230	105932B	POWERPACK       			BLANCA	17    	1731A       	1220435	GL  	LYC   	O540  	IO540K1E5   	41532	EA  					MLG	BURNED OUT      	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	15	14746	18   				7532156				THIS COMPONENT WAS INSTALLED FRESHLY OVERHAULED ON APRIL 6, 2006 AND HAS A TOTAL IN USE TIME OF 18.0 HOURS.  AFTER TAKEO	FF THE PILOT NOTICED THE LANDING GEAR WOULD NOT RETRACT.  TROUBLESHOOTING OF THE LANDING GEAR SYSTEM FINDS THE HYDRAULIC	 POWER PACK MOTOR WINDINGS ARE OPEN, MOTOR WILL NOT RUN.  UNIT WAS OVERHAULED UNDER WO NR AH-16326.  (K)				1	L	7	1 	3O	3	O		A18CE   	1E4				 
2007080800114	20070808	00114	WP  	2007	8	8	2007FA0000688    	1	20070710	G	2400		BRACKET         			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ALTERNATOR	LOOSE           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	9988F					S1791	RL2203051A			ALTERNATOR BRACKET LOOSE AT ENGINE BOSS.  BOLT CAUSES DAMAGE TO ENGINE CRANKCASE WHEN LOOSE.  FRETTING OF ARM AND ENGINE	 CRANKCASE OCCURS.  (K)					1	G	7	1 	3O	3	O		4H12    	1E10				 
2007082100072	20070821	00072	CE  	2007	8	21	2007FA0000689    	1	20070701	G	2497	S159660L	CIRCUIT BREAKER 			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	80213					17266449				PILOT STATED SMOKE IN COCKPIT.  INSPECTION REVEALED ALTERNATOR OUTPUT C/B FAILED, ALTERNATOR HAD BROKEN AND LOOSE PARTS 	INTERNALLY, AND VOLTAGE REGULATOR FAILED.  OPENED C/B AND FOUND INTERNAL PARTS HAD MELTED CAUSING SMOKE.  NO SIGNS OF WI	RE OVERHEATING, OR SECONDARY DAMAGE WAS FOUND.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082100074	20070821	00074	CE  	2007	8	21	2007FA0000690    	1	20070707	G	5312	07126161	BULKHEAD        			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470*       	17026	SO  					BS 230	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	2787Q	4575 				18257987				DURING INSPECTION OF THE AFT TAILCONE BULKHEAD (STATION 230.187) A CRACK APPROX .375 INCH LONG WAS DISCOVERED.  THE CRAC	K LOCATION WAS ON THE LT SIDE EMANATING FROM THE RUDDER CUTOUT HOLE AND PROGRESSING TOWARD THE BULKHEAD FLANGE.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007082100076	20070821	00076	CE  	2007	8	21	2007FA0000691    	1	20070625	G	2420	991059111RX	ALTERNATOR      			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	232AF	573  				18281180	L2860348A			AC ARRIVED AT 1R4 WITH A FAILED ALTERNATOR.  SYSTEM WAS TESTED TO CONFIRM THAT THE ALTERNATOR WAS THE PROBLEM.  ON 6/25/	07 THE ALTERNATOR IN QUESTION WAS REMOVED FROM THE AC.  UPON REMOVING THE ALTERNATOR THE TECHNICAN FOUND THE SAFETY LOCK	 WIRE FOR THE ALTERNATOR HOUSING HALVES WAS BROKEN AND ONE OF THE FOUR CAP SCREWS WAS MISSING AND THE OTHER (3) WERE LOO	SE.  THE AC WAS INSPECTED AGAIN TO DETERMINE IF ANY OTHER PART COULD HAVE COME IN CONTACT WITH THE ALTERNATOR TO CAUSE T	HE SAFETY LOCK WIRE TO BREAK.  NO CONFLICTS WERE NOTED DURING THIS INSPECTION.  DIGITAL PICTURES HAVE BEEN TAKEN FOR REC	ORD AND ARE AVAILABLE UPON REQUEST.  (K)	1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007080800116	20070808	00116	SW  	2007	8	8	2007FA0000692    	1	20070706	G	5302	206020123048	RIB             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL BOOM	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	245AR					4398				DURING THE COURSE OF A SCHEDULED INSPECTION, THE RT HORIZONTAL STABILIZER WAS REMOVED TO TROUBLESHOOT A PROBLEM WITH AN 	AUXILIARY STROBE LIGHT THAT IS ATTACHED TO THE STABILIZER.  DURING REMOVAL, THE FLANGE ON THE IB RIB THAT ATTACHES THE S	TABILIZER TO THE TAILBOOM WAS FOUND CRACKED AND SEPARATED INTO 2-PIECES.  DUE TO THE LOCATION OF THE CRACK IT WAS NOT VI	SIBLE WITH THE STABILIZER INSTALLED.  (K)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007082400138	20070824	00138	EA  	2007	8	24	2007FA0000693    	3	20070621	G	6110		BOLT            			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O360  	O360*       	41514	EA  	SNSNCH	W80	W80CM8      	EA  	PROPELLER	LOOSE           	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	530AK					184385		AF5140		PILOT REPORTED SLIGHT VIBRATION DURING FLIGHT OF APPROX (1) HOUR.  WHEN POWER WAS REDUCED FOR LANDING, VIBRATION BECAME 	MORE EVIDENT.  INITIAL INSP FOUND (1) PROP BOLT HAD COME OUT FWD AND THROUGH SPINNER AND PROP WAS LOOSE.  WITH REMOVAL O	F SPINNER, FOUND (2) BOLTS BACKED OUT, (1) THROUGH THE SPINNER AND (1) NEXT TO IT.  (2) BOLTS REMAINED SAFETIED, BUT NOT	 TIGHT.  THE REMAINING PAIR OF BOLTS, THE SAFETY WIRE WAS BROKEN BETWEEN THE BOLTS AND THE BOLTS WERE BACKED OUT APPROX 	(1) INCH.  AFTER COMPLETE REMOVAL OF PROP, WHICH REQUIRED CUTTING THE HEAD OFF OF (1) BOLT, THE ATTACHMENT BUSHING FOR T	HIS BOLT WAS BROKEN OFF FLUSH WITH THE CRANKSHAFT FLANGE.  ANOTHER ATTACHMENT BUSHING WAS ALSO BROKEN OFF, FLUSH WITH TH	1	H	7	1 	3O	3	O		1A2     	E286	5	N	P27NE	 
2007082100142	20070821	00142	CE  	2007	8	21	2007FA0000695    	1	20070718	G	5311		SPAR            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					MLG WW	DAMAGED         	G			W1NR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	60WH					340A0083				WHILE INVESTIGATING A NOISE IN THE LANDING GEAR ACTUATOR GEARBOX, IT WAS DISCOVERED THA THE AN3-6A BOLTS ATTACHING THE A	CTUATOR MOUNTING BRACKET, PN 50110133, TO THE FRONT CENTER SPAR WERE LOOSE.  AN ATTEMPT TO TIGHTEN THE BOLTS REVEALED TH	AT THE NUTPLATES INSIDE THE SPAR WERE STRIPPED.  THE NUTPLATES ARE NOT REFERENCED IN THE IPM AND APPEARS HAVE BEEN INSTA	LLED INSIDE THE SPAR DURING THE MFG PROCESS (INACCESSIBLE).  AS A RESULT OF THE ABOVE CONDITION, WHEN THE GEAR IS RAISED	 OR LOWERED, THE BRACKET AND GEARBOX PULL AWAY FROM THE FWD CENTER SPAR AND TRANSMIT ALL THE FORCES TO THE AFT ATTACHMEN	T BULKHEAD, FLEXING THAT BULKHEAD BY MORE THAN .1250 INCH.  NO INSTRUCTIONS FOR REPLACEMENT OF NUTPLATES IN MM.  (K)	1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007082100267	20070821	00267	EA  	2007	8	21	2007FA0000697    	2	20070711	G	7414	M3816	CONDENSER       	SLICK       		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					LT MAGNETO	DISCONNECTED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	7508H				63008049	S1628	2594851A			SPRING CLIP ON TERMINAL WIRE CAME OFF ALLOWING WIRE TO DISCONNECT.  (K)						1	G	7	1 	3O	3	O		4H12    	1E10				 
2007082100268	20070821	00268	SO  	2007	8	21	2007FA0000698    	2	20070730	G	8530	TISN712ACA	CYLINDER        			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520CB     	17032	SO  					NR 6	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	69RP	744  				TE766				NR 6 CYLINDER WAS NEW ECI REV 3 E SERIES CRACKED BETWEEN FINS 1-3 BEHIND FUEL INJECTOR.  THIS IS 6TH ECI REV 3 E SERIES 	TO CARCK IN THE SAME LOCATION.  (K)					1	L	7	2 	3O	3	O		3A16    	E5CE				 
2007082100269	20070821	00269	CE  	2007	8	21	2007FA0000699    	1	20070703	G	2910	EM0159	SHUTOFF VALVE   			RAYTHN	390   	390         	7150030	CE  										HYD SYSTEM	JAMMED          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	18RF					RB127				PILOT REPORTED RT ENGINE HYDRAULIC SHUTOFF VALVE WOULD NOT CLOSE FOLLOWING PREFLIGHT CHECKS.  FOUND VALVE ASSY STUCK OPE	N.  REPLACED VALVE ASSY WITH NEW VALVE ASSY, OPERATIONS NORMAL.  VALVE ASSY (PN 45AS65014003) HAVE NOTICED THESE VALVE A	SSY TENDING TO FAIL WITH SHORT TIE SINCE NEW IN MFG INSTALLATIONS.  VALVE ASSY SEEMS FAIRLY RELAIBLE WHEN USED IN OTHER 	INSTALLATIONS.  (K)			1	L	7	2 	3F			RT	A00010WI					 
2007082100270	20070821	00270	CE  	2007	8	21	2007FA0000700    	1	20070711	G	3220	04425037	FORK            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					NOSE GEAR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	68246					15282208				DURING INSPECTION, FOUND NOSE GEAR FORK CRACKED (1.5 INCH LONG) ON LT UPPER RADIUS OF FORK.  AIRCRAFT IS USED FOR TRAINI	NG.  (K)					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007082100272	20070821	00272	EU  	2007	8	21	2007FA0000701    	1	20070709	G	3233		ROD             			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG ACTUATOR	CRACKED         	B			X6UR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	15	40TA	11851				194	75131			(REF CNTRL NR WW1045)  RECOVERED AIRCRAFT FROM TAXI WAY AFTER A LANDING WITH NO MLG GREEN LIGHTS.  LT GEAR STARTED RETRA	CTING DURING TAXI.  FOUND LT AFT GEAR RETRACT ACTUATOR PISTON ROD BROKEN INSIDE PISTON WHICH HAD CAUSED A MIS-DIRECT OF 	GEAR DOWN FLOW TO ROUTE INTO RETURN AND UNLOCKING THE GEAR JURY BRACE.  THE PISTON ROD HAD BEEN CRACKED FOR A PERIOD OF 	TIME APPROX .3333 THROUGH PRIOR FAILURE.  (K)			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2007082100146	20070821	00146	SW  	2007	8	21	2007FA0000702    	1	20070803	G	3250	S18233	BEARING         			BBAVIA	7     	7GCB        	2110130	SW  	LYC   	O320  	O320*       	41508	EA  					STEERING ROD	CRACKED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	01	2423	3342 				7GCB55				NOSE LANDING GEAR STEERING ROD END BEARING (P/N S-1823-3) FAILED IN THREADED PART OF ROD, ALLOWING NOSE GEAR TO TURN SID	EWAYS, RESULTING IN EXCESSIVE SIDE LOAD ON NOSE LANDING GEAR ASSEMBLY, CAUSING IT TO FAIL AND SEPARATE FROM THE AIRCRAFT	 RESULTING IN MINOR DAMAGE TO COWLING, PROPELLER, EXHAUST PIPES.  THIS ROD END BEARING SHOWS SIGNS OF CORROSION, PITTING	 AND IS PROBABLY THE ORIGINAL 1963 PART.			1	H	7	1 	3O	3	O		A759    	E274				 
2007082100171	20070821	00171	CE  	2007	8	21	2007FA0000703    	1	20070806	G	3411		STATIC LINE     			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	621RB					211				THIS RVSM AIRCRAFT HAD AN ALTIMETRY SYSTEM SPLIT. CONTACTED STC GROUP HOLDER FOR PROPER ROUTING OF STATIC SYSTEM PLUMBIN	G. FOUND CO-PILOTS STATIC SYSTEM INSTALLATION WAS NOT CROSS-COUPLED WITH PILOTS SYSTEM. INSTALLED FABRICATED HOSES TO TH	E CO-PILOTS SYSTEM TO MEET THE INTENT OF STC NR ST00563DE-D IAW MASTER DOCUMENT LIST.  CO-PILOTS STATIC SYSTEM NOT INSTA	LLED CORRECTLY AT STC INSTALLATION OR SYSTEMS HAVE BEEN ALTERED/MODIFIED POST-STC AND DID NOT FOLLOW APPROVED DRAWINGS.			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007082100194	20070821	00194	NE  	2007	8	21	2007FA0000704    	2	20070809	G	7310		LINE            			BOEING	737   	7373T0      	1384582	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					FUEL CONTROL	LEAKING         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	19	1732		320  			23372				FLOAT STICKS, CAUSING FUEL TO COME OUT OF CARBURETOR SPLIT LINE. LEAKING FUEL FROM GASKET.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007082100195	20070821	00195	SO  	2007	8	21	2007FA0000705    	1	20070809	G	2434	KELLY4111810	ALTERNATOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	19	17324	17   				287916050				ALTERNATOR FAILED AFTER 17.6 HOURS.						1	L	7	1 	3O	3	O		2A13    	E274				 
2007082100197	20070821	00197	SO  	2007	8	21	2007FA0000706    	1	20070809	G	2434	KELLY4111810	ALTERNATOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	17324		174  			287916050				ALTERNATOR FAIL AFTER 174 HOURS OF NORMAL OPERATION.						1	L	7	1 	3O	3	O		2A13    	E274				 
2007090600030	20070906	00030	WP  	2007	9	6	2007FA0000708    	1	20070813	G	5250		LOCK            			DOUG  	DC8   	DC8*        	       	WP  										COCKPIT DOOR	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										NOTIFY BY AIR SECURITY REPORT THAT OUR COCKPIT LKD SYSTEM INFORMS US ONLY IF IT'S ARMED OR NOT, BUT NOT IF THE DOOR IS C	ORRECTLY CLOSED AND LOCKED.  DURING ONE OF THE LAST FLT'S MY COCKPIT DOOR HAS BEEN OPENED BY THE PURSER WITHOUT MY PERMI	SSION.  THE DOOR SEEMED CLOSED BUT IT WASNT AND HE COULD OPEN IT EASILY.  IT IS UNSAFE FOR US ON BOARD AND FOR ALL PEOP	LE THAT WE FLY OVER.EUROPEAN AVIATION SAFETY AGENCYPOSTFACH 10 12 53D-50452 KOELN, GERMANYI'M  MD80 CPT OF ALITALIA , I 	NOTIFY BY AIR SECURITY REPORT THAT OUR COCKPIT LKD SYSTEM  INFORMS US ONLY IF IT'S ARMED OR NOT, BUT NOT IF THE DOOR IS 	CORRECTLY CLOSED AND LOCKED.DU	2	L	7	4 	4J			F	4A25    					 
2007082100289	20070821	00289	EA  	2007	8	21	2007FA0000710    	2	20070603	G	7322	30804	FLOAT           			AMTR  	COZY  	COZY        	05613R8	GL  	LYC   	O290  	O290*       	41506	EA  					CARBURETOR	SATURATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	369CZ									ENGINE FAILED ON SHORT FINAL DUE TO CARB FLOODING FLOAT IN CARB HALF FULL OF GAS.						1	M	7	1 	3O	3	O	NT	EXPA1M71	E229				 
2007082400247	20070824	00247	GL  	2007	8	24	2007FA0000711    	1	20070710	G	2497		RESISTOR        			DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  					ALTERNATOR	DAMAGED         	D			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	187DS	169  				40574				MFG FABRICATED AN IN-LINE RESISTOR FROM THE ALTERNATOR TO THE VOLTAGE REGULATOR.  THE RESISTOR WAS LOCATED APPROXIMATELY	 2 INCHES FROM AUX TERMINAL ON ALTERNATOR.  IT WAS STRENGTHENED WITH MULTIPLE LAYERS OF HEAT-SHRINK AND TERMINAL WAS CRI	MPED ON THE SOLID WIRE LEAD OF THE RESISTOR.  THE AIRCRAFT HAD INTERMITTENT ALT FAIL WARNING BUT HAD NORMAL, POSITIVE SY	STEM CHARGING.  UPON DISCOVERY OF THE FAULT, THE RESISTOR LEAD WAS HELD IN THE TERMINAL CRIMP BY THE HEAT SHRINK BUT THE	 SOLID WIRE WAS BROKEN, MOMENTARILY MAKING CONTACT CAUSING THE FAULT.  THE PROBLEM WAS CORRECTED BY SOLDERING A SMALL SE	CTION OF WIRE TO THE RESISTOR AND INSTALLING A NEW TERMINAL TO WIRE.  MFG CUSTOMER SUPPORT WAS CONTACTED AND THEY WERE A	1	L	7	1 	3O	3	O	NT	A47CE   	E1CE				 
2007082400266	20070824	00266	CE  	2007	8	24	2007FA0000712    	1	20070727	G	2621		SQUIB           			BEECH 	300   	300BEECH    	1152930	CE  										FIRE BOTTLE	GROUNDED        	B			ML2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	350RK					FL516				DURING COMPLETION OF THE INITIAL 200 HOUR PHASE 1 INSPECTION, THE RT ENGINE FIRE BOTTLE SQUIB WAS FOUND TO BE IN A GROUN	DED CONDITION.  THE TERMINALS WERE WIRED TOGETHER WITH SAFETY WIRE AND A TAG THAT STATED (DISCONNECT AT INSTALLATION, TH	E AIRCRAFT SQUIB WIRING WAS ATTACHED OVER THE SAFETY GROUND WIRE.  THIS GROUNDED CONDITION IS TYPICALLY FOUND ON SQUIBS 	THAT ARE PACKAGED FROM THE VENDOR FOR SHIPPING.  DURING INSTALLATION OF THE SQUIB ONTO THE FIRE BOTTLE, THE SAFETY GROUN	D IS REMOVED.  IN THIS CONDITION, THE SQUIB CANNOT DETONATE TO PUT OUT AN ENGINE FIRE.  LOG BOOKS WERE NOT AVAILABLE FOR	 RESEARCH AT THE TIME THE DISCREPANCY WAS DISCOVERED, ALTHOUGH THE AIRCRAFT WAS NEW ENOUGH THAT IT WAS UNLIKELY ANY ENGI	2	L	7	2 	4T				A24CE   					 
2007082400269	20070824	00269	SO  	2007	8	24	2007FA0000713    	2	20070731	G	8530		CYLINDER        			CESSNA	310   	T310Q       	2074244	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 6	LEAKING         	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	7714Q					310Q0214	521496			WHILE PERFORMING OTHER MAINTENANCE A FUEL STAIN WAS NOTICED BETWEEN THE SECOND AND THIRD COOLING FIN AFT OF THE FUEL INJ	ECTOR ON THE NR 6 CYLINDER OF THE RT ENGINE.  THIS CONDITION PROMPTED A CLOSER INSPECTION OF THE ENGINE RESULTING IN THE	 DISCOVERY OF SIMILAR STAINING ON THE NR 1 AND NR 5 CYLINDERS.  EACH CYLINDER WAS INDIVIDUALLY PRESSURIZED AND LEAK CHEC	KED WITH A SOAPY WATER SOLUTION, NR 6 CYLINDER PRODUCED LARGE BUBBLES.  THE CYLINDERS ARE ECI CASTING NR AEC65385 AND TH	ERE WAS (A) STAMPED ON THE ROCKER BOX FLANGE WHICH REQUIRES NO FURTHER ACTION IAW AD 04-08-10.  BY THE PILOTS STATEMENT 	THEY BELIEVE THERE IS APPROX. 1000 HOURS ON THESE CYLINDERS.  RECOMMEND THAT A GOOD VISUAL INSPECTION BE PERFORMED AT 10	1	L	7	2 	3O	3	O		3A10    	E8CE				 
2007082400298	20070824	00298	SW  	2007	8	24	2007FA0000714    	1	20070726	G	5711	5146R	SPAR            			BBAVIA	7     	7FC         	2110124	SW  	CONT  	C90   	C90*        	17009	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	9032B	3177 				123				AIRCRAFT WAS BEING MODIFIED TO INCLUDE THE INSTALLATION OF WING SPAR INSP HOLE KITS AS SUPPLIED IAW STC NR SA00527SE.  A	 PORTION OF THE WING LEADING EDGE SKIN WAS REMOVED AND THE WING SPAR WAS VISUALLY INSPECTED AS SPECIFIED IN THE INSTALLA	TION INSTRUCTIONS SUPPLIED WITH THE STC.  DURING THIS VISUAL INSPECTION, A CRACK WAS OBSERVED ON THE TOP SURFACE OF THE 	RT WING FRONT SPAR.  THE CRACK WAS OBSERVED ON THE TOP SURFACE OF THE RT WING FRONT SPAR.  THE CRACK ORIGINATES AT THE I	B END OF THE AFT PLYWOOD REINFORCEMENT PLATE.  REINFORCEMENT PLATE IS LOCATED ON THE AFT SIDE OF THE FRONT SPAR, UNDER T	HE LIFT STRUT ATTACHMENT FITTING.  THE CRACK PROGRESSES OB ALONG THE TOP SURFACE OF THE SPAR AT A SLIGHT FWD ANGLE (CRAC	1	H	7	1 	3O	3	O		A759    	E252				 
2007082400307	20070824	00307	CE  	2007	8	24	2007FA0000715    	1	20070807	G	2910	8907021	ACCUMULATOR     			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	HYS SYS	RUPTURED        	C			XPTS	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SO	19	61265	1440 				ME135				DURING TRAINING FLIGHT IN PREP FOR COMMERCIAL/AMEL, PILOT PERFORMED INTENTIONAL SHUTDOWN OF LT ENGINE (FEATHERED).  WAS 	UNABLE TO RESTART WITH ACCUMULATOR AND BEGAN PROCEDURE TO RESTART WITHOUT ACCUMULATOR WHICH WAS UNSUCCESSFUL.  PILOT RET	URNED TO DEPARTURE AND LANDED.  AN INVESTIGATION OF THE ACCUMULATOR REVEALED A RUPTURED DIAPHRAGM.  REPLACED LT ACCUMULA	TOR AND RT ACCUMULATOR WAS REPLACED AS A PRECAUTIONARY METHOD.  (K)			1	L	7	2 	3O	3	O		A29CE   	1E10	5	C	P43GL	 
2007082400308	20070824	00308	NE  	2007	8	24	2007FA0000716    	1	20070801	G	3340	SB4580	LAMP            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL2S1   	60057	NE  					SEARCH LIGHT	BURNED OUT      	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	554L					760567				POSSIBLE MFG PARTS NOT TO SPECIFICATIONS.  MFG OF ORIG UNKNOWN. (GENERIC) LESS THAN 7 FLT HOURS IAW LAMP (AVERAGE) FROM 	INSTALLATION TO REPLACEMENT.  HAVE REPLACED AT LEAST 5 LAMPS IAW AIRCRAFT IN LESS THAN 30 FLIGHT HOURS EACH.  NO CIRCUIT	 BREAKERS POPPING.  TROUBLESHOOTING SHOWS NO DISCREPANCIES ON EITHER AIRCRAFT.  NO MFG INFORMATION ON PARTS BOX OR ON TH	E PART.  (K)			1	G	7	2 	3U	4	U	NC	H1NE    	E00054EN				 
2007082400309	20070824	00309	NE  	2007	8	24	2007FA0000717    	1	20070801	G	3340	SB4580	LAMP            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL2S1   	60057	NE  					LANDING LIGHT	BURNED OUT      	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	552J					760518				POSSIBLE MFG PARTS NOT TO SPECIFICATIONS.  MFG OF ORIGIN UNKNOWN. (GENERIC) LESS THAN 7 FLT HOURS PER LAMP (AVERAGE) FRO	M INSTALLATION TO REPLACEMENT.  HAVE REPLACED AT LEAST 5 LAMPS PER AC IN LESS THAN 30 FLIGHT HOURS EACH.  NO CIRCUIT BRE	AKERS POPPING.  TROUBLESHOOTING SHOWS NO DISCREPANCIES ON EITHER AC.  NO MFG INFO ON PARTS BOX OR ON THE PART COPY OF OR	IGINAL CERTIFICATION ATTACHED.  (K)			1	G	7	2 	3U	4	U	NC	H1NE    	E00054EN				 
2007082400249	20070824	00249		2007	8	24	2007FA0000718    	2	20070821	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  										ENGINE	OUT OF LIMITS   	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SO	15	471ER	134  	61   			172S10511				DURING PRE TAKEOFF RUN UP, THE MAG DROP (BOTH MAGS) WAS BEYOND LIMITS. THIS AIRCRAFT HAD A RECENT HISTORY OF RICH SERVO 	OPERATION FOLLOWED BY ADJUSTMENTS, WHICH WOULD NOT STABILIZE. THE SERVO WAS CHANGED. THIS PROBLEM IS COMMON ON MANY OF T	HE AIRCRAFT IN THIS FLEET AND HAS CAUSED FLEET-WIDE ADJUSTMENTS WHEN SUBSTANTIAL CHANGES IN ATMOSPHERIC TEMPERATURE OCCU	R. IN MANY CASES THE SERVO MUST BE CHANGED WITH ONLY A FEW HOURS SINCE NEW.			1	H	7	1 	3O			NT	3A12    					 
2007082400265	20070824	00265	EA  	2007	8	24	2007FA0000719    	2	20070821	G	7300	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF LIMITS   	B				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SO	15	471ER	134  	61   			172S10511	L3340351E			DURING PRE TAKE OFF RUN UP, THE MAG DROP (BOTH MAGS) WAS BEYOND LIMITS. THIS AIRCRAFT HAD A RECENT HISTORY OF RICH SERVO	 OPERATION FOLLWED BY ADJUSTMENTS, WHICH WOULD NOT STABILIZE. THE SERVO WAS CHANGED. THIS PROBEM IS COMMON ON MANY OF TH	E AIRCRAFT IN THIS FLEET AND HAS CAUSED FLEET-WIDE ADJUSTMENTS WHEN SUBSTANTIAL CHANGES IN ATMOSPHERIC TEMPERATURE OCCUR	. IN MANY CASES THE SERVO MUST BE CHANGED WITH ONLY A FEW HOURS SINCE NEW.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007082400268	20070824	00268	CE  	2007	8	24	2007FA0000720    	1	20070821	G	2710	0510105364	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERONS	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	454ER	987  				172S10256	L3283951E			DURING A ROUTINE INSPECTION, THE AILERON BALANCE CABLE WAS FOUND BADLY WORN IN THE LT WING AT STATION 71.125. THE CABLE 	IS DIRECTED OVER A FAIRLEAD AT THIS LOCATION AND TYPICALLY WEARS VERY BADLY AT THIS CONTACT POINT. BECAUSE THE WEAR PATT	ER IS OVER A STRAIGHT RUN OF CABLE THERE IS NO BENDING OF THE CABLE WHICH WOULD CAUSE THE STRANDS TO FRAY OUTWARD. BECAU	SE OF THIS, THE CABLE CAN BE WORN THROUGH MANY STRANDS AND YET APPEAR NORMAL. ONCE THE CABLE IS REMOVED FROM THE AIRCRAF	T AND BENT AS SHOWN IN THE AC43.13-1B, PAGE 7-35, FIGURE 7-16, THE BROKEN STRANDS BECOME READILY APPARENT. THIS HAS BEEN	 AN ISSUE FOR A LONG TIME ON THIS MODEL AIRCRAFT. IF NOT INSPECTED CAREFULLY THE CABLE CAN DETERIORATE TO A DANGEROUS CO	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007082400320	20070824	00320	GL  	2007	8	24	2007FA0000721    	1	20070822	G	2497		CABLE           			DIAMON	DA40  	DA40        	2990002	GL  										ALTERNATOR	BROKEN          	G				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			WP	05	541AJ	265  				40541				ALTERNATOR CABLE INSTALLED AT THE FACTORY WAS TOO SHORT.  CABLE CONNECTS TO ALTERNATOR CIRCUIT BREAKER.						1	L	7	1 	3O			NT	A47CE   					 
2007082400321	20070824	00321	SO  	2007	8	24	2007FA0000722    	1	20070812	G	5520		HORN            	PIPER       		PIPER 	PA18  	PA18180     	7101880	SO  	LYC   	O320  	O320*       	41508	EA  					ELEVATOR	DAMAGED         	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			WP	23	4363Z		39   			188682				AFTER DEPARTURE PILOT NOTED UNUSUAL STICK RESTRICTION AND ABORTED TOW OF GLIDER. RETURNED FOR LANDING. UPON INSPECTION T	HE LOWER ARM/HORN OF THE RT ELEVATOR HORN HAD BROKEN. ALL (3) OTHER ARMS WERE UNDAMAGED AND SHOWED NO SIGN OF CRACKS. BO	LTS WERE INTACT AND HOLDING CONTROL CABLE.				1	H	7	1 	3O	3	O		1A2     	E274				 
2007082400322	20070824	00322	SO  	2007	8	24	2007FA0000723    	2	20070823	G	8550	S23611	CHECK VALVE     			CESSNA	206   	TU206C      	2073334	CE  	CONT  	O520  	TSIO520C    	17040	SO  					ENGINE OIL	WORN            	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	17	71924	4839 				U2061226	178337R			AFTER FLIGHT A/C SITTING ON RAMP DEVELOPED LARGE OIL LEAK FROM TURBOCHARGER.  FOUND OIL CHECK VALVE FLAPPER VALVE SEVERE	LY WORN.					1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2007090600088	20070906	00088	CE  	2007	9	6	2007FA0000725    	1	20070808	G	2410	CS3100	SENSOR          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					MASTER CNTRL BOX	INTERMITTENT    	B			MYNR	O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			GL	11	9424F	658  				17280390				CURRENT SENSOR INDICATES 60A AND WHEN MASTER IS TURNED ON FUNCTIONS NORMALLY FROM TIME TO TIME, TAP ON UNIT AND IT FLUCT	UATES THEN ACTS PROPERLY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007090600087	20070906	00087	CE  	2007	9	6	2007FA0000726    	1	20070703	G	3260	903610373	DOWNLOCK SWITCH 			RAYTHN	C90   	C90GT       	7150062	CE  										MLG	FALSE INDICATION	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	106ML	203  				LJ1757				PILOT REPORTED LT MAIN LANDING GEAR DOWN AND LOCKED INDICATION WITH LANDING GEAR RETRACTED.  FOUND SWITCH ASSY INDICATOR	 SHOWING GREEN DOWN AND LOCKED INDICATION IN GEAR RETRACTED POSITION.  REPLACED SWITCH ASSY WITH NEW UNIT.  LANDING GEAR	 RETRACTION/ EXTENSION SYSTEM TESTS NORMAL.  (K)				1	L	7	2 	3T			RT	3A20    					 
2007090600073	20070906	00073	NE  	2007	9	6	2007FA0000727    	3	20070620	G	6111	6533A12	BLADE           	HAMSTD      		AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	22D	22D40       	NE  	PROPELLER	BROKEN          	G				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			GL	15	23667				84119	3010410	20788	PP810268		(9 INCHES) OF PROP BLADE BROKE OFF IN FLIGHT.  THE SEVERE VIBRATION CAUSED PILOT TO LAND IN MUDDY FIELD.  AIRCRAFT WAS T	OTALED.  (K)					1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P736	 
2007090600078	20070906	00078	CE  	2007	9	6	2007FA0000728    	1	20070731	G	2420	DOFF10300B	ALTERNATOR      			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  		SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	9628X	88   				18268567	470887	851589		ALTERNATOR SHORTED, THIS UNIT IS (1) OF (3) REPLACED IN THE LAST MONTHS.  (K)						1	L	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2007090600070	20070906	00070	CE  	2007	9	6	2007FA0000729    	2	20070803	G	8520	538684	BUSHING         	CONT        		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					CONNECTING ROD	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	19WE					3449037	819271R			DURING THE PROCESS OF INSPECTING (6 EA) CONNECTING RODS IAW SB 07-1 AND SB 00-3, IT WAS FOUND THAT ALL WRIST PIN BUSHING	S WERE INSTALLED NOT IAW THEIR POSITIONS AS REQUIRED IN THE APPLICABLE SB AS REFERENCED.  SPLIT LINE OF BUSHING ON WRONG	 SIDE OF CENTERLINE.  PARTS AS RECEIVED FROM MFG.  (K)				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007090600036	20070906	00036		2007	9	6	2007FA0000730    	4	20070813	G	3444	ADS430101AC	ANTENNA         			PIAGIO	P180  	P180        	6960204	EU  										FUSELAGE	SEPARATED       	B			KKQR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	11	395KT	3985 				1044				RADAR ALTIMETER REPORTED INOPERATIVE.  FOUND ANTENNA SENSOR GONE FROM THE BASE, LEAVING .2500 INCH HOLE THROUGH THE COAX	 CONNECTION.  THE FLAT ANTENNA MOUNTS TO A CURVED FUSELAGE WITHOUT CONTOUR ADAPTATION.  (K)					1	H	7	2 	3O			RT	A59EU   					 
2007090600090	20070906	00090	SW  	2007	9	6	2007FA0000731    	1	20070625	G	2120	2784187019	PIPE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					RT WING BLEED AI	ARCED           	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	160WA					TC399				IB OF RT NACELLE, BLEED AIR PIPE (PN 2784187019), CHAFED OR BURNED THROUGH THE ASBESTOS SLEEVE SURROUNDING THE STARTER R	ELAY WIRING, WHICH THEN ARCED A HOLE IN THE BLEED PIPE, WHICH THEN BURNED THE SHIELDING FROM THE STARTER RELAY WIRES, WH	ICH THEN ARCED A HOLE IN A HYDRAULIC LINE (PN 2781032403), RESULTING IN A FIRE.				2	L	7	2 	4T	3	T	RT	A8SW    	E2WE				 
2007090600055	20070906	00055	CE  	2007	9	6	2007FA0000732    	1	20070517	G	2432	6041H274	RELAY           			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520*    	17040	SO  					BATTERY	FAILED          	D			A8XR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	16EZ					310R1277				AIRCRAFT EMERGENCY LANDED WITH COMPLETE ELECTRICAL FAILURE, LG EMERGENCY EXTENDED AND LANDED SAFELY.  FOUND BATTERY RELA	Y FAILURE.  UNIT REMOVED 200 AMP FOUND TO BE INCORRECT (PN).  SB MEB99-4 ADDRESS THIS PROBLEM, HAD NOT BEEN COMPLIED WIT	H, CORRECT RELAY 100 AMP PN 0850469-1 (6041H193) INSTALLED, OPS CHECK OK.  (200 AMP RELAY HAD TO HAVE BEEN REPLACED PRIO	R TO 1999 WHEN AC IPC REVERSED BATTERY AND STARTER RELAY PN COMPLIANCE WITH SB WOULD HAVE PREVENTED THIS PROBLEM.  (K)			1	L	7	2 	3O	3	O		3A10    	E8CE				 
2007090600056	20070906	00056	GL  	2007	9	6	2007FA0000733    	3	20070810	G	6114	PHCC3YF1RF	HUB             	HARTZL      		CESSNA	207   	207         	2073602	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	PROPELLER	CRACKED         	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					EE2379A					HUB, NDI SHOWS RELEVANT INDICATION OF CRACK.(K)						1	H	7	1 	3O	3	O		A16CE   	E3SO	5	C	P25EA	 
2007090600050	20070906	00050	CE  	2007	9	6	2007FA0000735    	1	20070809	G	2497	36153	GROUND WIRE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A6       	52043	EA  					GCU	BROKEN          	D				B	A			EMER. DESCENT           	UNSCHED LANDING         			B	G	H	SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   	CR	CRUISE         	1			CE	07	1925P	9715 				BB1094				WIRE NR P73G16N AT RT ENGINE FIREWALL GROUND POINT GS15 SEPARATED FROM THE WIRE TERMINAL DURING CRUISE FLIGHT. THIS WIRE	 CONNECTS GROUND TO THE GCU PIN G. THE RT GENERATOR OUTPUT SPIKED AND OPENED THE 325 AMP RT BUSS CURRENT LIMITER, THE 50	 AMP RT INVERTER CURRENT LIMITER, AND DAMAGED RADIOS, THE GCU AND SYSTEMS WIRED TO THE RT BUSS. UPON INSPECTION, THE INS	ULATION OF P73G16N WAS FOUND STRIPPED TOO FAR FROM THE WIRE END THEREBY GIVING NO SUPPORT OF THE WIRE INTO THE TERMINAL 	AT THE INSULATION CRIMP AREA.		1	L	7	2 	4T	3	T		A24CE   	E4EA				 
2007090600053	20070906	00053	CE  	2007	9	6	2007FA0000736    	1	20070823	G	3246	178K481	TIRE            			LEAR  	60    	60LEAR      	5170707	CE  										LT MLG	DEFLATED        	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	27	903AM					269				NOTIFIED BY FLIGHT CREW LT MAIN LANDING GEAR IB AND OB TIRES SEPARATED FROM WHEELS DURING TAXI.  TIRES DETACHED FROM WHE	EL ASSEMBLIES BUT DID NOT SEPARATED FROM AIRCRAFT.  TIRES WERE NOT BLOWN.  DAMAGED TIRES AND WHEELS ASSEMBLIES WERE REMO	VED.  UPON INSPECTION, NO OTHER DAMAGES NOTED ON LANDING GEAR OR SURROUNDING STRUCTURE.  NO FOD DAMAGE TO AIRCRAFT.  REP	LACED WITH SERVICEABLE WHEELS/TIRES ASSEMBLIES.			2	L	7	2 	4F			RT	A10CE   					 
2007091200003	20070912	00003	NM  	2007	9	12	2007FA0000741    	1	20070828	G	3246	AN535A	BOLT            	PARKERHANFIN		COLUMB	LC41  	LC41550FG400	5150011	NM  										WHEEL ASSY	BROKEN          	B				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			EA	25	1469W	143  	143  		MFG406	41733				ON LANDING PILOT FELT AND HEARD A VIBRATION AND BUMPING SOUND.  REMOVED RT LANDING GEAR FAIRING AND INSPECTED BRAKE ASSY	.  ON THE WHEEL FOUND ONE WHEEL HALF ATTACH BOLT MISSING AND ONE BROKEN AND EXTENDING OUT OF THE WHEEL TO THE EXTENT OF 	CAUSING A GOUGE IN THE BRAKE MASTER CYLINDER AND TORQUE PLATE.  ONE BOLT OUT OF THREE WAS HOLDING THE WHEEL HALVES TOGET	HER.			1	L	7	1 	3O			NT	A00003SE					 
2007090600022	20070906	00022	NE  	2007	9	6	2007FA0000747    	2	20070817	G	7310	3011849	TUBE            			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					LT ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	50AW	15   				LA142	PCE92358			FUEL LEAK NOTED ON SHUTDOWN OF LT ENGINE.  FUEL TUBE P/N 3011849 CRACKED AT CONNECTION TO START CONTROL UNIT.						1	L	7	2 	4T	4	T		A31CE   	E4EA				 
2007090600035	20070906	00035	EA  	2007	9	6	2007FA0000748    	2	20070718	G	7310	3011849	TUBE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					LT ENGINE	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	100CM	5    				31T8020073				FUEL LEAK NOTED ON SHUTDOWN.  FUEL TUBE P/N 3011849 WAS CRACKED AT CONNECTION TO START CONTROL UNIT.						1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2007090600059	20070906	00059	CE  	2007	9	6	2007FA0000749    	1	20070829	G	7810	K99102991	EXHAUST PIPE    			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ENGINE	CRACKED         	B			W99R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	22MG		1900 			4140533				DURING COMPLIANCE WITH AD 2000-01-16 THE TAIL PIPE ON THE RT ENGINE WAS FOUND WITH A 6 INCH CRACK.  THE LAST INSPECTION 	WAS 40 HRS PRIOR.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2007090600012	20070906	00012	NE  	2007	9	6	2007FA0000752    	2	20070725	G	7200		ENGINE          			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LEFT	FAILED          	D				A				UNSCHED LANDING         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			SW	13	71WB					LW127				AIRCRAFT IN CRUISE AT 22,000 WITH ALL ENGINE INDICATIONS NORMAL.  A LOUD NOISE FOLLOWED BY POWER LOSS AND REDLINE ITT ON	 THE LT ENGINE.  THE CT BLADES, ITT PROBES, PT VANE AND PT BLADES ALL MELTED AND WENT THROUGH THE EXHAUST STACKS.  COMPR	ESSOR STATOR AND SPACER RUB.  POSSIBLE COMPRESSOR UNSTACK FAILURE.  THIS IS THE FIRST COMPLETE MELT DOWN FAILURE HAVE EV	ER SEEN AT ALTITUDE.  (K)			1	L	7	2 	3T	4	T		3A20    	E4EA				 
2007090600058	20070906	00058	EU  	2007	9	6	2007FA0000753    	1	20070724	G	2910	704A34412938	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					HYD SYSTEM	LEAKING         	B			PG9R	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			WP	19	170PA					2637				AC HAD HYDRAULIC LIGHT, PILOT PERFORMED A PRECAUTIONARY LANDING AT THE AIRPORT.  UPON INSP FOUND HYDRAULIC LINE FROM PUM	P TO MANIFOLD LEAKING AT THE BOTTOM OF THE SWEDGE FITTING.  HYDRAULIC LINE WAS REPLACED WITH NEW LINE.  HYDRAULIC SYSTEM	 WAS SERVICED, GROUND RUN, AND LEAK CHECK NORMAL.  FLIGHT CONTROL CHECK NORMAL.  AC WAS RETURNED TO SERVICE.  (K)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007090600057	20070906	00057	EA  	2007	9	6	2007FA0000754    	1	20070803	G	2740	604923063	MOTOR           			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					HORIZ STAB TRIM	UNSERVICEABLE   	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	43R					5334				WHILE OPERATING HORIZ STAB TRIM ON CHANNEL NR 2 ONLY THE FOLLOWING OCCURS.  PUSHING BUTTON ON CONTROL WHEELS TO NOSE UP,	 HORIZONTAL ACTUALLY WENT DOWN THEN DISCONNECTED.  REPEATED ATTEMPTS, KEPT TRIMMING TO NOSE DOWN POSITION.  COULD NOT GE	T HORIZONTAL TO TRIM NOSE UP ON JUST CHANNEL NR 2.  ONCE CHANNEL NR 1 WAS ENGAGED HORIZONTAL STAB TRIM WORKED CORRECTLY.	  THIS PART WAS SENT TO THE MFG BY THE PREVIOUS OPERATOR  FOR THIS EXACT PROBLEM.  MFG REPLACED PARTS AND RETURNED IT TO	 SERVICE.  PROBLEM REOCCURRED, UNIT REMOVED AND SENT BACK TO MFG.  (K)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007090600002	20070906	00002	CE  	2007	9	6	2007FA0000755    	1	20070802	G	8011	85070213	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	865SP					172S8124				STARTER WAS INTERMITTENT AND FAILED COMPLETELY.  AVERAGE LIFE FOR THE LAST (2) STARTERS HAS BEEN 115 HRS EACH.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007090600076	20070906	00076	NE  	2007	9	6	2007FA0000758    	2	20070828	G	7314		DRIVE SHAFT     	SUNDSTRANDEM		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUEL PUMP	SHEARED         	D				E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			SO	11	544P		1340 		9489	BB1265	PCE94081			WHILE AT CRUISE FLIGHT, LT ENGINE SHUTDOWN WITHOUT WARNING. LANDED WITHOUT INCIDENT. FOUND HIGH PRESSURE FUEL PUMP SHAFT	 SPLINES SHEARED ON INSIDE OF DRIVE COUPLING RENDERING FUEL PUMP AND FUEL CONTROL INOPERABLE. INSPECTION WOULD NOT BE PO	SSIBLE WITHOUT PUMP REMOVAL AND DISASSEMBLY OF DRIVE COUPLING.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007090600038	20070906	00038	NE  	2007	9	6	2007FA0000759    	2	20070831	G	7220	BRR40289	FAIRING         	RROYCE      		GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					LP FAN	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	73M	3889 				547	11204			DURING INSPECTION OF THE AIR INTAKE ROTATING FAIRING, WE FOUND A CRACK BETWEEN THE MOUNT BOLT HOLE AND THE ADJACENT ALIG	NMENT PIN HOLE.					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2007091700020	20070917	00020	EA  	2007	9	17	2007FA0000760    	2	20070716	G	8550	LW13383	BAFFLE          	LYC         		FOUND 	FBA   	FBA2C1      	3640103	EA  	LYC   	O540  	IO540L1A5   	41532	EA  					OIL SUMP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	796	600  				50	L2947748A			ENGINE OIL SUMP BAFFLE CONTACTED BOTTOM OF OIL SUMP CRACKING BAFFLE SUPPORT ATTACH POINTS AND SHEARING RIVETS ATTACHING 	BAFFLE CENTER REINFORCEMENT.  SHEARED RIVET LODGED IN OIL PRESSURE RELIEF VALVE CAUSING LOSS OF OIL PRESSURE.  ENGINE RE	MOVED FOR OVERHAUL.				1	H	7	1 	3O	3	O	NC	A7EA    	1E4				 
2007091700024	20070917	00024	EA  	2007	9	17	2007FA0000761    	2	20070716	G	8550	LW13383	BAFFLE          			FOUND 	FBA   	FBA2C1      	3640103	EA  	LYC   	O540  	IO540L1A5   	41532	EA  					OIL SUMP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	794	500  				51	L29544548A			ENGINE OIL SUMP BAFFLE CONTACTED BOTTOM OF OIL SUMP CRACKING BAFFLE SUPPORT ATTACH POINTS AND SHEARING RIVETS ATTACHING 	BAFFLE CENTER REINFORCEMENT.					1	H	7	1 	3O	3	O	NC	A7EA    	1E4				 
2007091700025	20070917	00025	GL  	2007	9	17	2007FA0000768    	1	20070804	G	2810		CAP             			AMTR  	SKRAID	SKYRAIDER   	05610GI	GL  	ROTAX 	447   	ROTAX447    	55555	EU  					FUEL TANK	OUT OF ADJUST   	G				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		DE	DESCENT        	1			GL	25	31711	35   				SK1966				AT CONCLUSION OF 2 HOUR FLIGHT, APPROXIMATELY 2 MILES FROM DESTINATION AIRPORT, PILOT REPORTED AN UNCOMMANDED SIGNIFICAN	T POWER REDUCTION.  A PRECAUTIONARY LANDING WAS EXECUTED ON A COUNTY ROAD.  SUBSEQUENT INVESTIGATION FOUND 1.5 GALLON FU	EL IN RT TANK, NONE IN LT TANK.  EVIDENCE OF FUEL SIPHONING FROM RT FUEL CAP.  PILOT STATED WHEN LT FUEL CAP WAS REMOVED	, HISSING NOISE WAS HEARD.  PROBABLE THAT COMBINATION OF SIPHONING RT TANK/CAP AND NO VENTING OF LT TANK/CAP CAUSED A FU	EL IMBALANCE AND INTERRUPTION OF FUEL FLOW TO HEADER TANK/ENGINE, RESULTING REDUCTION OF ENGINE OPERATION.  RECOMMEND AN	Y EXPERIMENTAL AIRCRAFT USING FUEL CAPS WITH THREADED CENTER STEM/(O) RING ASSEMBLY FOR VENTING BE MODIFIED TO INCLUDE A	1	H	7	1 	  	3	I		EXPA1H71	EXPE3I				 
2007091700070	20070917	00070	SW  	2007	9	17	2007FA0000769    	1	20070905	G	5711		SPAR            			BBAVIA	7     	7GCBA       	21101PH	SW  	LYC   	O320  	O320*       	41508	EA  					RT WING	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	9902Y	1480 	9    			7GCBA8				RT WING MAIN SPAR FOUND FRACTURED IB OF STRUT ATTACH. CURRENT AD INADEQUATE TO PREVENT FURTHER FAILURES. THIS AIRCRAFT H	AS LESS THAN 14 HR SINCE LAST ANNUAL INSPECTION..					1	H	7	1 	3O	3	O		A759    	E274				 
2007091700008	20070917	00008	SW  	2007	9	17	2007FA0000770    	1	20070905	G	5711		SPAR            			BBAVIA	7     	7GCBA       	21101PH	SW  										RT WING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	9902Y	1480 	9    			7GCBA8				RT WING MAIN SPAR FOUND FRACTURED IB OF STRUT ATTACH. CURRENT AD INADEQUATE TO PREVENT FURTHER FAILURES. THIS AIRCRAFT H	AS LESS THAN 14 HR SINCE LAST ANNUAL INSPECTION..					1	H	7	1 	3O				A759    					 
2007091700059	20070917	00059	CE  	2007	9	17	2007FA0000772    	1	20070401	G	3210	NAS464P426	BOLT            			CESSNA	320   	320E        	2074514	CE  	CONT  	O520  	TSIO520B    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	RT MLG	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	3424Q					320E0024				AIRCRAFT HAS EXPERIENCED A RT LANDING GEAR FAILURE UPON LANDING.  PRIOR TO THIS INCIDENT, THE LANDING GEAR HAD BEEN CHEC	KED DURING THE AIRCRAFT ANNUAL INSPECTION AND FOUND TO BE OUT OF RIG IAW SERVICE MANUAL D508-3-13 STANDARDS. THE AIRCRAF	T EXPERIENCED A PARTIAL POWER FAILURE UPON THE FIRST FLIGHT AFTER THE AIRCRAFT HAD BEEN RIGGED.  SUSPECT THE LANDING GEA	R WAS NOT LOCKED PROPERLY UPON LANDING ON THE FIRST FLIGHT DUE TO THE PARTIAL ELECTRICAL POWER FAILURE.  UPON THE THIRD 	FLIGHT LANDING, THE RT GEAR COLLAPSED.  PROBABLE CAUSE MAY HAVE BEEN FROM THE FIRST LANDING WHERE GEAR MAY NOT HAVE BEEN	 ALL THE WAY DOWN.  THE BOLT TO THE LANDING GEAR STRUT SHEERED AT THE ATTACH POINT OF THE STRUT, AND ONE ATTACH POINT BR	1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
2007091700023	20070917	00023	CE  	2007	9	17	2007FA0000778    	1	20070906	G	2820	3011849	LINE            			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					FUEL SYS	CRACKED         	B				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			EA	03	50AW	6848 				LA142	PCE92358			FUEL TUBE CRACKED AT BACKSIDE OF B-NUT SLEEVE LOCATION, CAUSING FUEL TO LEAK UNDER PRESSURE INTO ENGINE NACELLE AREA FOR	WARD OF FIREWALL.  TUBE FAILED IN FLIGHT CAUSING INITIAL CHANGES IN FUEL FLOW INDICATIONS TO BE NOTICED.					1	L	7	2 	4T	4	T		A31CE   	E4EA				 
2007091700003	20070917	00003	CE  	2007	9	17	2007FA0000780    	1	20070812	G	2910	AE1011889G0116	LINE            			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE300 	AE3007A     	 	GL  					HYDRAULIC SYS	RUPTURED        	B			CNQ3	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	13	912QS	7516 				7500012				THE NOSE WHEEL STEERING CENTERING FLEXIBLE HYDRAULIC HOSE RUPTURED WHERE THE HOSE BODY IS SWEDGED TO A 45 DEGREE FITTING	 WHICH ATTACHES TO A BULKHEAD FITTING IN THE NOSE WHEEL WELL.  THIS CONDITION ALLOWED THE LOSS OF HYDRAULIC FLUID IN THE	 (A SYSTEM).  AIRCRAFT LANDED WITHOUT INCIDENT.  THIS HOSE IS CURRENTLY CONSTRUCTED OF KEVLAR AND IS BEING REPLACED WITH	 STAINLESS STEEL BRAIDED VERSION ALONG WITH OTHER HOSES WHICH ATTACH TO THE NOSE GEAR.  (K)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007091700069	20070917	00069	SO  	2007	9	17	2007FA0000781    	2	20070810	G	8520		CRANKSHAFT      								CONT  	O520  	GTSIO520L   	17032	SO  					ENGINE	FAILED          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19							A511M2			CRANKSHAFT FAILED NDI SB MSB96-10.  (K)											3	O			E7CE				 
2007091700019	20070917	00019	GL  	2007	9	17	2007FA0000782    	3	20070810	G	6114		HUB             	HARTZL      		CESSNA	207   	207         	2073602	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	PROPELLER	CRACKED         	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					EE2379A			EE2379A		HUB, NDI SHOWS RELEVENT INDICATION OF CRACK. (K)						1	H	7	1 	3O	3	O		A16CE   	E3SO	5	C	P25EA	 
2007091700072	20070917	00072	SO  	2007	9	17	2007FA0000783    	1	20070816	G	2730	62701153	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					ELEVATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	30521					447995076				AFT LOWER ELEVATOR CONTROL CABLE BROKE AT TURN BUCKLE BETWEEN CRIMPED BARREL AND END THREADS.  SENT CABLE ASSY TO NTSB F	OR LAB REPORT.  (K)					1	L	7	2 	3O	3	O		A19S0   	E286				 
2007091700026	20070917	00026	EA  	2007	9	17	2007FA0000784    	2	20070708	G	7322	30804	FLOAT           	PRECISION   		AMTR  	VANS  	RV9A        	05614C3	GL  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	70C	70CM6       	EA  	CARBURETOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	12HE	33   			75992004	91367	L2005739A	38893K		THE ENGINE DIED ON FINAL TO AIRPORT, PUMPED THE THROTTLE, AND THE ENGINE STARTED RUNNING AGAIN, RETARDED THROTTLE, AND T	HE ENGINE DIED AGAIN.  LANDED WITHOUT INCIDENT.  COULD NOT GET THE ENGINE TO RESTART ON THE GROUND.  ENGINE WAS STARTED 	THE NEXT DAY, THE FUEL FLOW WAS SHOWING 11 TO 12 GPH AT IDLE.  REMOVED THE CARBURETOR AND ONE PONTOON OF THE PLASTIC FLO	AT WAS 90 PERCENT FULL OF FUEL.  (K)			1	L	7	1 	3O	3	O	NT	EXPA1L71	E274	5	N	P28NE	 
2007091700034	20070917	00034	CE  	2007	9	17	2007FA0000785    	1	20070807	G	2612	61423473275	SENSOR          			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C752  	NE  	FIRE DETECTION	FAULTY          	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	636B	754  				BC61				AT APPROXIMATELY 1635 LOCAL, IN CLOUDY CONDITIONS, ON A MAINTENANCE TEST FLIGHT, THE NR 1 ENGINE FIRE LIGHT BRIEFLY ILLU	MINATED, THEN EXTINGUISHED.  ALL ENGINE GAUGES INDICATED NORMALLY.  ALREADY IN DESCENT, THROUGH 4,500 FT, AND CONTINUED 	TO A SAFE LANDING.  MAINTENANCE DISCOVERED FAULTY LOWER AFT SENSOR AND REPLACED IT.  (K)				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE	 
2007091700010	20070917	00010	GL  	2007	9	17	2007FA0000786    	1	20070516	G	7160	D4F732612001	AIR BOX         			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	425FP	357  				40FC025				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE.  (K)					1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2007091700067	20070917	00067	GL  	2007	9	17	2007FA0000787    	1	20070521	G	7160	D4F732612001	AIR BOX         			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	422FP	383  				40FC022				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE WHILE IN FLIGHT.  (K)					1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2007091700032	20070917	00032	NE  	2007	9	17	2007FA0000788    	2	20070810	G	7320	8168776007	EEC             			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	FAILED          	B			HDNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911KB					0013	BB0027			EEC CAUSED ENGINE TO DROP FROM FULL POWER TO IDLE IN CRUISE FLIGHT WITH AN ENGINE FAILURE AND ENGINE MANUAL HORN AND LIG	HT.  (K)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2007091700006	20070917	00006	SO  	2007	9	17	2007FA0000789    	2	20070809	G	8520	530196A1	CRANKSHAFT      								CONT  	C85   	C8512       	17008	SO  					ENGINE	DESTROYED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13							21407612			DURING LEVEL FLIGHT THIS AIRCRAFT SUSTAINED LOSS OF PROPELLER.  AIRCRAFT LANDED ON A COUNTY HIGHWAY SATISFACTORILY WITH 	NO DAMAGE OR INJURIES.  INVESTIGATION REVEALED THE ENGINE CRANKSHAFT FAILED IMMEDIATELY AFT OF THE PROPELLER ATTACH POIN	T (THIS CRANKSHAFT HAS A TAPERED SHAFT, NOT A FLANGE).  THE PROPELLER WAS LOCATED AT A LATER TIME BY A HIKER IN A STATE 	PARK.  INSPECTION OF THE ENGINE AND PROPELLER INDICATES THE PROBABILITY THAT THE ENGINE HAD SUSTAINED SUDDEN STOPPAGE AT	 A PRIOR TIME.  THIS MAY HAVE RESULTED IN A MINUTE CRACK/FRACTURE THAT EVENTUALLY PROPAGATED INTO THE TOTAL FAILURE OF T	HIS CRANKSHAFT.  SINCE THERE WAS NO DAMAGE TO THE AIRCRAFT OR OCCUPANTS, THIS SITUATION HAD BEEN DETERMINED TO BE AN INC						3	O			E233				 
2007091700013	20070917	00013	SW  	2007	9	17	2007FA0000790    	1	20070901	G	3610	2784187015	PIPE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					BLEED AIR	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	226AM					TC229				NOTE: AIRCRAFT HAS BEEN PARKED FOR 2 YEARS AFTER BEING DAMAGED IN HURRICANE.  AIRCRAFT WAS BEING DISASSEMBLED FOR SALVAG	E.  IB OF RT NACELLE, BLEED AIR PIPE, PN: 27-84187-015, HAS CHAFED/BURNED THROUGH THE ASBESTOS SLEEVE SURROUNDING THE ST	ARTER RELAY WIRING AND HAS ARCED A HOLE IN THE BLEED PIPE, WHICH THEN ALLOWED BLEED AIR TO MELT THE SHIELDING FROM ONE O	F THE WIRES.  (K)			2	L	7	2 	4T	3	T	RT	A8SW    	E2WE				 
2007091700033	20070917	00033	WP  	2007	9	17	2007FA0000794    	1	20070901	G	5730		SKIN            			DOUG  	DC9   	DC915       	3022036	WP  	PWA   	JT8   	JT8D7       	52053	NE  					WING	DAMAGED         	D				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SO	17	305PA					45740				BIRD STRIKE ON LT LEADING EDGE, CAUSING DEEP DENT AMD A TEAR 5 INCHES VERTICAL AND 4 INCHES HORIZONTAL, FOUND ON POST FL	IGHT INSPECTION. REPAIRED IAW SRM CHAPTER 57-06.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
2007091700036	20070917	00036	CE  	2007	9	17	2007FA0000797    	1	20070809	G	2810	FC100	FUEL CAP        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					FUEL CELL	VENTING         	G				B				EMER. DESCENT           				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			GL	15	58776	40   	40   			18262288				FUEL CAPS WERE INSTALLED ON AIRCRAFT IAW STC SA2376CE AND HAD BEEN IN SERVICE FOR ABOUT 40 HOURS IN A 4 MONTH PERIOD. TH	EY BEGAN VENTING FUEL FROM BOTH TANKS RESULTING IN A FORCED EMERGENCY LANDING DUE TO FUEL STARVATION.					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2007091800102	20070918	00102	EA  	2007	9	18	2007FA0000798    	2	20070603	G	7322	30804	FLOAT           			AMTR  	COZY  	COZYIII     	05605BK	GL  	LYC   	O290  	O290        	41506	EA  					CARBURETOR	SATURATED       	B			JULR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	369CZ	40   				1517				ENGINE FAILED ON SHORT.  FINAL DUE TO CARB: FLOODING FLOAT IN CARB, HALF FULL OF GAS.  (K)						1	M	7	1 	3O	3	O	RT	EXPA1M71	E229				 
2007091700007	20070917	00007	SO  	2007	9	17	2007FA0000799    	1	20070905	G	7820		MUFFLER         			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					EXHAUST	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7066B	36   				185140				ENGINE EXHAUST TAIL PIPE FAILED AT THE MUFFLER WELD.  WITH 36 HOURS TOTAL TIME SINCE NEW.  LEADING EDGE EXHAUST SYSTEM W	AS INSTALLED BY STC SA02200AK.					1	H	7	1 	3O	3	O		1A2     	E274				 
2007091700027	20070917	00027	EU  	2007	9	17	2007FA0000800    	1	20070809	G	3233	485034	ACTUATOR        			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					RT MLG	UNSERVICEABLE   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	919SS					NA0473				RT MLG ACTUATOR CRACKED ATTACH HOUSING DISCOVERED DURING WHEEL WELL INSPECTION, PART WAS NOT LEAKING BUT COULD SEPARATE 	AT ANY MOMENT AND CAUSE SEVERE DAMAGE TO AIRCRAFT DATE OF ASSY OF ACTUATOR 1/92.  (K)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007091700018	20070917	00018	EU  	2007	9	17	2007FA0000801    	1	20070809	G	5343	25FC5801A	SUPPORT         			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					LT MLG	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	919SS	5860 				NA0473				LT MLG DOOR IB AFT SUPPORT REMOVED FOR OTHER MAINTENANCE AND SEVERE INTERGRANULAR CORRODION DISCOVERED FROM LAVATORY LEA	KAGE AS INDICATED BY STAINING ON PART LOCATION WHERE BONDING STRAP ATTACHES.  CORROSION SEVERE AND IS ENOUGH TO CAUSE PA	RT TO FAIL.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007091700074	20070917	00074		2007	9	17	2007FA0000802    	1	20070910	G	3245	6006	TUBE            																	TIRE	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03										6.00 X 6 TIRE TUBES WILL NOT FIT IN 6.00 X 6 WHEEL. STEM APPEARS TO NOT BE IN CENTER AND SIZE OF TUBE IS SMALLER THAN NO	RMAL.  (2) TUBES FOUND TO BE IN THIS CONDITION.  WHEN WE ATTEMPTED TO RETURN THE TUBES TO OUR VENDOR, WOULD NOT ACCEPT A	 RETURN AND THAT THE TUBES WERE NOT DEFECTIVE.																	 
2007091700040	20070917	00040	NM  	2007	9	17	2007FA0000805    	1	20070911	G	2910	82970009325	LINE            			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  					HYDRAULIC SYS	LEAKING         	H				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	99	387BC					351				PILOT NOTED LOSE HYDRAULIC LINE. DECLARED EMERGENCY AND LANDED. NO NOSE WHEEL STEERING ON GROUND.  INSPECTED ALL HYDRAUL	IC LINES AND FITTINGS. NOTED EDP LINE GOING TO PRESSURE MANIFOLD B NUT WAS ABLE TO GET HALF A TURN. SYSTEM SERVICED AND 	FUNCTIONAL CHECKED SERVICEABLE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007091700063	20070917	00063		2007	9	17	2007FA0000809    	1	20070912	G	3220	13022101	TAIL WHEEL      																		WORN            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	912S									TAILWHEEL SPRING P/N 13022.101 SHOWED EVIDENCE OF LOOSENESS AND ELONGATION OF THE FORWARD ATTACH POINT HOLE.  THE ATTACH	 BOLT P/N AN5-22A EXHIBITED SIGNS OF FRETTING WEAR CONTRIBUTING TO THE TAILWHEEL LOOSENESS.  IT WOULD APPEAR THAT THIS C	ONDITION COULD INDUCE A SIGNIFICANT SIDE LOAD ON THE TAILWHEEL SPRING AFT ATTACHMENT CLAMP AND HARDWARE.  THIS CONDITION	 WOULD BE DIFFICULT TO DETECT WITH THE WEIGHT OF THE AIRCRAFT ON THE TAILWHEEL.  IT IS RECOMMENDED THAT THE CONDITION IN	SPECTION INCLUDE SUPPORTING THE FUSELAGE FORWARD OF THE TAILWHEEL SPRING FORWARD ATTACHMENT POINT AND CHECKING THE TAILW	HEEL ASSEMBLY FOR SECURITY AND TIGHTNESS.														 
2007092500184	20070925	00184	CE  	2007	9	25	2007FA0000810    	1	20070731	G	3222		STRUT           			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					NLG	LEAKING         	B			AQHR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	11	5348E					18281212				FOUND NOSE STRUT ASSEMBLY LEAKING.  REMOVED STRUT ASSEMBLY FROM AIRCRAFT.  ASSEMBLED WITH PN TCNS-1 SEAL KIT IWA SRM AND	 MM.  RELEASED TO AC OWNER.  OWNER FOUND FLUID NR 4 ON WHEEL FAIRING AFTER TAXI TO HANGAR.  INSPECTION FOUND FLUID COMIN	G FROM BEHIND NOSE GEAR STEERING ASSEMBLY.  CONTACTED TECH SERVICE, RECOMMENDED THA WE REPLACE THE STRUT TUBE (PN 074309	01).  REMOVED LEAKING STRUT TUBE FROM AIRCRAFT.  INSTALLED NEW 07430901 TUB USED NEW SEAL KIT TCNC-1 AND SERVICED.  INSP	ECTED OLD TUBE FOR DAMAGE.  FOUND THA THE TUBE WAS LEAKING BETWEEN THE INNER TUBE AND THE OUTER-MACHINED PART.  FOUND PI	NHOLE IN BRAZING OF THE PARTS.  (K)	1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007092500181	20070925	00181	NM  	2007	9	25	2007FA0000811    	1	20070906	G	2410	B1731	BELT            			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360C1F     	41514	EA  					ALTERNATOR	BROKEN          	D				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			WP	23	8372G	852  				2782				ALTERNATOR LIGHT CAME ON DURING CRUISE FLIGHT.  FOLLOWED HELICOPTER FLIGHT MANUAL PROCEDURES AND RETURNED TO LANDING.  U	PON INSPECTION IT WAS DISCOVERED THAT THE ALTERNATOR BELT HAD BROKEN AND DEPARTED THE AIRCRAFT IN FLIGHT.  NO OTHER DAMA	GE RESULTED				1	G	7	1 	3O	3	O		H10WE   	E286				 
2007092500249	20070925	00249	SW  	2007	9	25	2007FA0000812    	1	20070919	G	6320	20401077503	QUILL ASSY      			BELL  	204   	UH1H        	1181407	SW  	LYC   	T53   	T53*        	41549	NE  						WORN            	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	3053Q		82   			661104				QUILL INTERNAL SPLINES WORN AND DAMAGED IN QUILL TUBE CONTACT AREA						1	G	7	1 	4U	4	U		EXPA1G71	E1EA				 
2007092500089	20070925	00089	SO  	2007	9	25	2007FA0000813    	1	20070920	G	5712	7847504	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	2702R	6441 				28R35252				CRACKS FOUND DURING INSPECTION.  CRACKS FOUND IN LOWER RELIEF EDGE MADE USE OF REPAIR KIT P/N: 767 - 397 NOT POSSIBLE. T	HE CRACK REQUIRED REPLACEMENT OF ENTIRE RIB ASSY WITH NEW PART 78475-004 (AN IMPROVED PART). HAVE DIGITAL PHOTOS OF THE 	CRACKED RIB, THE CRACKS ARE CAUSED BY FLEXING OF THE SPAR BY THE LANDING GEAR SIDE BRACE DUE TO SIDE LOADS DURING LANDIN	G. IF NO REPLACED I DON'T SEE AN INFLIGHT FAILURE, BUT COULD SEE POSSIBILITY OF LANDING GEAR COLLAPSE.			1	L	7	1 	3O	3	O		2A13    	1E10				 
2007092500110	20070925	00110	SO  	2007	9	25	2007FA0000815    	1	20070920	G	5712	7847504	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	2702R	6441 				28R35252				CRACKS FOUND DURING INSPECTION, CRACKS FOUND IN LOWER RELIEF EDGE MADE USE OF REPAIR KIT P/N: 767 - 397 NOT POSSIBLE. TH	E CRACK REQUIRED REPLACEMENT OF ENTIRE RIB ASSY. WITH NEW MFG PART 78475-004 (AN IMPROVED PART).  HAVE DIGITAL PHOTOS OF	 THE CRACKED RIB, THE CRACKS ARE CAUSED BY FLEXING OF THE SPAR BY THE LANDING GEAR SIDE BRACE DUE TO SIDE LOADS DURING L	ANDING. IF NO REPLACED I DON'T SEE AN INFLIGHT FAILURE, BUT COULD SEE POSSIBILITY OF LANDING GEAR COLLAPSE.			1	L	7	1 	3O	3	O		2A13    	1E10				 
2007092500142	20070925	00142	SO  	2007	9	25	2007FA0000816    	1	20070917	G	3810	91000106	SOCKET          			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  						BURNED          	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			GL	15	23M	3606 				579				THE SOCKET ON ONE OF THE (2) LAMPS BURNED CAUSING AN ELECTRICAL ODOR IN THE BAG BIN WHERE THE STERILIZER IS LOCATED.  TH	E 2 AMP CIRCUIT BREAKER WHICH CONTROLS THE POWER TO THE STERILIZER DID NOT POP.					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2007092500145	20070925	00145	CE  	2007	9	25	2007FA0000817    	1	20070917	G	2434	DOFF10300B	ALTERNATOR      			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  						FAILED          	D				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			SW	15	732YK		458  			21061879				OVERHAULED DOFF10300B ALTERNATOR FAILED AFTER 458 HOURS IN 35 MONTHS OF USE.						1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007092500163	20070925	00163	SO  	2007	9	25	2007FA0000818    	2	20070919	G	8530	639614639615	ROCKER          			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					VALVE ROCKER	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	4960R		287  			17256296	025668R			ROCKER COVERS REMOVED DURING 100 HOUR INSPECTION TO INSPECT INTAKE AND EXHAUST ROCKERS FOR CORRECT INSTALLATION. FOUND N	R1 AND NR6 CYLINDERS HAD INTAKE ROCKER (P/N 639614) INSTALLED IN THE EXHAUST VALVE POSITION. PARTS MANUAL CALLS FOR P/N 	639615 ROCKER TO BE INSTALLED IN EXHAUST VALVE POSITION. THIS IS THE SECOND ENGINE DISCOVERED WITH THE SAME ABNORMALITY 	AFTER RECENT OVERHAULS FROM SAME OVERHAUL FACILITY.			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2007092500170	20070925	00170	EA  	2007	9	25	2007FA0000819    	2	20070924	G	7414	LW14227	BEARING         	LYC         		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					MAGNETO	DESTROYED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5147L	857  	857  			284432	L3421136A			BEARING LW14227 CAGE DESTROYED AND APPROXIMATELY 50 PERCENT MISSING.  THIS IS THE ENGINE SIDE BEARING OF THE LW15416 MAG	NETO DRIVE ADAPTER (MAGNETO ISOLATION DRIVE FOR RT MAGNETO)ENGINE HAS 857 HOURS SINCE FACTORY OVERHAUL IN 2000.					1	L	7	1 	3O	3	O		2A13    	E286				 
2007092500171	20070925	00171	EA  	2007	9	25	2007FA0000820    	2	20070924	G	8540	LW14227	BEARING         			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					ENGINE	DESTROYED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5147L	857  	857  			284432	L3421136A			BEARING LW14227 CAGE DESTROYED AND APPROXIMATELY 50 PERCENT MISSING.  THIS IS THE ENGINE SIDE BEARING OF THE LW15416 MAG	NETO DRIVE ADAPTER (MAGNETO ISOLATION DRIVE FOR RIGHT HAND MAGNETO).  ENGINE HAS 857 HOURS SINCE FACTORY OVERHAUL IN 200	0.				1	L	7	1 	3O	3	O		2A13    	E286				 
2007092500250	20070925	00250	CE  	2007	9	25	2007FA0000822    	1	20070904	G	3210	AN39227	PIN             			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					MLG	SHEARED         	G				A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			GL	13	998PL	848  	100  			E3036				THE LOWER IB BUSHING ON THE LOWER TORQUE LINK KNEE WAS DRY AND THE PIVOT PIN WHICH RIDES IN THE BUSHING WAS VERY TIGHT P	OSSIBLY DUE TO A PLUGGED GREASE ZERK FITTING. THIS APPARENTLY CAUSED THE CLEVIS RETAINING PIN TO SHEAR (AS EVIDENCED BY 	THE SHEAR MARKS ON THE REMAINING PORTION OF THE PIN), THE PIVOT PIN TO FALL OUT AND THE GEAR TO EXTEND TO THE POINT WHER	E IT WAS ONLY BEING HELD BY THE BRAKE LINE. ONCE THE AIRCRAFT TOUCHED DOWN THE UNRESTRAINED WHEEL ASSEMBLY TURNED AND WA	S TORN FROM THE REST OF THE GEAR.		1	L	7	1 	3O	3	O		3A15    	E3SO				 
2007100200050	20071002	00050	EA  	2007	10	2	2007FA0000823    	2	20070824	G	7414	M3548	ROTOR           			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					SHAFT	FAILED          	C			E92R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	733XN	367  			05120929	17268632				PILOT DEPARTED ON A VFR, DAY FLIGHT.  DURING THE CLIMB FROM DEPARTURE, THE PILOT NOTICED A SLIGHT ENGINE ROUGHNESS THAT 	LASTED ONLY A SECOND.  THE ENGINE SMOOTHED OUT UNTIL THE AC WAS LEVELED OUT AT CRUISE ALTITUDE AND CRUISE POWER SETTINGS	 THE ENGINE BEGAN RUNNING ROUGH.  THE PILOT PERFORMED A MAGNETO CHECK IN FLIGHT FINDING THE RT MAGNETO INOPERATIVE.  THE	 PILOT SWITCHED TO LT MAGNETO AND RETURNED TO LAND AT DEPARTURE WITHOUT INCIDENT.  UPON OPENING THE MAGNETO, THE ROTO GE	AR PN M3827 AND THE GEAR IN THE DISTRIBUTOR BLOCK ASSY PN K3822 WERE NOT DAMAGED AND WERE FREE OF OBSTRUCTION AND MOVED 	WITHOUT BINDING.  THE SHAFT BROKE JUST BELOW THE SLOT IN THE SHAFT THAT HOLDS THE CAM WHICH OPENS THE CONTACTS.  THERE D	1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2007100200052	20071002	00052	CE  	2007	10	2	2007FA0000824    	1	20070826	G	5343	05430161	FITTING         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					NLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	97873	11305				17276236				AC WAS BEING TAXIED FROM THE RAMP TO THE TAXIWAY, AND DURING TAXI, THE PILOTS REPORTED THAT THE NOSE GEAR STEERING SEEME	D TO BE MALFUNCTIONING.  UPON INSPECTION, THE NOSE GEAR STRUT APPEARED TO BE PRESSED UP AGAINST THE REAR HALF OF THE LOW	ER COWLING.  THE LOWER NOSE GEAR FITTING (PN 0543016-1) WAS INSPECTED AND FOUND TO BE CRACKED COMPLETELY OFF ON THE RT S	IDE.  THE LT SIDE OF THE NOSE GEAR FITTING WAS STILL INTACT.  THE CAP PN 05430181 WHICH CLAPS THE NOSE GEAR STRUT TO THE	 LOWER NOSE GEAR FITTING WAS FOUND TO BE MISSING FROM THE AIRCRAFT.  THE HARDWARE WHICH ATTACHED THE LT SIDE OF THE CAP 	TO THE LOWER NOSE GEAR FITTING WAS FOUND TO BE MISSING ALONG WITH THE CAP.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007100200058	20071002	00058	SO  	2007	10	2	2007FA0000825    	2	20070821	G	7314	64936849A1	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FUEL SYSTEM	FAILED          	C			B4VS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	708DC					C0408	650211	AG9712		THE MIXTURE CONTROL SHAFT ON THE ENGINE DRIVEN FUEL PUMP FROZE UP AT HALF TRAVEL BETWEEN FULL RICH AND IDLE CUT OFF.  TH	IS CREATED A LEAN MIXTURE CONTROL WAS DISCONNECTED FROM THE FUEL PUMP, THEN THE FUEL PUMP CONTROL SHAFT HAD TO BE FREED 	UP.  THE MIXTURE CABLE WAS COMPLETELY FREE WITH NO BINDING ONCE DISCONNECTED FRO THE FUEL PUMP.  THE FUEL PUMP WAS REPLA	CED AND SENT BACK TO MFG.  (K)			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007100200086	20071002	00086	CE  	2007	10	2	2007FA0000826    	1	20070808	G	2731	NAS302261510	CONTROL CABLE   			BEECH 	300   	300BEECH    	1152930	CE  										ELEVATOR TRIM	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	122RG	389  				FL448				DURING SCHEDULED INSPECTION OF THE AC, THE MECHANIC FOUND THE LT ELEVATOR PITCH TRIM CONTROL CABLE CHAFING ON THE ELEVAT	OR CABLE PASS THROUGH HOLE LOCATED IN SKIN PN 101-620000-3.  THE ELEVATOR CABLE PASS THROUGH HOLE REQUIRED TRIMMING TO A	LLOW PROPER CLEARANCE.  ADJUSTMENTS TO PASS THROUGH HOLE ACCOMPLISHED IAW IAW MFG.  (K)				2	L	7	2 	4T				A24CE   					 
2007100200087	20071002	00087	CE  	2007	10	2	2007FA0000827    	1	20070814	G	7500	4536102150V431	MANIFOLD        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	DAMAGED         	B			KKQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	858MK	2402 				141				LT PYLON OVERHEAT INDICATION OCCURRED IN FLIGHT.  FOUND HIGH PRESSURE BLEED AIR MANIFOLD MATING FLANGE DEFORMED.  REPLAC	ED ASSY 4536102150V43-1 WITH NAV ASSY 45361020228-001.  CAUSE MAY BE AGE OR REPEATED CLAMPING.  ORIGINAL PART HAS BEEN S	UPERSEDED BY THE MFG.  (K)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007100300004	20071003	00004	SO  	2007	10	3	2007FA0000828    	2	20070906	G	8530	SA52000A20P	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 2	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	4891Z	1790 				U20606044	818885R			CYLINDER HEAD HAS A CRACK.  BEGINNING AT INTAKE PORT AND EXTENDING TO UPPER SPARK PLUG HOLE.  (K)						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007100200090	20071002	00090	WP  	2007	10	2	2007FA0000829    	1	20070831	G	6720	369D21800501	CONTROL SYSTEM  			HUGHES	369   	369D        	4470706	WP  										T/R PITCH	ROUGH           	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	C6DCM		1181 							DURING 100 HR INSPECTION, PLAY WAS NOTICED BETWEEN THE ROTATING AND NOT-ROTATING SWASH PLATES OF THE TAIL ROTOR PITCH CO	NTROL AFTER REMOVAL, IT WAS NOTED THAT THE BEARING WAS DRY AND ROUGH.  RECORDS INDICATE IT WAS REGREASED IN DEC OF 2006.	  (K)				1	G	7	1 	3U				H3WE    					 
2007100300006	20071003	00006	CE  	2007	10	3	2007FA0000830    	1	20070912	G	5755		COVER           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					SPOILER MIXER	CORRODED        	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	156DH					RK36				WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND SPOILER MIXER ASSEMBLY BOX COVER NOT SEALED.  REMOVED COVER AND FOUND 	CORROSION ON ACTUATOR AND MIXER ASSEMBLY.  RECOMMEND THAT THE SPOILER MIXER AREA BE INSPECTED THOROUGHLY THE BOX COVER R	EMOVED.  INSTALLED THE BOX COVER WITH THE APPROPRIATE SEALANT.  (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007100300007	20071003	00007	CE  	2007	10	3	2007FA0000831    	1	20070912	G	2120	45A63517073	AIR DUCT        			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BLEED AIR	CRACKED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	156DH					RK36				WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND THE LEFT AFT FUSELAGE BLEED AIR LINE BELLOWS BLOWN APART PN 45A63517-0	73 AND THE RT AFT FUSELAGE BLEED AIR LINE BELLOWS BRAIDING FRAYING PN 45A63517-075.  WHEN THE LT BLEED AIR LINE BLEW APA	RT IT CRACKED A FUSELAGE BULKHEAD AT UPPER FRAME STATION 329.92 AND BP 29.92L.  WOULD RECOMMEND THAT DETAILED INSPECTION	S OF THESE BLEED AIR LINES BE PERFORMED AT SCHEDULED INTERVALS AND THE UPPER FRAME STATION IN THE AREA AROUND THE BLEED 	AIR LINES BE CAREFULLY INSPECTED FOR DAMAGE.  IT IS SUSPECTED THAT BOTH THE BLEED AIR LINES FAILED DUE TO FATIGUE OR TIM	E IN SERVICE.  (K)	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007100300008	20071003	00008	CE  	2007	10	3	2007FA0000832    	1	20070912	G	5610	45AS3101012	WINDOW          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					COPILOT	CRACKED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	141DR					RK184				WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND COPILOT COCKPIT SIDE WINDOW CRACKED USING THE PRISM INSPECTION METHOD.	  THE D-INSPECTION REQUIRES THAT BOTH WINDSHIELDS BE INSPECTED BY REMOVING THE WINDSHIELD RETAINERS OR USING OPTICAL PRI	SM INSPECTION METHOD.  THERE IS NO STATEMENT IN THE AC MM OR IN THE A-D INSPECTION CHECKLIST THAT REQURIES YOU TO INSPEC	T THE COCKPIT SIDE WINDOWS IN THE SAME MANNER AS THE WINDSHIELDS.  ALL OF THE WINDOWS IN THE COCKPIT AREA ARE INSTALLED 	OR FASTENED IN THE SAME MANNER AS THE WINDSHIELDS.  IT IS SUSPECTED THAT THE COPILOT SIDE WINDOW CRACKED FROM FATIGUE, O	R TOTAL TIME INSTALLED.  THE WINDOW WAS MFG MAY OF 1997.  WOULD RECOMMEND THAT INSPECTION OF ALL COCKPIT WINDOWS WITH A 	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007100300010	20071003	00010	CE  	2007	10	3	2007FA0000833    	1	20070912	G	5510		STRUCTURE       			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	DAMAGED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	141DR					RK184				WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND 6 SHEARED RIVETS AND 2 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE A	TTACHMENT PIVOT FITTING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER.  IT IS SUSPECTED THAT THE MISSING RIV	ETS FAILED FROM FATIGUE.  RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION, CONTACTING MFG FOR REPAIR OPTIONS.  T	HIS IS SECOND AC THAT THE SAME DISCREPANCY HAS BEEN FOUND.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007100300011	20071003	00011	CE  	2007	10	3	2007FA0000834    	1	20070912	G	5510		STRUCTURE       			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	DAMAGED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	156DH					RK36				WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND 8 SHEARED RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FIT	TING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER.  IT IS SUSPECTED THAT THE MISSING RIVETS FAILED FROM FAT	IGUE.  RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION.  (K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007100300012	20071003	00012	CE  	2007	10	3	2007FA0000835    	1	20070802	G	2760	3321209	ADJUSTER        	LEAR        		LEAR  	25    	25D         	5170514	CE  										BRAKE VALVE	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09					9711105					UPON VISUAL INSPECTION OF THE POWER BRAKE VALVE PN 60810741-804, SN 9711105, IT WAS FOUND THAT THE ADJUSTMENT SCREW HAD 	BEEN GROUND DOWN AND MODIFIED.  AS WE BEGAN TO LOOK THROUGH SB 23/24/25-32-12 AND FOUND THAT  THIS UNIT PN WAS NOT IN TH	IS SB.  WE THEN FOUND THAT THIS UNIT WAS FOR A LEAR 60.  WE THEN LOOKED INTO THE MFG PARTS BREAKDOWN AND FOUND THAT THE 	LEVER AS WELL AS THE MODIFIED ADJUSTMENT SCREW, THE STOP SCREW AND PIN DID NOT BELONG ON THIS PN OF POWER BRAKE VALVE.  	THISE PARTS ARE FOR A PN 2380002 OR PN 2381443 OR PN 3321200-3 POWER BRAKE VALVE.  WE CONTACTED OUR CUSTOMER AND FOUND T	HAT THIS UNIT WAS REMOVED FROM LEAR 25D.	2	L	7	2 	4J				A10CE   					 
2007100300013	20071003	00013	CE  	2007	10	3	2007FA0000836    	1	20070806	G	3411		STATIC SYSTEM   			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  						MISINSTALLED    	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	09	621RB					211				THIS RVSM AIRCRAFT HAD AN ALTIMETRY SYSTEM SPLIT.  CONTACTED STC GROUP HOLDER FOR PROPER ROUTING OF STATIC SYSTEM PLUMBI	NG.  FOUND CO-PILOTS SYSTEM WAS NOT CROSS COUPLED WITH PILOTS SYSTEM.  INSTALLED FABRICATED HOSES TO THE CO-PILOTS SYSTE	M TO MEET STC NR ST 00563DE-D.  PROBABLE CAUSE: CO-PILOTS STATIC SYS NOT CROSS-COUPLED AT STC INSTALLATION OR SYSTEM WAS	 MODIFIED/ ALTERED POST-STC WITHOUT APPROVED DATA.  (K)			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007100300014	20071003	00014	NE  	2007	10	3	2007FA0000837    	2	20070822	G	7230		BLADE           			BOEING	737   	737800*     	       	NM  	CFMINT	CFM56 	CFM567B26US 	 	NE  					HPC	DAMAGED         	B			QEMY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	EIDCN				XAEF2436		892123			ENGINE SURGED ON WING AND WAS INDUCTED INTO SHOP FOR I/V.  DURING STRIP IT WAS NOTED THAT 1 OFF HPC STAGE 3 BLADE HAD BE	EN LIBERATED TOGETHER WITH A SECTION OF THE DOVETAIL FROM THE STG 3 DISK.  SECONDARY DAMAGE WAS ALSO NOTED ON THE HPC RO	TOR AND STATORS.  INSPECTION OF THE FRONT STATOR CASES REVEALED THAT A VSV STAGE 3 LEVER ARM WAS MISSING AND APPEARED NO	T TO HAVE INSTALLED.  NB ESN 892123 INPUTTED AS 1ST SV SINCE NEW.  (K)			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007100300015	20071003	00015	GL  	2007	10	3	2007FA0000838    	2	20070815	G	7230	6898607	BEARING         			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C20      	03013	GL  					NR 1	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	411HV					0040A	CAE845096			PILOT REPORTED CHIP LIGHT CAME ON DURING TRAINING FLIGHT.  LANDED AS SOON AS POSSIBLE AND PROBE REMOVED AND CLEANED.  GR	OUND RUN MADE IAW MM AND CHIP PULLED AND INSPECTED.  MORE METAL FOUND SO ENGINE REMOVED FROM AC AND INSPECTED.  FOUND NR	 1 BEARING OF COMPRESSOR ASSY FAILING.  NO EVIDENCE OF OVERHEATING OR OIL STARVATION.  PILOT REPORTED NO LOSS OF OIL PRE	SSURE DURING FLIGHT.  (K)			1	G	7	1 	3U	3	U	0	4H12    	E4CE				 
2007100300018	20071003	00018	SO  	2007	10	3	2007FA0000840    	2	20070818	G	7322	1048931	CARBURETOR      			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	2347R					18255447	1316145R			PILOT REPORTED THAT AFTER A NORMAL START, HE WAS UNABLE TO ADVANCE THE THROTTLE CONTROL TO CRUISE OR TAKEOFF POWER.  A P	ARTIAL DISASSEMBLY OF THE CARBURETOR REVEALED THAT THE AIR METERING PIN/AIR METERING JET WAS BLOCKING THE THROTTLE SHAFT	 TRAVEL.  THE CARBURETOR WAS SENT FOR REPAIR.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007100300019	20071003	00019	EA  	2007	10	3	2007FA0000841    	2	20070818	G	8530	AEL65102	CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 4	FAILED          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			GL	13	9815L					17276618				DURING CRUISE FLIGHT, THE PILOT REPORTED A LOUD BANG FOLLOWED BY EXCESSIVE VIBRATION, INCREASED POWER TO FULL TO MAINTAI	N ALTITUDE AND MADE A WELL-EXECUTED,, PRECAUTIONARY LANDING.  AFTER SHUTDOWN THERE WAS A LARGE OIL PUDDLE DEVELOPING UND	ER THE AIRCRAFT.  AIRPLANE COWL REMOVED AND NR 4 CYLINDER WAS FOUND TO HAVE THE TOP HALF SEPARATED FROM THE BOTTOM.  THI	S CYLINDER REPORTED TO BE IN SERVICE LESS THAN A YEAR.  THE CYLINDER HAS THE CASTING NR AEL85099 WHICH IS NOT SUBJECT TO	 AD2006-12-07 OR SB NR 05-8.  ENGINE HAS (3) OTHER CYLINDERS WITH THE SAME CASTING NUMBER INSTALLED.  IT IS ESTIMATED TH	AT ENGINE LOST 2.5 QUARTS OF OIL DURING THE FEW MINUTES BETWEEN THE SEPARATION AND THE SHUTDOWN.  MECHANIC SUGGEST FAA L	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007100300020	20071003	00020	SO  	2007	10	3	2007FA0000842    	2	20070907	G	8530	654375	ROCKER SHAFT    								CONT  	O200  	O200*       	17020	SO  					CYLINDER	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	977CC						256314			IAW OWNERS REQUEST, REMOVED ALL (4) ROCKER COVERS TO INSPECT THE ROCKER SHAFT AND SET SCREWS.  AFTER REMOVING THE ROCKER	 COVERS. FOUND ALL(4) SET SCREWS LOOSE AND ALL (4) SHAFTS MOVED TOWARD THE INTAKE SIDE OF THE BOSSES.  NONE HAVE CUT THE	 ROCKER COVERS YET, IN ANOTHER 20 HOURS OR SO THEY WOULD.  NOTE: THE NEW ENGINE HAVE A FLAT CUT INTO THE ROCKER SHAFT, A	ND A SET SCREW IN THE CENTER BOSS, TO RETAIN THE SHAFT.  ALSO, THE SHAFT IS SHARP ON THE END, UNLIKE THE OLD STYLE, AND 	HAVE A CUT MARK ACROSS THE END OF THE SHAFT FOR USE IN ALINING THE FLAT FOR THE SET SCREW.  THE SET SCREW IS A MS51963-6	4, AND USES NO LOCKTITE, OR MECHANICAL TYPE LOCK.  THE FLAT IN THE ROCKER SHAFT IS NOT DEEP ENOUGH TO PROVIDE ADEQUATE L						3	O			E252				 
2007100300022	20071003	00022	GL  	2007	10	3	2007FA0000844    	1	20070813	G	2731	700232	CABLE           			WACO  	YMF   	YMFF5C      	9600425	GL  	JACOBS	R755  	R7557       	35003	EA  	HAMSTD	2B	2B20        	NE  	PITCH SERVO	INOPERATIVE     	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	919TT					F5C111	22353	31606		THE PITCH SERVO BRIDLE CABLE WAS FOUND TO BE LOOSE AND NOT CONNECTED TO THE CAPSTAN.  IT WAS WOUND BETWEEN THE BOTTOM EN	D OF THE CAPSTAN AND THE CAPSTAN END PLATE WITH THE CLAMP TO THE ELEVATOR CABLE HAVING BEEN SLIDING ON THE ELEVATOR CABL	E.  THE ELEVATOR WAS FOUND TO BE FREE TO MOVE NORMALLY IT IS NOT KNOWN HOW THIS MALFUNCTION OCCURRED.  IT IS POSSIBLE TH	AT THE BRIDLE CABLE CLAMP WAS NOT SUFFICIENTLY TIGHT ALLOWING THE BRIDLE CABLE TO BECOME SLACK AND COMING LOOSE IN THE C	APSTAN.  (K)		1	Q	7	1 	3R	3	R		ATC542  	5E11	5	C	P255	 
2007100300023	20071003	00023	SO  	2007	10	3	2007FA0000845    	2	20070817	G	7414	6314	MAGNETO         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					ENGINE	ARCED           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	814RA	444  				1663	FP4677			DURING ANNUAL INSPECTIO, 500 HR MAG INSP COMPLIED WITH EARLY DUE TO NR OF HOURS PREVIOUSLY FLOWN.  BOTH MAGNETOS SHOWED 	SAME INTERNAL ARCING, SO SEVERE, THAT BRUSH HOLDER PN K3823 WAS MELTED/ BURNED UP, CONTACTED SLICK TECH SUPPORT 904-739-	4360, OUR MAG S/N`S WERE MATCHED TO PROBLEM MAGS WHICH SLICK WAS AWARE OF CARBON USED IN MFG OF BRUSHES TOO SOFT, CARBON	 DUST CAUSED ARCING.  IT IS A WONDER THIS CUSTOMERS ENGINE CONTINUED TO RUN.  (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2007100300026	20071003	00026	CE  	2007	10	3	2007FA0000846    	1	20070913	G	5520	05341221	HORN            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ELEVATOR	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	672EB	1827 				172S8672				ELEVATOR HORN BEARING LOOSE IN BORE OF HORN, PN 0534122-1, BEARING ITSELF IS NOT WORN OUT BUT THERE IS PLAY BETWEEN THE 	TWO PARTS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007100300017	20071003	00017	GL  	2007	10	3	2007FA0000849    	1	20070926	G	5350	18583002	FAIRING         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					RT WING ROOT	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	21	631SR	200  	200  			2442				LOWER SECTION OF RT WING ROOT FAIRING SEPARATED FROM AIRCRAFT IN FLIGHT.  FAIRING IS RETAINED WITH JUST A FEW SCREWS AND	 AN AREA OF THE LOWER PORTION OF FAIRING IS RETAINED WITH DOUBLE SIDED TAPE AND AN AREA OF DOUBLE SIDED TAPE CAME DEBOND	ED AND AIR GOT UNDER IT AND IT RIPED OFF.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007100300025	20071003	00025	CE  	2007	10	3	2007FA0000850    	1	20070927	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			SW	99		12033	280  				PCE85195			WHILE PERFORMING SCHEDULED MAINTENANCE, REMOVED RT EXHAUST STACKS TO FACILITATE INSPECTING THE EXHAUST DUCT.  FOUND A 1 	INCH CRACK IN THE SKI SLOPE.  SB 3380 WAS COMPLIED WITH 711 HOURS EARLIER.  POWER SECTION WAS PULLED AND SENT OFF FOR RE	PAIR.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007101100208	20071011	00208	CE  	2007	10	11	2007FA0000851    	1	20071001	G	3250	S11073	ROD END         			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470*       	17026	SO  					MLG	BROKEN          	G				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	15	2145G					51445				ROD END AT STEERING COLLAR SHEARED CAUSING LOSS OF DIRECTIONAL CONTROL.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2007101100211	20071011	00211	NE  	2007	10	11	2007FA0000852    	3	20070924	G	6114	MS24665134	COTTER PIN      			RKWELL	OV10  	OV10A       	6402512	GL  						HAMSTD	33LF	33LF        	NE  	PROP SPINNER	MISSING         	G				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	614V					33813				SPINNER WAS LOST FROM RT ENGINE WHILE IN A RT TURN AT 7000 FT DAMAGING ONE PROPELLER BLADE. SPINNER NOT RECOVERED.						1	H	7	2 	4T			RT	EXPX1H72		5	C	P20EA	 
2007101100220	20071011	00220	CE  	2007	10	11	2007FA0000853    	1	20070920	G	7810	310103901	FLANGE          			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A135     	52043	NE  					EXHAUST	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	90XS					LW342				(2) NEW ENGINES WERE INSTALLED IAW MFG MODIFICATIONS, WITH 938.0 HRS SINCE NEW.  AIRCRAFT WAS IN FOR A PHASE INSPECTION 	AND FOUND 3 OUT OF L1 EXHAUST FLANGES ON THE ENGINE CRACKED.  ACCORDING TO THE MFG PARTS MANUAL, EXHAUST STIFFENERS ARE 	NOT USED ON THIS SN AC AND ARE NOT USED WITH MFG INSTALLATION INSTRUCTIONS.  (K)				1	L	7	2 	3T	4	T		3A20    	E4EA				 
2007101500227	20071015	00227	CE  	2007	10	15	2007FA0000854    	1	20070809	G	7810	40B22318	EXHAUST STACK   			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	ENGINE	LOOSE           	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	168JS	98   				T20608735	L1266161E			DURING AN INSPECTION, FOUND THE EXHAUST STACK AT NR 2 CYLINDER, PULLED DOWN .0625 INCH APPROX.  FURTHER INVESTIGATION FO	UND THE NR1, NR3, NR5 AND NR 6 ENGINE CYLINDERS EXHAUST STACKS PULLED DOWN, BUT NOT AS MUCH.  AFTER RECOMMENDATIONS FROM	 ENGINE MFG ALSO, THE SUPPLIER EXHAUST SYSTEM (WHICH IS ONE IN THE SAME).  DURING THE ENGINE CYLINDER REMOVAL PROCESS FO	UND LOWER FWD, .7500 INCH STUD NUT UNDER TORQUED.  FURTHER INVESTIGATION REVEALED THE FORWARD 2 STUDS BOTH BELOW, MFG RE	COMMENDED DRIVING TORQUE OF CYLINDER HOLDDOWN STUDS IN CASE.  INSTALLED NEW OVERSIZE (.003) STUDS IAW ENG MFG RECOMMENDA	TIONS.  INSTALLED NEW NR 2 ENGINE CYLINDER AND NEW EXHAUST CROSSOVER PIPE AS REQUIRED.  TIGHTENING THE EXHAUST FLANGE NU	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P58GL	 
2007101500229	20071015	00229	GL  	2007	10	15	2007FA0000855    	2	20070906	G	7320	23072790	FADEC           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  						FAILED          	B			VK1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	509PD	350  				53703	CAE847760			AIRCRAFT WAS STARTED IN A NORMAL MANNER.  JUST PRIOR TO LIFT OFF THE (FADEC FAIL), (AUTO RELIGHT) WARNING LIGHTS ILLUMIN	ATED AND THE FADEC FAIL HORN SOUNDED.  NO LIMITATIONS WERE RECORDED OR OBSERVED.  THE FADEC CONTROL ASSY WAS RETURNED TO	 MFG FOR ANALYSIS.  (K)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2007101500233	20071015	00233		2007	10	15	2007FA0000856    	4	20070911	G	3457	066011480102	RECEIVER        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					GPS	SMOKE           	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			GL	25	24MG		1664 			208B0850				SHORTLY AFTER TAKEOFF FROM ISP THE PILOT NOTICED SMOKE IN THE COCKPIT.  THE PILOT IMMEDIATELY RETURNED TO DEPARTURE AND 	LANDED.  THE PILOT REPORTED THAT THE SMOKE APPEARED TO BE CAUSED BY AN ELECTRICAL PROBLEM.  THE PILOT REPORTED THAT THE 	GPS NO LONGER OPERATED.  ON 9/12/2007, MECHANIC INSPECTED THE AIRCRAFT, REMOVED THE GPS AND FOUND THAT IT SMELLED OF ELE	CTRICAL SMOKE, THE MECHANIC EXAMINED THE RADIO RACK, WIRING HARNESSES AND ENTIRE INSTRUMENT PANEL AREA AND FOUND NO PROB	LEM.  THE ENGINE COMPARTMENT AND ELECTRICAL EQUIPMENT BOX WERE INSPECTED WITH NO PROBLEMS FOUND.  THE AIRCRAFT WAS GROUN	D RUN AND ALL ELECTRICAL EQUIPMENT WAS OPERATIONAL TESTED WITH THE GPS UNIT REMOVED AND ALL OPERATED NORMALLY.  THE GPS 	1	H	7	1 	3T	3	T		A37CE   	E2NE				 
2007102300058	20071023	00058	CE  	2007	10	23	2007FA0000858    	1	20070427	G	5711	1369	SPAR            			BBAVIA	11    	11CC        	9140404	CE  	CONT  	C85   	C85*        	17008	SO  					RT WNG	DETERIORATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	4546E					11CC249				REPORT IAW AD 200-25-02R1 PARAGRAPH D (4) LOOSE, MISSING AND RUSTED NAILS IN RIBS ALLOWING RUSTY MOISTURE INTO SPAR, FRE	TTING ON TOP CAP GREATER THAN .0625 INCH ON LOOSE RIBS, CRACKS AT AILERON BELLCRANK BRACKET, CAUSED FROM OVER TORQUING O	F BOLTS, PREVIOUS WING TIP DAMAGE, LOGS MISSING HISTORY, SPARS REPLACED.  (K)				1	H	7	1 	3O	3	O		A796    	E233				 
2007101600001	20071016	00001	SW  	2007	10	16	2007FA0000859    	1	20070726	G	5711	5146R	SPAR            			BBAVIA	7     	7FC         	2110124	SW  	CONT  	C90   	C90*        	17009	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	06	9032B	3177 				7FC123				AC WAS BEING MODIFIED TO INCLUDE THE INSTALLATION OF WING SPAR INSPECTION HOLE KIT IAW STC NR SA005278E.  A PORTION OF T	HE WING LEADING EDGE SKIN WAS REMOVED AND THE WING SPAR WAS VISUALLY INSPECTED AS SPECIFIED IN THE INSTALLATION INSTRUCT	IONS SUPPLIED WITH THE STC.  DURING THIS VISUAL INSPECTION, A CRACK WAS OBSERVED ON THE TOP SURFACE OF THE RT WING FRONT	 SPAR.  THE CRACK ORIGINATES AT THE IB AND OF THE AFT PLYWOOD REINFORCEMENT PLATE.  REINFORCEMENT PLATE IS LOCATED ON TH	E AFT SIDE OF THE FRONT SPAR, UNDER THE LT STRUT ATTACHMENT FITTING.  THE CRACK PROGRESSES OB ALONG THE TOP SURFACE OF T	HE SPAR AT A SLIGHT FORWARD ANGLE (CRACK ANGLE TOWARD THE FORWARD PLYWOOD REINFORCEMENT PLATE).  THE SURFACE OF THE CRAC	1	H	7	1 	3O	3	O		A759    	E252				 
2007101600002	20071016	00002	SO  	2007	10	16	2007FA0000860    	1	20070815	G	3297		CONNECTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					NLG STEERING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	11	509QS	6740 				637				EXCESSIVE CORROSION AT CONNECTOR PINS CAUSING NWS FAIL MSG.  SUGGEST PERIODIC INSPECTION AND CLEANING OR IMPROVED CONNEC	TOR SEALING FROM MOISTURE.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2007101600003	20071016	00003	GL  	2007	10	16	2007FA0000861    	1	20070820	G	7810	15070001	EXHAUST HEADER  			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					NR 5	CRACKED         	D			UV4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	516CR	306  				1309				NR 5 EXHAUST HEADER HAS CRACKED OFF AT FLANGE, JUNE 6/06 AT 440.6, NOV 18/06 AT 636.1 HOBBS, MAY 18/07 AT 746.7 HOBBS AN	D AGAIN AUG 20/07 HOBBS NOT AVAILABLE.  AFTER INSPECTING HEADER IT WOULD SEEM THAT A HEAVER GAUGE PIPE WOULD RESOLVE THE	 PROBLEM.  THE LAST HEADER WAS INSTALLED WITH BACK UP FLANGES WELDED TO PIPE AT FLANGE SECTION WITH NO EFFECT.  (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007101600004	20071016	00004	GL  	2007	10	16	2007FA0000862    	2	20070815	G	7230	672332390	RETAINING RING  	RROYCE      							ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	FRACTURED       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05		2    					CAC37235			OPERATOR REPORTED ENGINE CHIP LIGHTS AND A PRECAUTIONARY LANDING WAS MADE.  INSPECTION OF ENGINE CHIP DETECTORS REVEALED	 ONE SMALL PIECE OF THE FAILED RETAINING RING HAD CAUSED THE LIGHT.  THE COMPRESSOR WAS REMOVED FROM THE ENGINE AND FURT	HER INVESTIGATION REVEALED THE RETAINING RING HAD FRACTURED INTO 5 PIECES.  3 PIECES WERE CONTAINED IN THE RETAINING RIN	G GROOVE OF THE IMPELLER, 1 PIECE WAS IN THE GEARBOX SUMP AREA AND THE 5TH PIECE WAS RECOVERED FROM THE CHIP DETECTOR.  	THE FAILED RETAINING RING SCORED THE SPUR ADAPTER GEAR ADJACENT TO THE RETAINING RING GROOVE IN THE IMPELLER.  NO FURTHE	R DAMAGE WAS NOTED.  A NEW SPUR ADAPTER GEAR AND RETAINING RING WERE INSTALLED AND THE COMPRESSOR RETURNED TO SERVICE.  						3	U			E4CE				 
2007101600009	20071016	00009	GL  	2007	10	16	2007FA0000863    	1	20070814	G	2720	30730501	RUDDER PEDAL    			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  					COCKPIT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	304C					2113				RUDDER PEDAL OPERATION CAN LEAD TO NO BRAKE OPERATION AT FULL TRAVEL OF RUDDER.  SENDING IN THIS FIELD APPROVAL REQUEST 	FOR A VERNIER MIXTURE CONTROL. BELIEVE THAT THE LT RUDDER PEDAL WHEN PRESSED FULLY ALLOWS YOU TO DEPRESS THE RT BRAKE OV	ER CENTER THUS GIVING YOU NO BRAKE AND DILEMMA WHEN APPLYING THE BRAKE.  THE SAME THING HAPPENS IN REVERSE WHEN THE RT P	EDAL IS DEPRESSED FULLY AND THEN THE LT BRAKE WILL GO OVER CENTER AND BECOME USELESS.  THIS AC, AS AN EXAMPLE WAS GROUND	 LOOPED AT 68 HRS TT.   IF THIS CONDITION CAN BE ACHIEVED EASILY ON THE GROUND THEN IT COULD HAPPEN ON LANDING, IN A CRO	SSWIND OR TURN.  FURTHER MORE THE BRAKE PEDAL IN THE OVER CENTER CONDITION WILL BE POINTED FORWARD AND AT A 90 DEGREE AN	1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2008011400199	20080114	00199	EU  	2008	1	14	2007FA0000864    	2	20070809	G	8530	02722001002R1	CYLINDER HEAD   			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	240TS					42072				ENGINE BEGAN LOSING COOLANT BY PRESSURIZING THE COOLING SYSTEM WITH COMBUSTION PRESSURE AND BLOWING COOLANT OVERBOARD.  	WHEN CYLINDER HEAD WAS REMOVED, EACH CYLINDER HAD A CRACK BETWEEN THE GLOW PLUG AND EXHAUST VALVE RECESS.  THE ENGINE HA	D PASSED A COMPRESSION CHECK AND IT IS SUSPECTED THAT THE CRACKS WOULD ONLY LEAK WHEN THE ENGINE WAS WARMED TO OPERATING	 TEMPERATURE.  THE RESULTANT COOLANT LOSS ONLY INCREASES THE PROBABILITY OF FURTHER TEMPERATURE EXCURSIONS.  A PROBABLE 	CAUSE WOULD BE INADEQUATE DISTANCE IN THE CASTING OF THE CYLINDER HEAD BETWEEN THE EXHAUST VALVE RECESS AND THE GLOW PLU	G.  ALTERNATE CAUSES INCLUDE INADEQUATE COOLING PROVIDED BY THE AIRFRAME MFG, INADEQUATE WATER JACKETING IN THE ENGINE R	1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008011400200	20080114	00200	EU  	2008	1	14	2007FA0000865    	2	20070809	G	8530	02722001002R1	CYLINDER HEAD   			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	350TS					42061				ENGINE BEGAN LOSING COOLANT BY PRESSURIZING THE COOLING SYSTEM WITH COMBUSTION PRESSURE AND BLOWING COOLANT OVERBOARD.  	WHEN CYLINDER HEAD WAS REMOVED, EACH CYLINDER HAD A CRACK BETWEEN THE GLOW PLUG AND EXHAUST VALVE RECESS.  THE ENGINE HA	D PASSED A COMPRESSION CHECK AND IT IS SUSPECTED THAT THE CRACKS WOULD ONLY LEAK WHEN THE ENGINE WAS WARMED TO OPERATING	 TEMPERATURE.  THE RESULTANT COOLANT LOSS ONLY INCREASE THE PROBABILITY OF FURTHER TEMPERATURE EXCURSIONS.  A PROBABLE C	AUSE INCLUDE INADEQUATE COOLING PROVIDED BY THE AIRFRAME MFG, INADEQUATE WATER JACKETING IN THE ENGINE RESULTING IN HOT 	SPOTS WHICH COULD LEAD TO CRACKING, AND ENGINE RUNNING AT A HIGHER RPM THAN THE COOLING SYSTEM COULD HANDLE.	1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2007101600010	20071016	00010	CE  	2007	10	16	2007FA0000866    	1	20070907	G	2497	691835432	BUSS BAR        			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					LT JBOX	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	227DH	655  				6800086				THE AIRCRAFT WENT TO START ENGINES, 6 CAS MESSAGES APPEARED ON THE DISPLAY.  TROUBLESHOT PROBLEM AND FOUND MOUNTING STUD	 FOR EMERGENCY BUSS BAR WAS LOOSE CAUSING ARCING AND WELDING OF THE STUD.  THIS STUD WAS LOOSE FROM FACTORY.  DO AN INSP	ECTION OF ALL STUDS TORQUE CHECK) (K)				2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
2007101600011	20071016	00011	CE  	2007	10	16	2007FA0000867    	1	20070911	G	6100	AN520C8R6	SCREW           			BEECH 	58    	58          	1152740	CE  										PROPELLER	UNSAFETIED      	B			EHHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	755P	63   				TH2162				HAVE SEEN THIS ATTACHMENT ARRANGEMENT ON MANY AC.  FOUND NON SAFETIED SCREWS ATTACHING PROPELLER DEICE BRUSH ASSY TO MOU	NTING.  REMOVED NON SAFETIED SCREWS WITHOUT LOCKING DEVICES WITH MS35265-44 SCREW THAT CAN BE LOCKED WITH SAFETY WIRE.  	(K)				1	L	7	2 	3O				3A16    					 
2007101600012	20071016	00012	EU  	2007	10	16	2007FA0000868    	1	20070911	G	6210	10901030115	BLADE           			AGUSTA	A109  	A109        	0260109	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	2MF	663  				7277	CAE834542			EXCESSIVE 1 PER REVOLUTION VIBRATION NOTICED IN MAIN ROTOR SYSTEM.  THE AIRCRAFT WAS LANDED WITHOUT INCIDENT.  INVESTIGA	TION REVEALED CORD WISE CRACKS IN UPPER AND LOWER SKINS AT STATION 1979 EXTENDING FROM THE TRAILING EDGE TO THE AFT SIDE	 OF THE SPAR.  THE HONEYCOMB CORE OF THE BLADE IS ALSO SEPARATED AND DAYLIGHT CAN BE SEEN THROUGH CRACKS IN THE BLADE.  	THE CRACKS IN BOTH SKINS THEN EXTEND SPAN-WISE ALONG THE SPAR FROM STA 1925 TO STA 2075.  THESE CRACKS ARE EXACTLY AS DE	SCRIBED IN TECH BULLETIN 109-50, PART 1 REQUIRES DAILY VISUAL INSPECTIONS OF BLADES WITH GREATER THAN 500 HOURS OF OPERA	TION BETWEEN STATIONS 1550 AND 3100.  BT 109-50, PART II REQUIRES INSPECTION OF THIS AREA WITH A 3X MAGNIFYING GLASS EVE	1	G	7	2 	3U	3	U		H7EU    	E4CE				 
2007101600013	20071016	00013	GL  	2007	10	16	2007FA0000869    	1	20070801	G	5542		SKIN            			DIAMON	DA40  	DA40        	2990002	GL  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	469JP	654  				40469				FOUND 3 INCH CRACK AFT OF RUDDER BALANCE WEIGHT IN COMPOSIT SKIN FWD OF UPPER ATTACH POINT.  AIRCRAFT WAS BASED OUT OF A	 HEAT RELATED AREA.  (K)					1	L	7	1 	3O			NT	A47CE   					 
2007101600014	20071016	00014	NE  	2007	10	16	2007FA0000870    	2	20070912	G	7200	30606266	BLADE           			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					3RD STG ROTOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	115SK	1855 				330				BROKEN TURBINE BLADE.  ENGINE SENT TO MFG FOR INVESTIGATION.  (K)						2	L	7	3 	4F	4	F		A46EU   	E1NM				 
2008011400201	20080114	00201	EU  	2008	1	14	2007FA0000871    	2	20070809	G	8530	02722001002R1	CYLINDER HEAD   			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					ENGINE	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	240TS	421  				42072				ENGINE BEGAN LOSING COOLANT BY PRESSURIZING THE COOLING SYSTEM WITH COMBUSTION PRESSURE AND BLOWING COOLANT OVERBOARD.  	WHEN THE ENGINE WAS REMOVED AND THE OIL DRAINED, COOLANT WAS FOUND IN THE OIL AND FILLING UP CYLINDER NR 3.  IT IS SUSPE	CTED THAT IF THE CYLINDER HEAD WOULD HAVE BEEN REMOVED, EACH CYLINDER WOULD HAVE HAD A CRACK BETWEEN THE GLOW PLUG AND E	XHAUST VALVE RECESSES.  THE ENGINE HAD PASSED A COMPRESSION CHECK AND IT IS SUSPECTED THAT THE CRACKS WOULD ONLY LEAK WH	EN THE ENGINE WAS WARMED TO OPERATING TEMPERATURE.  THE RESULTANT COOLANT LOSS ONLY INCREASES THE PROBABILIITY OF FURTHE	R TEMPERATURE EXCURSIONS.  A PROBABLE CAUSE WOULD BE INADEQUATE DISTANCE IN THE CASTING OF THE CYLINDER HEAD BETWEEN THE	1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2007101600015	20071016	00015	CE  	2007	10	16	2007FA0000872    	1	20070719	G	5730		SKIN            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					WINGS	CORRODED        	D			BX4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	648SB					421C0648				LT AND RT WING UPPER SKINS UNDER THE NACELLE FUEL BLADDER TANKS HAD CORROSION PRESENT TO THEM AND RELATED AREA AROUND TH	E BLADDER BAYS.  WO NR 10688.  (K)					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007101600016	20071016	00016	EA  	2007	10	16	2007FA0000873    	2	20070827	G	7414	6361	MAGNETO         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540AH1A  	42003	EA  					LT	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	691MA					3257291				THIS AIRCRAFT HAD A SET OF MAGS INSTALLED AT APPROXIMATELY 400 HRS TT, AT 596 HRS TT, INSTALLED ANOTHER O/H MAG ON THE L	T, DUE TO AN OVERHEAT SITUATION.  IT APPEARS THAT THE COIL HAS BROKEN DOWN DUE TO EXCESS HEAT, DURING NORMAL OPERATION. 	 NEW AC SHOULD HAVE AIR BLAST TUBES INSTALLED FOR EACH MAGNETO, AS WELL AS A COOLING KIT FOR THE VACUUM PUMP.  THE MAGS,	 NOR THE VACUUM PUMP CAN OPERATE UNDER THESE CONDITIONS WITHOUT AN OUTSIDE AIR SUPPLY.  SB 1157A AFFECTS AC FOR THE TACH	OMETER SENSOR ALLOWING MOISTURE TO DAMAGE THE MAGNETO.  (K)		1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2007101600021	20071016	00021	CE  	2007	10	16	2007FA0000874    	1	20070728	G	3250	MC05430221	ROD END         			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300*       	17022	SO  					NLG STEERING	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	2423U					17250023				LT SIDE STEERING ROD WITH 215.92 HRS SINCE NEW HAD THE REAR BALL END THAT ATTACHES TO THE RT RUDDER BAR ASSY BREAK.  THE	 BALL ROD END BROKE AND LEFT THE T/R STEERING ROD AS THE ONLY STEERING FOR THE NOSE GEAR.  THE RODS ARE NOT SOLID RODS, 	THEY ARE DESIGNED TO PUSH AND NOT TO PULL THAT SLIP INSIDE WHEN PULLED ON.  IT REQUIRES BOTH RODS TO STEER THE RT PEDAL 	AND LT ROD WILL TURN NOSE TO THE RT AND LT PEDAL AND RT ROD WILL TURN IT TO THE LT.  ON LANDING ROLL OUT, THE PLANE STAR	TS TO DRIFT TO THE LT AND WITH THE LT RUDDER PEDAL TO NOSE GEAR DISCONNECTED. NOSE GEAR WOULD NOT RESPOND AND THE PLANE 	WAS SLOWING UP TO THE POINT OF LOSING ENOUGH AIR FLOW OVER THE RUDDER FOR IT TO CONTROL THE PLANE.  THE PILOT STARTED TO	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2007101600018	20071016	00018	SO  	2007	10	16	2007FA0000875    	1	20071003	G	5530		BOLT            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					VERTICAL STAB	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	6365C	1776 	1776 			287890366				LOSE VERTICAL ATTACH BOLTS ON AFT BULKHEAD.						1	L	7	1 	3O	3	O		2A13    	E286				 
2007101600041	20071016	00041	GL  	2007	10	16	2007FA0000876    	1	20070919	G	7931	PT100GA	TRANSMITTER     			RYAN  	NAVION	NAVION      	6150160	GL  	CONT  	O520  	IO520B      	17032	SO  					ENGINE OIL PRESS	UNRELIABLE      	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	04	4131K					NAV41131	1212867B			AIRCRAFT LANDED WITH ZERO OIL PRESSURE INDICATION. AFTER TESTING WITH DIRECT READING GAUGE IT WAS DETERMINED THAT THE AC	TUAL ENGINE OIL PRESSURE WAS WITHIN LIMITS SPECIFIED BY THE MFG.  FURTHER TESTING REVEALED PRESSURE INDICATING SYSTEM WO	ULD OPERATE NORMALLY AFTER ENGINE TEMPERATURES HAD COOLED BUT WOULD PROVIDE FALSE INDICATIONS WITH ENGINE AT OPERATING T	EMPERATURE.  FEEL THIS IS A SERIOUS PROBLEM BECAUSE THIS SYSTEM IS STC APPROVED AS A PRIMARY INSTRUMENT AND ITS MALFUNCT	ION COULD CAUSE UNNECESSARY AND DANGEROUS OFF AIRPORT LANDINGS.		1	L	7	1 	3O	3	O	RT	A782    	E5CE				 
2007101600073	20071016	00073	NM  	2007	10	16	2007FA0000877    	1	20070807	G	2420	LC41550FG	ALTERNATOR      			COLUMB	LC41  	LC41550FG400	5150011	NM  	CONT  	O550  	TSIO550A    	41516	SO  					ENGINE	FAILED          	F				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NM	09	376PD	350  				41018				A FLIGHT TEST WAS BEING CONDUCTED ON 07/30/07 ON A REWORKED THERMAL SYSTEMS (KATS) EVADE SYSTEM, WHEN THE SYSTEM WENT UN	STABLE CAUSING THE ALTERNATOR TO GO OFF LINE.  THE TECHNICIAN MONITORING THE SYSTEM ON A DIAGNOSTIC LAPTOP COMPUTER ANNO	UNCED TO THE PILOT THAT THE SYSTEM WAS FAILED BUT THE PILOT DID NOT HAVE A "FAILED" ANNUNCIATION ON THE INSTRUMENT PANEL	.  KATS CONFIRMED THAT THERE WAS A PROBLEM WITH THE FAULT DETECTION SOFTWARE THAT WOULD ALLOW THIS UNDER VERY SPECIFIC C	ONDITIONS.  KATS STATED THAT THEY DO NOT BELIEVE THIS TO BE A SERIOUS SITUATION SINCE THE SYSTEM IS CERTIFIED INADVERTEN	T ICING ONLY.	1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
2007102300067	20071023	00067		2007	10	23	2007FA0000878    	4	20070629	G	3455	TDR906221270001	TRANSPONDER     								GARRTT	TFE731	TFE731*     	01518	WP  					TAILCONE	FAILED          	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	56EM					144				ON 6/27/2007 WHILE ENROUTE, THE PRIMARY TRANSPONDER FAILED WHILE THE AIRCRAFT WAS OPERATING IN AIRSPACE.  THE CREW WAS A	BLE TO SWITCH TO THE SECONDARY TRANSPONDER AND CONTINUE THEIR FLIGHT TO LOCK WITHOUT FURTHER INCIDENT.  UPON ARRIVAL, TH	E PRIMARY TRANSPONDER WAS CONFIRMED FAILED AND WAS REPLACED WITH A SERVICEABLE TRANSPONDER.  THE SYSTEM WAS TESTED IAW F	AR PART 43, APPENDIX F AND APPENDIX E, SUB PARA C, AND ICA NR 30A05002, REVISION C.  THE SYSTEM WAS FOUND TO BE OPERATIN	G NORMALLY AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (K)							4	F			E6WE				 
2007102300068	20071023	00068	CE  	2007	10	23	2007FA0000879    	1	20070909	G	2823	12161001	SELECTOR VALVE  			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C401   	GL  	FUEL SYSTEM	MISMANUFACTURED 	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	803AN	161  				20700570	248811R	765815		WHEN THE FUEL SELECTOR VALVE IS SELECTED TO THE RT TANK, FUEL IS BEING DELIVERED FROM THE LT TANK, VISE VERSA.  THIS WAS	 DISCOVERED DURING A SHORT FLIGHT IN WHICH THE PILOT NOTICED THE RT TANK FUEL GAUGE WAS DROPPING WHEN THE LT TANK WAS SE	LECTED.  THIS WAS LATER CONFIRMED DURING AN INSPECTION IN WHICH FUEL WAS DRAINED FROM BOTH TANKS.  IN FACT THE SELECTOR 	VALVE IS PUT TOGETHER INTERNALLY BACKWARDS.  (K)			1	H	7	1 	3O	3	O		A16CE   	E8CE	5	C	P47GL	 
2007102300069	20071023	00069	CE  	2007	10	23	2007FA0000880    	1	20070917	G	2420	DOFF10300JR	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  						INOPERATIVE     	D			UT2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	9531H	46   				17266205				THIS ALTERNATOR WAS OVERHAULED, OPERATED LESS THAN 50 HOURS, FAILED.  THE STUD THAT HOLDS THE DIODE PLATE IN THE ALTERNA	TOR WAS BROKEN, AND THE SECOND STUD WAS LOOSE.  THIS HAS BEEN AN ONGOING PROBLEM WITH OVERHAULS.  WE ARE A SMALL SHOP, Y	ET WE HAVE HAD MANY FAILURE WITH THIS PRODUCT IN THE PAST 2 YEARS.  APPROXIMATELY 70 PERCENT OF THE OVERHAULS WE HAVE IN	STALLED HAVE GONE BACK FOR WARRANTY.  PROBLEMS INCLUDE LOOSE DRIVE PULLEYS, LOOSE HARDWARE, SHORT CIRCUITS, DEAD FIELD W	INDINGS, DEFECTIVE BRUSHES.  MY SUPPLIERS STATE THAT THEY HAVE HAD MANY COMPLAINTS ABOUT THIS REPAIR.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007102300070	20071023	00070		2007	10	23	2007FA0000881    	4	20070918	G	8300	23066678	PINION GEAR     	ALLSN       							ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	FRACTURED       	B			YKER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17					CAG47225		CAE847225			RECEIVED THE ENGINE FOR REPAIR DUE TO VIBRATIONS, AND METAL IN OIL.  UPON DISASSEMBLY OF THE GEARBOX FOUND THE ROLLER RE	TAINER OF THE NR 3 BEARING FRACTURED IN (4) PLACES.  ALSO FOUND THAT THE NR 1 TURBINE WHEEL BLADE TIPS HAD BEEN RUBBING 	THE BLADE TRACK WHICH CAUSED THE VIBRATION.  TECH SUSPECTS THE FRACTURED RETAINER MAY HAVE BEEN A RESULT OF THE VIBRATIO	N. (K)								3	U			E1GL				 
2007102300071	20071023	00071	GL  	2007	10	23	2007FA0000882    	1	20070831	G	7820	20559002	MUFFLER         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	824ZB	559  				1674				CHECK MUFFLER IAW MFG SB, SB2X-78-07, ISSUED JUNE, 2007.  FOUND SPOT WELDS ON EXTERNAL BAFFLE CRACKED.  REPLACED MUFFLER	.  THIS SB APPLIES ONLY TO SR20`S SN 1005 THRU 1797.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2007102300072	20071023	00072	SO  	2007	10	23	2007FA0000883    	1	20070807	G	3213	7873804	AXLE            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	8905N	10353				3240690	L2683048E	CH35831B		ON TAXI TO TAKEOFF, AC TURNED AROUND AFTER BACK TAXI.  PIVOTING ON LT M/G.  SIDE LOAD BROKE AXLE AT END OF DRILLED OUT C	ENTER.  EVIDENCE OF PREVIOUS CRACKING FROM INSIDE OB.  (K)					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
2007102300074	20071023	00074	CE  	2007	10	23	2007FA0000884    	1	20070717	G	3240	07516800	PLATE           			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A6       	52043	EA  						CRACKED         	C			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	9602F	15966				20800103				FOUND TORQUE PLATE CRACKED DURING ROUTINE INSPECTION.  (K)						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2007102300075	20071023	00075	EU  	2007	10	23	2007FA0000885    	1	20070910	G	5753	257WF101A	VANE            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					TE FLAP	CORRODED        	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	150SB	5758 				258197				LT IB FLAP VANE, UPPER SKIN CORRODED BEYOND LIMITS.  POSSIBLE CAUSE: DISSIMILAR METAL CORROSION AS TRAILING EDGE IS MAGN	ESIUM AND SKIN IS ALUMINUM OR ENVIRONMENT IN WHICH THE VANE OPERATES. IT IS LOCATED BEHIND THE MLG.  ASSURE THE SKIN IS 	PROPERLY TREATED IAW CORROSION PREVENTION PROCEDURES AND PAINTED WITH EPOXY PRIMER BEFORE INSTALLATION.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007102300078	20071023	00078	EA  	2007	10	23	2007FA0000886    	2	20070817	G	8500		ENGINE          			BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  						MAKING METAL    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	98KA					P212	RL79259			DURING ROUTINE OIL CHANGE, METAL SHAVINGS WERE FOUND IN OIL FILTER AND SCREEN.  SHAVINGS WERE MAGNETIC.  THESE ENGINES D	O HAVE WEAR ISSUES ON CAM AND LIFTERS.  AFTER REMOVING OIL PAN, FOUND CAM BAD AND LIFTER WEAR.  OIL ANALYSIS DIDN`T PICK	 UP LARGER MICRON IN OIL.  RECOMMEND INSPECTION OF CAM AND LIFTER BEFORE 1000 HOUR.  REMOVED OIL PAN ON RT ENGINES AND F	OUND BEAD WEAR AS WELL.  NO METAL IN FILTER.  (K)			1	L	7	2 	3O	3	O		A12CE   	E10EA				 
2007102300080	20071023	00080	GL  	2007	10	23	2007FA0000887    	2	20070803	G	7250		TURBINE WHEEL   			CESSNA	STC   	STC206C     	1182107	CE  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	5746N	1654 	13   			45461	890629			AFTER 13 HOURS OF OPERATION SINCE OVERHAUL, DURING A POWER CHECK, THE TURBINE ASSY FAILED CAUSING THE FORCED LANDING OF 	THE HELICOPTER.  FORCED LANDING CAUSED SUBSTANTIAL DAMAGE TO THE AIRCRAFT.  (K)					1	H	7	1 	3O	3	U	NT	A4CE    	E1GL				 
2007102300083	20071023	00083	CE  	2007	10	23	2007FA0000888    	1	20070830	G	3246	C163003102	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	LT MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	9898Q					17265842	L3551036A	31674R		WHEEL IS A 3 PIECE CONSTRUCTION, OUTER RIM AND THE INNER SPACER.  BROKE APART ON TAXIING OF AIRCRAFT. JACKED AIRCRAFT AN	D INSTALLED SERVICEABLE UNIT, THREADS STRIPPED OUT OF CENTER SECTION.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2007102300086	20071023	00086	SO  	2007	10	23	2007FA0000889    	2	20070911	G	8530		ROCKER          			CUBCFT	CC11  	CC11100     	060002H	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4 CYLINDER	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	787AK	118  				CC1100006	256113			FOUND THE ROCKER ARMS REVERSED, INTAKE EXHAUST ROCKERS IN CYLINDER NR 4 LEADING TO POSSIBLE EXHAUST GUIDE AND VALVE DAMA	GE DO TO THE  EXHAUST ROCKER ARM HAS AN OILING PORT FOR THE EXHAUST VALVE AND THE INTAKE ROCKER ARM DOES NOT HAVE THE OI	LING PORT.  THE ROCKER ARMS WERE REMOVED AND INSTALLED CORRECTLY.  DAMAGE TO VALVE AND GUIDE UNKNOWN AT THIS TIME, WILL 	HAVE TO CONTACT MFG.  (K)			1	H	7	1 	3O	3	O	NC	        	E252				 
2007102300088	20071023	00088	SO  	2007	10	23	2007FA0000890    	2	20070911	G	8530	MS5196364	SETSCREW        			CUBCFT	CC11  	CC11100     	060002H	CE  	CONT  	O200  	O200A       	17020	SO  					CYL ROCKER BOSS	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	787AK	118  				CC1100006	256113			IN THE NEW STYLE CYLINDER ASSY PN 655482 FOR THE ENGINE, THE ROCKER ARM PIN PN 654375 IS RETAINED BY A SET SCREW PN MS51	966364 IN THE CENTER ROCKER BOSS SUPPORT.  FOUND IN THIS ENGINE (2) SET SCREWS LOOSE AND A THIRD FOUND RATTLING AROUND A	ND LODGED UNDER THE INTAKE ROCKER ARM BETWEEN THE CYLINDER HEAD.  THE ROCKER SHAFTS ARE MOVING OFF CENTER AND ROTATING A	ND WITH A MACHINED SHARP CUT IN THE END OF THE ROCKER SHAFT TO INDICATE WERE SET SCREW IS TO LINE UP WITH THE ROCKER SHA	FT, IT IS CUTTING THROUGH THE VALVE COVERS AND WILL LEAD TO LOSS OF ENGINE OIL AND OPERATION OF THE ENGINE AND POSSIBLE 	LOSS OF PERSONAL LIFE.  (K)	1	H	7	1 	3O	3	O	NC	        	E252				 
2007102300091	20071023	00091	SO  	2007	10	23	2007FA0000891    	2	20070914	G	8530	O200D	SETSCREW        			AMCNLG	AL3   	AL3         	060002K	CE  	CONT  	O200  	O200*       	17020	SO  					ROCKER ARM BOSS	MISMANUFACTURED 	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	65LC	42   				AL1083				CHECKING ROCKER ARM SHAFT SET SCREWS AND TO ASSURE INTAKE AND EXHAUST ROCKER ARMS NOT SWITCHED IAW INFORMATION TO OWNERS	 FORM INTERNET OWNERS AIRCRAFT FORUM. CYLINDER NR 1, SN AC06HB070, SET SCREW AND ROCKER ARMS, OK.  CYLINDER NR 2, SN AC0	6FA543, SET SCREW LOOSE ENOUGH TO ALLOW SHAFT TO MOVE, ROCKER ARMS, OK.  CYLINDER NR 3, SN AC06HA911, SET SCREW OK, INTA	KE AND EXHAUST ROCKER ARMS SWITCHED.  CYLINDER NR 4, SN AC06HA935, SET SCREW AND ROCKER ARMS, OK.  (K)			1	H	7	1 	  	3	O	3O	EXPA1H71	E252				 
2007102300087	20071023	00087	CE  	2007	10	23	2007FA0000892    	1	20071010	G	2750	1434425	FLEX DRIVE      			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					RT TE FLAPS	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	22NG					7500204				THE RT FLAP FLEX DRIVE HOUSING FAILED AT THE SWAGED END OF THE HOUSING AT THE IB END.  ON SEPTEMBER 11, 2007 THIS AIRCRA	FT HAD A SIMILAR EVENT WITH THE LT OB FLAP DRIVE WHICH ALLOWED THE FLEX DRIVE TO DISENGAGE FROM THE OB FLAP DRIVE CAUSIN	G THE FLAPS TOP REMAIN AT 3 DEGREES POSITION AND PREVENTING FURTHER EXTENSION OR RETRACTION. WE OPERATE 2  AIRCRAFT AND 	THIS IS THE 4TH FAILURE OF THE FLEX DRIVE BETWEEN THE 2 AIRCRAFT.			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007102300127	20071023	00127	WP  	2007	10	23	2007FA0000893    	2	20070914	G	7230	307516034	TURBINE WHEEL   			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					LP COMPRESSOR	FAILED          	E				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			NM	04	800WY	3172 				258556	107656			CLIMBING THROUGH FL270, A LOUD BANG IN REAR OF ACFT.   LT ENGINE COMPUTER LIGHT ILLUMINATED. PF BROUGHT LT ENGINE TO IDL	E, PNF PULLED CHECKLIST. AFTER SURVEY OF ENGINE PARAMETERS, PF TURNED LT ENGINE COMPUTER BACK ON TO CONTROL PARAMETERS. 	 ENGINE COMPUTER DID STAY ON & DID APPEAR TO CONTROLL ENGINE.  POWER ADVANCED SLOWLY ON LT ENGINE. AT APPROXIMATELY 70 %	 N1 ANOTHER LOUD BANG IN REAR & LT ENGINE COMPUTER LIGHT ILLUMINATED AGAIN. ENGINE PARAMETERS MOVED TO RED LINE. PF SHUT	DOWN LT ENGINE.  PNF CONTACTED ATC, DECLARED AN EMERGENCY & REQUESTED & RECEIVED DIRECT CLOSEST AIRPORT.  SINGLE ENGINE 	APPROACH CHECKLIST & PROGRAMMED FMS FOR AN APPROACH.  ACFT CLEARED FOR VISUAL APPROACH.  AFTER A NON-EVENTFUL LANDING.  	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007102300109	20071023	00109	CE  	2007	10	23	2007FA0000895    	1	20071001	G	3150		UNKNOWN         			BEECH 	MU300 	400A        	1155402	CE  											UNKNOWN         	E				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	11	418GJ					RK418				AC EXPERIENCED A FLAP ASYMMETRIC LIGHT IN FLIGHT.  THE CREW DID NOT TRY TO PUT THE FLAPS DOWN AND DIVERTED FOR A NO FLAP	 LANDING.  CRITICAL CARE MAINTENANCE DROVE DOWN TO REPAIR THE AIRCRAFT.  MAINTENANCE COULD NOT DUPLICATE THE PROBLEM AFT	ER SEVERAL ATTEMPTS.  MAINTENANCE INSPECTED AND CLEANED ALL CONNECTORS, INSPECTED HYDRAULIC SYSTEMS, AND FLAP RIGGING AN	D CABLES.  MAINTENANCE C/W ALL OPERATIONAL CHECK IAW THE MM.  THE PROBLEM WAS NEVER DUPLICATED.			2	H	7	2 	4F			RT	A16SW   					 
2007102300003	20071023	00003	CE  	2007	10	23	2007FA0000897    	1	20071012	G	2730		CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ELEVATORS	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	379TA	1560 				172S9379	L3083351A			CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS PER AC43.13-1A, CABLE INSPECTION.  CABLE WAS WORN DUE TO 	CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7.  IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS 	CONSTANT CONTACT.  MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT	S.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300135	20071023	00135	CE  	2007	10	23	2007FA0000898    	1	20071012	G	5712	051179616	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	MISALIGNED      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	373ES	3780 				17280052	L2701351A			CONTROL CABLE, (P/N 0510105-339), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION.  CABLE WAS WORN DUE TO 	CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7.  IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS 	CONSTANT CONTACT.  CESSNA MAINTENANCE MANUAL DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAK	AGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300140	20071023	00140	CE  	2007	10	23	2007FA0000900    	1	20071012	G	2730		CONTROL CABLE   			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ZONE 100	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	7262Y	1400 				18280812	L1241261E			CONTROL CABLE, (P/N 0510105-189), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION.  CABLE WAS WORN DUE TO 	CONSTANT CONTACT WITH MICARDA GUARD PLATE OVER FUEL LINES AT FUEL SELECTOR AREA JUST FORWARD OF FRONT SEATS.  THE CABLES	 ARE IN CONSTANT CONTACT WITH PLATES EVEN WITH CABLE TENSION CORRECT.  MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR CO	MMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007102300134	20071023	00134	CE  	2007	10	23	2007FA0000904    	1	20071012	G	5712	051179616	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	MISALIGNED      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	625SP	1560 				172S8616	L2922551A			CONTROL CABLE, (P/N 0510105-339), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION.  CABLE WAS WORN DUE TO 	CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7.  IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS 	CONSTANT CONTACT.  MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT	S.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300137	20071023	00137	CE  	2007	10	23	2007FA0000906    	1	20071012	G	5712	051179616	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	MISALIGNED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	658SP	4200 				172S8063	L2796451A			CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION.  CABLE WAS WORN DUE TO 	CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7.  IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS 	CONSTANT CONTACT.  MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT	S.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300138	20071023	00138	CE  	2007	10	23	2007FA0000907    	1	20071012	G	5712	051179616	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	MISALIGNED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	2630U	1628 				17280568	L2761951A			CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION.  CABLE WAS WORN DUE TO 	CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7.  IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS 	CONSTANT CONTACT.  MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT	S.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300004	20071023	00004	CE  	2007	10	23	2007FA0000908    	1	20070919	G	3230	JE1	STOP            			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470*      	17026	SO  					MLG GEARBOX	BROKEN          	B			OF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	20SS	3235 				310Q0521				PILOT HAD NO LT GEAR DOWN INDICATION.  HE CYCLED GEAR WITH NO SUBSEQUENT GEAR DOWN INDICATION.  HE ATTEMPTED MANUAL EXTE	NSION, CRANKED TO THE MECHANICAL STOP IN THE GEARBOX AND BROKE THE STOP.  BELLCRANK CONTINUED PAST DOWN AND THEN WENT PA	RTIALLY (UP).  GEAR COLLAPSED ON LANDING. (K)				1	L	7	2 	3O	3	O		3A10    	E1CE				 
2007102300165	20071023	00165	CE  	2007	10	23	2007FA0000909    	1	20070911	G	5280	45A3161521	DOOR            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG	CRACKED         	B			ZKFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61	262PA					RK203				FOUND DURING INSPECTION.  NOSE GEAR FOLLOW UP DOOR PN 45A31615-21 ON BRACKETS, PN 45A31613-9 AND 45A31613-7 AT ATTACHING	 RIVET HAS CRACKS GOING FORWARD TO AFT THROUGH THE FIRST RIVET ALONG THE RIVET ROW.  RELATIVE WIND PUSHING AFT ON THE DO	OR WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION.  USING THICKER MATERIAL DURING MFG AND OR ADDING A DOUB	LER.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007102300166	20071023	00166	CE  	2007	10	23	2007FA0000910    	1	20070920	G	5280	45A3161521	DOOR            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG	CRACKED         	B			ZKFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61	268PA					RK323				FOUND DURING INSPECTION.  NOSE GEAR FOLLOW UP DOOR, P/N 45A31615-21 ON BRACKETS PN 45A31613-9, 45A31613-7 AND 45A31616-3	 AT ATTACHING RIVET HAS CRACKS GOING FORWARD TO AFT THOUGH THE FIRST RIVET ALONG THE RIVET ROW. RELATIVE WIND PUSHING AF	T ON THE DOOR WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION.  USING THICKER MATERIAL DURING MFG AND OR AD	DING A DOUBLER.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007110100172	20071101	00172	CE  	2007	11	1	2007FA0000911    	1	20070917	G	5280		STRUCTURE       			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG DOOR	CRACKED         	B			ZKFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61	26PA					RK256				FOUND DURING INSPECTION.  NOSE GEAR FOLLOW UP DOOR PN 45A31615-21 ON BRACKETS PN 45A31613-9 AND 45A31613-7 AT ATTACHING 	RIVET HAS CRACKS GOING FORWARD TO AFT THROUGH THE FIRST RIVET ALONG THE RIVET ROW.  RELATIVE WIND PUSHING AFT ON THE DOO	R WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION.  USING THICKER MATERIAL DURING MFG AND OR ADDING A DOUBL	ER.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007110100173	20071101	00173	CE  	2007	11	1	2007FA0000912    	1	20071001	G	5610	45AS3101012	WINDOW          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	480M					RK6				WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND NR 2 (COPILOT) SIDE WINDOW CRACKED USING THE PRISM INSPECTION METHOD. 	 THE D-INSPECTION REQUIRES THAT BOTH WINDSHIELD RETAINERS OR USING OPTICAL PRISM INSPECTION METHOD.  THE IS NO STATEMENT	 IN THE AIRCRAFT MM OR IN THE A-D INSPECTION CHECKLIST THAT REQUIRES YOU TO INSPECT THE COCKPIT SIDE WINDOWS IN THE SAME	 MANNER AS THE WINDSHIELDS.  ALL OF THE WINDOWS IN THE COCKPIT AREA ARE INSTALLED OR FASTENED IN THE SAME MANNER AS THE 	WINDSHIELDS.  IT IS SUSPECTED THAT THE COPILOT WINDOW CRACKED FROM FATIGUE, OR TT INSTALLED. WOULD RECOMMEND THAT INSPEC	TIONS OF ALL COCKPIT WINDOWS WITH A PRISM AT SCHEDULED INTERVALS BE COMPLETED.  (K)	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007102300011	20071023	00011	CE  	2007	10	23	2007FA0000914    	1	20071003	G	5510		FITTING         			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	480M					RK6				WHILE PERFORMING AN A-D INSPECTION FOUND 8 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A	21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER.  IT IS SUSPECTED THAT THE LOOSE RIVETS WERE CAUSED BY FATIGUE AND A	GE.  RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION.  RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS.  THIS IS THE	 3RD AIRCRAFT IN A ROW THAT THESE SAME RIVETS HAVE BEEN LOOSE OR MISSING.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007102300007	20071023	00007	CE  	2007	10	23	2007FA0000915    	1	20071001	G	5520		HINGE BRACKET   			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT ELEVATOR	CORRODED        	B			SI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	52FT					S5500056				LT OB HINGE BRACKET BROKE OFF DURING AILERON REMOVAL.  APPEARS TO HAVE FAILED DUE TO CORROSION. (K)						1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2007102300010	20071023	00010	CE  	2007	10	23	2007FA0000916    	1	20070928	G	7830		STRUCTURE       			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					THRUST REVERSER	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	10UF				0011	166	P74521C			DURING THE PILOT PREFLIGHT, THE PILOT HAD NOTICED THAT THERE WAS A TEAR IN THE SHEET METAL OF THE LT ENGINE THRUST REVER	SER INNER SKIN.  WE COULD NOT IDENTIFY WHAT HAS CAUSED THIS TEAR.  THE UNIT WILL BE REPAIRED BY THE MFG AND WILL INFORM 	YOU WITH ANY INFO THEY GIVE TO US ABOUT THIS INCIDENT.  (K)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007102300017	20071023	00017	EA  	2007	10	23	2007FA0000917    	2	20070820	G	7322	3013460	ROD             			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					FUEL CONTROL	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	65	621KC					110335				DURING A 150 HR INSPECTION THE LOWER FUEL CONTROL ROD WAS FOUND BROKEN ON THREADED SHAFT WHERE IT SCREWS INTO COUPLING. 	 IT LOOKS LIKE IT MAY HAVE BEEN BENT AND A MORE DETAILED INSPECTION OF THIS COMPONENT SHOULD OCCUR. (K)					1	L	7	2 	4T	4	T		A21SO   	E4EA				 
2007110100175	20071101	00175	CE  	2007	11	1	2007FA0000918    	1	20070927	G	2435	23085001	STARTER GEN     			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LEFT	FAILED          	B			E81R	O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	03	350TT		4822 			FL413				PILOT REPORTED LT GENERATOR GOING OFF-LINE ON APPROACH.  FOUND STARTER/GENERATOR INOPERATIVE.  UPON REMOVAL NOTICED EVID	ENCE OF COOLING FAN TIPS RUBBING ON HOUSING, BEARINGS WORN (ARMATURE ASSY LOOSE).(K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007110100176	20071101	00176	GL  	2007	11	1	2007FA0000919    	1	20070913	G	7160		CONTROL ARM     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					CARB HEAT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	423FP	452  				40FC023				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE. (K)					1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2007110100177	20071101	00177	CE  	2007	11	1	2007FA0000920    	1	20071002	G	2420	DOFF10300JR	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	9531H	40   				17266205				ALTERNATOR, DEFECT UNKNOWN, FAILED INTERNALLY, GROUND POST LOOSE INTERNALY EXCESSIVE ARMATURE END PLAY.  RETURNED FOR WA	RRANTY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007110100178	20071101	00178	CE  	2007	11	1	2007FA0000921    	1	20071002	G	2420	DOFF10300JR	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	9531H	40   				17266205				ALTERNATOR, DEFECT UNKNOWN, FAILED INTERNALLY.  RETURNED FOR WARRANTY. (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007102300015	20071023	00015	CE  	2007	10	23	2007FA0000922    	1	20071002	G	8011	MHJ4003S	MOTOR           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					STARTER	NOISY           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	340RF	46   				340A0212				STARTER STARTED MAKING A LOUD SQUEALING NOISE WHEN OPERATING STARTER, AND SLOW ROTATION OF ENGINE.  REMOVED AND RETURNED	 FOR WARRANTY.  (K)					1	L	7	2 	3O	3	O		3A25    	E8CE				 
2007102600086	20071026	00086	CE  	2007	10	26	2007FA0000923    	1	20071005	G	2797		CONNECTOR       			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  						MISINSTALLED    	B			CNQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	964QS					7500164				PRIMARY STAB TRIM FAILED CLIMBING THROUGH FL280 AT 300 KTS.  NO CAS MESSAGE WAS PRESENT.  CLACKER WAS STUCK ON. STAB WAS	 NOT MOVING WHEN CLACKER WAS GOING OFF.  AUTO PILOT DISENGAGED ON ITS OWN DUE TO HEAVY NOSE CONFIG.  AFTER TROUBLESHOOTI	NG SHOULD THE ECM TO BE BAD.  REMOVED AND REPLACED (ECM NR 421400216J1) WITH NEW PART 4214-0021-11 (LATEST DASH NR)  COM	PLETED PRIMARY CHANNEL A/B TRAVEL VERIFICATION CHECKS IAW 750 MM, TASK 27-40-00-721, NO FAULTS NOTED.  FOUND THE PRIMARY	 AND SECONDARY CONNECTORS SWAPPED.  WHICH HAD NO EFFECT IN THIS FAILURE.  (K)		2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007102300012	20071023	00012	CE  	2007	10	23	2007FA0000924    	1	20070616	G	5712	051179616	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUSELAGE	MISLOCATED      	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	2630U	1628 				17280568	L2761951A			CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. 	 THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE.  IT IS BELIEVED THAT A HOLE MISLOCATIO	N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB.  MM DOES NOT CONTAIN ANY  (CABLE WEAR) LIMITS OR COMMENTS, ONLY CA	BLE WIRE BREAKAGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300001	20071023	00001	CE  	2007	10	23	2007FA0000925    	1	20071018	G	7603	632558A1	LINK ROD        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					THROTTLE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4640E	877  				18503824	832429R			THROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437)ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SID	E CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE W	ASHER AT THE THROTTLE BODY WERE MISSING AT THE TIME OF INSPECTION. IF THE LINK ROD FROM THE THROTTLE BODY ARM AND THE ME	TERING BLOCK ARM DETACHES, PROPER FUEL METERING CEASES.			1	H	7	1 	3O	3	O		3A24    	E5CE				 
2007102300052	20071023	00052	CE  	2007	10	23	2007FA0000926    	1	20070812	G	5712	051179616	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	379TA	1560 				172S9379	L3083351A			CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. 	 THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE.  IT IS BELIEVED THAT A HOLE MISLOCATIO	N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB.  MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CAB	LE WIRE BREAKAGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007102300160	20071023	00160	CE  	2007	10	23	2007FA0000929    	1	20070712	G	5712	051179616	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	MISALIGNED      	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	373ES	3780 				17280052	L2701351A			CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. 	 THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE.  IT IS BELIEVED THAT A HOLE MISLOCATIO	N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB.  MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CAB	LE WIRE BREAKAGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007110100187	20071101	00187	CE  	2007	11	1	2007FA0000930    	1	20071018	G	7603	632558A1	LINK ROD        	CONT        		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					THROTTLE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4640E	877  				18503824	832429R			THROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437) ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SI	DE CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE 	WASHER AT THE THROTTLE BODY WERE MISSING AT THE TIME OF INSPECTION.  IF THE LINK ROD FROM THE THROTTLE BODY ARM AND THE 	METERING BLOCK ARM DETACHES, PROPER FUEL METERING CEASES.			1	H	7	1 	3O	3	O		3A24    	E5CE				 
2007102300161	20071023	00161	CE  	2007	10	23	2007FA0000931    	1	20070912	G	5712	051179616	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	MISALIGNED      	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	658SP	4200 				172S8063	L3083351A			CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. 	 THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE.  IT IS BELIEVED THAT A HOLE MISLOCATIO	N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB.  MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CAB	LE WIRE BREAKAGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007110100186	20071101	00186	EA  	2007	11	1	2007FA0000932    	2	20071018	G	8520	AS18840	CAMSHAFT        			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	SPALLED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	6956Q	556  	556  			MA304	RL707851A			556 HOURS SINCE MAJOR OVERHAUL, CAMSHAFT AND LIFTERS SPALLED AND CORROSION IS EVIDENT.  ENGINE HAS BEEN OPERATED ON PHIL	LIPS XC 20W50 OIL.					1	L	7	1 	3O	3	O		A1CE    	1E10				 
2007110100193	20071101	00193	SO  	2007	11	1	2007FA0000933    	1	20071019	G	2432	MS915861	SHUNT           			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					MASTER BATTERY	BLOWN           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	788JG	440  				3257369				COMPLETE ELECTRICAL FAILURE. WHEN BATTERY MASTER SWITCH WAS TURNED ON, NO POWER REACHED MAIN BUSS.  FOUND BATTERY AMMETE	R SHUNT BURNED THROUGH.  BATTERY AMMETER SHUNT INSTALLED WAS 30 AMP VALUE. (P/N MS91586-1)  BATTERY AMMETER SHUNT SHOULD	 BE 100 AMP VALUE.  NO RECORD OF BATTERY AMMETER SHUNT BEING REPLACED SINCE AIRCRAFT WAS MANUFACTURED.  INSTALLED CORREC	T AMP VALUE SHUNT AND ELECTRICAL SYSTEM OPS CHECKED GOOD. PIPER P/N 486-684 (MS91586-6)  RECOMMEND THAT ALL SHUNTS BE CH	ECKED FOR ALL THIS MODEL AIRCRAFT. (ALTERNATOR AMMETER SHUNT IS SAME P/N)		1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2007110100182	20071101	00182	EA  	2007	11	1	2007FA0000935    	2	20071018	G	7414		PIN             			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					MAGNETO	GROOVED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	2916W	633  			G03EA044	447995300	L45577T			STOP PINS GROOVED BEYOND LIMITS.						1	L	7	2 	3O	3	O		A19S0   	E286				 
2007102300162	20071023	00162	CE  	2007	10	23	2007FA0000937    	1	20070912	G	2730		CONTROL CABLE   			CESSNA	182   	182S        	2072701	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ZONE 100	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	7262Y	1400 				18280812	L3083351A			LT AND RT ELEVATOR CONTROL CABLES, ( P/N 0510105-189), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDEL	INES IN AC43.13-1A.  CABLE WAS WORN DUE TO CONSTANT CONTACT WITH THE MICARDA PLATES OVER THE FUEL LINES AT FUEL SELECTOR	 AREA JUST FORWARD OF THE FRONT SEATS.  THE CABLE TENSIONS ARE CORRECT BUT THE CABLES ARE IN CONSTANT CONTACT WITH PLATE	S.  MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.			1	H	7	1 	3O	3	O	NT	3A13    	1E10				 
2007102600095	20071026	00095	SO  	2007	10	26	2007FA0000938    	1	20071022	G	3297	AN551	BOLT            	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					DRAG LINK	SHEARED         	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	574ER	3743 			NA	4496150				FORWARD DRAG LINK BOLT ON NOSE GEAR FAILED DURING TOUCH AND GO PRACTICE.  A/C RETURNED TO DEPARTURE AND LANDED WITH THE 	NOSE GEAR STUCK IN THE NOSEWHEEL WELL.					1	L	7	2 	3O	3	O		A19S0   	E286				 
2007102600097	20071026	00097	CE  	2007	10	26	2007FA0000939    	1	20071021	G	3260		LAMP            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					MLG INDICATOR	INOPERATIVE     	D				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			SO	11	442GJ					RK442				PILOT HAD NO GREEN DOWN AND LOCKED INDICATION FOR THE RT GEAR WHEN LANDING. PILOT CONFIRMED WITH THE TOWER THE GEAR WAS 	DOWN, ALSO THE PILOT CONFIRMED THAT THE LIGHT WOULD NOT ILLUMINATE WHEN TESTED. AFTER LANDING MAINTENANCE CHECKED OUT AI	RCRAFT AND REPLACED LAMP IN GEAR INDICATION. SYSTEM OPERATIONAL CHECK GOOD.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007120400004	20071204	00004	SW  	2007	12	4	2007FA0000941    	1	20071009	G	2700	KS178	ROLL SERVO      			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					INSIDE CASE	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	697SP	160  			5644	252002				MOTOR ASSY COMING LOOSE ON SERVO MOUNT. LOOSE HARDWARE, LOOSE MOTOR.  RECOMMEND SERVO TO BE INSPECTED FOR PROPER SERVO A	SSY (THAT MOTOR AND HARDWARE ARE NOT LOOSE).   (K)					1	L	7	1 	3O	3	O		2A3     	E9CE				 
2007102600109	20071026	00109	SO  	2007	10	26	2007FA0000942    	1	20070921	G	3220		LANDING GEAR    			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					NOSE	COLLAPSED       	C			AG3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	84643					348233033				AIRCRAFT TAXIED TO RUNWAY AFTER LOADING CARGO.  AFTER NORMAL RUNUP, THE PILOT TAXIED ONTO THE RUNWAY AND STOPPED.  THE P	ILOT ADVANCED THROTTLES AND RELEASED BRAKES, AFTER RELEASING BRAKE, THE NOSE GEAR COLLAPSED.  AIRCRAFT WAS RECOVERED AND	 TOWED OFF RUNWAY TO A SAFE TIE DOWN SPOT.  NO CAUSE IS YET KNOWN AS TO WHY THE NOSE GEAR COLLAPSED.  (K)				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2007102600110	20071026	00110	CE  	2007	10	26	2007FA0000944    	1	20071012	G	8011	6462751	STARTER         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					RT ENGINE	SHORTED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	421KD	29   				421C1006	808319R			OVERHAULED STARTER FAILED AFTER 30 HOURS.  (K)						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007102600111	20071026	00111	CE  	2007	10	26	2007FA0000945    	1	20071012	G	2913		PUMP            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					HYD SYSTEM	DAMAGED         	D			JAS2	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	408J					RB193				HYDRAULIC PUMP ASSY, PN 390-389022-0003, INSPECTED AND FOUND NOT DEFECTIVE.  FOUND DEFECTIVE/ DAMAGED PART PN MS28778-6,	 PACKING.  FLIGHT CREW COMPLETED ABNORMAL CHECKLIST.  UPON INSPECTION FOUND THAT PACKING AT HYDRAULIC PUMP PRESSURE OUTL	ET FITTING HAD FAILED.  THIS COMPONENT WAS WORKED ON IAW MFG SAFETY COMMUNIQUE , CONTROL NR JAS-SDR-001.  (K)				1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2007102600113	20071026	00113	NM  	2007	10	26	2007FA0000946    	1	20071016	G	5313		STRINGER        			BOEING	727   	727200      	138407E	NM  	PWA   	JT8   	JT8D217C    	52053	NE  					BS940-945	CRACKED         	B			FY4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	705AA					22462				THE AIRCRAFT INPUT FOR 4C CHECK AND CPCP ON SEPT 3, 2007.  DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FO	UND 5 INCH CRACK BOTH ON LT AND RT FUSELAGE STRINGER S18A BETWEEN BS940 AND BS945 ON SEPT 21, 2007.  A PROPOSAL WAS INIT	IALLY SUBMITTED ON SEPT 22.  AFTER REPAIR TO THE STRINGERS, FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORREC	TIVE ACTIONS DETAIL.  (K)			2	L	7	3 	4F	4	F	RT	A3WE    	E9NE				 
2007110200002	20071102	00002	EU  	2007	11	2	2007FA0000947    	1	20071003	G	3233	X110061	ACTUATOR        			DIAMON	DA42  	DA42        	2990004	EU  										MLG	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	240TS	681  				42072				PILOTS WERE UNABLE TO EXTEND RT MLG WITH THE EMERGENCY EXTENSION HANDLE IN FLIGHT.  EMERGENCY SYSTEM OPERATED WITHIN LIM	ITS ON THE GROUND.  UPON REMOVAL, THE ACTUATOR WAS FOUND TO BE VERY DIFFICULT TO MOVE.  ( K)					1	L	7	2 	3I			RT	A57CE   					 
2007102600112	20071026	00112	SO  	2007	10	26	2007FA0000948    	1	20071024	G	3220		CENTERING MECH  	PIPER       		PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520*    	17040	SO  					NLG	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	11	383SA					4608033				UPON TOUCHDOWN AIRCRAFT VEERED LT ABRUPTLY AND DEPARTED RUNWAY SURFACE. GEAR EXTENSION AND INDICATION WERE NORMAL. INVES	TIGATION REVEALED THAT UPON TOUCHDOWN THE NOSE LANDING GEAR HAD FAILED TO CENTER CORRECTLY DURING EXTENSION.					1	L	7	1 	3O	3	O	RT	A25SO   	E8CE				 
2007102600106	20071026	00106	NM  	2007	10	26	2007FA0000949    	1	20071017	G	5610	58935578	WINDSCREEN      			BOEING	737   	7377H4      	1384404	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	CRACKED         	D				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			WP	01	66ZB	2985 				29233				IN CRUISE, 41,000FT (8.5PSID), -60C, ARCING AND SMOLDERING OBSERVED FROM MID BOTTOM OF WINDOW PROPAGATING UP TO TOP FWD 	EDGE OF RT NR 2 SLIDING WINDOW.  WINDOW HEAT, RT, SIDE SWITCH SELECTED OFF. WHILE QRH CONSULTED, AS WINDOW COOLED, CRACK	ING OBSERVED ON OUTER PANE ONLY THROUGHOUT THE WINDOW AREA.  QRH STATES NO FURTHER ACTION REQUIRED DUE OUTER PANE NOT PR	IMARY STRUCTURAL SUPPORT.  FLIGHT CONTINUED AT 41,000 FT FOR NEXT 20 MINS TO TOP OF DESCENT.  LANDING CARRIED OUT NORMAL	LY.  WINDOW ASSY REPLACED..		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007102600107	20071026	00107	NM  	2007	10	26	2007FA0000950    	1	20071017	G	5610	58935578	WINDSCREEN      			BOEING	737   	7377H4      	1384404	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	CRACKED         	D				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			WP	01		2985 				29233				IN CRUISE, 41,000FT (8.5PSID), -60C, ARCING AND SMOULDERING OBSERVED FROM MID BOTTOM OF WINDOW PROPAGATING UP TO TOP FWD	 EDGE OF RT NR 2 SLIDING WINDOW.  WINDOW HEAT, RT, SIDE SWITCH SELECTED OFF. WHILE QRH CONSULTED, AS WINDOW COOLED, CRAC	KING OBSERVED ON OUTER PANE ONLY THROUGHOUT THE WINDOW AREA.  QRH STATES NO FURTHER ACTION REQUIRED DUE OUTER PANE NOT P	IMARY STRUCTURAL SUPPORT.  FLIGHT CONTINUED AT 41,000 FT FOR NEXT 20 MINS TO TOP OF DESCENT.  LANDING CARRIED OUT NORMAL	LY.  WINDOW ASSY REPLACED.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007113000142	20071130	00142	EA  	2007	11	30	2007FA0000951    	2	20070713	G	7261	56G23399	BAFFLE          			FOUND 	FBA   	FBA2C1      	3640103	EA  	LYC   	O540  	TIO540*     	41532	EA  					OIL SUMP	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	796	599  				50				OIL BAFFLE IN SUMP RUBBING ON BOTTOM OF SUMP.  4 OUT OF 6 HOLES CRACKED OUT AROUND MOUNTING AREA.  2 HOLES COMPLETELY WO	RN THROUGH AND STILL HAD PARTS OF BAFFLE UNDER WASHER AND MOUNTING SCREW.  (K)					1	H	7	1 	3O	3	O	NC	A7EA    	E14EA				 
2007110500008	20071105	00008	EA  	2007	11	5	2007FA0000952    	2	20071010	G	8530	AEL85099	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					NR 4	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	602FT	733  				2841196				CYLINDER HAD FAILURE, SEPARATION FROM BARREL AT 733 HRS, NOT INCORPORATED IN AD2006-12-7.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
2007110500009	20071105	00009		2007	11	5	2007FA0000953    	4	20071011	G	2562		BATTERY         	AMERIKING   		PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320*       	41508	EA  					ELT	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	32276					287515109				FOUND ELT BATTERY CASE BULGED ON BOTTOM.  FOUND ALL CONTACTS WITHIN BATTERY COMPARTMENT LOOSE DUE TO HIGH TEMPERATURE (C	OULD SEE WHERE PLASTIC HAD MELTED) COULD NOT DETERMINE WHAT CAUSED THE SHORT.  REPLACED ELT.  (K)					1	L	7	1 	3O	3	O		2A13    	E274				 
2007110500012	20071105	00012		2007	11	5	2007FA0000954    	4	20071011	G	2562		BATTERY         	AMERIKING   		CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470*      	17026	SO  					ELT	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	22GP					58202				DURING ANNUAL INSPECTION FOUND DRIED ALKILINE BATTERY SUBSTANCE ON EXTERIOR OF CASE.  OPEND CASE AND FOUND THAT THE BATT	ERIES, ALKALINE BATTERIES WERE COMING APART AT THE SEAMS AND LEAKING.  CLEANED BATTERY COMPARTMENT AND INSTALLED FRESH S	ET OF BATTERIES.  FUNCTION TESTED OK.  THIS IS THE THIRD SUCH OCCURENCE THIS YEAR. OF ACID LEAK INTO THE TRANSMITTER.  U	NIT HAD TO BE REPLACED.  (K)			1	H	7	1 	3O	3	O		3A21    	E1CE				 
2007110500014	20071105	00014	SO  	2007	11	5	2007FA0000955    	2	20070921	G	8530		CYLINDER HEAD   			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					NR 2	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	711JA					CE478				IN-FLIGHT NR 2 CYLINDER HEAD SEPARATED FROM CYLINDER BASE AT TOP OF SLEEVE. PUSHRODS AND TUBES BENT.  EXHAUST MANIFOLD B	ENT. NOZZLE ASSEMBLY DAMAGED.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007113000143	20071130	00143	CE  	2007	11	30	2007FA0000956    	1	20070919	G	5740	50270025	BRACKET         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520*      	17032	SO  					RT MLG WW	INOPERATIVE     	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	5338C					310R1544				THE RT MAIN LANDING GEAR WOULD NOT RETRACT INTO WHEEL WELL.  PILOT REPORTED LOUD BANG HEARD AFTER RETRACTING OF GEAR.  W	HEN EXTENDING THE GEAR FOR LANDING, THE RT GEAR WOULD NOT INDICATE GREEN BUT WAS VISUALLY CONFIRMED DOWN.  PILOT LANDED 	WITHOUT INCIDENT AND GREEN LIGHT ILLUMINATED UPON TOUCHDOWN.  INSPECTION OF THE RT GEAR FOUND THE TORQUE TUBE SUPPORT BR	ACKET ASSY, PN 50270025, BEARING PULLED LATERALLY FROM BRACKET AND ROD END FOR THE UPLOCK PUSH-PULL TUBE BROKEN OFF AT T	HE TORQUE TUBE ATTACH POINT PN HM4, AND FORWARD TORQUE TUBE ATTACH BOLT, PN NAS146-40, BENT SLIGHTLY.  FAILURE OF THE SU	PPORT BRACKET PN 5027002-5 POSSIBLY DUE TO FATIGUE.  (K)	1	L	7	2 	3O	3	O		3A10    	E5CE				 
2007113000145	20071130	00145	SO  	2007	11	30	2007FA0000957    	2	20071004	G	7414	10500556101	MAGNETO         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	MISOVERHAULED   	B			YD5R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	15	434SR	20   				2557	690898			AIRCRAFT ENGINE RUNNING ROUGH AND BACKFIRING ON FLIGHT TEST.  PILOT RETURNED AND GROUNDED AIRCRAFT FOR MAINTENANCE.  MAI	NTENANCE PERSONNEL PERFORMED INTERNAL INSPECTION OF CONVERTED MAGNETOS TO PRESSURIZATION.  MAGNETO CONVERTED TO PRESSURI	ZED, INSPECTION REVEALED CARBON BRUSHES MISSING ON BOTH MAGNETOS, INTERNAL TIMING WAS WRONG ON ONE OF THE MAGNETOS, WIRE	S WERE CHAFED, EXCESS GREASE WAS FOUND ON ROTOR BRUSH ASSEMBLY.  FURTHER INVESTIGATION OF AIRCRAFT WITH MAGNETO PN 10-55	0556-101 MODIFIED, INSTALLED ON AIRCRAFT FOR TURBO NORMALIZING. 6 ADDITIONAL MAGNETOS EXHIBITED THE SAME CONDITIONS LIST	ED ABOVE.  RECOMMENDATIONS FOR CORRECTION ARE TO CONVERT MAGNETOS IAW PUBLISHED SPECS AND PROCEDURES.  (K)	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007110500013	20071105	00013	EU  	2007	11	5	2007FA0000958    	2	20070913	G	7310	CASC216	REGULATOR       			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					FUEL FLOW	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	07	776MA	891  				447	11298			PILOTS REPORT FELT HEAVY VIBRATION FOR 3 TO 4 SECONDS, THEN HEARD A LOUD BANG FOLLOWED BY LT ENGINE SPOOLING DOWN.  AIRC	RAFT SAFELY LANDED AT AIRPORT.  CONTACTED MFG, WHO DISPATCHED A RESPONSE CREW TO AIRPORT.  FOUND THAT THE FUEL FLOW REGU	LATOR HAD FAILED IN FLIGHT.  (K)				2	L	7	2 	4F	4	F		A12EA   	E2EU				 
2007113000146	20071130	00146	WP  	2007	11	30	2007FA0000959    	2	20071002	G	7314	30708507	PUMP            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT ENGINE FUEL	FAILED          	B			X5ER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	354PM		4254 			015	P74271			RT ENGINE FAILED ON TAKEOFF ROLL JUST BEFORE 80 KNTS IAS.  AIRCRAFT WAS STILL ON GROUND.  FUEL PUMP, FAILED TO PUMP FUEL	.  (K)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007113000147	20071130	00147	SO  	2007	11	30	2007FA0000960    	1	20070906	G	3240		BRAKE           			MAULE 	MX7   	MX7180A     	5460186	SO  	LYC   	O360  	O360*       	41514	EA  					PARK SYS	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	30822					22003C				PARK BRAKE CABLE HANGING ON 90 DEGREE CABIN FITTING COMING THROUGH FIREWALL.  AIRCRAFT BRAKES LOCKED ON WHEN LANDING.  D	ISCONNECTED PARK BRAKE CABLE AND SAFETY WIRED BRAKE LOCK LEVERS ON MASTER CYLINDER IN NEUTRAL/OFF POSITION PLACARD PANEL	 MADE LOG BOOK ENTRY.  (K)				1	H	7	1 	3O	3	O	NC	3A23    	E286				 
2007110500015	20071105	00015	SO  	2007	11	5	2007FA0000961    	1	20070718	G	2140	1386725	HEATER          			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	LEAKING         	B				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			GL	25	650RS		1    			31T8020071				DURING OPERATION OF COMBUSTION HEATER, THE PILOT NOTED JET FUEL ODOR AND SMOKE IN CABIN.  HEATER OPERATION WAS TERMINATE	D, CABIN WAS VENTED.  EMERGENCY WAS DECLARED AND AIRCRAFT LANDED AT NEAREST AIRPORT WITHOUT INCIDENT.  UPON REMOVAL, A F	UEL LEAK WAS NOTED AT COMBUSTION HEAD AND FUEL SOLENOID AREA.  HEATER WAS REPLACED WITH A SERVICEABLE UNIT.  (K)				1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2007113000155	20071130	00155	SO  	2007	11	30	2007FA0000962    	1	20071018	G	3250	3526202	BUNGEE          			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					NLG STEERING	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	56978					287425077				SHORTLY AFTER TAKEOFF, AIRCRAFT WENT INTO SHARP RT TURN.  THE PILOT, BY USING FULL OPPOSITE RUDDER AND AVAILABLE RUDDER 	TRIM, WAS ABLE TO LAND AIRCRAFT SUCCESSFULLY.  INSPECTION DETERMINED THAT THE RT NOSE GEAR STEERING BUNGEE SPRING RETAIN	ER HAD DEPARTED AND THE SPRING WAS EXTENDED FROM THE BARREL ASSY.  THE TURN WAS ALSO EXAGGERATED BY THE LARGE FIN USED O	N THE NOSE WHEEL FAIRING.  AS IT IS DIFFICULT TO EXAMINE THE RETAINER DUE TO THE LOCATION OF THE BUNGEE ASSY UNDER THE E	XHAUST SYSTEM, IT CAN NOT BE DETERMINED IF THE BACK SIDE OF THE RETAINER IS BEING WORN OR CORRODED.  THIS PART IS ONLY H	ELD IN PLACE BY A FEW TWISTS OF SAFETY WIRE.  IT IS SUGGESTED THAT THE MFG LOOK AT THIS AS A MAJOR SAFETY ISSUE AND EITH	1	L	7	1 	3O	3	O		2A13    	E274				 
2007113000157	20071130	00157	CE  	2007	11	30	2007FA0000963    	1	20071018	G	3222	07436062	FITTING         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					NLG STRUT	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	6025D					18281830				LOWER STRUT SUPPORT FITTING CLAMPING RING CENTER BORE IS NOT CENTERED.  THIS CAUSES THE STEERING COLLAR AND LOWER STRUT 	SUPPORT TO CHAFE AND FOR METAL TO METAL CONTACT TO OCCUR.  HAVE TRIED TWO OTHER NEW LOWER STRUT SUPPORT FITTING RESULTIN	G WITH METAL TO METAL CHAFING.  INITIALLY CONTACTED MFG AND REPORTED THE PROBLEM REVEALING NUMEROUS IDENTICAL PARTS HAVE	 THE SAME DEFECT.  RECOMMEND THAT CONTACT BE MADE WITH MFG AND TO MEASURE FOR PROPER THICKNESS OF THE RING ON THE LOWER 	STRUT SUPPORT FITTING.  (K)		1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2007120400005	20071204	00005	SO  	2007	12	4	2007FA0000964    	1	20071017	G	2822	35328803	PUMP            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					FUEL BOOST	MALFUNCTIONED   	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NM	02	515MS	2750 				2842157				REPORTED ENGINE QUITTING DURING NORMAL CRUISE, PROBLEM ASSOCIATED WITH FUEL SYSTEM, ONCE ELECTRIC FUEL PUMP TURNED ON EN	GINE WOULD RUN NORMAL, FUEL PRESS READINGS CONFIRMED FUEL STARVATION PROBLEM, INITIAL INSPECTIONS FAILED TO FIND A PROBL	EM & COULD NOT BE DUPLICATED, REPLACED EDP WITH NEW & FLEW ACFT, PROBLEM REOCCURRED & APPEARED TO BE ISOLATED TO THE RT 	SIDE FUEL TANK SELECTION, REMOVED FUEL LINE AT CARB & PUMPED FUEL USING BOOST PUMP, MONITORED FLOW RATE FOR BOTH RT AND 	LT TANKS, INSTALLED VACUUM GAUGE IN SYSTEM AT GASCOLATOR AND MONITORED AMOUNT OF SUCTION CREATED FOR BOTH THE LT & RT, P	ROBLEM FINALLY DUPLICATED WHILE MONITORING & PUMPING FUEL, FOUND PROBLEM WAS NOT ISOLATED TO ONE SIDE BUT WOULD OCCUR ON	1	L	7	1 	3O	3	O		2A13    	E274				 
2007113000181	20071130	00181	EA  	2007	11	30	2007FA0000966    	2	20070810	G	8530	LW15322	VALVE           								LYC   	O360  	O360E1A6    	41514	EA  					CYLINDER	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03							RL15377T			DURING ASSEMBLY OF THE ENGINE AFTER MAJOR OVERHAUL, ONE OF THE FACTORY NEW CYLINDERS (PN LW15322) HAD A DIFFERENT INTAKE	 VALVE INSTALLED (PN 73938), AND THE CORRECT VALVE PN LW15314 WAS INSTALLED BY THE CYLINDER SHOP. THIS CYLINDER WAS FACT	ORY NEW.  (K)									3	O			E286				 
2007110500002	20071105	00002	GL  	2007	11	5	2007FA0000967    	1	20071031	G	3150	M835366022M	RELAY           			BOMBDR	BD700 	BD7001A10   	1390006	GL  										MASTER CAUTION	FAILED          	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	09		1690 				9114				MASTER CAUTION RELAY (WIRING DIAGRAM 31-52-00 SHEET 1 - K28, LOCATED ON CIRCUIT CARD DB5 OF JUNCTION BOX 4 FAILED CAUSIN	G BOTH MASTER CAUTION WARNING ANNUNCIATORS TO STAY ILLUMINATED - NO RESET AVAILABLE. THIS IS A SINGLE POINT OF FAILURE F	OR THE WARNING/CAUTION CONTROL SYSTEM. (3) INTEGRATED AVIONICS COMPUTERS FEED THIS MASTER CAUTION RELAY - SAME WITH THE 	MASTER WARNING.  AFTER DOING A LIMITED INDEPENDENT SURVEY, I DETERMINED THAT THIS HAS OCCURRED ON SEVERAL OTHER AIRCRAFT	.		2	L	7	2 	4F			RT	T00003NY					 
2007120400050	20071204	00050	SO  	2007	12	4	2007FA0000968    	1	20071102	G	2510	110744701	INERTIA REEL    	PIPER       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	SEAT HARNESS	SEVERED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8440M	8718 				288216002	L1042639A	A61404		PILOTS SHOULDER HARNESS INERTIA REEL LOCKED UP, UPON EXAMINATION THE METAL GUIDE WHICH SURROUNDS THE FABRIC AND GUIDES I	T ONTO THE REEL, HAD RUBBED AGAINST THE CENTER SHAFT OF THE REEL ITSELF.  THIS OVER TIME REDUCED THE DIAMETER OF THE SHA	FT UNTIL IT FAILED.				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007120400061	20071204	00061		2007	12	4	2007FA0000969    	1	20071029	G	6510	538715	SHAFT           																	TAIL ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										FINE TRANSVERSE CRACK(S) LOCATED NEAR THE CENTER PORTION OF PART.																			 
2007120400063	20071204	00063		2007	12	4	2007FA0000970    	1	20071029	G	6510	538715	SHAFT           																	TAIL ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										FINE TRANSVERSE CRACK(S) LOCATED NEAR THE CENTER PORTION OF PART.																			 
2007120400048	20071204	00048	CE  	2007	12	4	2007FA0000971    	1	20071031	G	3260	41EN16	SQUAT SWITCH    			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LEFT	FAILED          	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	11	8HQ					RJ50				PILOTS REPORTED THAT THE THRUST REVERSER ARM LIGHTS WERE ILLUMINATED IN FLIGHT. PILOTS LANDED AT LZU MAINTENANCE FOUND A	 FAULTY LT GROUND SAFE SWITCH. MAINTENANCE REPLACED SWITCH WITH NEW UNIT AIRCRAFT CHECKED GOOD.					2	H	7	2 	4F	4	F	RT	A16SW   	E1NE				 
2007113000152	20071130	00152	EA  	2007	11	30	2007FA0000974    	2	20071031	G	7414	K3975	COIL            	SLICK       		CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					RT MAGNETO	OPEN            	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	07	2378X	1168 			98060921	T20608023	L1003761A			PILOT REPORTED RT MAGNETO FAILED WHEN CHECKED DURING RUN UP. FOUND COIL HAD OPEN CIRCUIT WHEN CHECK IAW TABLE SEVEN IN U	NISON'S 4300/6300 SERIES MM P/N L-1363C.					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2007113000184	20071130	00184	GL  	2007	11	30	2007FA0000975    	1	20071031	G	3150	M835366022M	RELAY           			BOMBDR	BD700 	BD7001A10   	1390006	GL  											FAILED          	C				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			NM	09	999YY	1690 				9114				MASTER CAUTION RELAY (WIRING DIAGRAM 31-52-00 SHEET 1 - K28), LOCATED ON CIRCUIT CARD DB5 OF JUNCTION BOX 4 FAILED CAUSI	NG BOTH MASTER CAUTION WARNING ENUNCIATORS TO STAY ILLUMINATED - NO RESET AVAILABLE. THIS IS A SINGLE POINT OF FAILURE F	OR THE WARNING/CAUTION CONTROL SYSTEM. THREE INTEGRATED AVIONICS COMPUTERS FEED THIS MASTER CAUTION RELAY - SAME WITH TH	E MASTER WARNING.  AFTER DOING A LIMITED INDEPENDENT SURVEY, I DETERMINED THAT THIS HAS OCCURRED ON SEVERAL OTHER AIRCRA	FT.		2	L	7	2 	4F			RT	T00003NY					 
2007113000125	20071130	00125	WP  	2007	11	30	2007FA0000976    	2	20071029	G	7250	30606266	ROTOR           			ISRAEL	1125  	ASTRASPX    	4500205	EU  	ALIDSG	TFE731	TFE7313AR   	 	WP  					LPT3	SEPARATED       	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	07	400CP					131	113211			IAW SERVICE BULLETIN TFE731-72-5175.  BLADE SEPARATION ON ONE LPT3 BLADE AS LISTED IN TABLE 1 OF S/B 72-5175.						2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2007120400136	20071204	00136	EA  	2007	12	4	2007FA0000979    	2	20071018	G	7322		CONTROL ARM     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					CARB HEAT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	423FP					40FC023				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE.  (K)					1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2007120400137	20071204	00137	SO  	2007	12	4	2007FA0000980    	1	20071019	G	7820	E362000	MUFFLER         			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320B2B     	41508	EA  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	98SA	996  				187609088	L1333839A			THE TAILPIPE CRACKED AWAY FROM THE SHELL.  THERE ARE NO STRAPS WELDED FROM THE PIPE TO THE SHELL LIKE SOME OTHER MUFFLER	S.  THE METAL FAILED, NOT THE WELD.					1	H	7	1 	3O	3	O		1A2     	E274				 
2007120400139	20071204	00139	CE  	2007	12	4	2007FA0000981    	1	20071103	G	3710	RV05268	RELIEF VALVE    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					PNEUMATIC SYS	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	1232Y	3    				208B0566				RELIEF VALVE FOR BLEED AIR PNEUMATIC SYSTEM END WASHER AND CAP SEPARATED FROM VALVE AND LAYING IN BOTTOM OF COWLING.  SU	SPECT RIVET HOLDING PARTS ON IS TOO SOFT.  THIS IS THE THIRD VALVE TO FAIL LIKE THIS ON DIFFERENT AIRCRAFT IN THE LAST M	ONTH. AND ALL WERE NEW WITH LESS THAN 70 HOURS TIME IN SERVICE. (K)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007120400142	20071204	00142	SO  	2007	12	4	2007FA0000982    	1	20071028	G	3233	HM6	BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					RT MLG ACTUATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	108SG	2160 				24149				RT OB HEIM BEARING BROKE AT THREADS NEXT TO JAM NUT ON ACTUATOR ROD DURING TAKEOFF ROLL W/RESULTANT GEAR COLLAPSE. INCRE	ASE SIZE AND STRENGTH OF PART.  (K)					1	L	7	1 	3O	3	O		1A15    	E295				 
2007120400143	20071204	00143	CE  	2007	12	4	2007FA0000983    	1	20071022	G	3010	80713	CONTROLLER      			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					STAB DEICE	INOPERATIVE     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	415NP					024				REPLACED HORIZONTAL STAB HEAT CONTROLLER.  AFTER CHANGING CONTROLLER AIRCRAFT STILL HAD FAULT IN SYSTEM. T/S FURTHER DET	ERMINED REPAIRED CONTROLLER WAS NO GOOD.  CONTROLLER SHOWED A FAULT IN T8.  INSTALLED ANOTHER CONTROLLER SYSTEM CHECKED 	GOOD.  (K)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007120400164	20071204	00164	CE  	2007	12	4	2007FA0000986    	1	20071008	G	2910	165580001135	LINE            			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1A    	41514	EA  					HYD SYSTEM	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5246M	6712 				MC564				PILOT REPORTED HAVING TO SERVICE BRAKE HYDRAULIC RESERVOIR AND/OR RT SIDE OF THE BRAKES VERY SOFT.  DURING INSPECTION, F	OUND HYDRAULIC FLUID ON WIRE BUNDLE FORWARD OF COPILOTS RT RUDDER PEDAL.  CLEANED LINE AND LT LINE SIT FOR A COUPLE DAYS	, WHILE DOING AN INSPECTION ON THE REST OF THE AIRCRAFT.  FOUND HYDRAULIC FLUID ON LINE.  REMOVAL OF THE LINE REVEALED A	 WORN/CHAFED SPOT APPROX 12 INCHES TO THE LT OF THE B-NUT WHERE IT ATTACHES TO THE BULKHEAD FITTING FROM THE RESERVOIR. 	 DID NOT SEE THE CAUSE OF THE CHAFED AREA ON THE TUBE.  SUSPECT AIRFRAME VIBRATION CAUSED THE LINE TO VIBRATE.  RECOMMEN	D THAT ALL LINES ARE CHECKED FOR CLEARANCE FROM AIRFRAME STRUCTURE OR OTHER LINES.  (K)	1	L	7	1 	3O	3	O		A1CE    	1E10				 
2007120400165	20071204	00165	CE  	2007	12	4	2007FA0000987    	1	20071101	G	5312	45A3490111	BULKHEAD        			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BS 329	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	940VA					RK197				WHILE PERFORMING AN A-C INSPECTION FOUND RT AFT FUSELAGE BLEED AIR LINE ATTACH BRACKET PULLED FROM FUSELAGE BULKHEAD RES	ULTING IN A CRACK IN THE BULKHEAD AT FRAME STATION 329.92.  RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS  CRACK HAS BEEN 	FOUND ON BOTH SIDES OF THE AIRCRAFT.(K)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007120400166	20071204	00166	CE  	2007	12	4	2007FA0000988    	1	20071031	G	5551	45A2100291	PIVOT           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	940VA					RK197				WHILE PERFORMING AN A-C INSPECTION FOUND 8 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A	2118311 ON THE BOTTOM OF THE HORIZONTAL STABILIZER.  IT IS SUSPECTED THAT THE LOOSE RIVETS WERE CAUSED BY FATIGUE AND AG	E.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007120400103	20071204	00103	SO  	2007	12	4	2007FA0000989    	1	20071106	G	3211		LANDING GEAR    			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					MAINS	WORN            	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	07	22HW	5124 	893  			30791				PART (A) OF AD 77-13-21 REQUIRES INSPECTION OF LANDING GEAR EVERY 1000 HRS IAW SL 782.  AIRCRAFT EXPERIENCED A COLLAPSED	 RT MLG FOLLOWING A SCENARIO THAT IS IDENTIFIED IN SL 782.  THIS SCENARIO INCLUDES A POPPED LANDING GEAR MOTOR CIRCUIT B	REAKER RESULTING IN A FAILED MLG EXTENSION, FOLLOWED BY A MANUAL GEAR EXTENSION.  INVESTIGATION FOUND MANY OF THE PARTS 	IDENTIFIED IN SL 782 WERE WORN AND REQUIRED REPLACEMENT.  PART (A) OF THE AD 77-13-21 HAD BEEN COMPLETED 893 HRS AND 12 	YEARS AGO.  OWNERS AND OPERATORS SHOULD CONSIDER COMPLYING WITH AD 77-13-21 PART (A) MORE OFTEN THAN THE 1000 HRS AS REQ	UIRED.  AD 77-13-21 DOES NOT CONTAIN A CALENDAR REQUIREMENT.	1	L	7	2 	3O	3	O		A1EA    	1E12				 
2007120400130	20071204	00130	SO  	2007	12	4	2007FA0000990    	1	20070130	G	3230	452729	BEARING         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					ROD END	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	406RB	6700 				32R7880009				NOSE GEAR EXTENDED SUDDENLY AND UNCOMMANDED IN FLIGHT,  EXAMINED AND FOUND CYLINDER ROD END TO NOSE GEAR RETRACT ASSY WA	S BROKEN.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
2007120400167	20071204	00167	CE  	2007	12	4	2007FA0000995    	1	20071107	G	2420	6041H190	RELAY           			BEECH 	200   	A200        	1152921	CE  										RT STARTER GEN	MELTED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	99						BC27				RT STARTER GENERATOR RELAY P/N: 6041H190 MELTED AT BUSS BAR CONNECTION.						1	L	7	2 	4T				A24CE   					 
2007120400110	20071204	00110	CE  	2007	12	4	2007FA0000996    	1	20071107	G	5753	086210057	TUBE            			CESSNA	414   	414A        	2075907	CE  										TE FLAPS	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	27		7707 								DURING FLAP EXTENSION THE RT SIDE FLAPS RETRACTED SUDDENLY LEAVING THE LT FLAPS DOWN.  FOUND THE PUSHROD TUBE CONNECTING	 THE IB AND MIDDLE FLAP BELLCRANK TO HAVE FAILED AT THE OB END OF THE TUBE.  THE TUBE APPEARS TO HAVE BEEN ABOUT 60 PERC	ENT CRACKED THROUGH THE DIAMETER FOR SOME TIME, POSSIBLY SINCE NEW.  THIS FAILURE OCCURRED JUST BELOW THE LOCK NUT WHICH	 SECURES THE ROD END TO THE TUBE, AND THE FAILED AREA IS IN THE THREADED PORTION OF THE TUBE MAKING IT DIFFICULT OR IMPO	SSIBLE TO SEE A DEVELOPING CRACK.		1	L	7	2 	3O				A7CE    					 
2007120400070	20071204	00070	SO  	2007	12	4	2007FA0000997    	1	20071105	G	3220	452729	BEARING         			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG ROD END	FAILED          	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	01	83213	6282 				32R8113035				WHILE IN FLIGHT THE NOSE GEAR RETRACT CYLINDER PISTON ROD END FAILED, CAUSING IMMEDIATE EXTENSION OF THE NOSE GEAR.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
2007120400174	20071204	00174	GL  	2007	12	4	2007FA0000999    	1	20071108	G	2421		BRUSHES         	CESSNA      		CIRRUS	SR    	SR20        	05628AJ	GL  	LYC   	IO360 	IO360L2A    	 	EA  					ALTERNATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1180	494  			A180062	1576	L3328651E			DURING FLIGHT, PILOT REPORTED LOW VOLTAGE INDICATION.  RESET ATTEMPTS WERE UNSUCESSFUL.  PILOT RETURNED TO STATION. ALTE	RNATOR BRUSHES FOUND TO BE WORN BEYOND USE.					1	L	7	1 	3O	3	O	NT	A00009CH	1E10				 
2007120400173	20071204	00173	EU  	2007	12	4	2007FA0001000    	1	20071108	G	3320	6178A	POWER SUPPLY    			HAWKER	BAE125	BAE125700B  	7450007	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN LIGHTING	BURNED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	107LT					257146				DISCREPANCY WAS CABIN INDIRECT LIGHTING IS INTERMITTENT. FOUND SHORTED WIRING AT AFT LT SIDE VALANCE, 2 BURNED POWER SUP	PLIES AND SEVERAL CRACKED LAMP FIXTURES. CUSTOMER STATED THIS IS THE 3RD TIME THE POWER SUPPLIES WERE FOUND BURNED.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007110900245	20071109	00245	CE  	2007	11	9	2007FA0001001    	1	20071109	G	2750	040010740	CONTROL CABLE   			CESSNA	150   	150E        	2071812	CE  										TE FLAP	FRAYED          	B				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			WP	07	31ER	6487 	98   			15061072				ASSYMETRIC DEPLOYMENT OF FLAPS ON FINAL APPROACH.  LOUD SNAP HEARD NOVING FLAPS FROM 30 TO 40 DEGREES. MAINTENANCE FOUND	 THE LEFT FLAP EXTEND CABLE BROKEN AT THE OUTBOARD PULLEY.					1	H	7	1 	3O				3A19    					 
2007121300243	20071213	00243	SW  	2007	12	13	2007FA0001002    	1	20071106	G	5520		TORQUE TUBE     			SWRNGN	SA227 	SA227*      	       	SW  										LT ELEVATOR	SHEARED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		6734 				858				DURING A ROUTINE PHASE INSPECTION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE LT ELEVATOR PIVOT PIN ON THE TORQUE TUBE A	SSEMBLY PN 27-44026-007 WAS SHEARED. INITIAL INSPECTION REVEALED CORROSION/RUST AND EXTENSIVE PITTING IN THE PIN. THIS P	IN IS (1) OF (3) IN A LINEAR LINE ATTACHING THE ELEVATOR TO THE AIRCRAFT STABILIZER. THIS AIRCRAFT IS NORMALLY LOCATED O	UTSIDE EXPOSED TO THE WEATHER ELEMENTS NEAR SALT AIR/RAIN. THIS PART ALSO REVEALED A CORRODED VTA BEARING PN VTA04270.  	A VISUAL GVI IN THE SUSPECT AREA CAN EASILY INDICATE A PROBLEM FOR CORROSION.  RECOMMENDATION: (1) GVI OF TORQUE TUBE AS	SEMBLY IF THE AIRCRAFT IS STORED EXPOSED TO SALT AIR OR RAIN ON A ROUTINE BASIS. (2) GVI OF THE VTA BEARING.   IPC 27-30	2	L	7	2 	4T			RT	A5SW    					 
2007120500018	20071205	00018	EA  	2007	12	5	2007FA0001007    	1	20071031	G	3246	269A3245919	SKID            			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C30      	03013	GL  					LT MLG	DAMAGED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	63	411HU	122  				0040				UPON LANDING THE HELICOPTER IN A SLIGHT FWD AND LT MOTION IN FLAT GRASS AREA HEARD SLIGHT CLICK OR CLUNK, PIC DIDN`T SEE	 ANY DAMAGE, PICKED UP AIRCRAFT TO A HOVER AND GROUND CREW SAW FWD END OF LT SKID TUBE HANGING BELOW THE AIRCRAFT.  (K)					1	G	7	1 	3U	3	U	0	4H12    	E1GL				 
2007120500019	20071205	00019	CE  	2007	12	5	2007FA0001008    	1	20071029	G	2612	991203611	FIRE LOOP       			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					NR 1 ENGINE	FAILED          	D				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			CR	CRUISE         	1			GL	09	189WW					5605069				NR 1 ENGINE FIRE LOOP FAILED, CAUSING THE NR 1 ENGINE FIRE INDICATOR IN COCKPIT TO ERRONEOUSLY INDICATE A FIRE.  CREW FI	RED BOTH FIRE EXTINGUISHERS FOR THE ENGINE WHICH DID NOT EXTINGUISH THE FIRE INDICATOR.  THE CREW THEN DECLARED AN IN-FL	IGHT EMERGENCY.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007120500020	20071205	00020	SO  	2007	12	5	2007FA0001009    	1	20071003	G	3230	757496	PIN             	WIEBEL      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					LOWER CLEVIS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	31NW	5912 				318152139				EMERGENCY GEAR EXTENSION PUMP LOWER CLEVIS PIN BROKEN, FAILURE FOUND ON 2 SIMILAR AIRCRAFT.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007120500021	20071205	00021	SO  	2007	12	5	2007FA0001010    	1	20071101	G	7810	PA18ESA	PIPE            			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O360  	O360A1A     	41514	EA  	MCAULY	1A200	1A200FA     	GL  	EXHAUST	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7066B					185140	L76336			LEADING EDGE EXHAUST SYSTEM INSTALLED BY STC SA02200AK FAILED AT THE SAIL PIPE TO MUFFLER WELD.  SYSTEM HAS 36 HOURS SIN	CE NEW.  (K)					1	H	7	1 	3O	3	O		1A2     	E286	5	N	P874	 
2007120500022	20071205	00022	SO  	2007	12	5	2007FA0001011    	2	20071025	G	8550	SA56250	DRAIN           			BBAVIA	7     	7EC         	2110120	SW  	CONT  	O200  	O200*       	17020	SO  					ENGINE OIL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	274AC					101407				INSTALLED QUICK DRAIN VALVE (OIL) ON NEW AIRCRAFT/ ENGINE.  AIRCRAFT FLEW APPROX 1 HR , INITIAL FLIGHT TEST.  VERY MINUT	E OIL LEAK WAS NOTED FROM OIL QUICK DRAIN VALVE.  REMOVED VALVE TO FIND VALVE SNAP RING IN OIL DRAINED FROM ENGINE, ALSO	 FOUND O-RING SPLIT.  NOTE:  NO DAMAGE TO ENGINE OCCURRED. (K)				1	H	7	1 	3O	3	O		A759    	E252				 
2007120500024	20071205	00024	CE  	2007	12	5	2007FA0001012    	1	20071030	G	2140	HYLZ50336001	TRANSISTOR      	BARBERCOL   		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					TEMP CONTROL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	200CJ				377OK	BB143				PC BOARD IN ASSY PN HYLZ50336-001 HAD FAILURE, BURNED/ OVERHEATED TRANSISTOR.  NOTE: FAN IN ASSY WAS WORKING.  PC BOARD 	PN HYLZ 105-001.  (K)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007120500026	20071205	00026	CE  	2007	12	5	2007FA0001013    	1	20071105	G	2612	991203611	FIRE LOOP       			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					NR 1 ENGINE	FAILED          	D				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			CR	CRUISE         	1			EA	09	189WW					5605069				NR 1 ENGINE FIRE LOOP FAILED CAUSING THE NR 1 ENGINE FIRE INDICATOR IN COCKPIT TO ERRONEOUSLY INDICATE A FIRE.  CREW FIR	ED BOTH FIRE EXTINGUISHERS FOR THE ENGINE WHICH DID NOT EXTINGUISH THE FIRE INDICATOR.  THE CREW THEN DECLARED AN IN-FLI	GHT EMERGENCY.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007120500027	20071205	00027	SO  	2007	12	5	2007FA0001015    	1	20071105	G	2797	061E1P1E1	CONNECTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					RT FLAP RESOLVER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	507QS					625				BACK SHELL IS BROKEN/CRACKED AND SEPARATED FROM CONNECTOR PLUG ASSY.  POSSIBLE CAUSE IS WIRE BUNDLE TO CONNECTOR PLUG ST	RESSES AND PULLING ON BACK SHELL.  BACK SHELL IS MADE ON PLASTIC NOT METAL. IF BACK SHELL WAS MADE OF METAL IT WOULD HOL	D UP AS A STRAIN RELIEF FOR THE ATTACHING WIRE BUNDLE.  IF A PLASTIC BACK SHELL IS CONTINUED TO BE USED, WIRE BUNDLE SHO	ULD ALLOW SLACK ENOUGH NOT TO STRAIN THE STRAIN RELIEF.  A METAL BACKSHELL IS THE MORE POSITIVE FIX FOR THIS PROBLEM.  (	K)		2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2007120500028	20071205	00028	EU  	2007	12	5	2007FA0001016    	1	20071106	G	5330		SKIN            			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	WORN            	B			UOHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	942MS	6444 				5498				RT AND LT FUSELAGE SKIN AT TAILBOOM ATTACH BULKHEAD.  FOUND WORKING RIVETS ON BOTH SIDES. (40) FOUND SKIN UNDER WORKING 	RIVETS WORN .018. ASB 05-00-42 AS FACTOR.  FUSELAGE SENT TO A REPAIR FACILITY FOR SKIN REPLACEMENT.  (K)					1	G	7	2 	3U	3	U		H11EU   	E4CE				 
2007120500029	20071205	00029	SW  	2007	12	5	2007FA0001017    	1	20070830	G	8120	635630	TURBOCHARGER    			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	231GZ	959  				250253	8223022R			FOUND APPROX 1.25 INCH CRACK IN TURBO CHARGER HOUSING BELOW EXHAUST INLET AT WELD.  (K)						1	L	7	1 	3O	3	O		2A3     	E8CE				 
2007120500030	20071205	00030	EU  	2007	12	5	2007FA0001018    	1	20071024	G	2820		CONTROL UNIT    			AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CROSSFEED	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	47EG	903  			B72992	154				FUEL LEAKING FROM CENTRAL LB CROSSFEED UNIT AND DRAIN TUBE CAP BROKEN. REF MFG SERVICE ADVISORY FSA900EX-EASY-28-10-03-R	1.  (K)					2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2007120500034	20071205	00034	SO  	2007	12	5	2007FA0001019    	2	20071113	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	69RP	937  				TE766	282253R			CRACKED CYL HEAD BEHIND INJECTOR BETWEEN FIN NR 12, NR 3.  DEFECTIVE MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		3A16    	E8CE				 
2007120500035	20071205	00035	SO  	2007	12	5	2007FA0001020    	2	20071113	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					NR 3	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	69RP	937  				TE766	282253R			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECTIVE MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		3A16    	E8CE				 
2007120500036	20071205	00036	SO  	2007	12	5	2007FA0001021    	2	20071113	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	69RP	937  				TE766	282253R			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  DEFECTIVE MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		3A16    	E8CE				 
2007120500037	20071205	00037	SO  	2007	12	5	2007FA0001022    	2	20071113	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	69RP	937  				TE766	2822253R			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  DEFECTIVE MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		3A16    	E8CE				 
2007120500038	20071205	00038	SO  	2007	12	5	2007FA0001023    	2	20071113	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	69RP	937  				TE766	282253R			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  DEFECTIVE MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		3A16    	E8CE				 
2007120500039	20071205	00039	SO  	2007	12	5	2007FA0001024    	2	20071108	G	8530	TISN712BCA	CYLINDER HEAD   			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4165G	677  				402B1212	510771			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR1, NR3.  DEFECT IN MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007120500040	20071205	00040	SO  	2007	12	5	2007FA0001025    	2	20071108	G	8530	TISN712BCA	CYLINDER HEAD   			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4165G	677  				402B1212	510771			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  DEFECT IN MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007120500041	20071205	00041	SO  	2007	12	5	2007FA0001026    	2	20071108	G	8530	TISN712BCA	CYLINDER HEAD   			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4165G	677  				402B1212	510771			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  DEFECT IN MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007120500042	20071205	00042	SO  	2007	12	5	2007FA0001027    	2	20071108	G	8530	TISN712BCA	CYLINDER HEAD   			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4165G	677  				402B1212	510771			CRACKED CYL HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007120500043	20071205	00043	SO  	2007	12	5	2007FA0001028    	2	20071107	G	8530	TISN712BCA	CYLINDER HEAD   			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4165G	677  				402B1212	510771			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR1, NR3.  DEFECT IN MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007120500044	20071205	00044	SO  	2007	12	5	2007FA0001029    	2	20071113	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	69RP	937  				TE766	282253R			CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3.  DEFECTIVE MFG PROCESS.  (K)						1	L	7	2 	3O	3	O		3A16    	E8CE				 
2007120500046	20071205	00046	CE  	2007	12	5	2007FA0001030    	1	20071106	G	5740	5012007716	SUPPORT BRACKET 			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLGWW	CRACKED         	B			HSRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	28KP	6171 				LJ845				DRAG LEG SUPPORT BRACKETS FOUND CRACKED ON BOTH LT AND RT SIDES DURING A ROUTINE INSPECTION.  MOST LIKELY FATIGUE CRACKS	 OR A ROUGH LANDING.  (K)					1	L	7	2 	3T	3	T		3A20    	E2NE				 
2007120500047	20071205	00047	CE  	2007	12	5	2007FA0001031    	1	20071106	G	5740	5012007717	SUPPORT BRACKET 			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG WW	CRACKED         	B			HSRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	28KP	6171 				LJ845				DRAG LEG SUPPORT BRACKETS FOUND CRACKED ON BOTH LT AND RT SIDES DURING A ROUTINE INSPECTION.  MOST LIKELY FATIGUE CRACKS	 OR A ROUGH LANDING.  (K)					1	L	7	2 	3T	3	T		3A20    	E2NE				 
2007120500049	20071205	00049	CE  	2007	12	5	2007FA0001032    	1	20071022	G	2120	354021	DUCT            			RKWELL	NA265 	NA26560     	7630106	CE  	PWA   	JT12  	JT12A8      	52042	NE  					CABIN PRESSURE	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	59K					30682	P672922NB			ATTACHING SLEEVE SLID OFF OF DUCT CAUSING LOSS OF PRESSURIZATION.  EMERGENCY PRESSURIZATION FUNCTIONED NORMALLY.  CLAMPS	 TIGHTENED TOO TIGHT AND DEFORMED FIBERGLASS DUCT.  RECOMMEND METAL SLEEVE BE INSTALLED TO ALLEVIATE DEFORMATION. (K)					2	L	7	2 	4J	4	J	RT	A2WE    	1E9				 
2007120500050	20071205	00050	SO  	2007	12	5	2007FA0001033    	1	20071106	G	5312	49099	BULKHEAD        			LUSCOM	8     	8F          	8190114	SO  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9937B	2115 				S41				DURING AN ANNUAL INSPECTION, FOUND AFT FUSELAGE BULKHEAD CRACKED AT TOP OF CUTOUT FOR ELEVATOR HORN.  50 PERCENT.  THIS 	IS WHERE THE VERTICAL AND HORIZONTAL STABILIZERS ATTACH.  THIS AREA IS HIDDEN BEHIND THE WEB OF THE VERTICAL STAB AFT SP	AR AND WAS FOUND WHEN COMPONENTS WERE REMOVED TO REPAIR FWD SPAR (FOUND CRACKED) OF THE HORIZONTAL STAB.  THE VERTICAL S	TAB IS NOT OF THE ROUNDED TIP TYPE, HAS AN ALUMINUM FWD ATTACHMENT AND STEEL AFT ATTACHMENT.  (K)			1	H	7	1 	3O	3	O		A694    	E274				 
2007120500051	20071205	00051	CE  	2007	12	5	2007FA0001034    	1	20070913	G	5230	1211673323	DOOR            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					RT AFT CARGO	MISRIGGED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	168JS	154  				T20608735				MM (52-30-00 PG 201), (THE AFT DOOR IS HINGED AT FUSELAGE STA 112 AND IS A STRUCTURAL, LOAD CARRYING MEMBER WHEN CLOSED 	AND LOCKED).  REMOVED AFT CARGO DOOR ROYALITE AND TRIM TO GAIN ACCESS TO  LWR AFT CABIN LOWER HOOK ADJUSTMENT ROD.  THIS	 WAS DUE TO A CLUB MEMBER IMPROPERLY CLOSING THE DOOR AND BENDING THE ROD.  THE PERSON FAILED TO PULL-DOWN RED HANDLE WH	EN CLOSING DOOR AND JAMMED THE LOWER HOOK.  HOWEVER, FOUND THE ADJUSTMENT RODS LOOSE(UPPER AND LOWER) AND WOULD EASILY T	URN, INCLUDING THE TURNBUCKLES, UPPER AND LWR.  THIS WAS DUE TO THE JAM NUTS FOR THE TURNBUCKLES LOOSE AND/OR BACKED OFF	 TO WHERE THERE WERE BOTTOM OF THREADS ON THE ADJUSTMENT RODS FOR THE HOOKS.  IF LEFT UNADDRESSED COULD CAUSE PREVENTING	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2007120500053	20071205	00053	CE  	2007	12	5	2007FA0001035    	1	20071114	G	2820	0500106326	LINE            			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470*       	17026	SO  					FUEL SYS	MISROUTED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	6WH	2365 				18052492				(2) AILERON CABLES, (1) FLAP CABLE AND THE FUEL LINE ARE ALL ROUTED THROUGH THE LT LOWER AFT DOOR POST AREA.  THE FUEL L	INE IS PROTECTED BY A PLASTIC SLEEVE BUT THE CABLE WORE THROUGH THE SLEEVE AND WAS WEARING INTO THE FUEL LINE.  THE LINE	 IS APPROX 20 INCHES LONG WITH (4) BENDS.  SUGGEST A (1) TIME INSPECTION IN CASE OTHER AC MIGHT HAVE THIS PROBLEM.  (K)				1	H	7	1 	3O	3	O		5A6     	E273				 
2007120500054	20071205	00054	CE  	2007	12	5	2007FA0001036    	1	20071108	G	5610		WINDSHIELD      			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					COCKPIT	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	03	93TX					7500099				AC IN FLIGHT AND AT CRUISE ALTITUDE THE LT WINDSHIELD HEAT FAILED, A VISABLE SHORT OR ARCING AREA WAS SEEN, CONDITION OF	 UNIT MATCHED WITH SWITCH (OFF) 30 SEC LATER WINDSHIELD CRACKED IN A SPIDER WEB FASHION.  AC LANDED IN STL.  WINDSHIELD 	REPLACED BY SERVICE CENTER WITH A NEW STYLE WINDSHIELD PN 139731-1 (9914380-13).				2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2007120500055	20071205	00055		2007	12	5	2007FA0001037    	1	20071101	G	3246		BEARING         																	NLG WHEEL	WRONG PART      	B			SCSZ	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33					1170					ON OCT 10, INFORMED BY TECH THAT THEY HAD AN INSTALLED NOSEWHEEL (PN 277A6000-851, SN 1170) ON AIRCRAFT, WITH A WRONG BE	ARING INSTALLED.  IAW STS, THE ERROR WAS ONLY DISCOVERED AFTER THE WHEEL HAD BEEN INSTALLED, BUT BEFORE THE AC WAS RELEA	SED TO SERVICE.  REPORTED ERROR WAS THAT THE INNER BEARING DIAMETER  WAS 11MM TOO WIDE. ONCE WHEEL WAS RETURNED TO SHOP,	 INVESTIGATION SHOWED THAT A WRONG BEARING HAD BEEN INSTALLED.  INSTEAD OF THE CORRECT BEARING, A MD80 BEARING HAD BEEN 	INSTALLED.  INVESTIGATION OF THE ASSY PROCESS REVEALED NO DISCREPANCIES IN THE PROCESS ITSELF.  IT HAS THEREFORE BEEN JU	DGED AS A HUMAN ERROR.  IN ORDER TO RAISE AWARENESS AMONG THE TECHNICIANS AND ENSURE PREVENTIVE MEASURES, THE PRODUCTION														 
2007120500056	20071205	00056	SO  	2007	12	5	2007FA0001038    	1	20070828	G	7810	76048	GASKET          			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					EXHAUST	WRONG PART      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7325L					31P7400206				VISUALLY INSPECTED RT ENG AFTER RECOVERING THE A/C FROM A FIELD.  FOUND MELTED WIRING AT NR 6 CYLINDER AND BEHIND IT.  T	HE P-LEAD FOR THE RT MAG WAS MELTED AND WHEN TESTED FOUND TO BE SHORTED OUT.  THIS SHUT-OFF RT MAG.  THE NR 6 BOTTOM PLU	G WIRE WAS HANGING LOOSE AND THE NUT ATTACHING LEAD TO THE PLUG WAS MELTED OFF. SEVERAL OTHER PLUG WIRES WERE BURNED AS 	WELL. CAUSE OF THIS DAMAGE WAS A BLOWN OUT EXHAUST GASKET ON NR 6 CYLINDER. WHEN THE GASKET BLEW OUT, HOT EXHAUST WAS AL	LOWED TO BURN UP THE PLUG WIRES AND MAG P-LEAD.  P-LEAD THEN SHUT OFF THE RT MAG PROTECTIVE COATING WAS BURNED OFF.  SO 	NOW AT BEST, HAVE 1 MAG WORKING AND ONLY FIRING ON 5 CYLINDERS, AND A LARGE EXHAUST LEAK WHICH WILL LOWER MANIFOLD PRESS	1	L	7	2 	3O	3	O		A8EA    	E19EA				 
2007120400343	20071204	00343	SO  	2007	12	4	2007FA0001039    	1	20071118	G	2721	62829003	SHAFT           	PIPER       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					RUDDER TRIM	SHEARED         	C				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			EA	15	149LH	1697 				2842192				THE RUDDER TRIM SHAFT ASSEMBLY'S SPRING RETAINING PIN SHEARED AT WELD, CAUSING HIGH LT RUDDER STIFFNESS AND PREVENTING T	HE NOSE WHEEL FROM BEING TURNED WITH TOW BAR.					1	L	7	1 	3O	3	O		2A13    	E274				 
2007120500016	20071205	00016	EU  	2007	12	5	2007FA0001040    	2	20071108	G	7320	057610E000201	FADEC           			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE1250299  		EU  						MALFUNCTIONED   	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	15	490TS	6    				42AC090	020201763			DURING FLIGHT TRAINING MANEUVERS, SIMULATED SINGLE ENGINE OPERATIONS AT 5000 FT ASL, THE LT ENGINE WAS THROTTLED BACK TO	 FLIGHT IDLE (5 PERCENT POWER, THROTTLE RETARDED). UPON RETURN TO NORMAL POWER OPERATIONS THE LT ENGINE BEGAN TO SURGE F	ROM 20-100 PERCENT POWER, REGARDLESS OF THROTTLE POSITION, ENGINE WAS UNCONTROLLABLE.  THE LT ENGINE FADEC WAS SELECTED 	FROM ECU A TO ECU B AND CONTROL OF LT ENGINE WAS REGAINED. THE AIRCRAFT RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHER	 INCIDENT. DISCREPANCY COULD NOT BE DUPLICATED DURING GROUND TESTS. LT ENGINE OPERATED NORMALLY ON BOTH ECU A AND ECU B 	OF THE LT FADEC. LT FADEC REPLACED AND AIRCRAFT RELEASED FOR TEST FLIGHT. NO FURTHER ENGINE SURGING NOTED.	1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2007120400327	20071204	00327	NE  	2007	12	4	2007FA0001042    	2	20071115	G	7320	RSA10AD1	FUEL CONTROL    			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  					ENGINE	MALFUNCTIONED   	G				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			WP	05	51E	1759 				015	L2570748A			THE AIRCRAFT EXPERIENCED AN INFLIGHT ENGINE SHUTDOWN RESULTING IN A FORCED LANDING ON THE BEACH. THE CAUSE OF THE INFLIG	HT ENGINE SHUTDOWN WAS THE INTERNAL FAILURE OF THE FUEL SERVO.  THE FUEL SERVO WAS EVALUATED . THE FAILED UNIT WAS SENT 	TO THE MANUFACTURER FOR FURTHER EVALUATION. AFTER FURTHER INVESTIGATION THEY DETERMINED THE CAUSE OF THE INTERNAL FAILUR	E WAS DUE TO FOD ENTERING THE FUEL SERVO AND WORE AWAY AT THE REGULATOR ASSEMBLY. THE DIFINITIVE CAUSE IS STILL UNDER IN	VESTIGATION AT MFG.		1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
2007121300260	20071213	00260	CE  	2007	12	13	2007FA0001043    	1	20071024	G	3222	3908204080001	STOP            			RAYTHN	390   	390         	7150030	CE  										NLG STRUT	DISTORTED       	B			E81R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	03	112CM					RB123				PILOT REPORTED LANDING GEAR UNLOCKED INDICATION AFTER GEAR RETRACTION AFTER TAKEOFF.  FOUND NLG STOPPER ASSY DAMAGED AND	 PREVENTING NLG ASSY FROM CENTERING AND ENGAGING UPLOCK ASSY.  REPLACED STOPPER ASSY AFTER NLG DISASSEMBLY AND INSPECTIO	N, LANDING GEAR OPERATIONS NORMAL.  REPORTED THAT AIRCRAFT WAS PREVIOUSLY TOWED WITH NLG TORQUE LINKS CONNECTED.  FLIGHT	 CREW, GROUND OPERATIONS, PERSONNEL AND TECHS SHOULD BE AWARE OF CORRECT PREMIER TOWING PROCEDURES AS SPECIFIED IN THE 3	90 MM, SEC 9-10-01-201.  (K)		1	L	7	2 	3F			RT	A00010WI					 
2007121300261	20071213	00261	CE  	2007	12	13	2007FA0001044    	1	20071114	G	3210	12116013	CASTING         			CESSNA	206   	T206H       	2073303	CE  										LT MLG	CRACKED         	B			RDDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11		1250 				T20608075				AIRCRAFT OPERATED ON MOSTLY UNIMPROVED AIRSTRIPS.  PART IS SAME AS 206F AND G MODELS.  PART IN QUESTION WAS INSTALLED AT	 TIME OF MFG OF AIRPLANE.  CASTING IS CRACKED IN (3) DIFFERENT LOCATIONS.  WE OPERATE NUMEROUS OF THESE AC AND HAVE A LO	NG HISTORY WITH 206 AIRCRAFT.  WE HAVE SEEN CRACKS OF THIS NATURE BEFORE, BUT RARELY WITH SO LITTLE TIME IN SERVICE.  (K	)			1	H	7	1 	3O			RT	A4CE    					 
2007121300280	20071213	00280	CE  	2007	12	13	2007FA0001045    	1	20071113	G	2420	E3FF10300AA	ALTERNATOR      			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  						FAILED          	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			WP	27	4814K		10   			P21000332	513626			DURING NIGHT IMC APPROACH, LOW VOLTAGE LIGHT ILLUMINATED AND BUS VOLTAGE DROPPED BELOW 24 VOLTS.  PILOT RECYCLED ALTERNA	TOR SWITCH BUT WAS UNABLE TO KEEP ALTERNATOR ON LINE.  PILOT REDUCED LOADS AND SUCCESSFULLY EXECUTED APPROACH AND LANDED	 WITHOUT INCIDENT.  CHARGING SYSTEM TROUBLESHOOT BY MECHANIC.  FOUND LATERNATOR OUTPUT TO BE 26 VOLTS UNLOADED, AND WITH	 50 PERCENT LOAD ON BUSS, LATERNATOR VOLTAGE WOULD DROP BELOW 24 VOLTS.  NOTE: SECOND ALTERNATOR FAILURE IN 50 HOURS.  (	K)		1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007121300281	20071213	00281	CE  	2007	12	13	2007FA0001046    	1	20071110	G	2420	E3FF10300AA	ALTERNATOR      			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  						FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	27	4814K		50   			P21000332	513626			DURING DAY VMC FLIGHT, LOW VOLTAGE LIGHT ILLUMINATED AND BUS VOLTAGE DROPPED BELOW 24 VOLTS.  PILOT MINIMIZED LOADS, DID	 A MANUAL GEAR EXTENSION, AND LANDED WITHOUT INCIDENT.  CHARGING SYSTEM TROUBLESHOOT BY MECHANIC.  FOUND ALTERNATOR OUTP	UT TO BE 26 VOLTS UNLOADED, AND WITH 50 PERCENT LOAD ON BUS, ALTERNATOR VOLTAGE WOULD DROP BELOW 24 VOLTS.  NOTE: ALTERN	ATOR OVERHAULED.  (K)			1	H	7	1 	3O	3	O		3A21    	E8CE				 
2007121300282	20071213	00282	CE  	2007	12	13	2007FA0001047    	1	20071107	G	2910	632701617	LINE            			CESSNA	525   	525A        	2076615	CE  	WILINT	FJ44  	FJ442A      		GL  					HYDRAULIC SYS	SEPARATED       	B			RO3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	03	361JR					525A0361				FOUND FLAP RETRACT LINE SEPARATED FROM BACK OF B-NUT.  SYSTEM FLUID WAS LOST.  SUSPECT DEFECT WAS AT TIME OF MANUFACTURE	.  (K)					1	L	7	1 	4F	4	F	RT	A1WI    	E3GL				 
2007121300283	20071213	00283	CE  	2007	12	13	2007FA0001048    	1	20070911	G	3210	12116013	CASTING         			CESSNA	206   	T206H       	2073303	CE  										MLG	CRACKED         	B			RDDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11		1776 				T20608105				AIRCRAFT OPERATED ON MOSTLY UNIMPROVED AIRSTRIPS.  PART IS SAME AS 206F AND G MODELS.  PART IN QUESTION WAS INSTALLED AT	 TIME OF MFG OF AIRPLANE.  CASTING CRACKED AND FAILED UPON LANDING.  AFT BOLT ALSO WAS CRACKED AND SHEARED.  LANDING WAS	 A NORMAL APPROACH AND LANDING.  GEAR LEG BROKE LOOSE FROM OB CASTING AND PUSHED BACKWARDS, PINCHING BRAKE LINE AND LOCK	ING UP LT BRAKE.  (K)			1	H	7	1 	3O			RT	A4CE    					 
2007121300273	20071213	00273	NE  	2007	12	13	2007FA0001050    	2	20071127	G	7261		ENGINE          			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NR 1	LEAKING         	E				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			SO	11	8HQ					RJ50	100151			ON THE DECENT, THE CREW HAD AN OIL PRESSURE LOW LIGHT AT THAT TIME THE CREW OBSERVED THE OIL PRESSURE GAUGE WAS INDICATI	NG LOW PRESSURE. THE CREW SHUTDOWN THE NR 1 ENGINE DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. UPON INSPECTION BY MAI	NTENANCE IT WAS FOUND THAT THE OIL FILL CAP WAS NOT PROPERLY LATCHED DOWN AND THAT OIL HAD LEAKED OUT OVER THE COURSE OF	 THE FLIGHT. DO TO THE AMOUNT OF OIL MISSING FROM THE OIL TANK THE ENGINE IS BEING REMOVED FOR FURTHER INSPECTION.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007121300315	20071213	00315	SO  	2007	12	13	2007FA0001051    	1	20071130	G	3220		SPRING          			LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A65*        	17003	SO  					TAIL WHEEL	BROKEN          	G				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			SO	09	2099K	2826 				4826	6153488			ON TAKEOFF ROLL AND BEFORE ROTATION, THE TAILSKID SPRING ASSEMBLY BROKE AND THE TAIL WHEEL, CONNECTED TO THE FUSELAGE BY	 THE CONNECTOR SPRINGS, CAME TO REST ON TOP OF THE ELEVATOR AND WEDGED ITSELF AGAINST THE RUDDER, EFFECTIVELY JAMMING IT	 IN PLACE, CAUSING THE AIRCRAFT TO YAW 30 TO 40 DEGREES AND CREATED AN EXTREME SIDE SLIP NOT ALLOWING THE AIRCRAFT TO CL	IMB.			1	H	7	1 	3O	3	O		A694    	E205				 
2007121300320	20071213	00320	EU  	2007	12	13	2007FA0001052    	1	20071115	G	3250		STEERING SYS    			AMTR  	EVKTOR	SPORTSTAR   	0600012	EU  	ROTAX 	912   	ROTAX912ULS 	55172	EU  					NLG	SENSITIVITY     	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	617EV					20071001				AFTER A NORMAL LANDING, CFI (WITH 80 HOURS IN TYPE) AND STUDENT (WITH 1.2 HOURS IN TYPE) LOST CONTROL OF THE AIRCRAFT, E	XITED THE RUNWAY, AND CAME TO REST IN A DRAINAGE DITCH.  THEY STATED THAT THE EXTREME SENSITIVITY OF THE NOSEWHEEL STEER	ING LED TO PILOT INDUCED OSCILLATIONS THAT GREW PROGRESSIVELY WORSE UNTIL THE AIRPLANE WAS COMPLETELY UNCONTROLLABLE.  T	HE SENSITIVITY OF THE NOSEWHEEL STEERING IS A COMMON COMPLAINT, AND HAS BEEN CITED IN SEVERAL OTHER INCIDENTS.			1	L	7	1 	3O	3	O	NT	EXPA1L71	EXPE3O				 
2007121300317	20071213	00317	SO  	2007	12	13	2007FA0001053    	2	20071130	G	8510	641909	LOCK PLATE      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					CRANKSHAFT	MISSING         	D				H				DEACTIVATE SYST/CIRCUITS				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CR	CRUISE         	1			SO	15	707DT	65   	65   		HO13474	421B0468	218370R			THIS ENGINE WAS REMOVED ON AUGUST 31, 2007, HOBBS TIME 1523.9 DUE TO CRACKED ENGINE CASE. THE ENGINE WAS SENT TO RAM AIR	CRAFT FOR REPAIR. RAM REPAIRED THE ENGINE ON SEPT 20, 2007. THIS ENGINE WAS REINSTALLED BACK ON THE AIRCRAFT. DURING A N	IGHT FLIGHT ON NOVEMBER 20, 2007 THE PILOT HAD AN ALTERNATOR FAILURE. HE REPORTED THE PROBLEM THE NEXT DAY. UPON INSPECT	ION OF THE ALTERNATOR, IT WAS FOUND IN PIECES, WITH THE MOUNT HOUSING STILL ATTACHED TO THE ENGINE. THE INSIDE OF THE AL	TERNATOR INSTALLATION HOLE WAS INSPECTED.THE INSPECTION REVEALED THAT THE ATTACH BOLTS ON THE ALTERNATOR FACE GEAR HAD N	O TAB LOCK PLATES INSTALLED. THE ATTACH BOLTS CAME LOOSE AND DAMAGED THE ENGINE AND ALTERNATOR. RAM AIRCRAFT WAS NOTIFIE	1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007121300341	20071213	00341	SO  	2007	12	13	2007FA0001054    	2	20071121	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	36    	36BEECH     	1151602	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1194A	785  				E159	807201R			CRACKED BEHIND INJECTOR BETWEEN FIRST AND THIRD FIN.  SAME AS ALL THE OTHERS.  THE (NEW) E-SERIES CYLINDER HEAD IS DEFEC	TIVE. (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007121300342	20071213	00342	SO  	2007	12	13	2007FA0001055    	2	20071121	G	8530	TISN712ACA	CYLINDER HEAD   			BEECH 	36    	36BEECH     	1151602	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1194A	901  				E159	807201R			CYLINDER HEAD CRACKED BEHIND INJECTOR BETWEEN FIN NR 1 AND 3.  DEFECTIVE MFG PROCESS.  (K)						1	L	7	1 	3O	3	O		3A15    	E5CE				 
2007121300343	20071213	00343	CE  	2007	12	13	2007FA0001056    	1	20071113	G	2450		CIRCUIT BREAKER 			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  						INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	24442	251  				17280862				PILOT SQUAWKED ON INTERMITTENT SWITCH.  THE SWITCH WAS DISASSEMBLED AND INSPECTED.  THE BONDED INTERNAL CONDUCTOR HAD SE	PARATED FROM CONTACTOR.  A TOTAL OF 20 SWITCHES IN OUR FLEET, HAVE ALREADY BEEN REPLACED.  UPON INSPECTION, NUMEROUS SWI	TCHES HAD SIMILAR PROBLEMS INTERNALLY.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2007121300346	20071213	00346	EA  	2007	12	13	2007FA0001057    	2	20071127	G	7414	06058002	BOOSTER         			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					MAGNETO	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	1473T					28R7235300	RL1904551A			PILOT REPORTED ROUGH ENGINE; IGNITION SYSTEM TROUBLESHOOT FOUND START MAGNETO STARTER BOOSTER INTERNALLY SHORTED, GROUND	ING MAGNETO P-LEAD CAUSING MAGNETO FAILURE.  REMEDIED BY REMOVING START FROM AIRCRAFT AND MAGNETO OPERATING NORMALLY.  (	K)				1	L	7	1 	3O	3	O		2A13    	1E10				 
2007121300364	20071213	00364	CE  	2007	12	13	2007FA0001058    	1	20071204	G	2497		CONNECTOR       			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ELECTRICAL	ARCED           	B				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			GL	07	23404	10027				B234				PARTIAL ELECTRICAL POWER LOSS TO COMPONENTS FROM RT NR 1 AND NR 2 SUBPANEL CIRCUIT BREAKERS.  FOUND RT CIRCUIT PANEL CON	NECTOR SOCKET MODULE AND SOCKET RT 1B BURNED.  REPLACED MODULE (NR 8 WIRE-4 SOCKET) AND 4 SOCKETS.  REPLACED PINS (4).  	FUNCTION CHECK SATISFACTORY.  SUGGEST THESE HEAVY WIRE CONNECTIONS BE CHECKED MORE CLOSELY ON THE OLDER AIRCRAFT. THIS P	ARTICULAR AIRCRAFT IS 30 YEARS OLD.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2007121300327	20071213	00327	NM  	2007	12	13	2007FA0001060    	1	20071203	G	3060	SMR6201	STRAP           			COLUMB	LC41  	LC41550FG400	5150011	NM  	CONT  	O550  	TSIO550C    		SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	PROPELLER DEICE	DEBONDED        	D				K				NONE                    				G			MULTIPLE FAILURE          			IN	INSP/MAINT     	1			SW	07	969GM	266  				41616		LX163B		PROPELLER DEICE BOOT RETAINER STRAP DEBONDED OVER HALF OF THE BLADE CIRCUMFERENCE.  OTHER (2) BLADES DEBONDED ABOUT .3. 	 THIS STRAP HOLDS THE IB END OF THE DEICE BOOT AND TRIES TO KEEP THE LONG DEICE LEADS FROM PULLING UP THE BOOT.  THE PRO	P DEICE BOOT BEGINS TO COME LOOSE AFTER THE STRAP DEBONDS.  THE RETAINER STRAPS NEED TY-RAPS TO HOLD THE LEADS, AS IS CO	MMON PRACTICE ON OTHER PROPELLERS.			1	L	7	1 	3O	3	O	NT	A00003SE	E5SO	5	C	P25EA	 
2007121400290	20071214	00290	EU  	2007	12	14	2007FA0001061    	1	20071203	G	2435		COMMUTATOR      	BFGOODRICH  		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					STARTER GEN	FAILED          	B				B	A			EMER. DESCENT           	UNSCHED LANDING         			H	E		ELECT. POWER LOSS-50 PC   	VIBRATION/BUFFET          		CR	CRUISE         	1			CE	07	462PC				97102	462	PCEPR0336			DURING CRUISE FLIGHT, LOUD NOISE FROM ENGINE COMPARTMENT FOLLOWED BY VIBRATION AND LOSS OF PRIMARY ELECTRICAL POWER.  UP	ON INSPECTION, ONE SEGMENT FROM COMMUTATOR WAS MISSING AND AFT END OF GENERATOR AND BRUSHES HAD SUSTAINED HEAVY DAMAGE. 	 AFTER REPLACEMENT WITH OVERHAULED UNIT, NO ABNORMALITIES WERE NOTED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2007121400335	20071214	00335	CE  	2007	12	14	2007FA0001066    	1	20071119	G	2751	100TA1966N4	TRANSMITTER     			BEECH 	MU300 	400A        	1155402	CE  										TE FLAPS	INOPERATIVE     	B			E81R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	03	420CT					RK517				TROUBLESHOT IN-FLIGHT (FLAP ASSYMETRY) ANNUNCIATOR INDICATION.  FOUND RT FLAP POSITION TRANSMITTER RESISTANCE TO GO ABOV	E SERVICE LIMITS WHEN COLD SOAKED.  REPLACED RT FLAP POSITION TRANSMITTER AND ADJUSTED LT , RT FLAP FOLLOW-UP SWITCHES A	ND POSITION TRANSMITTER RIGGING AS REQUIRED.  VERIFIED FLAP SYSTEM RIGGING CABLE TENSIONS WITHIN SERVICE LIMITS.  FLAP S	YS FUNCTIONAL TESTS OK.  SUGGEST MFG INVESTIGATE CURRENT PRODUCTION TRANSMITTER ASSY FOR QC OR MOISTURE INGRESS FAULTS. 	 HBC PN 45AS86805-031, MFG DATE 8/07/2006.  (K)		2	H	7	2 	4F			RT	A16SW   					 
2007121400337	20071214	00337	CE  	2007	12	14	2007FA0001067    	1	20071119	G	7830	64760	CONTROL VALVE   			BEECH 	MU300 	400A        	1155402	CE  										THRUST REVERSER	MALFUNCTIONED   	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	420CT					RK517				TROUBLESHOT INOPERATIVE THRUST REVERSER DEPLOYMENT.  FOUND LT, RT REVERSERS MECHANICALLY STIFF AND DIFFICULT TO OPERATE.	  THRUST REVERSER LINKS AND PIVOTS FOUND DRY, INITIAL 400 HR LUBRICATION NOT DUE FOR 55 HRS.  LUBED REVERSERS IAW MM.  1	2-20-00, VERIFIED OPERATIONS OK.  FOUND LT REVERSER NOT DEPLOYING UNTIL AFTER RT DEPLOYED.  REPLACED LT CONTROL VALVE, O	PERATIONAL CHECKS NORMAL.  SUGGEST ALL THRUST REVERSER LUBES BE COMPLIED WITH AT 200 HR INITIAL INSPECTION.  SUGGEST MFG	 INVESTIGATE CNTRL VALVE FOR POSSIBLE QUALITY CONTROL OR SYSTEM CONTAMINATION ISSUES.  (K)		2	H	7	2 	4F			RT	A16SW   					 
2007121400339	20071214	00339	CE  	2007	12	14	2007FA0001068    	1	20071111	G	2730	MS250836BB5	BONDING JUMPER  			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ELEVATOR	FRAYED          	B			E81R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	400MV	1596 				RK286				TROUBLESHOT REPORT OF HORIZONTAL STABILIZER ANTI-ICE SYSTEM FAIL INDICATION.  NOTED ELEVATOR HORN HEAT SYSTEM RESISTANCE	 READINGS ERRATIC WHEN ELEVATORS MOVED.  FOUND ELEVATOR BONDING JUMPERS FRAYED AND CORRODED.  REPLACED ELEVATOR BONDING 	JUMPERS, ELEVATOR HORN HEATER RESISTANCE READINGS NOW WITHIN SERVICE LIMITS.  HORIZONTAL STABILIZER ANTI-ICE SYSTEM TEST	S IAW MM 30-12-00 NORMAL, NO FAULTS INDICATED.  RECOMMEND TECH/INSP NOTE CONDITION OF ELEVATOR BONDING JUMPERS CLOSELY D	URING SCHEDULED INSPECTIONS AND REPLACE JUMPERS WHEN DETERIORATION EVIDENT.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007121400341	20071214	00341	NE  	2007	12	14	2007FA0001069    	2	20071111	G	7230		PIPE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					GAS GENERATOR	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	400MV				A000*LNX	RK286				PERFORMED HOT SECTION INSPECTION PRIOR TO SCHEDULED 1800 HR INTERVAL TO INVESTIGATE COMPLAINT OF SLOW STARTING.  UPON DI	SASSEMBLY, FOUND DIFFUSER PIPES OF GAS GENERATOR CASE CRACKED AND PORTIONS MISSING AT APPROXIMATE 10:30, 11:00 POSITION.	  SUSPECT CAUSED BY STREAKING FUEL NOZZLES WITH COKED-UP TIPS FROM LOW IDLE OPERATION WITH EFC OFF.  PILOTS AND TECH SHO	ULD BE AWARE OF MONITORING ENGINE RPM DURING TAXING OPERATIONS WITH EFC TURNED-OFF.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007121400349	20071214	00349	CE  	2007	12	14	2007FA0001070    	1	20071201	G	2420	AC2101	CONTROL UNIT    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ALTERNATOR	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	2472J	215  				172S10072	L3240751E	ZK23029		THE AIRCRAFT FACTORY INSTALLED ACU BEGAN FAILING AT 200 HOURS (INTERMITTENT ALTERNATOR DROPPING (OFF LINE) FOR A FEW SEC	ONDS) (ON ONE OCCASION, THE FIELD CB DISENGAGED)  A NEW ACU WAS INSTALLED AT 215.9.  AT 246.1 THE SAME PROBLEM SURFACED,	 AND THE THIRD ACU WAS INSTALLED.  THE SERVICE CENTER HAS HAD THE SAME PROBLEM WITH OTHER AC.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2008010800347	20080108	00347	CE  	2008	1	8	2007FA0001072    	1	20071208	G	2751		WARNING SYSTEM  			CESSNA	310   	310K        	2074228	CE  										T/E FLAP	MALFUNCTIONED   	E				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			SO	11	418GJ					310K0067				AC EXPERIENCED FLAP ASYMMETRIC LIGHT IN CRUISE FLIGHT CREW DIVERTED TO ATL LIGHT WENT OUT AND FLAPS WORKED PROPERLY FOR 	AN UNEVENTFUL LANDING. PROBLEM COULD NOT BE DUPLICATED SO BOTH FLAP FOLLOW UPS WERE REPLACED IAW THE MM. AIRCRAFT OPS CH	ECK GOOD.				1	L	7	2 	3O				3A10    					 
2008010800350	20080108	00350	SO  	2008	1	8	2007FA0001073    	1	20071211	G	3211	67042013	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  										RT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	570ER	4145 				4496146				RT AFT MAIN TRUNNION CASTING, P/N 67042-013, FOUND TO BE CRACKED DURING INSPECTION.  THIS IS A NEARLY IDENTICAL CRACK TO	 ONE FOUND AUGUST 2006 ON A SISTER SHIP.					1	L	7	2 	3O				A19S0   					 
2007121400344	20071214	00344	SO  	2007	12	14	2007FA0001074    	1	20071130	G	2720		CONTROL SYSTEM  			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					RUDDER	SEIZED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	557C					3449247				WITH FULL RT RUDDER TRIM, RT RUDDER FOR HARD CLIMBING RT TURN, RUDDER FROZE WITH FULL RT DEFLECTION.  RUDDER CABLE TURNB	UCKLE IN TAIL SECTION WAS (CAUGHT) UNDER BULKHEAD TOP EDGE CAUSING RUDDER TO FREEZE IN FULL RT DEFLECTION - DESPITE SIGN	IFICANT LT RUDDER PRESSURE.				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2008010800356	20080108	00356	CE  	2008	1	8	2007FA0001075    	1	20071212	G	2730	053200135	ADAPTER         			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300*       	17022	SO  					LT ELEVATOR	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	3901S	6491 				17251101				LT ELEVATOR TORQUE TUBE ARM ADAPTER RIVET HOLES WERE WORN POSSIBLY DUE TO UNSECURED CONTROLS IN GUSTY WINDS.						1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2008010800371	20080108	00371		2008	1	8	2007FA0001076    	2	20071215	G	7414	10357586	DISTRIBUTOR GEAR	CONT        																MAGNETO	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		500  	500  							500-HOUR INSPECTION PERFORMED ON BOTH MAGNETOS REMOVED FROM. FOUND AXLE CRIMPED WASHER LOOSE ON SHAFT AND WORN TO THE PO	INT OF FALLING OFF GEAR. THIS IS THE SECOND TIME THIS CONDITION HAS BEEN FOUND ON MAGNETOS USING THIS GEAR. TTS NEW 500 	AND 580.																	 
2008010800372	20080108	00372		2008	1	8	2007FA0001077    	2	20071215	G	7414	10357586	DISTRIBUTOR GEAR	CONT        																MAGNETO	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		500  	500  							500-HOUR INSPECTION PERFORMED ON BOTH MAGNETOS REMOVED. FOUND AXLE CRIMPED WASHER LOOSE ON SHAFT AND WORN TO THE POINT O	F FALLING OFF GEAR. THIS IS THE SECOND TIME THIS CONDITION HAS BEEN FOUND ON MAGNETOS USING THIS GEAR. TTSNEW 500 AND 58	0.																	 
2008010800367	20080108	00367	EU  	2008	1	8	2007FA0001078    	1	20071214	G	3230	PNDIN47108VE	RETAINING CLIP  	DIAMON      		DIAMON	DA42  	DA42        	2990004	EU  										LT MLG	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	904ER	100  	2    			42281				DURING PREFLIGHT THE PILOT NOTICED THAT THE LMG DOWNLOCK PIN (P/N-D60-3237-11-34) HAD NO RETAINING CLIP(P/N-DIN471-08-VE	RZ) AND HAD SHIFTED AFT. THE FORWARD DOWNLOCK HOOK WAS COVERING ONE HALF OF THE HOLE SINCE THERE WAS NO PIN TO STOP ITS 	MOVEMENT. THE REMAINING CLIP BROKE IN HALF WHEN IT WAS REMOVED. IT APPEARED TO BE BRITTLE. A NEW PIN WAS INSTALLED WITH 	NEW CLIPS. THOSE CLIPS HAD MORE SPRING TO THEM. ALSO, THE GROOVES IN THE PIN ARE VERY SHALLOW.			1	L	7	2 	3I			RT	A57CE   					 
2008010800368	20080108	00368	EU  	2008	1	8	2007FA0001079    	1	20071214	G	3230	PNDIN47108VE	RETAINING CLIP  	DIAMON      		DIAMON	DA42  	DA42        	2990004	EU  										LT MLG	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	904ER	100  	2    			42281				DURING PREFLIGHT THE PILOT NOTICED THAT THE LMG DOWNLOCK PIN (P/N-D60-3237-11-34) HAD NO RETAINING CLIP(P/N-DIN471-08-VE	RZ) AND HAD SHIFTED AFT. THE FORWARD DOWNLOCK HOOK WAS COVERING ONE HALF OF THE HOLE SINCE THERE WAS NO PIN TO STOP ITS 	MOVEMENT. THE REMAINING CLIP BROKE IN HALF WHEN IT WAS REMOVED. IT APPEARED TO BE BRITTLE. A NEW PIN WAS INSTALLED WITH 	NEW CLIPS. THOSE CLIPS HAD MORE SPRING TO THEM. ALSO, THE GROOVES IN THE PIN ARE VERY SHALLOW.			1	L	7	2 	3I			RT	A57CE   					 
2008010800385	20080108	00385	SO  	2008	1	8	2007FA0001080    	1	20071115	G	3213	653319004	CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					RT MLG	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17	8218Z	11743				288090320				RT M/G CYLINDER FAILED AT THE UPPER TORQUE LINK ATTACH LUGS WHILE TAXIING FROM THE ACTIVE RUNWAY: THE AIRCRAFT  (SINCE N	EW) IS USED FOR FLIGHT TRAINING IN A 141 FLIGHT SCHOOL.  THE PREMATURE FAILURE OF THE CYLINDER WAS PROBABLY CAUSED BY A 	HARD LANDING.  (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
2008010800387	20080108	00387	WP  	2008	1	8	2007FA0001081    	1	20070926	G	7921	20006A	OIL COOLER      			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  						CRACKED         	D				A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	11	97CP					0421	L1414339A			AT A 100 HR INSPECTION ON HELICOPTER, INSTALLED A NEW OIL COOLER REPLACING THE ORIGINAL OIL COOLER.  (NOVEMBER 5, 2007, 	HOUR METER 1042) WHILE FLYING, NOTICED THE OIL TEMPERATURE RISING AND THE OIL PRESSURE DROPPING.  MADE AN UNSCHECULED LA	NDING AND DISCOVERED THE TAILBOOM COVER WITH ENGINE OIL.  TRACED THE OIL BACK TO THE OIL COOLER, REMOVED OIL COOLER AND 	PRESSURE TESTED IT AND FOUND A .7500 INCH CRACK IN THE COOLER CORE.  (TT 16.8 HOURS) (K)			1	G	7	1 	3O	3	O		H10WE   	E274				 
2008010800388	20080108	00388	CE  	2008	1	8	2007FA0001082    	1	20070926	G	5320		BRACKET         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  						CRACKED         	D			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	731BH					4410360				FOUND BROKEN T-BRACKET DURING ROUTINE 2, 3, D INSPECTION.  (K)						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2008010800389	20080108	00389	CE  	2008	1	8	2007FA0001083    	1	20070927	G	5350	581201412	TAIL CONE       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  						CRACKED         	D			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	731BH	7779 				4410360				FOUND CRACK DURING ROUTINE 2,3,D PHASE INSPECTION.  (K)						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2008010800393	20080108	00393	CE  	2008	1	8	2007FA0001084    	1	20071109	G	5753	3516505084	NOSE RIB        			BEECH 	95    	B95         	1153404	CE  	LYC   	O360  	O360A1A     	41514	EA  					T/E FLAP	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			EA	17	9349Y	4288 				TD445	L421536			IN-FLIGHT, PILOT LOWERED FLAPS AND AIRCRAFT STARTED TO ROLL TO THE RT.  PILOT NOTICED RT FLAP WAS RETRACTED, HE THEN RET	RACTED FLAP HANDLE.  AIRCRAFT LANDED SAFELY, WITHOUT INCIDENT.  UPON INSPECTION, FOUND RT FLAP ROD ATTACH BRACKET BROKEN	 AND FLAP NOSE RIB NUTPLATE FLANGE TORN.  INSPECTED LT SIDE AND FOUND NOSE RIB FLANGE AND WEB CRACKED.  (K)				1	L	7	2 	3O	3	O		3A16    	E286				 
2008010900387	20080109	00387	CE  	2008	1	9	2007FA0001085    	1	20071109	G	5753	3516505084	NOSE RIB        			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  					T/E FLAP	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	810WA	4552 				TE486	267930R			AT ANNUAL INSPECTION, FOUND CRACKED FLAP ROD ATTACH POINT RIB.  RT FLAP ONLY.  (K)						1	L	7	2 	3O	3	O		3A16    	E5CE				 
2008010900388	20080109	00388	CE  	2008	1	9	2007FA0001086    	1	20071109	G	5753	3516505084	NOSE RIB        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					T/E FLAP	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	20TC	3144 				E873	281740R			AT ANNUAL INSPECTION FOUND BOTH LT AND RT FLAP ATTACH POINT RIBS CRACKED. (K)						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2008010900389	20080109	00389	CE  	2008	1	9	2007FA0001087    	1	20071109	G	5753	3516505084	RIB             	BEECH       		BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520BA     	17032	SO  					T/E FLAP	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	4475S	4248 				D9775	280904R			AT ANNUAL INSPECTION FOUND RT FLAP ROD ATTACH POINT RIB CRACKED. (K)						1	L	7	1 	3O	3	O		3A15    	E5CE				 
2008010900390	20080109	00390	CE  	2008	1	9	2007FA0001088    	1	20071109	G	5753	3516505084	RIB             	BEECH       		BEECH 	95    	95B55       	1152729	CE  	CONT  	O520  	IO520E      	17032	SO  					T/E FLAP	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	127RW	4421 				TC1958	215825R			AT ANNUAL INSPECTION FOUND CRACK ON FLAP RIB.  (FLAP ROD ATTACH POINT) BOTH LT AND RT FLAPS.  (K)						1	L	7	2 	3O	3	O	RT	3A16    	E5CE				 
2008010900391	20080109	00391	CE  	2008	1	9	2007FA0001089    	1	20071109	G	5753	3516505084	RIB             	BEECH       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O550  	IO550B      	 	SO  					T/E FLAP	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	89AU	5255 				CE1129	675607			AT ANNUAL INSPECTION, FOUND RT FLAP ROD ATTACH POINT RIB CRACKED.  (K)						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2008011000024	20080110	00024	GL  	2008	1	10	2007FA0001090    	1	20071126	G	7160		CONTROL ARM     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					AIRBOX	BROKEN          	C			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	423FP	28   				40FC023				CARBURETOR HEAT CONTROL ARM BROKEN OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INT	AKE.  RECOMMEND INSTALLED THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER.  DIFFERENT WELDING PROCESS, OR DIFFERENT ATTA	CHMENT PROVISION ALTOGETHER.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008011000131	20080110	00131	NM  	2008	1	10	2007FA0001091    	1	20070525	G	2761	252T13021	MANIFOLD        			BOEING	767   	767*        	       	NM  										SPOILERS	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										MANIFOLD CRACKED IN THE FILTER BOWL AS DESCRIBED IN BETWEEN WHAT IS DESCRIBED IN THE SERVICE LETTER AND THIS UNIT FRACTU	RED COMPLETELY.  VISUAL INSPECTION APPEARS TO SHOW THAT THE CRACK ORIGINATED IN THE THREAD ROOT AT THE THINNEST AREA OF 	THE HOUSING.  THE CRACK PROPAGATED UNTIL THERE WAS DUCTILE OVERLOAD FAILURE OF THE HOUSING.  (K)				2	L	7	2 	4F			RT	A1NM    					 
2008011100005	20080111	00005	SO  	2008	1	11	2007FA0001092    	1	20071130	G	2530	243185502	OVEN            			GULSTM	GVSP  	GVSPG550    	3980203	SO  	RROYCE	BR700 	BR700710A110	 	NE  					GALLEY	FAILED          	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	11	607PM	105  				5146				FLIGHT CREW REPORTED THE ODOR OF ELECTRICAL SMOKE IN THE GALLEY.  THE ODOR WAS COMING FROM THE OVEN, THEN THE OVEN CB OP	ENED (POP).  THE OVEN WAS REMOVED AND REPLACED WITH A NEW UNIT.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2008011100008	20080111	00008	EA  	2008	1	11	2007FA0001094    	1	20071211	G	2520		SEAT BACK       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					SEAT	BROKEN          	B			SCIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	252SA				1691	614	PCE50502			BOTH LOWER SEAT BACK BRACES BROKE JUST ABOVE THE WELDS, ABOVE WHERE THE FLANGE BOLTS ON TO THE SEAT BOTTOM.  (K)						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2008010900393	20080109	00393		2008	1	9	2007FA0001095    	4	20071218	G	3160	70000006003	DISPLAY         			PIPER 	PA46  	PA46500TP   	7104622	SO  	GARRTT	TPE331	TPE33111U   	01514	WP  					COCKPIT	MISREPAIRED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	3110T	318  				4697221				WE SENT IN BOTH AIRCRAFT PFD'S FOR REPAIR AND SB COMPLIANCE.  BOTH UNITS WERE REPAIRED AND REINSTALLED.  WE TRIED TO CAL	IBRATE THE ADHRS AND THE PILOT PFD CONTINUED TO GIVE AN ERROR.  WE SPOKE WITH ANOTHER SHOP AND WERE TOLD THEY HAVE HAD T	HE SAME PROBLEM.  IN FACT, WE WERE TOLD THEY NORMALLY HAVE PROBLEMS WITH REPAIRED UNITS (ABOUT 50 PERCENT OF THE TIME).				1	L	7	1 	3O	4	T	RT	A25SO   	E4WE				 
2008011100010	20080111	00010	EU  	2008	1	11	2007FA0001096    	1	20071121	G	7120	80446101403	MOUNT           			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	180AV	6059 				1018				OIL COOLER RETURN LINE CHAFED AGAINST ENGINE MOUNT. DID NOT SHOW SIGNS OF CHAFING STATICALLY DURING ROUTINE INSPECTIONS,	 WAS CHAFING DURING FLIGHT. INSTALLED REDESIGNED OIL LINE THAT CANNOT COME IN CONTACT WITH MOUNT.  MFG DID NOT INFORM OP	ERATORS ABOUT REDESIGNED OIL LINE, P/N MS8000M300JF, SAID USE AS SPARE IN ILLUSTRATED PARTS CATALOG. ALSO INSTALLED NEW 	ENGINE MOUNT.			1	H	7	2 	3O	3	T	RT	A59EU   	E2NE				 
2008011100056	20080111	00056	CE  	2008	1	11	2007FA0001097    	1	20071212	G	5720	509800913	BUMPER BLOCK    			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					RT MLG	UNBONDED        	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	266RD	1628 				LJ1633				COMMUNIQUE NR 2000-04 ANNOUNCED THAT STARTING LJ-1088 AND AFTER THAT LANDING GEAR BUMPER BLOCK WILL BE BONDED TO THE MAI	N SPAR WHERE IT CROSSES INSIDE THE LANDING GEAR WHEEL WELLS.  THIS AC FOUND THE RT LANDING GEAR BUMPER BLOCK ON THE FLOO	R OF HIS HANGER.  NOT KNOWING WHAT THIS PART WAS THE OWNER ALMOST THREW IT IN THE TRASH.  LUCKILY HE KEPT IT FOR AT OUR 	NEXT PHASE INSPECTION, WE FOUND THAT IT WAS MISSING AND TOLD THE OWNER, WHO REMEMBER STORING THIS UNKNOWN PART IN A LOCK	ER AT THIS HANGER.  CLEANED THE AREA AND ATTACHED THE BUMPER BY APPLYING THE EC2216 EPOXY IAW THE COMMUNIQUE.  THIS BLOC	K ON EARLIER AC WERE BOLTED ONTO THE SPAR.  THIS METHOD WAS MOST LIKELY DISCONTINUED BECAUSE ELIMINATION OF APPLYING EXT	1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2008011100015	20080111	00015	SW  	2008	1	11	2007FA0001098    	1	20071219	G	6710		ATTACH FITTING  			BELL  	412   	412         	1182202	SW  	PWA   	PT6   	PT6*        	52043	EA  					CYCLIC STICK	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	107X	19997				33113				DURING INSPECTION FOR BHT ASB-412-07-127 (CYCLIC STICK BEARING INSPECTION) IT WAS FOUND THAT THE LATERAL CONTROL TUBE PN	 412-001-307-101 FIXED (OB) CLEVIS PN 212-001-059-001 OR -103 HAD GOUGED THE CYCLIC LEVER ASSEMBLY BEYOND REPAIRABLE LIM	ITS AND THE BEARING GREASE SEAL RETAINER WAS DISLODGED.  THIS DAMAGE WAS CAUSED BY ANGULAR MISSALIGNMENT OF THE FIXED CL	EVIS WITH RELATION TO THE ADJUSTABLE (IB) CLEVIS.  IT WAS ALSO NOTED THAT BOTH CLEVIS'S WERE A DIFFERENT DESIGN THAN THE	 OTHER CLEVIS'S INSTALLED ON THE CYCLIC OF THIS AND OTHER 412 AIRCRAFT AVAILIABLE FOR INSPECTION.  THIS DESIGN WAS A STR	AIGHT (TUNNING FORK) DESIGN AS APPOSED TO THE OTHER CLEVIS DESIGN WITH AN ELONGATED (C) SHAPE WHICH ALLOWED FOR MORE CLE	1	G	7	2 	4U	3	T		H4SW    	E2NE				 
2008011100052	20080111	00052	SO  	2008	1	11	2007FA0001103    	1	20071220	G	5200	99271000	BRACKET         			PIPER 	PA32  	PA32R301    	7103218	SO  										ACCONDENSOR DOOR	CORRODED        	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	19	9087V	3700 				32R8613005				AIR CONDITIONING CONDENSOR DOOR P/N 99271-000 FAILED IN FLIGHT WHILE DEPLOYED. THE SMALL EXTRUDED ANGLE BRACKET ON THE R	T SIDE OF DOOR WHERE THE BEARING ASSY P/N 99561-000 CONNECTS TO THE DOOR CORRODED WHERE THE TWO MEET. THIS CONDITION IS 	IMPOSSIBLE TO INSPECT UNLESS THE MECHANIC DROPS THE CONDENSOR DOOR DOWN. THE LT SIDE WAS IN PERFECT CONDITION. THE MAIN 	CAUSE OF THE CORROSION IS THE FACT THAT THAT THE ENGINE EXHAUST TRAVELS DOWN THE RT SIDE OF THE BOTTOM OF THE AIRCRAFT. 	THIS PORTION OF THESE LOW WING PIPERS ALWAYS SHOW MORE SURFACE CORROSION ON THE RT SIDE OF THE BELLY.		1	L	7	1 	3O				A3SO    					 
2008011100012	20080111	00012	NM  	2008	1	11	2007FA0001104    	1	20071219	G	5330		SKIN            			UNIVAR	415   	415C        	0420302	NM  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	31140					3143				IAW AD2002-26-02,- CORROSION FROM WATER, DIRT AND ACID FROM BATTERY ATE THROUGH BOTTOM SKINS 415-13058-1,415-13047L AND 	R, RIBS 415-13016L AND R AND BOTTOMS OF SERVICE ASSEMBLY NR 5.  AIRCRAFT HAD SAT SINCE 1977.					1	L	7	1 	3O				A718    					 
2008011100101	20080111	00101	GL  	2008	1	11	2007FA0001106    	1	20071222	G	2497		WIRE HARNESS    			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ALTERNATOR	DAMAGED         	D				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CR	CRUISE         	1			SO	15	1501C	1    				0528				ALTERNATOR FAILED ON FIRST FLIGHT AFTER INSTALLATION FROM OVERHAUL. FOUND FIELD WIRE RIPPED OUT OF FIELD BRUSH AND BARE 	WIRE DEBRIS INSIDE ALTERNATOR CASE. SUSPECT WIRE EPOXY HOLD DOWN VIBRATED LOOSE ALLOWING ROTOR ASSEMBLY TO SNAG WIRE.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2008011100145	20080111	00145	NE  	2008	1	11	2007FA0001107    	2	20071129	G	7250		TURBINE BLADES  								RROYCE	RB211 	RB211TRENT89	 	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35							61160			DURING INSPECTION, A CRACKED FIRTREE POST HAS BEEN HIGHLIGHTED.  THE DISC HAS BEEN SCRAPPED OFF AND THIS ISSUE HAS BEEN 	FORWARDED TO MFG.  THE DISC HAS BEEN SENT TO LAB FOR ANALYSIS.  REF NR: MEM5 D070133. (K)										4	F			E00050EN				 
2008011100146	20080111	00146	NE  	2008	1	11	2007FA0001108    	2	20071029	G	7200		BEARING         								RROYCE	RB211 	RB211535E4  	54555	NE  					ENGINE	DAMAGED         	W			DR5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35							31141			DAMAGE FOUND ON STRIP.  HP AND IP SHAFTS SEIZED, HP/IP BEARING DAMAGED, ALSO LP VISIBLE COUPLINGS AND SEAL ARM.  DESIGN 	ORGANIZATION AND UK CAA HAVE BEE NOTIFIED.  THE ENGINE WAS BEING OPERATED BY AA AT TIME OF IN-FLIGHT SHUTDOWN.  THE ENGI	NE WAS RECEIVED IN OCTOBER, 2007 FOR REPAIR.  (MEMS D070108) (K)									4	F			E12EU				 
2008011100153	20080111	00153	NM  	2008	1	11	2007FA0001109    	1	20071224	G	5320	SB727570112	BRACKET         			BOEING	727   	727233      	138408A	NM  										BS 760	CRACKED         	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	CGXFA					20938				RT PREVENTATIVE MODIFICATION FWD IB ANGLE CRACKED AT BS 760.95.   REPAIRED CRACK AT RT BL 70.5, BS 760.95, UPPER AND LOW	ER MOST FORWARD HOLES.  OVERSIZED CRACKED HOLE IAW 57-112.  NDT PERFORMED TO CONFIRM CRACK TERMINATION. COMPLIED WITH TE	RMINATION REPAIR IAW SB 727-57-0112.   REMOVED RT PREVENTATIVE MODIFICATION FWD IB ANGLE BRACKET.    (K)				2	L	7	3 	4F			RT	A3WE    					 
2008011100143	20080111	00143	EA  	2008	1	11	2007FA0001110    	1	20071227	G	5522	16920	SKIN            			FRCHLD	FH227 	FH227D      	3373050	EA  										ELEVATOR	CRACKED         	M				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17										A SMALL CRACK WAS FOUND UNDERNEATH ELEVATOR STATIC WICK BASES APPROX. BL 84.0 ON BOTH LTAND RT ELEVATOR CONTROL SURFACES	. A SECOND AIRCRAFT IN THE FLEET REVEALED A SIMILIAR CRACK UNDERNEATH THE STATIC BASE ON THE RT ELEVATOR ONLY.  SUSPECT 	THE CRACK WAS CAUSED BY VIBRATION ON STATIC WICK IN THE SLIPSTREAM OF THE ENGINES. REPAIRED IAW SRM 51-90-04 REPAIR SCHE	ME NR 6.			2	H	7	2 	4T				7A1     					 
2008011100201	20080111	00201	SO  	2008	1	11	2007FA0001111    	2	20071217	G	8520	SA6419311075	THRU BOLT       								CONT  	O520  	IO520C      	17032	SO  					CRANKCASE	BROKEN          	B			VI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15							17256H			INSTALLING ALL NEW SA641931-10.75 LOT NR K070059179, REV E THRU BOLTS IN ENGINE.  AFTER TORQUE, WITHIN A FEW HOURS THE T	HRU BOLT SNAPPED, AT THE OIL RING GROOVE.  THIS IS THE THIRD THRU BOLT THAT HAS SNAPPED AFTER TORQUE, AND SETTING.  PROB	ABLE CAUSE, IS IMPROPER HEAT TREATING DURING OR AFTER PLATING.  (K)									3	O			E5CE				 
2008011100202	20080111	00202	CE  	2008	1	11	2007FA0001112    	1	20071130	G	2400	727755	CIRCUIT BREAKER 			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						FAILED          	B			D0FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	18728	1489 				172S9929				CIRCUIT BREAKER WILL RESET AFTER BEING TRIPPED BY ROTATING THE KNOB.  THIS RESULTS IN A BREAKER THAT IS RESET WHILE BEIN	G IN THE TRIPPED POSITION.  THIS BREAKER WILL PRODUCE THIS RESULT EVERY TIME THAT THIS PROCEDURE IS TRIED. THIS PARTICUL	AR BREAKER WAS INSTALLED IN THE AUTOPILOT SYSTEM.  THE CIRCUIT BREAKER IN QUESTION IS ATTACHED.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008011100203	20080111	00203	SO  	2008	1	11	2007FA0001113    	1	20071214	G	1400	EWD0420839	BOLT            			EMB   	145   	EMB145LR    	3260212	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					BEARING CAP	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21	673AE					145797				NEW BOLT BROKEN DURING TORQUE.  TORQUE VALUE NEVER OBTAINED BEFORE THE BOLT BROKE.  THIS BOLT HOLDS THE BEARING CAP IN P	LACE THAT HOLDS THE MAIN LANDING GEAR ON THE AIRCRAFT.  (K)					2	L	7	2 	4T	4	F	RT	T00011AT	TE6CH				 
2007032600145	20070326	00145	CE  	2007	3	26	2007FA0313001    	1	20070313	G	5210	55123515	HINGE           	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					PAX DOOR	CRACKED         	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	13	6763L	6986 				5500673				DESCRIPTION AMENDED TO SAY THAT THE LOWER LUG WAS CRACKED INSTEAD OF THE UPPER LUG.						1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007032200066	20070322	00066		2007	3	22	2007FA032201     	4	20070308	G	2200	6226717104	SERVO           			BEECH 	MU300 	400A        	1155402	CE  										ELEVATOR CONTROL	MALFUNCTIONED   	E				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			WP	05	188JF	351  				RK446				DIFFICULTY OCCURRED UPON DESCENT.  PILOT DISENGAGED AUTO-PILOT AND FELT RESISTANCE IN THE ELEVATOR CONTROL SYSTEM.  ON I	NSPECTION OF THE SYSTEM THE AUTO-PILOT ACTUATOR WAS FOUND PARTIALLY ENGAGED. UNIT WAS REPLACED AND THE AIRCRAFT RETURNED	 TO SERVICE.  THIS AIRCRAFT WAS LAST INSPECTED ON 11/28/2006 AT 218HR.				2	H	7	2 	4F			RT	A16SW   					 
2007041100001	20070411	00001	SO  	2007	4	11	2007FA041101     	1	20070407	G	7160		AIR BOX         			PIPER 	PA18  	PA18105SPEC 	7101808	SO  	LYC   	O360  	O360*       	41514	EA  					CARBURETOR	FAILED          	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	8326	96   	7    			182341				CARBURATOR AIR BOX AIR FILTER RETAINING SHAFT SHEARED ADJACENT TO FISH MOUNTH WELD AT FORWARD EDGE OF HORIZONTAL PLATE (	APPROXIMATELY 1/3 SHAFT LENGTH FROM BASE).  AIR FILTER DOME, SHAFT AND RETAINING NUT APPEARANTLY DEPARTED AIRPLANE IN FL	IGHT. AIR FILTER WAS FOUND LOOSE IN COWL AIR SCOOP AFTER LANDING.  NO OPERATIONAL INDICATIONS AND NO DAMAGE TO PROPELLER	, COWL, FUSELAGE OR LANDING GEAR.  AIRPLANE COMPLETELY REBUILT 2004. NEW K & N AIR FILTER INSTALLED AT ANNUAL INSPECTION	 NOVEMBER 2006. PHOTOS AVAILABLE.		1	H	7	1 	3O	3	O		1A2     	E286				 
2007032300001	20070323	00001	SW  	2007	3	23	2007FA0703221    	1	20070322	G	3234	5059	HANDLE          			MOONEY	M20   	M20A        	5870204	SW  	LYC   	O360  	O360*       	41514	EA  					MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	17	1068B					1295				GEAR HANDLE (MECHANICAL RETRACTION HANDLE) BROKE OFF IN THE PILOT'S HAND DURING GEAR EXTENSION ON LANDING APPROACH. THE 	LANDING GEAR DISENGAGED BUT IT DID NOT EXTEND FULLY.   THE BREAK WAS JUST BELOW THE WELD.					1	L	7	1 	3O	3	O		2A3     	E286				 
2007102300153	20071023	00153	CE  	2007	10	23	2007FA1015001    	1	20071015	G	2435	MHB6016	STARTER GEN     			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	52298	376  				17274489	L1342739A			STARTER BENDIX DRIVE HAS NOT BEEN FULLY RETRACTING AFTER ENGINE START AND HAS BEEN SCRAPING THE ENGINE STARTER RING GEAR	, CAUSING WEAR ON STARTER RING GEAR AND BENDIX ENGAGEMENT GEAR.  WHEN THE BENDIX DRIVE DOES NOT DISENGAGE FROM STARTER R	ING GEAR COMPLETELY, THE BENDIX DRIVE DISENTIGRATES ALSO DAMAGING THE ENGINE STARTER RING GEAR.  THIS IS A REOCCURING 	PROBLEM. WITH SILVER BENDIX DRIVES, P/N EBB-75A.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007030900061	20070309	00061	CE  	2007	3	9	2007H0002        	1	20070305	G	2730	556545092	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR	MISOVERHAULED   	B			R3R2	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	2663Y					550602				ACTUATOR RODS PROVIDED WITH UNIT WERE TOO SHORT TO MOVE ELEVATOR TABS THE REQUIRED AMOUNT.						1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008011100229	20080111	00229		2008	1	11	2008FA0000005    	4	20071220	G	2565		CABLE           																	ESCAPE SLIDE	WRONG PART      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35										INCORRECT PULL HANDLE CABLE (FIRING CABLE) DEPLOYMENT CABLE WAS SECURED WITH TAPE WHICH HINDERED DEPLOYMENT OF SLIDE.  I	NCORRECT HANDLE AND CABLE ASSEMBLY FITTED.  CABLE NOT THREADED TROUGH GROMMET DUE TO INCORRECT FIRING CABLE ASSEMBLY.  C	MM 25-61-10, STEPS 26 PAGE 50 WAS NOT FOLLOWED. 8130-3 TRACKING NR SBP-5473, SO NR 287413, PO NR R9246, DATED 10/23/2007	, MO 0598171.																 
2008011400027	20080114	00027	NE  	2008	1	14	2008FA0000020    	2	20071015	G	7200		ENGINE          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  						MAKING METAL    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	179CB		26   			1412	34435			ON GROUND RUN, ENGINE CHIP DETECTOR ILLUMINATED. BOTH DETECTORS HAD METAL SLIVERS. SAMPLES TAKEN, AND MFG CONDEMNED ENGI	NE.  ENGINE REMOVED FROM SERVICE, AND RETURNED TO MFG FOR REPAIR.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008011400026	20080114	00026	NE  	2008	1	14	2008FA0000022    	2	20071221	G	7261		OIL JET         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2F    	60010	NE  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	183CB	618  	18   			1421	34428			ENGINE EXPERIENCING INTERNAL OIL LEAKAGE.  MFG CONDEMNED ENGINE. ENGINE REMOVED SERVICE, AND RETURNED TO MFG FOR REPAIR.						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008011400025	20080114	00025	NE  	2008	1	14	2008FA0000024    	2	20071019	G	7200		ENGINE          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2F    	60010	NE  						MAKING METAL    	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	197CB	249  	49   			1448	34506			ENGINE CHIP DETECTOR ILLUMINATED. BOTH CHIP DETECTORS HAD METAL CONTAMINATION. SAMPLES TAKEN, AND MFG CONDEMNED ENGINE. 	ENGINE REMOVED FROM SERVICE, AND RETURNED TO MFG FOR REPAIR.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008012200105	20080122	00105		2008	1	22	2008FA0000026    	2	20071227	G	7322	10603511	CARBURETOR      																	ENGINE	FAILED          	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										CARBURETOR FAILED THE STUMBLE TEST, FOUND TO BE ACCELERATOR CIRCUIT.  PART RETURNED TO PRECISION FOR FURTHER EVALUATION.	  (K)																		 
2008012200107	20080122	00107	CE  	2008	1	22	2008FA0000027    	1	20071212	G	5320	109033	BRACKET         			CESSNA	185   	185A        	2072804	CE  	CONT  	O470  	IO470F      	17026	SO  					ALTERNATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	10044	45   				1850419				INSTALLED PLANE POWER ALTERNATOR CONVERSION KIT, STC SA 10682SC ON AC.  DURING OIL CHANGE FOUND ALTERNATOR BRACKET CRACK	ED TOTOALLY IN HALF.  ALTERNATOR HAD ONLY BEEN IN USE 3 WEEKS AND APPROX 45 HRS.  (K)					1	H	7	1 	3O	3	O		3A24    	3E1				 
2008012200112	20080122	00112	SO  	2008	1	22	2008FA0000028    	1	20071226	G	7312	MS21919DG3	CLAMP           			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					HEAT BOX	LOOSE           	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			AL	01	7637D					225346				ENGINE DID NOT RESPOND WHEN POWER APPLIED ON A LOW FLY BY AND CAUSED THE PLANE TO LAND NEXT TO RUNWAY IN SNOW,  DAMAGING	 ACFT.  FOLLOWING PROBLEMS WERE FOUND ON POST INCIDENT INSPECTION OF ENGINE AND EITHER ONE CAN CONTRIBUTE TO LOSS OF LIT	TLE ALONE BOTH TOGETHER.  FOUND CARBURETOR HEAT CABLE CLAMP LOOSE ON CABLE HOUSING.    WRONG CLAMP INSTALLED ON CARBURET	OR HEAT CABLE HSG AT REAR OF AIR BOX. AND MUFFLER END WITH THE CARB HEAT SHROUD HAS A SUBSTANTIAL EXHAUST LEAK INTO THE 	CARB HEAT SHROUD.  THE INSIDE OF THE CARB HEAT SHROUD, SCAT HOSE AND AIR BOX ARE VERY SOOTY FROM EXHAUST GASSES.  THE EX	HAUST MUFFLER CLAMP LEAKING.  THIS WILL CAUSE A POWER LOSS DUE TO THE HOT INDUCTION AIR,   (K)	1	H	7	1 	3O	3	O		1A6     	E274				 
2008012200050	20080122	00050	NE  	2008	1	22	2008FA0000029    	2	20071230	G	7261		WARNING LIGHT   			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					CHIP DETECTOR	FALSE ACTIVATION	D				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			GL	21	372HS					1460	34517			ENGINE CHIP LIGHT IN CRUISE FLIGHT.  INSPECTED BOTH MAGNETIC PLUGS FOR FOREIGN MATERIAL, NONE WAS NOTED.  INSPECTED AND 	TESTED MAGNETIC PLUG HEADS IAW 79-38-00-750-801, INSPECTION AND OPS CHECKS WERE GOOD.  REMOVED AND REPLACED ENGINE OIL A	ND RETURN FILTER IAW 79-24-05-901-801-A01.  OPS AND LEAK CHECKS GOOD.  (K)				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008012200128	20080122	00128	NE  	2008	1	22	2008FA0000030    	3	20071211	G	6111	6607132886	BLADE           	ROTOL       												ROTOL	R389	R389*       	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		34226								BLADE RECEIVED FROM CUSTOMER WITH A CRACKED ROOT END OUTERSLEEVE.  NO REPAIR AVAILABLE.  PART HAS BEEN REMOVED FROM FURT	HER SERVICE. (K)															6	C	P30NE	 
2008012200148	20080122	00148	SW  	2008	1	22	2008FA0000031    	1	20071205	G	6710	2040012741	LINER           			BELL  	204   	UH1B        	1181410	SW  										COLLECTIVE	WORN            	D			H50L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	46969					638548				PILOT EXPERIENCED COLLECTIVE BOUNCE ON TAKEOFF.  INSPECTION OF COLLECTIVE LINERS SHOWED A SUFFICIENT AMOUNT OF LINER REM	AINING IN THE WEAR AREA.  WITH FURTHER INSPECTION, THE MINIMUM COLLECTIVE FRICTION WAS TOO LOW.  INSPECTION ON NR 3 AND 	NR 6 PHASE IAW TM 55-1520-219-PMS, PAGE 6, ITEM NR 2.14 REQUIRES TO INSPECT COLLECTIVE FRICTION LINERS FOR WEAR.  ADJUST	MENT OF MINIMUM COLLECTIVE FRICTION SHOULD ALSO BE INCLUDED IN THE PHASE INSPECTION CHECKLIST ALONG WITH VISUAL INSPECTI	ON OF THE LINERS.  (K)		1	G	7	1 	4U				EXPA1G71					 
2008012200149	20080122	00149	SO  	2008	1	22	2008FA0000032    	1	20071212	G	8011	MHB4016	STARTER         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	INOPERATIVE     	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19			326  							OPERATOR COMPLAINED THAT THE ENGINE STARTER WOULD NOT ENGAGE.  AFTER INSPECTION, FOUND THAT THE STARTER FIELD CASE HAD S	EPARATED FROM GEAR HOUSING.  A DETAILED INSPECTION OF THE FIELD CASE SCREW HOLES REVEALED THAT MOST OF THE THREADS WERE 	STRIPPED OUT AND HOLES WERE ELONGATED.  WOULD RECOMMEND THAT AT EACH 100 HR/ANNUAL INSPECTION, PERFORM TORQUE CHECK OF G	EAR HOUSING TO CASE ATTACH SCREWS AND REPAIR AS REQUIRED.  (K)			1	L	7	1 	3O	3	O		2A13    	E286				 
2008012200066	20080122	00066	EA  	2008	1	22	2008FA0000033    	1	20071015	G	2740	21207008	ACTUATOR        			CNDAIR	CL600 	CL6002B16   	1900305	EA  										PITCH TRIM	FAILED          	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	BMAI	6552 				5049				PITCH TRIM ACTUATOR, PN 21207-008, SN 344:  CONNECTOR P5CD- PINS A, B AND D ARE SHORTED TO PIN E.  THE SHORT IS LESS THA	N 1.  PIN C HAS A 25 SHORT TO PIN E.  FLEXING THE CONNECTOR CAUSES THE SHORT TO COME AND GO.  (K)					2	L	7	2 	4F			RT	A21EA   					 
2008012200051	20080122	00051	SO  	2008	1	22	2008FA0000034    	1	20071012	G	5540	63451000	SUPPORT         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					RUDDER BAR	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146R	5820 				2843160				FOUND CRACKED AFT ZEE ASSY PN 62664-000.  THE ZEE ASSY IS RIVETED TO THE TOP FWD END OF TUNNEL PLATE PN 62601-003 AND AS	 AN ATTACHMENT POINT FOR THE RUDDER BAR SUPPORT ASSY PN 63451-000 USING 4 STANDARD AN3-4A BOLTS, WHICH ARE SECURED THROU	GH NUTPLATES THAT ARE RIVETED ON BOTH FORE AND AFT ZEE ASSEMBLIES.  CRACKING POSSIBLY CAUSED BY LOOSENESS IN TOE BRAKE S	UPPORT BRACKETS PN 63468-000 ON BOTH PILOT AND CO-PILOTS SIDE.  THE STANDARD AN3-13A BOLTS USED TO ATTACH THESE TOE BRAK	E SUPPORT BRACKETS LOOSEN OVER TIME AND CAUSE LOSS OF SUPPORT TO THE RUDDER PEDAL BAR ASSY PN 63420-000.  EXCESS MOVEMEN	T IN RUDDER BAR SUPPORT ASSY.  THIS FLEXING TRANSFERS DOWN TO THE ZEE ASSEMBLIES CAUSING METAL FATIGUE AND SUBSEQUENT CR	1	L	7	1 	3O	3	O		2A13    	E286				 
2008012200043	20080122	00043	GL  	2008	1	22	2008FA0000035    	1	20071218	G	7312		CONTROL ARM     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360*       	41514	EA  					CARB HEAT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	418FP					40FC018				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE.  RECOMMEND INSTALLED THINKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING PROCESS, OR DIFFERENT ATTACH	MENT PROVISION ALTOGETHER.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008012200126	20080122	00126	NE  	2008	1	22	2008FA0000042    	2	20071212	G	8530		CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	E				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AL	05	777DH		1434 			47	42222299			CYLINDER CRACKED IN THE AREA OF EXHAUST VALVE.						1	H	7	1 	3R	3	R		A806    	5E1				 
2008021200238	20080212	00238	NE  	2008	2	12	2008FA0000045    	3	20070823	G	6111	6607132886	BLADE           	ROTOL       												ROTOL	R389	R389*       	NE  	NR 1	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		39882	4932 		DR6828288			DR6828288		PROP REMOVED DUE TO NR 1 BLADE LOOSE IN HUB.  NR 1 BLADE SN 689 WAS FOUND TO HAVE A CRACKED OUTER SLEEVE ON BLADE ROOT E	ND.  BLADE WAS REJECTED AND REMOVED FROM FURTHER SERVICE.  (K)															6	C	P30NE	 
2008013100304	20080131	00304	CE  	2008	1	31	2008FA0000064    	1	20071119	G	2435	23085001	STARTER GEN     			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  						FAILED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	03	80BZ					FA117	PCE95242			THE NR 1 BEARING FAILED RESULTING IN A CATASTROPHIC FAILURE AND AN IN FLIGHT SHUTDOWN.  THE ENGINE WAS REMOVED AND SENT 	FOR REPAIR.  DURING THE FAILURE INVESTIGATION, ELECTRICAL ARCING WAS FOUND ON THE NR 1 BEARING, INPUT SHAFT, AND STARTER	/GENERATOR DRIVE GEAR.  SD ADVISORY NR AV-2007-05 ISSUED THAT STATES ACCUMULATION OF BRUSH DUST CAN CAUSE STARTER GENERA	TOR ARMATURE LEAKAGE.  OUR RESEARCH DOES NOT SHOW ANY PREVENTATIVE MAINTENANCE ACTIONS THAT MAY BE PERFORMED TO THE STAR	TER GENERATOR TO CHECK FOR ELECTRICAL DISCHARGE.  (K)		2	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008012900294	20080129	00294	CE  	2008	1	29	2008FA0000065    	1	20070824	G	3246		WHEEL HALF      			CESSNA	310   	310L        	2074230	CE  										LANDING GEAR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	63EL	2200 				310L0088				UPON CHANGING A TIRE ON A CLEVELAND WHEEL ASSEMBLY ON ABOVE AIRCRAFT IT WAS DISCOVERED THAT THE PORTION OF THE WHEEL HAL	F THAT HOLDS THE BEARING RACE WAS CRACKING. IT HAD CRACKED OVER 180 DEGREES AROUND THE AXLE OPENING, WHICH COULD HAVE EV	ENTUALLY HAD A SERIOUS ACCIDENT.				1	L	7	2 	3O				3A10    					 
2008020400105	20080204	00105	SO  	2008	2	4	2008FA0000067    	2	20071219	G	7414		GEAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					RT MAGNETO	MAKING METAL    	B			XGKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	293DC					C0193	806439			PRIOR TO PERFORMING SB 03-7 INSPECTION, 2 NEW GEARS WERE ORDERED FROM MFG IN EVENT WOULD NEED THEM DURING INSPECTION.  A	T 372.9 TACH TIME, THE RT MAGNETO GEAR BROKE A TOOTH DURING START AND WAS IDENTIFIED DURING  PRE-TAKEOFF RUNUP.  THE ENG	INE WAS INSPECTED AND FOUND TO HAVE METAL PARTICLES DISTRIBUTED THROUGHOUT THE ENGINE.  (K)				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2008022000062	20080220	00062	GL  	2008	2	20	2008FA0000076    	1	20071221	G	3233		ACTUATOR        			AMTR  	QUTAIR	QUESTAIRVENT	0561898	GL  	CONT  	O550  	IO550N      	17042	SO  	MCAULY	2A34C	B2A34C205   	GL  	MLG	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	19	203V	35   				22				NOSE GEAR LINEAR ACTUATOR TRIPPED CIRCUIT BREAKER INFLIGHT AND WAS NOT DETECTED PRIOR TO LANDING.  THE AIRCRAFT WAS INAD	VERTENTLY LANDED WITH THE NOSE GEAR NOT EXTENDED.  WHEN THE AIRCRAFT WAS RECOVERED, THE AIRCRAFT WAS LIFTED SO THE GEAR 	COULD BE EXTENDED.  WHEN POWER WAS APPLIED TO THE AIRCRAFT AND THE CIRCUIT BREAKER WAS RESET THE NOSE GEAR EXTENDED NORM	ALLY AND LOCKED IN THE DOWN POSITION, THE CIRCUIT BREAKER DID NOT TRIP.  OTHER AIRCRAFT IN THE FLEET HAVE HAD PROBLEMS W	ITH THE GEAR ACTUATOR BREAKERS BEING TO LOW OF A RATING BUT THIS AIRCRAFT HAS THE HIGHER RATED BREAKER INSTALLED.		1	L	7	1 	3O	3	O	RT	EXPA1L71	E3SO	5	C	P3EA	 
2008031000331	20080310	00331	CE  	2008	3	10	2008FA0000090    	1	20071112	G	2797	C352B20	WIRE            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					PITCH TRIM	CHAFED          	B			AKGR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CE	05	213BK	3287 				RK216				PITCH TRIM INOPERATIVE REMOVED RT FWD GALLEY AND RT FWD PARTITION.  FOUND WIRE BUNDLE CHAFED BEHIND PARTITION.  REPAIRED	 (3) WIRES THAT WERE CHAFED THROUGH TO THE CONDUCTORS.  PROVIDED CLEARANCE BETWEEN WIRE BUNDLE AND PARTITION.  INSTALLED	 ANTI-CHAFE MATERIAL ON PARTITION.  AT THE TIME OF THE REPAIR NO OTHER COMPONENTS HAD MALFUNCTIONED FRO THE OTHER (2) CH	AFED WIRES.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2008031000342	20080310	00342	SO  	2008	3	10	2008FA0000097    	2	20071226	G	8520	649900	CRANKSHAFT      			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O550  	TSIO550C    		SO  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	47BC					4608129	814584			CRANKSHAFT BROKE JUST AFT OF PROPELLER MOUNTNG FLANGE.  (K)						1	L	7	1 	3O	3	O	RT	A25SO   	E5SO				 
2008031000345	20080310	00345	SO  	2008	3	10	2008FA0000098    	1	20071226	G	3221	1303400	MOUNT           			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AL	01	7637D					225346				FOUND NOSE GEAR MOUNT CORRODED THIN IN SPOTS ON THE LOWER TUBES FROM THE INSIDE.  ORIGINAL THICKNESS .049 INCH AND IN TH	E THIN SPOTS THE THICKNESS WAS LESS THAN .020 INCH.  THE MOUNT HAD BEEN REPAIRED BY WELDING AND ONE WELD WAS A COLD WELD	 THAT CRACKED AND ALLOWED MOISTURE INTO THE INSIDE OF THE TUBING.  ANNUAL INSP 35 HOURS BEFORE FAILURE.  THE MOUNT FAILE	D ON A SOFT FIELD LANDING AND CAUSED SUBSTANTIAL DAMAGE AFTER AN ENGINE FAILURE.  IN MY OPINION THE THIN WALL FROM THE C	ORROSION IS WHY THE MOUNT FAILED.  RECOMMENDATIONS TO PREVENT SUCH RECURRENCES ARE TO INSPECT ALL WELDS FOR CRACKS, ESPE	CIALLY FIELD REPAIRS.  THESE FIELD REPAIR WELDS NEED TO BE EXAMINED FOR THE QUALITY OF THE WELD, CRACKS AND PIN HOLES EA	1	H	7	1 	3O	3	O		1A6     	E274				 
2008031900366	20080319	00366	EA  	2008	3	19	2008FA0000103    	2	20071030	G	7414	6393	MAGNETO         								LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	WORN            	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			GL	15	51RF	58   								ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING, OUT OF LIMITS.  DISASSEMBLED MAG AND FOUND	 THE CAM WORN OUT . 58.7 HRS SINCE NEW.										3	O			1E4				 
2008032400435	20080324	00435	SO  	2008	3	24	2008FA0000105    	1	20071204	G	3213	31661STCSA4618NM	FITTING         			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O360  	O360A1A     	41514	EA  					RT MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AL	03	723C					181150				PILOT STATED THAT HE PERFORMED AN OFF AIRPORT LANDING ALONG A BEACH WHILE HUNTING.  UPON LANDING, THE UPPER RT MLG CABAN	E FITTING BROKE.  THE LANDING GEAR SAFETY CABLES PREVENTED A TOTAL GEAR COLLAPSE.  (K)					1	H	7	1 	3O	3	O		1A2     	E286				 
2008033100046	20080331	00046	SO  	2008	3	31	2008FA0000109    	1	20071221	G	3210	6569100	TORQUE LINK     			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					MLG	SEPARATED       	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	23	9855W	6910 				2823369				TORQUE LINK SEPARATED ON ABORTED LANDING ALLOWING WHEEL AND AXLE ASSY TO SEPARATED FROM AC.  SAFE LANDING ON UPPER CASTI	NG ASSY WAS MADE WITH DAMAGE TO CASTING AND FLAP.  AD 72-08-06 OR THIS LINK CALLED FOR 500 HR INSP.  INTERVAL PAR 203.8 	HR PRIOR.  WOULD SUGGEST THAT AD SHOULD BE CHARGED TO RETIRE THESE PARTS AT 5000 HR.  (K)				1	L	7	1 	3O	3	O		2A13    	E274				 
2008033100144	20080331	00144	GL  	2008	3	31	2008FA0000134    	1	20070727	G	2822	51000020	PUMP            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					FUEL SYS	INOPERATIVE     	C			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	423FP	156  				40FC023				AFTER A PREVIOUS FLIGHT AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE.  INADEQ	UATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS.  PROVIDE RAM AIR PROPER COOLING OF THE FUEL PUMP A	ND MOTOR.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008033100145	20080331	00145	GL  	2008	3	31	2008FA0000136    	1	20070221	G	2822	51000020	PUMP            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					FUEL SYSTEM	INOPERATIVE     	D			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	424FP	232  				40FC024				AFTER A PREVIOUS FLIGHT, AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE.  INADE	QUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS.  PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP 	AND MOTOR.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008033100174	20080331	00174	EU  	2008	3	31	2008FA0000147    	1	20070615	G	6710		COVER           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					COLLECTIVE STICK	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	11	4048L	2732 				3020	9245			COLLECTIVE MOUNTED HOIST EMERGENCY RELEASE (JETT) SWITCH COVER SECURITY.  IF THE BASE OF THE COVER IS LOOSE AND TURNED 1	80 DEGREES, AS WAS THE CASE HERE, THE COVER OPENS FORWARD AND EXTENDS OFF OF THE END OF THE COLLECTIVE.  IN THIS CONDITI	ON WHEN THE COLLECTIVE IS FULLY LOWERED, THE PUSHBUTTON COVER JAMS AGAINST THE GENEVA MODIFIED CENTER CONSOLE UNTIL THE 	PILOT PUSHES THE COLLECTIVE THROUGH THE BINDING, AND THE HINGED COVER POPS UP AND OUT OF THE WAY.  IN THIS CONDITION, WI	TH THE COLLECTIVE JETT SWITCH OPEN COVER WEDGED AGAINST THE CENTER CONSOLE, A PILOT MAY FEEL THAT THE COLLECTIVE IS FULL	Y DOWN WHEN IT IS NOT.	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008041000261	20080410	00261	CE  	2008	4	10	2008FA0000222    	1	20071116	G	3260	513771	DOWNLOCK SWITCH 			CESSNA	210   	210L        	2073448	CE  										MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	987M	3344 				21061093				EXAMINATION OF THE LANDING GEAR SYSTEM REVEALED THAT THE LT LDG DOWN LIMIT SWITCH PLUNGER WAS DAMAGED AND STUCK IN THE D	EPRESSED POSITION WITH APPROX .012 INCH AIRGAP BETWEEN PLUNGER TIP AND STRIKER PLATE.  WITH SIMULATED AIR LOADS APPLIED 	TO THE LT MAIN GEAR THE LANDING GEAR PUMP WOULD SHUT OFF PRIOR TO THE LT MAIN GEAR LOCKING IN THE DOWN LOCK.  THE GEAR P	OSITION INDICATOR IN THE COCKPIT INDICATED GREEN AND THE UNSAFE HORN DID NOT SOUND WHEN THE THROTTLE WAS RETARDED.  (K)			1	H	7	1 	3O				3A21    					 
2008041000233	20080410	00233	EA  	2008	4	10	2008FA0000228    	2	20071016	G	8530		INTAKE VALVE    			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	49811				23C064444	15281332				FOLLOWING ACCIDENT THAT RESULTED IN ENGINE FAILURE, INVESTIGATION FOUND NO COMPRESSION ON THE NR 1 CYL AND REPORTED VALV	E CLEARANCE WAS 0.002 INCH. THE CYL WAS NOT REMOVED AND THE AC WAS RELEASED INTO CUSTODY.  REMOVED THE NR 1 CYLINDER AND	 VALVES.  BOTH VALVES HAD ACCELERATED WEAR TO THE VALVE SEATS WITH EVIDENCE OF LEAKAGE.  LAST VALVE GUIDE CHECK WAS PERF	ORMED 46 HOURS EARLIER WITHIN LIMITS.  (K)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2008042500111	20080425	00111	SO  	2008	4	25	2008FA0000251    	1	20071114	G	5343	95555000	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					NLG MOUNT	SEPARATED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	467TC					347870006				SB 1123B TABLE 1, ITEM 14 STATES TO INSPECT TUNNEL BRACKET 95554-000 AND FITTING 95555-000 FOR CONDITION AND ATTACHMENT.	  ACCORDING TO FIGURE 1A, THE CONDITION INDICATED NO PROBLEMS, HOWEVER FITTING 95555-000 WAS SEPARATED FROM BRACKET 9555	4-000.  ALL 4 AN426 RIVETS HAD SHEARED, ALLOWING FITTING TO SHIFT POSITIONS, ALLOWING NOSE GEAR OVERCENTER GEOMETRY TO C	HANGE, RESULTING IN GEAR COLLAPSE.  ITEM 14 DESCRIBES INSPECTION THROUGH AND ACCESS OPENING IN BOTTOM SKIN AT BL 0.0 JUS	T AFT OF STATION 49.5.  IT IS UNCLEAR WHETHER THIS  ACCESS OPENING IS TO BE CUT IN THE SKIN AND A DOUBLER AND INSPECTION	 PLATE INSTALLED OR IF THIS HOLE IS ALREADY PRESENT.  NO PA-34 AC IN OUR FLEET HAS THIS OPENING.  THIS DEFECT WAS NOTED 	1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2008042800299	20080428	00299	NM  	2008	4	28	2008FA0000255    	1	20071202	G	2497		CIRCUIT BREAKER 			AMD   	FALC50	FALCON2000  	2730170	NM  	PWC   	PW308 	PW308C      	52182	NE  						MISINSTALLED    	W			BO5Y	K				NONE                    				W	B		INADEQUATE Q C            	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			EA	33	4QG					028				MAU 1B AND AGM 2 FAIL IN FLIGHT AND RECOVERED AFTER 3 SECONDS.  SHUNT (IPC 24-05-10, ITEM 210) INSECURED ON BREAKER, ELE	CTRIC ARC.  ONE SCREW ON BREAKER L501X, TOO THREAD LENGTH OVERSIZED.  RESULTS: EXCHANGE SHUNT AND BREAKERS.  (K)					2	L	7	2 	4F	4	F	RT	A50NM   	E00065EN				 
	20080603		CE  	2008	6	3	2008FA0000319    	1	20071225	G	5100		UNKNOWN         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  						UNKNOWN         	D				O				OTHER                   				G			MULTIPLE FAILURE          			CR	CRUISE         	1			WP	05	6079C					R18200371	RL1970540A			INFLIGHT FAILURE OF PART OR PARTS UNKNOWN WITH NO SYMPTOMS FROM WITHIN COCKPIT, IE: OIL PRESSURE, OIL TEMPERATURE, AND C	YLINDER HEAD TEMPERATURES WERE ALL INDICATING WITHIN NORMAL RANGES.  OUTWARD MANIFESTATIONS WERE EXCESSIVE BLOW-BY OIL O	N BELLY OF THE AIRPLANE.  OTHER MANIFESTATIONS WERE: AN INTERRUPTION IN THE SMOOTH MOVEMENT OF THE PROP (WHEN ROTATING B	Y HAND) AT THE SAME LOCATION IN THE ROTATION ON EVERY OTHER COMPLETE ENGINE ROTATION, IE: RELATED TO THE CAMSHAFT (720 D	EGREES OF ROTATION).  A CRACK IN THE LT SIDE OF THE ENGINE CASE OVER THE BASE OF THE NR 5 CYLINDER WHERE THE ENGINE CASE	 FARES INTO THE INTAKE VALVE PUSHROD TUBE.  A CRACK IN THE RT SIDE OF THE ENGINE CASE OVER THE BASE OF THE NR 6 CYLINDER	1	H	7	1 	3O	3	O	RT	3A13    	E295				 
	20080715		GL  	2008	7	15	2008FA0000342    	1	20070910	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360LYC*   	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	PAX DOOR	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			WP	07	686US	615  				40640	L3262751A	CH39554B		ON TAKEOFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K)						1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920	 
	20080715		GL  	2008	7	15	2008FA0000344    	1	20071106	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360LYC*   	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	PAX DOOR	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			WP	07	605US	225  				40675	L3276151A	CH399768		WHILE TAXIING INTO TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)						1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920	 
	20080715		EA  	2008	7	15	2008FA0000375    	2	20071226	G	7322	MS21919DG3	CLAMP           	PIPER       		PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					CARB HEAT	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	7637D					225346				ENGINE DID NOT RESPOND WHEN POWER WAS APPLIED ON A LOW FLY BY OF THE RUNWAY AND CAUSED THE PLANE TO LAND NEXT TO THE RUN	WAY IN THE SNOW DAMAGING THE AIRCRAFT. THE FOLLOWING TWO PROBLEMS WERE FOUND ON POST INCIDENT INSPECTION OF THE ENGINE A	ND EITHER ONE CAN CONTRIBUTE TO LOSS.  THE FIRST PROBLEM FOUND WAS THE CARBURETOR HEAT CABLE CLAMP WAS LOOSE ON THE CABL	E HOUSING. THIS WOULD ALLOW THE HOUSING TO SLIP IN THE CLAMP AND SOMETIME NOT MAKE STOP TO STOP TRAVEL. THE WRONG CLAMP 	WAS INSTALLED ON THE CARBURETOR HEAT CABLE HOUSING AT REAR OF AIR BOX. THE CLAMP INSTALLED  WAS PN MS21919GD3 (3/16) INC	H DIAMETER ADEL CLAMP. THE ADEL CLAMP USED HAS AN CHLOROPRENE RUBBER CUSHION WITH A MAXIMUM TEMP OF 212 DEGREES (F). THE	1	H	7	1 	3O	3	O		1A6     	E274				 
	20080715		SO  	2008	7	15	2008FA0000376    	1	20071226	G	7810	1423500	CLAMP           			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					EXHAUST PIPE	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	7637					225346				ENGINE DID NOT RESPOND WHEN POWER WAS APPLIED ON A LOW FLY BY OF THE RUNWAY AND CAUSED THE PLANE TO LAND NEXT TO THE RUN	WAY IN THE SNOW DAMAGING THE AIRCRAFT.  THE FOLLOWING PROBLEM WAS FOUND ON POST INCIDENT INSPECTION OF ENGINE AND EITHER	 ONE CAN CONTRIBUTE TO LOSS. THE PROBLEM FOUND WAS THE MUFFLER END WITH THE CARB HEAT SHROUD HAS A SUBSTANTIAL EXHAUST L	EAK INTO THE CARB HEAT SHROUD. THE INSIDE OF THE CARB HEAT SHROUD, SCAT HOSE AND AIR BOX ARE VERY SOOTY FROM EXHAUST GAS	SES.  THE EXHAUST MUFFLER PN 10308-03 END THAT EXHAUST PIPE PN 12043-23 END SLIDES INTO AND HAS PN 14235-00 EXHAUST CLAM	P AROUND IT IS LEAKING.  THE PIPE END THAT SLIPS INTO THE MUFFLER IS VERY LOOSE, NOT A TIGHT SEAL LIKE NORMAL. THE CLAMP	1	H	7	1 	3O	3	O		1A6     	E274				 
	20080715		EU  	2008	7	15	2008FA0000386    	1	20071101	G	3250		STEERING SYS    			PIAGIO	P180  	P180        	6960204	EU  										NLG	CONTAMINATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07										STEERING SYSTEM DISENGAGEMENT DURING TAXI.  STEERING DRIFT DURING ENGAGEMENT. STEERING HART TO TURN (NO INPUT). STEERING	 RELIABILITY VERY LOW.  STEERING CONTAMINATION DURING MFG BENCH TESTING.  AIRCRAFT RUNWAY EXCURRSION DURING LANDING AND 	TAXI DUE TO STEERING CONTROL LOSS.  AIRCRAFT DAMAGED FROM STEERING DRIFT DURING LANDING.  (K)				1	H	7	2 	3O			RT	A59EU   					 
	20080715		EA  	2008	7	15	2008FA0000417    	2	20071221	G	8500	IGSO480	ENGINE          			BEECH 	65    	A65         	1152803	CE  	LYC   	O480  	GSO480*     	41529	EA  					LEFT	SEIZED          	G				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8108R					LC329	L119933C			AIRCRAFT LANDED WITH LT ENGINE SHUTDOWN (IN-FLIGHT SHUTDOWN). INITIAL INVESTIGATION REVEALED THAT THE ENGINE WAS SEIZED.	 OIL SCREEN WAS REMOVED AND FOUND HEAVILY CONTAMINATED WITH METAL PARTICLES.  ENGINE OIL SUMP DRAIN PLUG WAS REMOVED.  L	ARGE METAL PARTICLES, SOME APPROXIMATELY .25 IN DIAMETER WERE REMOVED FROM IMMEDIATELY INSIDE THE SUMP DRAIN HOLE.  OTHE	R PARTICLES APEAR TO BE GEAR TEETH, AS SHEARED FROM THE GEAR.  ENGINE WAS REMOVED FROM THE AIRCRAFT(12-18-2007) AND SENT	 TO CUSTOMER DESIGNATED REPAIR FACILITY.  (K)		1	L	7	2 	3O	3	O		3A20    	E284				 
	20080715		GL  	2008	7	15	2008FA0000423    	1	20071106	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  										REAR PASSENGER	DEPARTED        	G				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			WP	28	605US					40675				WHILE TAXIING INTO TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)						1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000425    	1	20070910	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  										REAR PAX DOOR	DEPARTED        	G				O				OTHER                   				S			AFFECT SYSTEMS            			TO	TAKEOFF        	1			WP	28	686US					40640				ON TAKEOFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)						1	L	7	1 	3O			NT	A47CE   					 
2007032200048	20070322	00048	CE  	2007	3	22	20582007TJ001    	1	20070313	G	5344	551123515	HINGE           	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					PAX DOOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	6763L	6986 				5500673				DURING A DAILY INSPECTION OF THE AIRCRAFT A CRACK WAS FOUND ON THE UPPER LUG OF THE DOOR HINGE. DURING REPLACEMENT OF TH	E HINGE THE LUG COMPLETELY BROKE IN (2) PEICES.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007121400292	20071214	00292	NM  	2007	12	14	220757           	1	20071205	G	2913	65446747	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										MODULE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					0728					HOUSING WAS FOUND CRACKED DURING TEARDOWN IN SHOP.						2	L	7	2 	4F			RT	A16WE   					 
2007120500045	20071205	00045		2007	12	5	243DR1           	4	20071121	G	2216	1C7921888	SERVO           			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ELEVATOR TRIM	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	243DR	4056 				U20604747				WHILE UNDERGOING A SCHEDULED INSPECTION, MECHANIC FOUND ELEVATOR TRIM SYS WAS MISRIGGED. TRAVEL LIMITS WERE NOT CORRECT 	AND WERE ACTUALLY RIGGED OPPOSITE WITH REGARDS TO MAX TRAVEL UP/DOWN. TRAVEL LIMITS IN MM NR D2070-3-13 FIGURE 1-1 WERE 	MISINTERPRETED, MFG SHOULD REVISE THIS MANUAL SECTION TO BE MORE SPECIFIC SINCE WE HAVE SEEN THIS BEFORE. ADDITIONALLY I	T WAS FOUND THAT ELEVATOR TRIM SYS COULD NOT BE RIGGED BECAUSE CENTURY 2000 AUTOPILOT ELEVATOR TRIM SERVO WAS NOT INSTAL	LED CORRECTLY WHEN SYS WAS INSTALLED ON 10/9/2001 UNDER STC SA3479SW-D.  FOUND SERVO MISMOUNTED, IT DID NOT MATCH CENTUR	Y DRAWING 69D1754.  REINSTALLED THE TRIM SERVO IAW THE STC DRAWINGS.	1	H	7	1 	3O	3	O		A4CE    	E8CE				 
2007051500183	20070515	00183	GL  	2007	5	15	26519A           	3	20070502	G	6111	A4564	BUSHING         	MCAULY      		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	BLADE LINK	CRACKED         	B			WIWA	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	07	122JB	1850 				208B1025		020657		VIBRATION REPORTED BY PILOT.  OPERATOR WAS UNABLE TO DYNAMIC BALANCE.  OPERATOR NOTICED ONE BLADE HAS ROTATIONAL PLAY.  	UPON DISASSEMBLY NR 2 BLADE LINK BUSHING P/N A4564 WAS FOUND CRACKED WITH PIECES MISSING.  THE LINK P/N B4743 AND BLADE 	ACTUATING PIN P/N B5072-1 WERE DAMAGED FROM METAL TO METAL CONTACT.				1	H	7	1 	3T	3	T		A37CE   	E2NE	5	C	P60GL	 
2007051100151	20070511	00151	SW  	2007	5	11	31038042507      	1	20070425	G	5610	3G5630F00111A2	WINDOW          			AGUSTA	AB139 	AB139       	0260110	SW  	PWA   	PT6   	PT6*        	52043	EA  					CREW DOOR	DEPARTED        	B				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			EA	17	139BK					31038				DURING CRUISE FLIGHT AT AN ALTITUDE OF 2000FT, IAS 152KTS,THE CO-PILOT DOOR WINDOW SEPARATED FROM AIRCRAFT.						2	G	7	2 	6U	3	T		R00002RD	E2NE				 
2007040200151	20070402	00151	CE  	2007	4	2	40675            	1	20070320	G	2741	45AS610023139	ACTUATOR        			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					PITCH TRIM	INOPERATIVE     	C			R71A	O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			WP	05	790SS	1550 				RK363				DIFFICULTY OCCURED UPON DESCENT.   PILOT RECIEVED A WARNING PITCH TRIM WAS NOT SYNCRONIZED WITH AUTOPILOT SYSTEM AND TO 	PREPARE FOR RESISTANCE WHEN AUTOPILOT IS DISCONNECTED. PITCH TRIM ACTUATOR WAS FOUND INOPERATIVE IN THE EMERGENCY MODE/A	UTOPILOT MODE.  REPLACED PITCH TRIM UNIT AND RETURNED AIRCRAFT TO SERVICE. THIS AIRCRAFT WAS LAST INSPECTED ON 11-9-06 A	T 1408.6 TT.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007120400107	20071204	00107	CE  	2007	12	4	470884           	1	20071105	G	4940	CH3459	IGNITER         	HONEYWELL   	RE100       	LEAR  	45    	45LEAR      	5170805	CE  										APU	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	762EL	549  			P205	107				TIP OF IGNITER BROKE OFF AND WAS FOUND DURING COMPLIANCE WITH SB45-28-12.						2	L	7	2 	4F			RT	T00008WI					 
2007100300005	20071003	00005	SO  	2007	10	3	4757             	2	20070925	G	8530	AEC631397	CYLINDER        	CONT        		CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT ENGINE	CRACKED         	B			FCPR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	09	919FA	1120 			276632R	414A0628	276632R			PILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT C	OULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE N	R 4 CYLINDER TO BE CRACKED AT THE PARTING SURFACE. EXHAUST WAS ESCAPING FROM THE CRACK CAUSING THE (AIR PULSING) SOUND.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007121400346	20071214	00346	CE  	2007	12	14	68DA             	1	20070213	G	5512		SKIN            			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					HORIZONTAL STAB	WRINKLED        	B			ODAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	68DA					BE14				DURING ROUTINE MAINTENANCE, MECHANIC DISCOVERED THAT THE HORIZONTAL STABILIZER SKIN WAS WRINKLED AT THE AFT RT ATTACH PI	VOT POINT.					1	L	7	2 	4T	3	T		A14CE   	E2WE				 
2007062500008	20070625	00008	GL  	2007	6	25	A101913          	2	20070612	G	7260	23038229	GEAR            	ALLSN       	T63A720     						ALLSN 	250C  	T63A720     	03002	GL  					GEARBOX ASSY	FRACTURED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25					NA		AE405995			ENGINE WAS SENT FOR REPAIR DUE TO GENERATING METAL.  UPON DISASSEMBLY FOUND THAT THE SHAFT ON THE FORWARD SIDE OF THE CE	NTRIFUGAL BREATHER GEAR WAS FRACTURED IN THE AREA OF THE RADIUS WHERE THE SHAFT JOINS THE GEAR.  THE RELATIVE MOTION BET	WEEN THE SHAFT AND THE GEAR WAS THE CAUSE OF METAL GENERATION.									3	U			E4CE				 
2007062500009	20070625	00009	GL  	2007	6	25	A1019131         	2	20070612	G	7260	23038229	GEAR SHAFT      	ALLSN       	T63A720     						ALLSN 	250C  	T63A720     	03002	GL  					GEARBOX ASSY	FRACTURED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25					NA		AE405995			ENGINE WAS SENT FOR REPAIR DUE TO GENERATING METAL.  UPON DISASSEMBLY FOUND THAT THE SHAFT ON THE FORWARD SIDE OF THE CE	NTRIFUGAL BREATHER GEAR WAS FRACTURED IN THE AREA OF THE RADIUS WHERE THE SHAFT JOINS THE GEAR.  THE RELATIVE MOTION BET	WEEN THE SHAFT AND THE GEAR WAS THE CAUSE OF METAL GENERATION.									3	U			E4CE				 
2007120400293	20071204	00293	CE  	2007	12	4	AFASVRA3181      	1	20071114	G	2432	G25	BATTERY         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MASTER	OVERHEATED      	D				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			NM	03	9582V	556  				17264384	L4623627A			AIRCRAFT 12 VOLT BATTERY OVERHEATED CAUSING: ELECTROLYTE BOILING OVER, CORRODING OF ALUMINUM BATTERY BOX, LANDING LIGHT 	PLASTIC SWITCH MELTING, LANDING LIGHT PLASTIC CONNECTOR IN COWLING MELTING, LANDING LIGHT INOP AND ALTERNATOR FAILURE WI	THOUT THE LANDING LIGHT CB TRIPPING.  PILOTS COMPLYING WITH FAA RECOMMENDATIONS OF LEAVING LANDING LIGHTS ON WITHIN 5 NM	 OF AIRPORT ARE THE CAUSE OF THIS PROBLEM DURING TRAINING SORTIES OF 1 TO 2 HOURS WITH THE LANDING LIGHTS ON FOR THE DU	RATION OF FLIGHT. THESE AIRCRAFT ARE FLOWN IN A PILOT TRAINING OPERATION WHERE SORTIES ARE 1 TO 2 HOURS ENDURANCE AND 8 	TO 10 TAKEOFFS AND LANDINGS WITH THE LANDING LIGHT/LIGHTS ON FOR THE DURATION OF THE FLIGHT.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007040900033	20070409	00033	SO  	2007	4	9	AMCR200700001    	1	20070329	G	2822	B12520	PRESSURE SWITCH 			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					BOOST PUMP	FAILED          	B			AMCR	O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			GL	09	706VA	1267 				1528				DURING DESCENT, THE RT MAIN FUEL PUMP FAILED. MAINTENANCE FOUND THAT THE FUEL PRESSURE SWITCH ON THE RT MAIN FUEL PUMP H	AD FAILED. THIS IS THE SECOND FAILURE OF A PUMP PRESSURE SWITCH WE KNOW OF WITHIN THE LAST 4 MONTHS.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007062500012	20070625	00012	NE  	2007	6	25	AMCR200700002    	1	20070612	G	2612	61423473205	FIRE DETECTOR   			SKRSKY	S76   	S76B        	8143007	NE  										NR 1 ENGINE	FAULTY          	B			AMCR	O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			GL	09	520AC	2282 				760380				UPON STARTER ENGAGEMENT FOR FIRST ENGINE START (EITHER ENGINE), THE NR 1 ENGINE FIRE ANNUNCIATOR WOULD ILLUMINATE ALONG 	WITH A FIRE TONE, BUT NO T-HANDLE ILLUMINATION. ILLUMINATION AND TONE WOULD CEASE AROUND 35-45% RPM. ALL FIRE DETECTION 	TESTS WOULD CHECK OK. REPLACEMENT OF NR 1 BOTTOM FLAME DETECTOR FIXED PROBLEM.				1	G	7	2 	4U				H1NE    					 
2007071800220	20070718	00220	NE  	2007	7	18	AMCR200700003    	1	20070709	G	3240	C20497000	BRAKE ASSY      			SKRSKY	S92   	S92A        	       	NE  										MLG	BINDING         	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	252DV	572  				920009				DURING WHEEL CHANGE (LT OB) COULD NOT REMOVE THE WHEEL OFF OF AXLE. FOUND ONE OF THE CENTER STATORS (A35579) OF THE BRAK	E ASSY TO BE PROTRUDING OUT OF THE PACK. THE STATOR CUT INTO THE WHEEL PREVENTING THE REMOVAL. WE DID NOT TEARDOWN THE B	RAKE BUT SUSPECT EITHER THE STATOR IS OUT OF ROUND OR HAS ID DAMAGE, OR THE TORQUE TUBE IS DAMAGED ALLOWING STATOR TO SH	IFT BEYOND THE PACK CIRCUMFERENCE. P/N 78286/92250-00801-102.			2	G	7	2 	4U				R00024BO					 
2007121400351	20071214	00351	CE  	2007	12	14	AMCR200700004    	1	20071207	G	5753	NAS509L6	JAM-NUT         			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					TE FLAPS	WRONG PART      	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	279DV	536  				0070				DURING COMPLIANCE WITH SL525B-27-01 WHICH IS CHECKING FLAP PUSH ROD FOR IMPROPER SAFETY WIRING, FOUND THAT THE AFT JAM N	UT (NAS509L6) WAS UP AGAINST THE CENTER STUD (6365028-10) RATHER THAN TIGHT AGAINST THE ROD END TUBE (6365028-9). EVERYT	HING WAS SAFETIED IN THIS POSITION.				1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2007031300018	20070313	00018	GL  	2007	3	13	AMTR02022007     	1	20070202	G	5314		KEELBEAM        			AMTR  	AIRCAR	SPENCERAIRCR	       	GL  										FUSLEAGE	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	41RH	2437 								DURING AN ACCIDENT INVESTIGATION OF A S12D, THE AIRFRAME REAR KEEL SUPPORT WAS FOUND TO HAVE EXCESSIVE CORROSION AND THE	 WOODEN STRUCTURE ATTACHED TO THE KEEL WAS DRY ROTTED. ALTHOUGH THE CORROSION IS EVIDENT, WE BELIEVE IT WAS NOT A CAUSE 	OF THE ACCIDENT. THE AIRCRAFT WAS BUILT IN 1975 AND WAS OPERATED IN A SALT WATER ENVIRONMENT. THE AIRCRAFT HAD JUST RECE	IVED A CONDITION INSPECTION. THERE WAS NO ACCESS TO INSPECT THE KEEL SUPPORT WHICH IS LOCATED AFT OF THE PASSENGER COMPA	RTMENT. IT IS RECOMMENDED THAT AN ACCESS PANEL BE MADE TO INSPECT THE KEEL ASSEMBLY AND THAT IT BE INSPECTED AT LEAST EV	ERY CONDITION INSPECTION.	1	H	7	1 	3O				EXPA1H71					 
2007082400242	20070824	00242	SW  	2007	8	24	AOC0701          	1	20070816	G	6210		BEARING         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					PITCH LINK	DAMAGED         	B			R29R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	31893					33110				DURING A PREFLIGHT INSPECTION OF THE SUBJECT AIRCRAFT, A PITCH CHANGE LINK BEARING (ATTACHED TO THE DRIVER END) APPEARED	 TO BE WORN. THE PILOT ATTEMPTED TO MOVE THE DRIVER TO CHECK FOR WEAR BUT THE BEARING, BOLT AND DRIVER WERE TIGHT. THE P	ILOT THEN OBSERVED THE BEARING WHILE THE OTHER PILOT PULLED SLIGHTLY UP ON THE COLLECTIVE CONTROL. AS THIS OCCURRED, THE	 PILOT FOUND THAT THE BOLT AND BEARING WERE MOVING APPROXIMATELY .1875 INCH. FURTHER INSPECTION REVEALED THAT THE STEEL 	BUSHING ON THE DRIVER, TRAILING (NUT) SIDE, WAS WORN DOWN CONSIDERABLY (.0001 - .0002 INCH OF STEEL REMAINING). HAD THIS	 BEEN ALLOWED TO CONTINUE, THE BOLT WOULD HAVE STARTED TO WEAR INTO THE SOFTER METAL OF THE DRIVER, EVENTUALLY CAUSING L	1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2007071100139	20070711	00139	EU  	2007	7	11	AS350B3          	1	20070628	G	6320	350A32031002	GEARBOX         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  						WARNING LIGHT   	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	17	808CP	161  				4151	23335			MGB CHIP LIGHT CAME ON IN FLIGHT. REMOVED CHIP PLUGS FROM THE MGB AND THE MAST FOUND PARTICLES ON THE MGB PLUG LESS THAN	 LIMITS CALLED OUT IN AEC AS350B3 SPM 20.08.01.601 NOTHING ON THE MAST PLUG.  PERFORMED 10 MIN. HOVER AND RECHECKED CHIP	 PLUGS IAW AEC AS350B3 MWC 05.53.00.608 NO MORE PARTICLES FOUND AND NO RE-OCCURRENCE OF THE CHIP LIGHT.				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007121300285	20071213	00285	CE  	2007	12	13	ATL07LA057       	1	20070319	G	2810		FUEL CELL       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					RT WING	LEAKING         	G			E7TA	E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	A		FLUID LOSS                	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			SO	11	500JP					2396				DURING START OF RT ENGINE, PILOT REPORTED HEARING A LOUD THUMP, NOTED FIRE COMING FROM THE BOTTOM OF THE RT COWLING.  SH	UTDOWN ENGINES, EVACUATED AIRCRAFT, AND NOTED APPARENT EXPLOSION HAD OCCURRED IN RT WING.    VISUAL INSPECTION DID NOT R	EVEAL CAUSE OF EVENT.  WING STILL HELD APPROXIMATELY 40 GALLONS OF FUEL AND WAS NOT LEAKING ALTHOUGH BOX CELL LINER HAD 	BEEN CRACKED OPEN FROM FORCE OF EXPLOSION.  FUEL TRUCK WAS DISPATCHED AND WING WAS FULLY TOPPED OFF TO INSPECT FOR LEAKS	; NONE WERE NOTED.   AIR IN RT FUEL SYSTEM WAS DISPLACED AND AFTER APPROXIMATELY 10 MINUTES A LEAK WAS DETECTED IN THE R	T WHEEL WELL.  FURTHER INVESTIGATION REVEALED THIS LEAK WAS ORIGINATING FROM A B-NUT ON THE OUTPUT SIDE OF THE AUXILIARY	1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2007061500220	20070615	00220	CE  	2007	6	15	B3OR2007131      	1	20070511	G	2731	556545092	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ZONE 300	BINDING         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26621					5500593				A NEWLY OVERHAULED ELEVATOR TRIM TAB ACTUATOR WAS BINDING AND WOULD NOT PROVIDE ADEQUATE DEFLECTION AT THE TRIM TAB ONCE	 INSTALLED.  FURTHER INVESTIGATION REVEALED THAT THIS ACTUATOR HAD EXCESSIVE PLAY AT THE END BEARINGS AND THAT THE PRIMA	RY SPROCKET PN WAS INCORRECT RELATIVE TO THE ASSEMBLY PN. THIS ASSEMBLY WAS OVERHAULED UNDER WORK ORDER NR 15356 ON 4/2/	2002.  THE ITEM WAS RETURNED TO THE OVERHAULING AGENCY FOR WARRANTY REPAIR.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007061500219	20070615	00219	CE  	2007	6	15	B3OR2007138      	1	20070518	G	2731	556545098	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR TRIM	BINDING         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26621					5500593				FOLLOWING INSTALLATION OF A NEWLY OVERHAULED ELEVATOR TRIM TAB ACTUATOR, PARTIAL BINDING OF THE ACTUATOR OCCURRED.  FURT	HER INVESTIGATION REVEALED THAT THIS ACTUATOR HAD EXCESSIVELY WORN END BEARINGS ALLOWING LATERAL PLAY IN INTERNAL JACKSC	REWS SUFFICIENT TO CAUSE BINDING ONCE INSTALLED.  ALSO DISCOVERED THAT THE LUBRICANT IN THIS ASSEMBLY WAS GREY IN COLOR,	 WHICH IS CONTRARY TO THE LOW MOISTURE CONTENT GREASE (PINK OR WHITE IN COLOR) STRICTLY SPECIFIED IN THE COMPONENT MM. T	HIS ASSEMBLY WAS RECENTLY OVERHAULED UNDER WO NR 1059 ON 3/20/2007.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007080800028	20070808	00028	NM  	2007	8	8	BAI71007         	1	20070710	G	6300	A1902	BELT            			ROBSIN	R22   	R22BETAII   	7640110	NM  	LYC   	O360  	O360A1D     	41514	EA  					M/R DRIVE	BROKEN          	B				B				EMER. DESCENT           				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	15	7109C	1085 				2952				MAIN ROTOR DRIVE BELTS SEPARATED IN FLIGHT CAUSING THE CLUTCH ACTUATOR TO RUN EXCESSIVELY. THE OVER-TRAVEL LIMIT-SWITCH 	LANYARD WAS SEVERED BY A PORTION OF THE BROKEN BELTS AND DID NOT PERFORM IT'S INTENDED FUNCTION. THE PIC HAD TO DISABLED	 THE CLUTCH ACTUATOR SYSTEM BY PULLING THE CLUTCH CIRCUIT BREAKER AND THEN AUTO ROTATED TO THE GROUND. THERE WAS NO ADDI	TIONAL DAMAGE TO THE AIRCRAFT OR INJURY TO OCCUPANTS AS A RESULT OF THE AUTOROTATION.			1	G	7	1 	3O	3	O		H10WE   	E286				 
2007012900195	20070129	00195	EA  	2007	1	29	CA070103011      	2	20070104	G	7250		TURBINE BLADES  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	FRACTURED       	W				O				OTHER                   				R	X		PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           		CR	CRUISE         	1			CA								41266			(CAN) ENGINE OIL PRESSURE AND TORQUE WERE SEEN TO FLUCTUATE IN FLIGHT FOLLOWED BY A LOUD NOISE AND AN ENGINE FLAMEOUT.  	SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR THE INVESTI	GATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103011)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007012900201	20070129	00201	GL  	2007	1	29	CA070105004      	2	20070105	G	7240	6899237	COMBUSTION CASE 	ALLSN       	250C28B     	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAE860657		CAE860657			(CAN) DURING A 200 HR INSPECTION A CRACK WAS FOUND IN THE ARM PIT AREA OF THE OUTER COMBUSTION CASE.  CASE REPLACED. (TC	 NR 20070105004)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007050700240	20070507	00240	SW  	2007	5	7	CA070105005      	1	20070105	G	7921	206061432031	IMPELLER        	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					OIL COOLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						VN7184					(CAN) 300 HR NDT FOUND CRACKS IN THE WEB AREA.  PART REPLACED. (TC NR 20070105005)						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007050700241	20070507	00241	CE  	2007	5	7	CA070105006      	1	20070104	G	5610	10138402523	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING PRESSURIZED FLIGHT THE LT WINDSHIELD CRACKED IN SEVERAL PLACES ALL ALONG THE IB SECTION OF THE WINDOW. THE 	WINDOW WAS ORIGINALLY A REPAIRED WINDOW AND WAS INSTALLED FOR 1512.9HRS/1450CYCLES BEFORE FAILING. (TC NR 20070105006)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007012900202	20070129	00202	CE  	2007	1	29	CA070105007      	1	20070103	G	2435	66082019	SHAFT           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					GENERATOR	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				616  							(CAN) LT GENERATOR CAME OFF LINE .5 HR BEFORE LANDING . THE INDICATOR SHOWED 0 AMPS, A RESET WAS ATTEMPED BUT DID NOT CO	ME ONLINE. WHEN MAINTENANCE REMOVED THE GENERATOR FOR INSPECTION, THE GENERATOR SHAFT WAS FOUND SHEARED. THE GENERATOR W	AS INSPECTED FURTHER AND ROTATED FREELY. CAUSE OF SHEARED SHAFT IS UNKNOWN. (TC NR 20070105007)				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007050800190	20070508	00190	CE  	2007	5	8	CA070108001      	1	20070103	G	3220		LANDING GEAR    			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	NOSE	INOPERATIVE     	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) AIRCRAFT EXPERIENCED NO NOSE GEAR. (TC NR 20070108001)						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007050800191	20070508	00191	CE  	2007	5	8	CA070108002      	1	20070103	G	3260	404EN16	DOWNLOCK SWITCH 			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG	MALFUNCTIONED   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA									CVBCBNM7CXZZ		(CAN) THE AIRCRAFT ORIGINALLY EXPERIENCED A GEAR WARNING SYSTEM FAILURE ON APPROACH.  SUBSEQUENTLY, THE DOWNLOCK SWITCHE	S WERE CLEANED AND LUBRICATED AND THE SYSTEM TESTED SERVICEABLE. THE NEXT FLIGHT HAD A LT MAIN GEAR INDICATION FAILURE, 	EMERGENCY PROCEDURES WERE FOLLOWED AND THE LT GEAR INDICATION WORKED PRIOR TO TOUCH DOWN. THE AIRCRAFT WAS RETURNED TO M	AINTENANCE AND THE LANDING GEAR SYSTEM WAS TROUBLESHOT EXTENSIVELY AND TEST FLOWN EACH TIME WORK WAS CARRIED OUT  UNSUCC	ESSFULLY.  THE SNAG ONLY OCCURRED AT HIGHER ALTITUDES OR COLDER TEMPERATURES. THE LT MAIN GEAR SWITCH WAS REPLACED DUE T	O SUSPECT WATER PROPAGATION AND FREEZING. THE AIRCRAFT WAS TEST FLOWN AT THE SAME ALTITUDES AND WAS SUCCESSFUL. THE AIRC	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007012900204	20070129	00204	EA  	2007	1	29	CA070108003      	1	20070108	G	2910	TA3050052403	FAIRLEAD        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HYDRAULIC SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14717	14717							(CAN) DURING MAINTENANCE INSPECTION, FOUND FAIRLEAD (CLAMP) ON NR 1 HYDRAULIC SYSTEM LINES FAIRLEAD IN AFT FUSELAGE (APU	 COMPARTMENT) WORN. [IPC 29-11-00 FIG 15 (H) ITEM 395. BLOCK HAS 3 HOLES FOR CLAMPING HYDRAULIC LINES AND CENTER HOLE (P	RESSURE LINE) MATERIAL WORN THROUGH TO CASE DRAIN LINE HOLE, ALLOWING PRESSURE LINE AND CASE DRAIN LINE TO START CHAFFIN	G. SEVERAL SIMILAR CLAMPS IN THIS AREA ALSO EXHIBITING SIMILAR SIGNS OF WEAR. FAIRLEAD (CLAMP BLOCK) ASSEMBLY REPLACED. 	AIRCRAFT RETURNED TO SERVICE. (TC NR 20070108003)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900213	20070129	00213	WP  	2007	1	29	CA070108009      	2	20070105	G	7200	TPE33111U6	ENGINE          			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LEFT	DAMAGED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA				366  							(CAN) UPON SHORT FINAL A "POP" WAS HEARD SIMILAR TO THE SOUND OF A DOOR SEAL.  THE AIRCRAFT YAWED A BIT YET NOT ENOEGH T	O ALERT THE FLIGHT CREW THAT IT WAS ANYTHING MORE THAN TURBULENCE.  OIL PRESSURE WAS NOTED TO BE DROPPING. AN ENGINE FAI	LURE OCCURED ON THE LH SIDE.  ENGINE WAS SHUT DOWN ON THE RUNWAY AND NOT IN THE AIR.  UPON MAINTENANCE INITIAL REVIEW MO	ST OF THE DAMAGE WAS AT THE BACK OF THE ENGINE.  THERE WAS NO NOTED DAMAGE AT THE FRONT, GEARBOX, OF THE ENGINE.  FURTHE	R INVESTIGATION WIL BE CARRIED WHEN ENGINE ARRIVES AT THE OEM.  MORE DETAILS THEN.   (TC# 20070108009)		2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007050900063	20070509	00063	CE  	2007	5	9	CA070108010      	1	20070105	G	5700	817861018	BOLT            			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			1437 								(CAN) SCHEDULED WING BOLT INSPECTION, NOTED RT UPPER AFT WING BOLT CRACKED ON BOLT  HEAD TO SHANK RADIUS. BOLT REPLACED 	WITH NEW. (TC NR 20070108010)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007012900219	20070129	00219	NM  	2007	1	29	CA070109002      	1	20070108	G	3040		INSULATION      	SIERRACIN   	80260007    	DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	WINDSHIELD HEAT	OUT OF POSITION 	W				H				DEACTIVATE SYST/CIRCUITS				W	B		INADEQUATE Q C            	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			30   			729					(CAN) INVESTIGATING SMELL OF SMOKE IN COCKPIT AFTER CREW TURNED ON WINDSHIELD HEAT.  FOUND THE LUG ON 3041-TB1 POSITION 	L2 HAD INSULATION BETWEEN THE SCREW HEAD AND THE LUG.  REMOVED THE INSULATION FROM UNDER THE HEAD OF THE SCREW. (TC NR 2	0070109002)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007012900222	20070129	00222	SO  	2007	1	29	CA070109006      	2	20070109	G	8530	AEC648005PL	PISTON RING     			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1344 	1344 							(CAN) MATERIAL FROM THE FACE OF THE TOP COMPRESSION RING HAD FLAKED AWAY ON PISTONS NR1, NR2, NR4, AND NR6 (TC NR 200701	09006).					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007012900224	20070129	00224	EA  	2007	1	29	CA070110001      	2	20070110	G	7200		ENGINE          								PWA   	PT6   	PT6A34      	52043	EA  						FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			31612	7695 							(CAN) (IFSD WITH MAJOR INTERNAL DAMAGE). THE ENGINE SUFFERED SEVERE DISTRESS WITH COMPLETE LOSS OF ALL TURBINE BLADES AN	D ASSOCIATED STATIC COMPONENTS. THE GG CASE AND EXHAUST DUCT WERE SUBJECTED TO SEVERE TORQUE LOADS AND WERE FOUND DISTOR	TED.  ENGINE WAS CONVERTED STC SE96-02.  DURING FLIGHT AND FOLLOWING A LOUD BANG FROM THE ENGINE, AN ENGINE SHUTDOWN WAS	 CARRIED OUT.  CSN: 48301, CSO 10087 TSHSI: 64, CSHSI 25.  THIS ENGINE CONVERTED VIA STC SE96-02 (TC NR 20070110001).								4	T			E4EA				 
2007031200048	20070312	00048	NM  	2007	3	12	CA070110004      	1	20070109	G	3240		BRAKE DISC      	BFGOODRICH  		DHAV  	DHC5  	DHC5A       	2803018	NM  										NR 1 BRAKES	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2492 		411					(CAN) DURING B4 CHECK ON THE AIRCRAFT, THE NR 1 TIRE WAS REMOVED TO SERVICE THE WHEEL BEARINGS, AT THIS TIME, A PIECE OF	 THE BRAKE DISC FELL FROM THE BRAKE UNIT. THE BRAKE UNIT WAS REMOVED AND A SERVICEABLE ONE WAS INSTALLED. UPON INVESTIGA	TION OF THE UNIT IT HAS BEEN DETERMINED THAT A BRAKE ADJUSTER HAD SEIZED RESULTING IN THE BRAKE DISC SITTING AT AN ANGLE	 INSTEAD OF AT 90 DEGREES TO THE AXLE LINE, THIS RESULTING FORCE CAUSED STRESS TO BE PLACED ON THE DISC RESULTING IN ITS	 FRACTURE, THIS ALSO CAUSED THE BRAKE PUCKS TO SCORE AND DAMAGE DISC FACE. IAW THE INSPECTION SCHEDULE, THE MAIN WHEELS 	ARE REMOVED EVERY 200 HOURS (B CHECK) TO INSPECT THE BRAKES AND WHEEL BEARINGS. THERE WAS NO FAULTS NOTED ON THE LAST B3	2	H	7	2 	4T			RT	        					 
2007012900229	20070129	00229	EA  	2007	1	29	CA070111003      	1	20070109	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING	JAMMED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) FLAPS FAILED ON APPROACH WHEN SELECTED TO 8 DEGREES, FLAPS DID NOT MOVE AND FLAP FAIL EICAS MESSAGE, OAT WAS -30 D	EGREES ON APPROACH, DURING CRUISE -58 DEGREES C, FAULTS CODES BEING RETRIEVED AND AIRCRAFT BEING PREPARED FOR FERRY FOR 	FOLLOW UP. (801573 1/9/2007 19:04) RESET FLAP SYSTEM AND SELECT FLAPS TO 8 DEGREES FOR FERRY FLIGHT, REFERENCE RJ-SL-27-	077 (801573 1/9/2007 20:14).  FLAPS RESET. AIRCRAFT FERRIED (803789 1/10/2007 07:29) (TC NR 20070111003).			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900230	20070129	00230	EA  	2007	1	29	CA070111004      	1	20070110	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					WING	JAMMED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) CREW REPORTED ON SHORT FINAL, WHEN SELECTING FLAPS TO 8 DEGREE THE FLAP FAIL MESSAGE APPEARED AND THE FLAPS DID NO	T MOVE OUT OF 0 DEGREE. MAINTENANCE UNABLE TO GET CODES.  A/C FERRIED FOR FURTHER INVESTIGATION AND TROUBLESHOOTING. (TC	 NR 20070111004)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900231	20070129	00231	EA  	2007	1	29	CA070111005      	1	20070110	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					WING	JAMMED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) FLAPS SELECTED TO 8 DEGREES, NO ISSUES, THEN SELECTED TO 20 DEGREES, NO ISSUES, FLAPS 30 SELECTED NO ISSUES, UPON 	SELECTION TO 45 DEGREES, FLAP FAIL AND THE FLAPS LOCKED AT 30 DEGREES, OAT -30 IN FLIGHT, - 15 DEGREES OPN APPROACH, TEM	P WAS -15. HAS OBTAINED FAULT CODES AND THEY HAVE BEEN FORWARDED TO TECH OPS (803789 1/10/2007 17:14). A/C GROUNDED FOR 	FURTHER INVESTIGATION AND TROUBLESHOOTING. (TC NR 20070111005)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900232	20070129	00232	EA  	2007	1	29	CA070111006      	1	20070110	G	2750		FLAP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) FLAP FAIL AT 20. ON APPROACH, ON FLAP EXTENSION, THEY FROZE AT 20 DEGREES.   OAT WAS ABOUT -25 DEGREES C AT THE TI	ME, ALTHOUGH THEY WERE ABOUT 1 HOUR AND 10 MINUTES IN FLIGHT AT ABOUT -50 DEGREES FOR MOST OF THE FLIGHT. AIRSPEED WAS 1	70 KNOTS AT THE TIME OF THE FAILURE.   (TC NR 20070111006)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900233	20070129	00233	GL  	2007	1	29	CA070111010      	3	20070108	G	6110	HCB4MP3A	PROPELLER       													HARTZL	HCB4M	HCB4MP3     	GL  		DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			16787	32   							(CAN) PROPELLER WAS RECEIVED FOR COMPLIANCE WITH AD 2006-24-07. PROPELLER PREVIOUSLY OVERHAULED ON SEPTEMBER 20, 2000. T	HE PROPELLER WAS DISSASSEMBLED AND THE FOLLOWING FINDINGS  WERE CORRECTED. (4) LOW STOP RODS WERE CORRODED BEYOND REPAIR	. (4) BLADE CLAMP ASSEMBLIES WERE REPLACED DUE TO CORROSION AND LACK OF PLATING. PISTON HAD A CORROSION PIT IN FELT RING	 GROOVE. HUB WAS REPLACED DUE TO CORROSION/RUST IN PILOT TUBES. NR 4 BLADE HAD WATER IN BLADE BORE BEHIND GREASE BUT NO 	EVIDENCE OF CORROSION. COUNTERWEIGHT BOLTS WERE ALL RUSTED AND WATER WAS FOUND IN BLADE CLAMP COUNTERWEIGHT BOLT HOLES. 	(TC NR 20070111010)											6	C	P56GL	 
2007012900234	20070129	00234	EA  	2007	1	29	CA070111011      	1	20070110	G	2750		FLAP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING	OBSTRUCTED      	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) FLAPS FAILED ON RETRACTION AFTER LANDING L 5 DEG, R 6 DEG. AFTER LANDING, FOUND SNOW COMPACTED, ALL SNOW REMOVED, 	FLAPS CYCLED.  (TC NR 20070111011)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900235	20070129	00235	EU  	2007	1	29	CA070111012      	1	20070111	G	5610		WINDOW          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				M			OVER TEMP                 			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE FIRST OFFICERS MAIN WINDOW CRACKED. THE AIRCRAFT RETURNED TO POINT OF DEPARATURE WITHOUT FURTHER 	PROBLEM. MAINTENANCE REPLACED THE WINDOW AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (TC NR 20070111012)					2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007012900236	20070129	00236	EA  	2007	1	29	CA070111013      	2	20070108	G	7310		FUEL LINE       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) THE FLIGHT CREW REPORTED FUEL LEAKAGE FROM THE RT ENGINE AREA AFTER SHUTDOWN. THE ENGINE COWLING WAS REMOVED AND I	NVESTIGATION HAD SHOWN THAT THE ENGINE DRIVEN FUEL PUMP TO FCU LINE HAD CHAFED AN THE BACK EDGE OF THE FCU.  THE LINE IS	 ON CONDITION AND NOT A TIMED UNIT.  A FLEET CAMPAIGN AND TECHNICAL INFORMATION BULLETIN WAS RELEASED TO ENSURE CORRECT 	ROUTING OF THE LINE AND ADEQUATE PROTECTION. ANY SUSPECT LINES REPLACED. (TC NR 20070111013)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2007012900238	20070129	00238	NE  	2007	1	29	CA070111015      	2	20070111	G	7310	3035987	FUEL LINE       			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK AT ENGINE FIREWALL PRESSURE LINE. THE LINE WAS DAMAGED BY CHAFFING ON COLLAR (P/N 3043536-01A) AND RETAI	NING PLATE (P/N 3043535-01). POST SB21460.  2 OTHER LINES COVERED BY THE SAME SB (INCORPORATED IN DEC.2001) SHOWED SAME 	DAMAGE AND NEEDS REPLACEMENT. (TC NR 20070111015)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007012900239	20070129	00239		2007	1	29	CA070111017      	4	20070104	G	2360		STRUCTURE       			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	FUSELAGE	UNBONDED        	W				O				OTHER                   				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) CREW REPORTED THAT WHEN THE AIRCRAFT ENTERED INTO A CLOUD, THE RADIOS BECAME UNREADABLE. ALL RADIO NAVIGATION EQUI	PMENT BECAME UNRELIABLE AS WELL AS THE GPS SYSTEM. AIRCRAFT ARRIVED AT MTC. BASE AND AVIONICS STATIC SPECIALIST CONTRACT	ED. P-STATIC TEST CARRIED OUT AND FOUND BONDING ISSUES ON MULTIPLE AIRFRAME COMPONENTS. REPAIRS CARRIED OUT AND P-STATIC	 TEST CARRIED OUT AGAIN. NO FURTHER FAULTS. (TC NR 20070111017)			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2007050900064	20070509	00064	CE  	2007	5	9	CA070111018      	1	20070109	G	3233	5082021811	SHAFT           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)  THE NOSE GEAR ACTUATOR WAS REMOVED TO PERFORM AN END PLAY CHECK. THE NOSE GEAR RETRACT DRIVE SPROCKET AND SHAFT (	PN 50-820218-11) ASSEMBLY WAS REMOVED FOR CLEANING. INSPECTION OF THE DRIVE SPROCKET AND SHAFT FOUND THAT A CRACK HAD FO	RMED ON THE END DIAMETER (.745) THAT ENGAGES THE SUPPORT BEARING. THE CRACK STARTS AT THE END OF THE SHAFT, EXTENDS AXIA	LLY FOR .350 AND THEN EXTENDS RADIALLY FOR ANOTHER .400. THE CRACK HAS THE APPEARANCE OF STRESS CORROSION. THE TOTAL TIM	E AND TOTAL CYCLES OF THIS PART IS UNKNOWN. (TC NR 20070111018)		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007050900066	20070509	00066	EU  	2007	5	9	CA070112002      	1	20070106	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 AND NEW BOLT P/N 932.35.71.	166 AND BEARING REPLACED. MFG AIRCRAFT NOTIFIED OF DEFECT.  (TC NR 20070112002)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007082000032	20070820	00032	SW  	2007	8	20	CA070112003      	1	20070111	G	5610	2719442003	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3016 								(CAN) UPON LANDING THE FLIGHT CREW WITNESSED THE LT HEATED WINDSHIELD CRACK FROM THE LOWER RT CORNER TO THE UPPER CENTER	 PORTION OF THE WINDOW. THE LANDING WAS REPORTED AS NORMAL AND NO ABNORMAL INDICATIONS WERE NOTICED PRIOR TO FAILURE OF 	THE WINDOW.  UPON INSPECTION BY MAINTENANCE, THE WINDOW WAS FOUND CORRECTLY INSTALLED AND TRIMMED TO FIT CORRECTLY. THE 	ATTACHING SCREWS WERE TORQUE CHECKED AND A FEW WERE FOUND SLIGHTLY UNDERTORQUED. IT IS UNLIKELY THIS CAUSED THE FAILURE 	AS THIS OPERATOR HAS HAD SEVERAL IN FLIGHT HEATED WINDSHIELD FAILURES WITHIN THE LAST 24 MONTHS. ANOTHER OPERATOR OPERAT	ING SIMILAR AIRCRAFT IN THE PNR HAS REPORTED INCREASED FAILURES AS WELL OF THESE HEATED WINDSHIELDS. THE WINDSHIELD IS B	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2007012900242	20070129	00242	NE  	2007	1	29	CA070112004      	3	20070110	G	6112		RELAY           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER DE-ICE	FAULTY          	W				O				OTHER                   				M			OVER TEMP                 			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN AIRCRAFT POWER APPLIED, BLADES NR 2 AND NR 4 ON LT PROP HEATED AND BURNED OUT THE HEATER ELEMENTS.  FOR PRECA	UTION RELAYS P/N KC-D4N AND E-387-C1 WERE REPLACED AND AIRCRAFT WAS TESTED WITH NO FAULTS FOUND. AIRFRAME HOURS=44789:11	. CYCLES=48426. (TC NR 20070112004)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000033	20070820	00033	EU  	2007	8	20	CA070113001      	1	20070102	G	5344	5531412027	HINGE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7953 	7953 							(CAN) AFTER A HEADS UP CONDITION FROM ANOTHER RCMP AIR SECTION.  AN INSPECTION OF CONDITION WAS CARRIED OUT ON MPI. THE 	PART INSPECTED WAS FOUND SEVERELY CORRODED AND IF LT UNCHECKED COULD AFFECT THE INTEGRITY OF THE CABIN DOOR FRAME.  THE 	HINGE PLATE MOUNTED AT THE BASE OF THE AIRSTAIR DOOR OPENING AND IS RIVETED TO THE DOOR SILL ASSY.  APPROXIMATELY 50 PER	CENT OF THE HINGE WAS AFFECTED BY CORROSION.  THE CAUSE IS THOUGHT TO BE FROM SALT ON PASSENGER BOOTS IN WINTER OPERATIO	NS.  THE HINGE IS DIFFICULT TO INSPECT UNTIL DERIVATE FROM THE DOOR SILL ASSY.THE MFG HAD SEALED BETWEEN THE HINGE ASSY 	AND THE DOOR SILL WITH PRC AND THIS PREVENTED DOOR SILL DAMAGE. (TC NR 20070113001)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007012900245	20070129	00245	SO  	2007	1	29	CA070114001      	2	20070109	G	8530		EXHAUST VALVE   			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	LEAKING         	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA				327  							(CAN) DURING ENGINE PERFORMANCE GROUND RUN AFTER INSPECTION, ENGINE WAS RUNNING ROUGH. ENGINE COMPRESSION CHECK CARRIED 	OUT AND CYLINDER NR 3 FAILED COMPRESSION CHECK AND AIR WAS LEAKING FROM THE EXHAUST.  ROUGH RUNNING DURING TAKEOFF WAS A	LSO REPORTED BY PILOT PREVIOUSLY WHICH COULD NOT BE CONFIRMED DURING GROUND-RUN AT THAT TIME AND AIRCRAFT WAS TEST FLOWN	 SATISFACTORY. (TC NR 20070114001)			1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007012900246	20070129	00246	EU  	2007	1	29	CA070114002      	2	20070112	G	7230	GEJ818P060A	BOLT            	CFMINT      	CFM563      						CFMINT	CFM56 	CFM563B2    	13802	EU  					FAN DISK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						722356					(CAN) ENGINE WAS INDUCTED INTO SHOP FOR SCHEDULED MAINTENANCE. DURING THE SHOP VISIT THE FAN DISK WAS REMOVED FROM THE F	AN ASSEMBLY AND ROUTED FOR OVERHAUL. THE DISK ATTACH BOLTS (QTY 30) WERE ROUTED FOR NDT INSPECTION.  FPI DETECTED ONE FA	N DISK ATTACH BOLT WAS CRACKED FROM THE HEAD AND EXTENDING AXIALLY INTO THE SHANK.  FURTHER INSPECTION WITH A 10X MAGNIF	YING GLASS REVEALED THAT THE CRACK HAD PROPAGATED FROM A FAINT AXIAL LINE ON THE SIDE OF THE HEAD THAT INITIALLY APPEARS	 TO BE A MFG DEFECT.  A SECOND BOLT (NOT CRACKED) WAS FOUND WITH THE IDENTICAL AXIAL LINE (SAME DIMENSION AND ANGLE) IN 	THE BOLT HEAD. REMAINING 28 BOLTS HAD NO DEFECTS NOTED.  ALL BOLTS INITIALLY APPEARED IN GOOD CONDITION WITH NO EVIDENCE						4	F			E21EU				 
2007050900067	20070509	00067		2007	5	9	CA070114003      	4	20070104	G	3442	066311400	INDICATOR       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WEATHER RADAR	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA							BB1343				(CAN) CREW REPORTS THAT IN CRUISE NOTED THE WEATHER RADAR FAILED AND IMMEDIATELY BOTH MAIN GENERATOR BUSES FAILED. CREWS	 RESET GENERATORS AND MONITORED BUS VOLTAGES AND LOADS, NORMAL. CREW THEN NOTED THE 28VDC CIRCUIT BREAKER POPPED ON THE 	AVIONICS BUS FOR THE WEATHER RADAR. BREAKER RESET BUT INDICATOR UNSERVICEABLE. AFTER AIRCRAFT RETURNED TO MTC BASE, MAIN	TENANCE CREW INSPECTED ELECTRICAL SYSTEM WITH NO FAULTS FOUND. RADAR INDICTOR REPLACED AND F/C NORMAL. UNSERVICEABLE WEA	THER RADAR SENT TO REPAIR FACILITY WITH DETAILS OF INCIDENT AND REQUEST FOR WORK / STRIP REPORT. (TC 20070114003)		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007082000034	20070820	00034	EU  	2007	8	20	CA070115001      	1	20070109	G	2500		INSULATION      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUSELAGE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7963 	7962 							(CAN) DURING AN INTERIOR REFURBISHMENT IT WAS NOTED THE FUSELAGE INSULATION FROM THE CABIN FLOOR AND UP HAD BADLY DEGRAD	ED INSULATION BAGS.  THE THERMAL ACOUSTIC FOAM IS SURROUNDED BY BAGS WITH A VAPOR FOIL ON THE INNER SURFACE AND SEALED T	O A THIN LATEX TYPE BARRIER ON THE OB SURFACE.  THE OUTER SURFACE HAD RUPTURED AND DEGRADED ON  ALL OUTER SURFACES OF TH	E INSULATION BAGS. ALL CABIN INSULATION HAD TO BE REMOVED AND REPAIRED WITH THE APPROVED TAPE.   IF LEFT UNCHECKED THIS 	COULD ADD  A CORROSION PROBLEM WITHIN THE FUSELAGE AS MOISTURE HAD WICKED INTO THE INSULATION IN SOME AREAS.  IF THE A/C	 WAS NOT HANGARED EACH NIGHT FOR DRYING IT COULD POSE A WEIGHT PROBLEM THAT WOULD BE UNKNOWN TO FLIGHT AND MAINTENANCE C	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007050900069	20070509	00069	SO  	2007	5	9	CA070115002      	1	20070109	G	2140	D405065D793	HEATER          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CABIN	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				649  							(CAN) PILOT REPORTED EXHAUST ODOR WHEN FRONT COMBUSTION HEATER WAS OPERATING. SOOT COLLECTED ON THE PILOT AND CO-PILOT W	INDSHIELDS ABOVE THE DEFROST VENTS.  COMPLETED A HEATER DECAY TEST WHICH CONFIRMED THE BURNER CAN WAS DEFECTIVE. REMOVED	 THE HEATER FROM THE AIRCRAFT AND DISCOVERED 2 HOLES IN THE BURNER CAN APPROXIMATELY .5 INCH WIDE AND OPEN ABOUT .2500 I	NCH. HEATER WAS REPLACED WITH OVERHAULED UNIT AND AIRCRAFT RETURNED TO SERVICES. (TC NR 20070115002)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007012900255	20070129	00255	EA  	2007	1	29	CA070115003      	1	20070113	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					WING	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLAPS FAILED UPON SELECTION TO 8 DEGREES, THEY DID NOT MOVE FROM 0 DEGREES, OAT -46 AT ALTITUDE, - 15 DEGREES ON A	PPROACH. AIRCRAFT LANDED FLAPS ZERO. (TC NR 20070115003)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050900070	20070509	00070	NE  	2007	5	9	CA070115004      	2	20070115	G	7200		ENGINE          			AIRBUS	320   	A320214     	3930316	EU  	CFMINT	CFM56 	CFM565B4P   	 	NE  					NR 1	FAILED          	W				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA								757267			(CAN) AFTER POWER SET FOR TAKEOFF, AND TAKEOFF ROLL COMMENCED, ENG NR 1 FAILED.  AIRCRAFT TAXIED BACK TO THE GATE. (TC N	R 20070115004)					2	L	7	2 	4F	4	F	RT	A28NM   	E38NE				 
2007012900257	20070129	00257		2007	1	29	CA070115005      	4	20070115	G	2562	E01G1	ELT             																	CABIN	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) OVER THE LAST YEAR, HAVE HAD SEVERAL ACK ELTS E-01 WITH FAULTY (G) SWITCHES. FAULTS INCLUDE:  INTERMITTENT ACTIVAT	ION, LIGHT ACTIVATION, NO ACTIVATION ACK HAS NO PUBLISHED DATA ON ACTIVATION BUT USES SIMILAR (G) SWITCH TO THE ELT WHIC	H HAS A PUBLISHED ACTIVATION OF 2 (GS).  HAVE ALSO SEEN SIMILAR FAULTS WITH ELTS.  (TC NR 20070115005)																	 
2007012900261	20070129	00261	EA  	2007	1	29	CA070115007      	2	20070112	G	8530		CYLINDER        	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	SEPARATED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				2175 		L787161A					(CAN) ON THE CLIMB OUT A LOSS OF POWER OCCURED ON THE RT ENGINE.  THE MANIFOLD PRESSURE DROPPED FROM TAKEOFF POWER TO 30	 INCHES. (TC NR 20070115007)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007050900076	20070509	00076	SW  	2007	5	9	CA070115014      	1	20070102	G	5730	204382	SKIN            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			452  								(CAN) DURING ANNUAL INSPECTION SEVERAL CRACKS WERE DETECTED AT THE RIVET HOLES WHERE THE FLAP BAY SKIN (PN 20438-2) ATTA	CH TO THE RIB FLANGES.  CRACKS WERE STOP DRILLED AND PLATE INSTALLED OVER THE RIB FLANGE AREA IAW AIR TRACTOR INSTRUCTIO	NS (ATTACHED).  THIS PROBLEM HAS BEEN FOUND ON EARLY SN AIRCRAFT (802-001 - 802A-0014), SUBSEQUENT S/N HAD EXTRA RIVETS 	INSTALLED BY MFG.  THIS AIRCRAFT S/N IS 802-0121.  (TC NR 20070115014)			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2007082000037	20070820	00037	CE  	2007	8	20	CA070115015      	1	20070112	G	5340	50110131	MOUNT           			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	MLG GEARBOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED LANDING GEAR ROUTINE INSPECTION, LANDING GEAR ACTUATOR GEARBOX MOUNTING BOLTS (3) FOUND MISSING A	ND REMAINING (1) BOLT FOUND SHEARED.  EMERGENCY GEAR OPERATION ATTEMPTED TO RELOCATE GEAR. EMERGENCY OPERATION INHIBITED	 DUE TO IMPROPER GEARBOX ALIGNMENT.  GEAR REPOSITIONED AND GEARBOX AND LANDING GEAR SYSTEM INSPECTED FOR CONDITION.  NEW	 MOUNTING BOLTS INSTALLED AND GEAR SYSTEM NORMAL AND EMERGENCY TESTED SERVICEABLE. (TC NR 20070115015)			1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2007012900304	20070129	00304	EA  	2007	1	29	CA070115016      	1	20070112	G	2731	C6CF14053	CONTROL CABLE   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TRIM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRIM CABLE WAS FOUND BROKEN AND WAS REPLACED. THE BROKEN CABLE IS BEING ANALYZED AT THEIR LOCAL AIRWORTHINESS AUTH	ORITY AND WE AWAIT THE RESULTS.  (TC NR 20070115016)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008030600281	20080306	00281	CE  	2008	3	6	CA070115017      	1	20070112	G	5312	97440019101	STIFFENER       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16398				BB84				(CAN)   SPECIAL INSP NR53 WAS COMPLETED IAW MM 5-20-05, WHICH INVOLVES THE FOLLOWING: AFT FUSELAGE AREA AND REAR PRESSUR	E BULKHEAD.  INSPECT THE ENTIRE FWD AND AFT SIDE OF THE REAR PRESSURE BULKHEAD FOR CRACKS AND LOOSE OR MISSING RIVETS. C	HECKED OXYGEN BOTTLE MOUNTING BRACKETS FOR CRACKS AND LOOSE OR MISSING RIVETS. CHECKED OUTFLOW AND SAFETY VALVE BOX FOR 	CRACKS AND LOOSE OR MISSING RIVETS. THE INSP INTERVAL IS INITIALLY 10,000 CYCLES AND AT 500 CYCLES THERE AFTER.  DURING 	THIS INSP OF THE REAR PRESSURE BULKHEAD (F.S. 347.75) THE AFT ZEE STIFFENER (P/N:97-440019-101) WAS FOUND CRACKED. THE C	RACK WAS LOCATED AT THE LOWER ATTACH POINT OF THE OXYGEN BOTTLE SUPPORT (P/N: 50-560019-13) WHICH ATTACHES TO THE ZEE ST	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007050900077	20070509	00077	SW  	2007	5	9	CA070117003      	1	20070115	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	DELAMINATED     	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			2751 								(CAN) DURING FLIGHT THE FLIGHT CREW HEARD A LOUD CRACK FROM THE RT HEATED WINDSHIELD. THEY IMMEDIATELY NOTICED THE WINDO	W PANES BEGIN TO DELAMINATE. NO OBJECT WAS WITNESSED HITTING THE AIRCRAFT OR WINDSHIELD. THE AIRCRAFT LANDED SAFELY AND 	THEN RETURNED TO BASE ON A FLIGHT PERMIT FOR REPAIRS. NO CRACKING IN THE WINDOW WAS EVIDENT. THE WINDOW WAS REPLACED BY 	MAINTENANCE. (TC NR 20070117003)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2007012900307	20070129	00307	EA  	2007	1	29	CA070117005      	2	20070117	G	7320	C6CF14043	CABLE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  						DAMAGED         	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NEW CABLE, THE BALL END OF THE TRIM CABLE IS OUT OF ROUND AND WILL NOT FIT INTO THE TRIM JACK ASSEMBLY. WHERE THE 	CABLE MEETS THE BALL END IT HAS BEEN BRAZED AND THE CABLE HAS NOW FRAYED AFTER ATTEMPTING TO INSTALL IT INTO HTE TRIM JA	CK ASSEMBLY. (TC NR 20070117005)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2007050900078	20070509	00078	WP  	2007	5	9	CA070117006      	1	20070117	G	6310	C1883	SPRAG CLUTCH    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			933  								(CAN) DURING AN AES 1000HR INSPECTION, A CRACK WAS FOUND ON THE CAGE IN THE MIDDLE OF (1) CROSSBAR. (TC NR 20070117006)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007050900186	20070509	00186	EA  	2007	5	9	CA070117007      	1	20070115	G	5610	601R3303311	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			9980 								(CAN) PILOT SIDE WINDOW INNER LAYER CRACKED.  SIDE WINDOW ACC AMM 56-12-01 REPLACED. OPERATIONAL TEST OF WINDOW TEMP CON	TR.  DO A LEAK TEST OF LT SIDE WINDOW AFTER REPLACEMENT ACC AMM 56-12-400-801 A01 PERFORMED SATISFIED (TC NR 20070117007	)				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007050900187	20070509	00187	EA  	2007	5	9	CA070117008      	1	20070115	G	3213	7339FT160T	SEAL            	BFGOODRICH  		CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					NLG STRUT	LEAKING         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA						SPP510096					(CAN) FLIGHT 5663 DEPARTED WITH 65 PASSENGERS ON BOARD WITH NO ISSUES NOTED.  ON APPROACH, AFTER GEAR DOWN SELECTION CRE	W NOTED A NWS INOP CAUTION MESSAGE.  TO GIVE THEMSELVES TIME TO GO THROUGH THE NWS INOP MESSAGE, THEY CARRIED OUT A GO A	ROUND.  AS THEY FLEW BY THE RUNWAY, THE TOWER INFORMED THEM THAT THE NOSEWHEELS APPEARED TO BE TURNED 90 DEGREES.  AN AC	 FLYING NEARBY OFFERED TO FLY BY THE AIRCRAFT AND INSPECT THE NOSE GEAR.  THE PILOT REPORTED THAT THE NOSE GEAR WHEELS W	ERE OFF CENTER BY 20 DEGREES.  AT THE GATE MAINTENANCE INSPECTED THE NOSE GEAR AND FOUND THAT THE STRUT WAS FLAT.  MAINT	ENANCE SERVICED THE STRUT AND NOTED THAT THE STRUT WAS LEAKING.  STL MAINTENANCE IS DISPATCHING MAINTENANCE AND SEALS TO	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007050900188	20070509	00188	CE  	2007	5	9	CA070118001      	1	20070115	G	5542	04330106	SKIN            	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING 100 HR INSPECTION ON AIRCRAFT, MECHANIC NOTICED THAT THERE WAS A CRACK BY THE LIGHTING HOLE BELOW THE 	TOP HINGE ATTACH BRACKET. NEW SKIN ORDERED AND WHEN RECEIVED NOTICED THAT MFG HAS REMOVED THIS LIGHTING HOLE.  REST OF A	IRCRAFT OF THIS TYPE IN FLEET WILL BE INSPECTED FOR THIS SAME DAMAGE. (TC NR 20070118001)				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007050900189	20070509	00189	EA  	2007	5	9	CA070118002      	1	20070117	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED A FLAP FAIL MESSAGE ON APPROACH. THE CREW SELECTED FLAP 8 AND FLAP FAIL MESSAGE CAME ON IMMEDIAT	ELY AND THE FLAPS FROZE AT 0 DEGREES INDICATED. ON THE GROUND A CB RESET WAS CARRIED OUT AND THE CODES WERE OBTAINED . T	HE AIRCRAFT WAS FERRIED WHERE AN INVESTIGATION IS STILL ONGOING BY LINE MAINTENANCE (TC NR 20070118002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900308	20070129	00308	SO  	2007	1	29	CA070118003      	2	20070110	G	7314	6467582	PUMP            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				1056 							(CAN) ENGINE DRIVEN FUEL PUMP OUTPUT IS LOW AT RATED RPM 2600. (TC NR 20070118003)						1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920	 
2007012900309	20070129	00309	GL  	2007	1	29	CA070118004      	3	20070112	G	6110	B2222	PLATE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3850 	2009 							(CAN) PROPELLER RECEIVED FROM CUSTOMER FOR ROUTINE OVERHAUL. PROPELLER DISMANTLED, PARTS NDT INSPECTED AND CRACK FOUND. 	NO AD`S OR BULLETIN`S ON THAT PART.  (TC NR 20070118004)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
2007012900310	20070129	00310	EA  	2007	1	29	CA070118005      	2	20070103	G	7320	3027791	SENSE LINE      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			5597 					PCE85142			(CAN) P3 TUBE SUDDENLY BROKEN WHILE AIRCRAFT WAS IN CLIMB. ENGINE FAIL TO IDLE, ENGINE WAS SHUTDOWN BY THE CREW.  AIRCRA	FT RETURN TO DEPARTURE AIRPORT WITHOUT OTHER DIFFICULTY. (TC NR 20070118005)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007050900190	20070509	00190	WP  	2007	5	9	CA070118006      	1	20070117	G	6210	369D21100516A	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2813 								(CAN) THE UPPER BLADE SURFACE IS CRACKED CHORDWISE FROM LEADING EDGE TO TRAILING EDGE BETWEEN BLADE STATION 120 AND 124.	 THE LOWER BLADE SURFACE IS ALSO CRACKED IN THE MID CORD AREA BETWEEN STATION 120 AND 124 BUT DOES NOT EXTENT TO THE LEA	DING EDGE OR TRAILING EDGE. (TC NR 20070118006)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007051100005	20070511	00005	EA  	2007	5	11	CA070118008      	1	20070117	G	2752	852D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	CONTAMINATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			6959 	6959 							(CAN) ON APPROACH CREW REPORTED A FLAPS FAIL MESSAGE AFTER SELECTION TO 8 DEGREES. FLIGHT COMPLETED A FLAPLESS LANDING W	ITHOUT INCIDENT. AIRCRAFT THEN COMPLETED A FERRY FLIGHT. TROUBLESHOOTING OF FAULT CODES AND REPAIRS CURRENTLY ONGOING BY	 MAINTENANCE. THE RT IB FLAP ACTUATOR WAS REPLACED DUE TO NOT ACCEPTING GREASE. SUSPECT MOISTURE INGRESS HAD FROZEN INSI	DE ACTUATOR. AS PART OF REPAIRS MOD IS601R227530052 REV B: FLAP DRIVE SYSTEM-ALTERNATE METALLIC SEAL FOR FLEXIBLE DRIVE 	SHAFT WAS INCORPORATED. (TC NR 20070118008)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100006	20070511	00006	EA  	2007	5	11	CA070118009      	1	20070116	G	2910	AE7090072	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 2 EDP	LOOSE           	W				O				OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA						MX598642					(CAN) ENROUTE CREW ADVISED THAT THEY HAD LOST NR 2 HYDRAULIC  SYSTEM AND WERE  DIVERTING.  CREW DECLARED AN EMERGENCY AN	D ADVISED PASSENGERS OF REASON. WHEN THE INCIDENT HAPPENED THE CREW HAD A HYD 2 LOW PRESSURE MESSAGE, WHEN THEY TURNED O	N NR 2 PUMP (HYD PUMP 2A) MESSAGE WAS CONTINUOUSLY ON. A FEW MINUTES LATER ALL NR 2 HYD QUANTITY WAS LOST.  MAINTENANCE 	INSPECTION REVEALED THAT THE QUICK DISCONNECT FITTING ON THE CASE DRAIN LINE TO THE NR 2 PUMP WAS LEAKING AROUND THE BAS	E OF THE COUPLER.  ONCE ALL THE FLUID LEAKED OUT IT STARVED THE PUMP CAUSING IT TO MAKE METAL CAUSING ENGINE VIBRATION A	ND EVENTUALLY SEIZE.  THE CASE DRAIN LINE, NR2 EDP, PRESS AND CASE DRAIN FILTERS WERE REPLACED AND AIRCRAFT WAS FUNCTION	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100007	20070511	00007	EU  	2007	5	11	CA070118010      	1	20070118	G	5302	350A13111620	BOLT            			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					TAILBOOM	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THIS IS (1) OF (2) BOLTS USED TO RETAIN THE HORIZONTAL STAB. TO THE TAIL BOOM OF THE HELICOPTER.  THE THREADED SEC	TION OF THE BOLT AND THE NUT WERE FOUND MISSING.  IT APPEARS THAT THE THREADED SECTION OF THE BOLT HAD BEEN CRACKED FOR 	SOME TIME BEFORE DEPARTING. (TC NR 20070118010)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007051100008	20070511	00008	EU  	2007	5	11	CA070118011      	1	20070104	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1263 							(CAN) DURING HYDRAULIC PRE-FLIGHT CHECK CAUSED CYCLIC TO MOVE 4-5 INCHES TOWARDS 8 OCLOCK POSITION.  SERVO REMOVED SERV	ICEABLE UNIT INSTALLED.  SERVO SENT OUT FOR REPAIR AWAITING TEARDOWN REPORT. (TC NR 20070118011)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007051100009	20070511	00009	EA  	2007	5	11	CA070119001      	1	20070117	G	5610	NP1393229	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6269 								(CAN) SEVERAL CRACKS IN LT SIDEWINDOW INNER AND CENTER. A/C AOG LT SIDEWINDOW CHANGED ACC AMM. ALL TESTS SATISFIED (TC N	R 20070119001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007012900311	20070129	00311	EU  	2007	1	29	CA070119003      	1	20070109	G	2930	AIR45428	INDICATOR       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	HYDRAULIC SYS	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE, THE CREW OBSERVED BOTH HYD SYSTEMS INDICATING APPROXIMATELY 1200 PSI WITH LOW FLOW LIGHTS ON. THE CREW CO	NTINUED WHERE ON APPROACH THE HYDRAULIC PRESSURE RECOVERED AND THE FLOW LIGHTS EXTINGUISHED. THE AIRCRAFT LANDED WITHOUT	 FURTHER PROBLEM. MAINTENANCE FOUND THE HYDRAULIC FLOW INDICATION VALVE LEAKING WHICH WAS REPLACED PRIOR TO THE AIRCRAFT	 RETURNING TO SERVICE. (TC NR 20070119003)			2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007012900312	20070129	00312	EA  	2007	1	29	CA070119004      	1	20070118	G	5343		FASTENER        			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NLG TRUNNION	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NLG TRUNNION FITTING FASTENERS FOUND LOOSE. REFERENCE IPC 53-20-00; FIGURE 25; ITEM 190. BOTH SIDES (LT AND RT) AF	T ROW OF BOLTS.  RE-TORQUED NUTS IAW SB8-53-49. (TC NR 20070119004)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100011	20070511	00011	EU  	2007	5	11	CA070119005      	1	20070118	G	3097	2840A	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ANTI ICE	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			851  								(CAN) AIRCRAFT IS IN CRUISE FLIGHT WHEN PILOT SELECTED NR 1 AND NR 2 ANTI-ICE (ON) DUE TO THE OAT AND VISIBLE MOISTURE. 	 ON SHORT FINAL TO THE BASE THE PILOT SELECTED BOTH ANTI-ICE SWITCHES TO THE (OFF) POSITION. IMMEDIATELY UPON ACTIVATING	 NR 1 SWITCH TO (OFF) THE PILOT HEARD AN AUDIBLE (CLICK).  LOOKING DOWN HE NOTICED THAT THE NR1 ANTI-ICE 3AMP BREAKER HA	D POPPED.  ONE UNSUCCESSFUL ATTEMPT WAS MADE TO RESET THE BREAKER.  AFTER THE AIRCRAFT HAD SHUTDOWN THE MAINTENANCE STAF	F TROUBLESHOT THE SYSTEM AND FOUND THAT THERE WAS A (DEAD SHORT) IN THE ANTI ICE SWITCH P/N 2840A.  THE SWITCH WAS REPLA	CED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070119005)	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2007051100016	20070511	00016	CE  	2007	5	11	CA070119009      	1	20070116	G	5711	122210614	SPAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	RT WING	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) EDGE DISTANCE OF RIVETS ON LOWER FLANGE LESS THAN MINIMUM ALLOWED.  REPLACEMENT OF PART REQUIRED TO REPAIR PROBLEM	. (TC NR 20070119009)					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2007080800125	20070808	00125	CE  	2007	8	8	CA070119010      	1	20070116	G	5711	12220052	SPAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	RT WING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REPLACEMENT OF LOWER OB SKIN, EDGE DISTANCE OF RIVETS THROUGH LOWER FLANGE LESS THAN MINIMUM ALLOWED IN 32 	PLACES FROM STAT. 100.0 TO STAT. 154.00  REPLACEMENT OF PARTS REQUIRED TO REPAIR PROBLEM. (TC NR 20070119010)					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2007051100018	20070511	00018	NM  	2007	5	11	CA070119011      	1	20070116	G	5343	69634801	BOLT            			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TRUNION	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			63218								(CAN) DURING A ROUTINE (C) CHECK INSPECTION, IT WAS NOTICED THAT THE LT MAIN LANDING GEAR TRUNION BOLT P/N 69-63480-1 AP	PEARED TO BE SHEARED. UPON REMOVAL OF THE GEAR, IT WAS CONFIRME4D THAT THE BOLT WAS SHEARED AND ALSO THE BEARING P/N 10-	61849-10 WAS CRACKED. THE ABOVE PN ARE WITH REFERENCE TO MFG IPC 32-10-00-01 P.4 ITEM 317.  (TC NR 20070119011)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051100019	20070511	00019	SO  	2007	5	11	CA070119012      	1	20070113	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	LEAKING         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA				1362 				L430261A			(CAN) EXCESSIVE SMOKE FROM THE LT ENGINE WAS REPORTED BY PASSENGER AND GROUND CONTROL DURING APPROACH TO AIRPORT. FLIGHT	 CREW DECLARED AN EMERGENCY AND AIRCRAFT LANDED AND PASSENGERS IMMEDIATELY DISEMBARKED. AIRPORT EMERGENCY RESPONSE VEHIC	LES ATTENDED. NO VISIBLE FLAMES OR FIRE WAS EVIDENT PRIOR TO OR AFTER LANDING. AIRCRAFT WAS TOWED FROM THE RUNWAY TO MAI	NTENANCE FACILITY. MAINTENANCE INVESTIGATION REVEALED EXCESSIVE OIL IN THE TURBOCHARGER EXHAUST. TURBOCHARGER REPLACED W	ITH O`HAULED UNIT AND AIRCRAFT/ENGINE OPERATION CHECKED NORMAL. (TC NR 20070119012)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007051100021	20070511	00021	SO  	2007	5	11	CA070120001      	1	20070118	G	8120		BEARING         			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			13433	121  				L206368A			(CAN)  RT ENGINE OIL CONSUMPTION HAD INCREASED, OIL RESIDUE FOUND ON EXHAUST STACK. INSPECTION FOUND THAT THE EXHAUST SI	DE OF THE RT TURBOCHARGER WAS COVER IN OIL. FOUND THAT THE INNNER SUPPORT BEARING AND SEAL HAD FAILED ALLOWING OIL TO BE	 INTRODUCED TO THE HOT SIDE OF THE TURBO. REPLACED TURBOCHARGER, CHANGED ENGINE OIL,  INSPECTED RT ENGINE OIL FILTER FOR	 METAL, NO FAULT FOUND.   (TC NR 20070120001)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007051100023	20070511	00023	EA  	2007	5	11	CA070122001      	1	20070119	G	3213	C6UM117227	RETAINING NUT   			DHAV  	DHC6  	DHC6        	2802606	EA  										AXLE	MISMANUFACTURED 	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) NEW AXLE NUTS FOR THE SERIES AIRCRAFT NOT FULLY ASSEMBLED. THE HOLES FOR THE (2) PINS HAVE BEEN DRILLED BUT NO PIN	S HAVE BEEN INSTALLED, INCOMPLETE PARTS. MARKING ON NUT WO-04403/1, DEC 07 2006 C6UM1172-27. (TC NR 20070122001)					1	H	7	2 	3T			RT	A9EA    					 
2007051100025	20070511	00025	WP  	2007	5	11	CA070122002      	1	20070122	G	7800	D3171	HEAT SHIELD     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			152  								(CAN) DURING A ROUTINE 100 HR ENGINE/AIRFRAME INSPECTION, IT WAS NOTED THAT THE SUBJECT HEAT SHIELD, THAT IS INSTALLED O	N THE ENGINE EXHAUST TAILPIPE, WAS FOUND CRACKED. THE CRACK ORIGINATED IN THE DOUBLER AREA WHERE THE FORWARD CLAMP IS AT	TACHED. THE CRACK LOOKS LIKE IT HAS ORIGINATED FROM A RIVET THAT ATTACHES THE DOUBLER AND BRACKET, WHICH PROVIDES A MEAN	S TO ATTACH THE CLAMP TO THE EXHAUST TAILPIPE. THE PART IN QUESTION HAS 151.3 HOURS SINCE NEW ON IT. THE AIRCRAFT IN QUE	STION HAS 495.0 HOURS SINCE NEW. THE PART WILL BE SUBMITTED TO MFG FOR WARRANTY. THIS IS THE 3RD HEAT SHIELD TO BE REPLA	CED ON THIS AIRCRAFT SINCE IT WAS NEW. THE PRIOR HEAT SHIELDS WHERE REPLACED AT 343.5 AIRCRAFT HOURS, AND 203.2 AIRCRAFT	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007051100026	20070511	00026	WP  	2007	5	11	CA070122003      	1	20070122	G	5310	D3807	SHROUD          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			202  								(CAN) DURING A ROUTINE 100 HR ENGINE/AIRFRAME INSP, IT WAS NOTED THAT THE SUBJECT SHROUD WAS CRACKED JUST AFT OF THE UPP	ER/AFT MOUNTING SCREW LOCATION. THE SHROUD IS PART OF A SERIES OF SHROUD COVERS THAT SURROUND THE ENGINE FOR COOLING PUR	POSES. THE SHROUD HAS 201.8 HOURS SINCE NEW ON IT. THE AIRCRAFT HAS ACCUMULATED 495.0 HOURS SINCE NEW. THIS IS THE SECON	D TIME THAT THIS PARTICULAR SHROUD HAS BEEN REPLACED. THE ORIGINAL SHROUD THAT CAME NEW WITH THE AIRCRAFT WAS FOUND CRAC	KED IN THE SAME LOCATION, AND REPLACED AT 293.2 AIRCRAFT HOURS. THIS SEEMS TO BE A WEAK AREA THAT IS SUBJECTED TO ENGINE	 VIBRATION. HAVE TAKEN NOTE OF THIS WEAK AREA AND HAVE STEPPED UP OUR VISUAL INSPECTIONS TO SPOT CRACKS IN THEIR EARLY D	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007051100028	20070511	00028	WP  	2007	5	11	CA070122004      	1	20070122	G	5311	C2617C2618	RIB             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			495  								(CAN) DURING A ROUTINE 100 HOUR ENGINE/AIRFRAME INSPECTION, IT WAS NOTED THAT THE SUBJECT PARTS WHERE CRACKED. THE CRACK	S WHERE FOUND AT THE FORWARD ANCHOR NUT LOCTIONS. THE RIBS ARE PART OF THE STRUCTURE THAT ENCLOSES THAT MAST AREA. THE R	IBS WHERE REPLACED WITH NEW ASSEMBLIES. THE AIRCRAFT IN QUESTION HAS 495.0 HRS SINCE NEW. (TC NR 20070122004)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007051100029	20070511	00029	EA  	2007	5	11	CA070122005      	1	20070119	G	5551	600210713	BUSHING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5433 								(CAN) CREAKING NOISE HEARD WHEN HORIZONTAL STABLIZER WAS CYCLED THROUGH FULL RANGE. HORIZONTAL STAB HINGE BUSHINGS.THEY 	WERE FOUND DRY.  IPC REF:27-43-01-01, ITEM NR 60. PARTS HAND LUBED AND RE-ASSEMBLED IAW MM TASK NR 000-13-320-121.  CURR	ENT INTERVAL FOR THIS  TASK IS 10,000 FLT.HRS (TC NR 20070122005)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100042	20070511	00042	EA  	2007	5	11	CA070122006      	1	20070121	G	5551	600210713	BUSHING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORZONTAL STAB	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5406 								(CAN) CREAKING NOISE HEARD WHEN THE HORIZONTAL STABILIZER WAS CYCLED THROUGH FULL RANGE.  AFT FITTING ON THE HORIZONTAL 	STABILIZER DISASSEMBLED.  BUSHING WAS FOUND DRY ( NO LUBRICATION ).  PARTS CLEANED, INSPECTED, HAND LUBED AND RE-ASSEMBL	ED IAW MM TASK NR 000-12-320-121.  CURRENT INTERVAL FOR THIS TASK IN THE MANUAL IS 10,000 FLIGHT HOURS. (TC NR 200701220	06)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100043	20070511	00043	NM  	2007	5	11	CA070122007      	1	20070105	G	2910	82970009235	LINE            			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			27198								(CAN) DURING TAKEOFF, AFTER SELECTING LANDING GEAR UP, NR 2 ENGINE HYD PUMP FAILED AND AFTER SEVERAL MIN, A/C LOST ALL O	F THE NR 2 HYD QUANTITY. SYSTEM NR 2 PRESSURE LOW AND QUANTITY DEPLETED, ALTERNATE LANDING GEAR EXTENSION.  AFTER INVEST	IGATION HYD TUBE, P/N 82970009-235 AT RT HYD SYSTEM (L/G BAY), WAS FOUND RUPTURED (IN THE FLARED AREA). TUBE WAS REPLACE	D; BLEEDING AND LEAK CHECK C/OUT OF RT HYD SYSTEM AND NO LEAKS OBSERVED.  (TC NR 20070122007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100065	20070511	00065	CE  	2007	5	11	CA070122008      	1	20070120	G	3230	508103385	DRAG LINK       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER SCHEDULED MAINTENANCE THE AIRCRAFT WAS REMOVED FROM THE HANGER AND WAS TOWED TO THE FUEL PUMPS TO BE LEAK CH	ECKED. AFTER TOWING THE AIRCRAFT ABOUT 500 FEET THE RT MLG COLLAPSED CAUSING DAMAGE TO THE RT MAIN LANDING GEAR AND DOOR	S, WING TIP, CARGO POD AND ONE BLADE OF THE RT PROP. THE AIRCRAFT WAS THEN LIFTED AND JACKED TO ALLOW INSPECTION OF THE 	LANDING GEAR AREA AND ALLOWED FOR A TEMPORARY DOWNLOCK TO BE MADE AND THE AIRCRAFT WAS RETURNED TO THE HANGER. THE AIRCR	AFT IS STILL BEING INSPECTED FOR OTHER UNSEEN DAMAGE. THE PRELIMINARY FINDINGS SHOW THAT THE PRIMARY FAILURE WAS OF THE 	DRAG LINK LOCK. THIS IS ONLY A PRELIMINARY REPORT A MORE CONCLUSIVE REPORT WILL BE ADDED TO THIS SDR WHEN THE FINDINGS A	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007051100044	20070511	00044	SO  	2007	5	11	CA070122009      	2	20070117	G	8530	EC649358CN	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NR 4	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			755  								(CAN) NR 4 CYILINDER FAILED, BURNING VARIOUS ENGINE COMPARTMENT WIRING AND DUCTING. (TC NR 20070122009)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2007051100045	20070511	00045	CE  	2007	5	11	CA070122010      	1	20070106	G	2497	1003641621	CONTROL PANEL   			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT LIGHTS	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) CREW REPORTED COCKPIT OVERHEAD PANEL LIGHTS CIRCUIT BREAKER POPPED AND ABOUT THE SAME TIME REPORTED SMELLING SMOKE	. PCB PANEL REMOVED AND FOUND TO OF SHORTED OUT CAUSING SMALL BURN HOLE THROUGH PANEL SCORCHING METAL BEHIND PANEL. CAUS	E OF SHORT BELIVED TO BE MOISTURE FROM EXCESSIVE CONDENSATION. (TC NR 20070122010)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007051100046	20070511	00046	SW  	2007	5	11	CA070122011      	1	20070122	G	6710	2040011841	COLLECTIVE STICK			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					MAIN ROTOR	RATCHETING      	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) PILOT COMPLAINED OF RATCHETING FEEL TO COLLECTIVE CONTROL STICK.  AIRCRAFT RETURNED TO BASE.  INSPECTION REVEALED 	THAT THE COLLECTIVE FRICTION SURFACE ROLL PIN WAS WORKING INTERNALLY AND CAUSING THE RATCHETING FEEL.  ELBOW WAS REPLACE	D. (TC NR 20070122011)				1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2007051100047	20070511	00047	CE  	2007	5	11	CA070123001      	1	20070119	G	7603	9938000521	CONTROL CABLE   			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	LT ENGINE	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) THE LT ENGINE COULD NOT BE SHUTDOWN ON THE GROUND USING THE CONDITION LEVER, THE PILOT HAD TO USE THE FIREWALL SHU	T-OFF IN ORDER TO SHUT THE ENGINE DOWN. INVESTIGATION BY MAINTENANCE FOUND THAT THE LT IDLE CONTROL CABLE ASSY FAILED AT	 THE MALE TERMINAL END AT THE ENGINE. THE MALE THREADED END PORTION SLIPPED OFF THE CABLE SLIDE AT THE POINT WHERE IT IS	 SWAGED/PRESSED ON. (TC NR 20070123001)			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2007051100049	20070511	00049	EA  	2007	5	11	CA070123002      	1	20070122	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AIRCRAFT HAD A FLAPLESS LANDING, AFTER FLAP SELECTION 8, LT FLAP INDICATED ZERO, RT UNKNOWN, CREW THEN SELECTED TO	 20 AND FLAPS TRAVELED TO APROX 5 DEGREES INDICATION WAS GREEN TRAVELED TO 5 DEGREES AND THEN TURNED WHITE. CREW THEN RE	TRACTED FLAPS BACK TO FLAP ZERO AND LANDED FLAPLESS, FLAP FAIL CAUTION WAS NOT ILLUMINATED.  FERRY FLIGHT FOR TROUBLESHO	OTING.  T/S C/O AND ALL DCU`S ARE DISPLAYING THE SAME INFO, APPEARS TO BE POTENTIOMETER FAIL.  WAITING FOR PART TO BE IN	STALLED. (TC NR 20070123002)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007080800126	20070808	00126	CE  	2007	8	8	CA070123004      	1	20070121	G	3040	99180021	FAN             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					WINDSHIELD	ODOR            	W				G	H			O2 MASK DEPLOYED        	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA			6004 								(CAN) ON APPROACH WHEN THE CREW SMELLED SOMETHING BURNING IN THE CABIN.  THE CABIN FILLED UP WITH SMOKE AND THE CREW PUT	 ON THEIR MASKS AND DROPPED THE PASSENGERS MASKS.  THEY LANDED WITHOUT DECLARING AN EMERGENCY.  AN AME WAS SENT TO AND D	ETERMINED THAT THE DEFOG FAN WAS AT FAULT.  THE FAN WAS DEFERRED AND WILL BE REPLACED ON ITS RETURN. (TC NR 20070123004)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007051100050	20070511	00050	EA  	2007	5	11	CA070123005      	1	20070118	G	2752	852D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	WORN            	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			5457 	5321 							(CAN) ON FINAL APPROACH CREW SELECTED FLAPS 20 DEGREES. FLAPS STUCK AT 8 DEGREES AND CREW RECEIVED A FLAP FAIL MESSAGE. 	CREW BROKE OFF APPROACH AND CONTACTED DISPATCH. AIRCRAFT SUBSEQUENTLY LANDED WITHOUT INCIDENT WITH FLAPS AT 8 DEGREES. M	AINTENANCE TROUBLESHOOTING FOUND EXCESSIVE LINEAR PLAY IN THE LT AND RT IB FLAP ACTUATORS. ACTUATORS REPLACED (RT IB ACT	UATOR PN CL600-2B19, S/N 5051. TSN 5321:44 HOURS, TSO 5321:44, CYCLES 4332) MOD SUM IS601R27530052 REV B: FLAP DRIVE SYS	TEM, ALTERNATE METALLIC SEAL FOR FLEXIBLE DRIVE SHAFT COMPLETED. SYSTEM RE-GREASED. FLAP SYSTEM RIGGED IAW AMM 27-51-10.	 SUCCESSFUL TEST FLIGHT COMPLETED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070123005)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100051	20070511	00051	EA  	2007	5	11	CA070123006      	1	20070122	G	3230	574205A	VALVE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			36649	9188 							(CAN) DURING APPROACH WHEN LANDING GEAR SELECTED DOWN, NO GEAR MOVEMENT. CIRCUIT BREAKERS, HYDRAULIC PX AND QUANTITY AND	 DOORS ALL NORMAL. AFTER APPROXIMATELY 10 MINUETS, LANDING GEAR DEPLOYED NORMALLY TO EXTENDED POSITION. AIRCRAFT FERRIED	 GEAR DOWN TO MAINTENANCE BASE. LANDING GEAR SELECTOR VALVE REPLACED, GEAR SWINGS CARRIED OUT. SERVICEABLE. AIRCRAFT RET	URNED TO SERVICE.  (TC NR 20070123006)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100066	20070511	00066	NE  	2007	5	11	CA070123007      	1	20070106	G	6420	9235806343101	CONE            	SKRSKY      		SKRSKY	S92   	S92A        	       	NE  										TAILROTOR G/B	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			596  			A13200020					(CAN) ON 06 JAN 07, THE TAIL ROTOR HEAD WAS IN PROCESS OF BEING REPLACED WHEN IT WAS NOTICED THAT THE IB SET OF SPLIT CO	NES WHICH CENTER AND SUPPORT THE TAIL ROTOR HUB LOADS WERE MISSING. FURTHER INVESTIGATION FOUND THAT WHEN THIS TAIL GEAR	BOX WAS INSTALLED 596 HOURS PREVIOUS ON 18 JUNE 06 THE MFG MM DID NOT HAVE ANY REFERENCE TO THE INNER SPLIT CONES.  NO M	ENTION OF THEM IN THE REMOVAL/INSTALLATION INSTRUCTION, OR THE REQUIRED PARTS LISTING OR ON ANY ILLUSTRATION.( NOTE: MFG	 MM HAVE SINCE BEEN UPDATED AS OF SEPT  06 TO INCLUDE THE IB SPLIT CONES)  FIELDS FOR P/N NOT LONG ENOUGH TGB P/N 92358-	06100-043 (TC NR 20070123007)	2	G	7	2 	4U				R00024BO					 
2007051100052	20070511	00052	EA  	2007	5	11	CA070123008      	1	20070123	G	5415	TA305002403	FAIRLEAD        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD LINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10220	8646 							(CAN) DURING MAINTENANCE INSPECTION , FOUND AFT FUSELAGE EQUIPMENT BAY HYDRAULIC LINE CLAMPS (FAIRLEAD), WITH CENTER (PR	ESSURE LINE) HOLES WORN THROUGH RUBBER/SILICON COMPOUND AND ALLOWING TUBING TO CHAFE ON METAL PORTION OF BLOCK.  BLOCK P	N TA3050024-03 CONSISTS OF (2) HALVES (INK STAMP P/N B0305103-002 OR 601R75126-3). CLAMP HALVES REPLACED. (TC NR 2007012	3008)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080520		CE  	2008	5	20	CA070123009      	1	20070123	G	5320	51220465	BRACKET         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  		CORRODED        	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) WHEN FLAPS LOWERED AC SEEMED TO ROTATE SLIGHTLY. PILOT RETURNED TO BASE. FLAP SYS INSPECTED AND FAULT FOUND WITH L	T FLAP BELLCRANK LOWER MOUNTING BRACKET. BELLCRANK MOUNTING HOLE WAS SEVERELY CORRODED ALLOWING LARGE BOLT MOVEMENT WHEN	 FLAPS OPERATED. BRACKET REMOVED AND NEW PART ON ORDER. (TC NR 20070123009)				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2007051100068	20070511	00068	NE  	2007	5	11	CA070123010      	2	20070123	G	7261	311145101	SEAL            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					NR 2 ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			15852	4083 							(CAN) CREW LANDED AND REPORTED ENGINE NR 2 LEAKING OIL. MAINTENANCE INSPECTED AND FOUND THE OIL LEVEL DOWN CONSIDERABLY,	 THEY INSPECTED THE FWD CHIP DETECTOR, OIL FILTER, FUEL OIL HEATER AND FOUND NO DEFECTS. THE ENGINE WAS GROUND RUN WITH 	A LITTLE OIL LEAKAGE FOUND. THE OIL BREATHER LINE WAS REMOVED AND THE A/C SENT ON A TEST FLIGHT. WHEN IT RETURNED THE BA	G WAS FULL (.5 LTR) WITH SOME SPILLAGE FROM THE BAG .THE A/C WAS GROUNDED AND WITH THE AID OF A MFG ENGINEER, THE REDUCT	ION GEAR BOX ASSY WAS REMOVED FROM THE ENGINE. CLOSE INSPECTION FOUND THE INTERNAL CARBON SEAL ASSY WITH SLIGHT DAMAGE A	ND STUCK IN THE OPEN POSITION. AS SOON AS THE SEAL WAS TOUCHED THE SPRING IN THE ASSY CLOSED THE OPENING IN THE SEAL ASS	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007080800127	20070808	00127	NM  	2007	8	8	CA070123012      	1	20070119	G	3520	RVA7101	CONTROL UNIT    			AMD   	FALC50	FALCON2000  	2730170	NM  										OXYGEN SYSTEM	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA				1564 							(CAN) UPON A NON-ROUTINE DEPLOYMENT OF THE OXYGEN MASKS ON THE GROUND BY MAINTENANCE.  OXYGEN CONTROL UNIT (10WJ) WAS PL	ACED INTO (OVERRIDE) TO MANUALLY DEPLOY THE PAX OXYGEN MASKS.  THEY DID NOT DEPLOY ON COMMAND.  MULTIPLE ATTEMPTS WERE M	ADE TO MANUALLY DEPLOY THE PAX OXYGEN MASKS IN (OVERRIDE).  THEY STILL DID NOT DEPLOY.  OXYGEN CONTROL UNIT (10WJ) WAS R	EPLACED IAW MP35-203, OPS TESTED SERVICEABLE.  PN OFF: RVA71-01  SN OFF: 0640 ATSO: 1563.8 ACSO: 711.  FAULTY OXYGEN CON	TROL UNIT FORWARDED TO MFG FOR EXCHANGE. (TC NR 20070123012)		2	K	7	2 	4F			RT	A50NM   					 
2007051100055	20070511	00055	EA  	2007	5	11	CA070123013      	1	20070117	G	2910	AE2460260G0074	HOSE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) ON FINAL APPROACH WITH GEAR DOWN AND AT 2000FT THE MESSAGE HYD NR3 LOW PRESS CAME ON EICAS WITH THE HYDRAULIC NR3 	RESERVOIR LEVEL AT 0 PERCENT.  CREW COMPLIED WITH QRH.   THE AIRCRAFT LANDED NORMALLY AND DEPLOYED THE THRUST REVERSER ,	 THE GROUND SPOILERS DEPLOYED AND OPERATED BRAKES .  THE AIRCRAFT AT A SPEED AROUND 70 KTS SUDDENLY DIVERTED ON THE RT E	ND SIDE . THE AIRCRAFT LEFT THE SIDE OF THE RUNWAY BY 13 METER AND ENDED UP ON THE GRASS AFTER THE A/C COVERED 50/55 MET	ERS  (TC NR 20070123013)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100056	20070511	00056	EA  	2007	5	11	CA070123014      	1	20070121	G	5610	NP13932114	WINDSHIELD      			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			565  								(CAN) RT WINDSHIELD CRACKED, FL240.IAS250 DIFF PRESS 7.4  RT WINDSHIELD REPLACED ACC AMM 56-11-01-400. CURE TIME OF SEAL	ANT TIL 21-01-2007, 20:00 LOC TIME. PLS PERFORM ADJUSTMENT OF WIPER ARM TENSION ACC AMM 30-42-09-400-801-A01 AND OPS TES	T OF WIPER AND PERFORM A LEAK TEST OF WINDSHIELD ACC AMM 56-11-01-400-801-A01 (E).  CONDITION OF SEALANT CHECKED OK.  AD	JUSTMENT OF WIPER ARM IAW.AMM. CHECKED OK. OPS TEST OF WIPER OK.  CABIN PRESSURE TEST UP TO DELTA P 6.0 PERFORMED FOUND 	SATISFIED. (TC NR 20070123014)		2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007051100058	20070511	00058	EA  	2007	5	11	CA070123015      	1	20070118	G	5610	NP13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			564  								(CAN) LT WINDSHIELD CRACKED.  LT WINDSHIELD REPLACED IAW AMM 56-11-01-000-801 (TC NR 20070123015)						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007051100126	20070511	00126	EA  	2007	5	11	CA070124001      	1	20070122	G	2840	73664310	COMPUTER        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUEL QUANTITY	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			10220	10220							(CAN) JUST PRIOR TO TOP OF CLIMB, LEFT FUEL QUANTITY AND TOTAL FUEL QUANTITY STARTED TO REDUCE, FOLLOWED BY FUEL IMBALAN	CE MESSAGE. CREW ELECTED TO RETURN TO DEPARTURE AIRPORT. ON FINAL APPROACH FUEL INDICATIONS RETURNED TO NORMAL. FUEL SYS	TEM INSPECTED, WITH NO LEAKAGE FOUND. AIRCRAFT DISPATCHED UNDER MEL. ON NEXT MAINTENANCE VISIT FUEL COMPUTER REPLACED. (	TC# 20070124001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007080800128	20070808	00128	CE  	2007	8	8	CA070124002      	1	20070122	G	3020	991240216	SOLENOID VALVE  			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ANTI-ICE SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) STILL IN CRUISE CONFIG PILOTS DECIDED TO SELECT ANTI-ICE IN PREPARATION FOR DECENT TO AIRPORT. AT THIS TIME, A LT 	ANTI-ICE FAIL LIGHT ILLUMINATED.  TROUBLESHOOTING LATER CONFIRMED THAT THE LT ENGINE ANTI-ICE VALVE HAD FAILED.  THE VAL	VE IS POWERED 28VDC CLOSED UNTIL THE PILOT SELECTS ANTI-ICE ON, THEN POWER IS REMOVED AND THE VALVE IS OPENED BY ENGINE 	BLEED AIR PRESSURE. THE SYSTEM IS INTENDED TO BE A FAILSAFE SYSTEM, WHERE A NO POWER SITUATION WILL ALWAYS ALLOW BLEED A	IR TO THE ENGINE INTAKE.  THIS PARTICULAR VALVE FAILED TO PROVIDE THE FAILSAFE CONDITION. NO ENGINE BLEED AIR WAS AVAILA	BLE TO THE ENGINE INLET ALLOWING AN EXCESSIVE BUILD UP OF ICE. THIS CONDITION COULD HAVE LED TO ICE INGESTION CAUSING EN	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007051100069	20070511	00069	CE  	2007	5	11	CA070124003      	1	20070119	G	5753	99160011	ROLLER          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAPS	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED INTERFERENCE WITH AILERON CONTROL UPON APPROACH WHEN FLAPS WERE APPROXIMATELY 30 PERCENT.  AIRCRAFT	 LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED RT OB FLAP IB HINGE ATTACH BRACKET, PN 35-165050-31, FAILED AT THE AFT	 ROLLER ASSY ATTACH AREA.  THIS IN TURN CAUSED THE OPPOSITE ATTACH BRACKET TO FAIL.  THIS CAUSED THE IB AFT AREA OF THE 	FLAP TO MOVE FREELY AND CHANGE THE NORMAL ATTITUDE OF THE FLAP CAUSING INTERFERENCE WITH THE IB RT AILERON SKIN.  THE HI	NGE ATTACH BRACKET FAILED FROM THE AFT ROLLER ASSY, P/N 99-160011, WEARING INTO THE HINGE ATTACH BRACKET.  INSPECTED ALL	 OTHER HINGE ATTACH AREAS AND FOUND SIMILAR WEAR IN OTHER AFT ROLLER ATTACH LOCATIONS.  THE ROLLER ASSEMBLY, PN 99-16001	1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007051100059	20070511	00059	EA  	2007	5	11	CA070125001      	1	20070125	G	3233	6008500185	ACTUATOR        			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			25189	6776 							(CAN) RT MAIN LANDING GEAR UNLOCK INDICATION APPROX. 15 - 20 MIN. AFTER ARRIVAL, NO PUMP, NO GEAR COMMAND, LOCK PARTIALL	Y MOVED TO UNLOCK POSITION. RETRACTING ACTUATOR REPLACED AND AC RETURNED TO SERVICE. 					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2007080800129	20070808	00129	CE  	2007	8	8	CA070125002      	1	20070124	G	3231	08411131	SCREW           			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RT MLG ADJ	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON LANDING RT MLG INADVETENTLY RETRACTED. AIRCRAFT VEERED OFF RUNWAY. AIRCRAFT INSPECTED AND CAUSE DEEMED FAILUR	E OF RT MLG ADJUSTING SCREW CAUSING SIDE BRACE ASSY TO UNLOCK. (TC NR 20070125002)					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2007051100127	20070511	00127	NM  	2007	5	11	CA070125003      	1	20070123	G	2612	3023143	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CARGO BAY	FALSE INDICATION	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			28530	28530							(CAN) ON DEPARTURE THROUGH 4000 FT, FLT CREW RECEIVED A MASTER WARNING BAGGAGE SMOKE INDICATION. FLIGHT CREW DECLARED AN	 EMERGENCY AND ELECTED TO RETURN TO DEPARTURE AIRPORT. THERE WAS A COMPANY LINE CHECK CAPTAIN ON BOARD WHO WITH THE FLIG	HT ATTENDANT WENT TO CHECK THE CARGO HOLD. THERE WAS NO INDICATION OF SMOKE. FLIGHT LANDED SAFELY WITHOUT FURTHER INCIDE	NT. MAINTENANCE REPLACED THE NR 1 BAGGAGE SMOKE DETECTOR , THE LAMPS IN THE NR 2 DETECTOR (P/N 376), CLEANED THE CONNECT	ORS OF BOTH DETECTORS AND GROUND TESTED THEM SERVICEABLE. ENGINE RUNS WERE CARRIED OUT WITH NO DUPLICATION OF THE ORIGIN	AL DEFECT. TIME SINCE LAST REPAIR OF THE NR 1 DETECTOR WAS 1883:46 HOURS. (TC 20070125003)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100070	20070511	00070	EU  	2007	5	11	CA070125004      	1	20070123	G	6220	601741	BEARING         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					PENDULUM ABSORB	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON LANDING AT THE MAINTENANCE BASE AND FOLLOWING HELICOPTER BEING SHUTDOWN, THE PILOT WAS EXITING AND LEAVING TH	E AIRCRAFT HE NOTICED THAT THE M/R PENDULUM ABSORBER ON THE YELLOW MAIN ROTOR BLADE WAS IN THE HORIZONTAL POSITION. CLOS	ER INSPECTION REVEALED THAT WHEN AN ATTEMPT TO ROTATE THE PENDULUM ABSORBER IT WAS EXTREMELY ROUGH AND DIFFICULT TO ROTA	TE.  PENDULUM ABSORBER WAS REMOVED AND DISASSEMBLED, WHERE IT WAS FOUND THAT ONE OF THE BEARINGS HAD A FRACTURED OUTER C	ASE.  THE BEARING APPEARED TO BE DRY, AS NO EVIDENCE OF LUBRICATION WAS FOUND.  NEW BEARINGS, SEALS, AND O-RINGS WERE IN	STALLED.  PENDULUM ABSORBER WAS RE-INSTALLED AND AIRCRAFT NOW RETURNED TO SERVICE. (TC NR 20070125004)	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2007051100071	20070511	00071	EA  	2007	5	11	CA070125005      	2	20070125	G	7250	312111101	BLADE           								PWA   	PT6   	PT6A65B     	52043	EA  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE PT6A-65B S/N: PCE-32399 WAS RECEIVED FOR OVERHAUL.  DURING THE ENGINE DISASSEMBLING IT WAS FOUND THAT T	HE COMPRESSOR TURBINE BLADES WERE SEVERELY RUBBED AND ONE BLADE FAILED AT FIRTREE.  ALSO THE INSPECTION REVEALED THAT TH	E COMPRESSOR TURBINE VANE TRAILING EDGE, SHROUD SEGMENTS AND SHROUD HOUSING ARE DAMAGED. THE POWER TURBINE COMPONENTS: 1	ST AND 2ND STAGES BLADES AND VANES FOUND IMPACT DAMAGED.    THE BLADE WHICH FAILED AT THE FIRTREE SHOWED EVIDENCE OF FAT	IGUE WITH AN ANOMALY AT THE ORIGIN.  NOTE: CODES DETERMINED FROM PILOT REPORT.  (TC NR 20070125005)							4	T			E4EA				 
2007051100060	20070511	00060	NE  	2007	5	11	CA070125006      	2	20070123	G	7261		ENGINE          			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 3	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			67467	8505 				666071			(CAN) ENROUTE, NR 3 ENGINE OIL LOSS, AIRCRAFT DIVERTED.  INSPECTED AND FERRIED AIRCRAFT.  ENGINE REPLACED (TC NR 2007012	5006)					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007051100061	20070511	00061	GL  	2007	5	11	CA070126001      	2	20070121	G	7200		ENGINE          			EMB   	135   	EMB135LR    	3260305	SO  	ALLSN 	AE300 	AE3007A     	 	GL  						MALFUNCTIONED   	W				E	B	A		ENGINE SHUTDOWN         	EMER. DESCENT           	UNSCHED LANDING         		B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA			9808 					CAE312136			(CAN) DURING CLIMB (280 KNOTS) AT FL350 , CREW HEARD A LOUD POP FOLLOWED BY MULTIPLE UNSPECIFIED EICAS MESSAGES AND ITT 	WAS IN THE AMBER RANGE.  ENGINE SHUTDOWN UNCOMMANDED.  F/A REPORTED WHITE SMOKE IN THE CABIN.  CREW CONSIDERED ATTEMPTIN	G A RE-START BUT OIL QUANTITY WAS ONLY 3 QUARTS. CREW DIVERTED AND A CMC DOWNLOAD REVEALED THAT AN OIL DEBRIS MESSAGE HA	D BEEN SET ON JANUARY 19. ENGINE ENROUTE TO MFG FOR INVESTIGATION, FURTHER REPORT WILL BE SUBMITTED ON ENGINE TEARDOWN. 	(TC NR 20070126001)		2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2007080800130	20070808	00130	CE  	2007	8	8	CA070126002      	1	20070125	G	3260	426EN98	SQUAT SWITCH    			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT MAIN GEAR	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) PRELIMINARY REPORT, SUSPECT THAT THE SHUTTLE VALVE THAT DIRECTS HYDRAULICS TO THE UP- OR DOWN-SIDE OF THE LANDING 	GEAR WAS STUCK OR BROKEN IN THE UP DIRECTION.  WHEN THE L/G WAS SELECTED DOWN ON THE ARRIVAL, NOTHING HAPPENED EXCEPT TH	E L/G DOORS OPENED THE FIRST TIME, NOTHING AT ALL ON THE SECOND ATTEMPT.  THE CREW WENT AROUND AND PUT THE L/G DOWN WITH	 EMERGENCY SYSTEM.  IT WORKED AND THEY HAD THREE GREEN, BUT THE EMERGENCY GEAR EXTENSION LEVER DID NOT LOCK AS IT SHOULD	, AND THE L/G RETRACTED ON ITS OWN SHORTLY THEREAFTER!  THE EMERGENCY SYSTEM WAS RE-ACTIVATED, THE L/G WENT DOWN AS IT S	HOULD AND THE LEVER WAS HELD IN THE DOWN POSITION.  THREE GREEN, NORMAL LANDING, AND THE A/C TURNED ONTO A TAXIWAY AND W	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007051100128	20070511	00128	NM  	2007	5	11	CA070126005      	1	20070126	G	5343	85310340015	FITTING         			DHAV  	DHC8  	DHC8106     	2809020	NM  										NLG WHEEL WELL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING "C-CHECK", WE FOUND THE NLG ACTUATOR FUSELAGE FITTING WITH A FASTENER BROKEN AND ALL THE OTHER ONE LOOSE. W	E EMBODIED THE SB 8-53-50. THIS SB WAS NOT ATTACH TO ANY AD. (TC# 20070126005)					2	H	7	2 	4T			RT	A13NM   					 
2007051100075	20070511	00075	SW  	2007	5	11	CA070126006      	1	20070121	G	5302	206020113207	TAIL BOOM       			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					VERTICAL FIN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3368 				52054				(CAN) UPON CHANGING FORMER P/N 206-020-113-093 ON VERTICAL FIN, DAMAGE/GOUGING DETECTED ON THE IB FIN SKIN WITHIN CLOSE 	PROXIMITY TO VERTICAL FIN MOUNTING HOLE. IT IS SUSPECTED THAT WHEN ORIGINALLY FITTING THE COWLS THAT THE FORMER WAS TRIM	MED AND THAT AT THIS TIME THE DAMAGE OCCURRED.   MFG WAS CONTACTED AND AN APPROVED REPAIR WAS PROVIDED AND CARRIED OUT. 	(TC NR 20070126006)			1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2007051100129	20070511	00129	SW  	2007	5	11	CA070126007      	1	20070121	G	5302	205030767005	FITTING         			BELL  	205   	205A1       	1181414	SW  										TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AIRFRAME INSPECTION, A CRACK WAS FOUND ON LONGERON P/N 205-030-207-005 UNDER FITTING P/N 205-030-767-005. F	ITTING REMOVED, INSPECTED FOUND TO BE CRACKED AT AFT SIDE OF BOLT LOCATION. CRACKS IN FITTING P/N 205-030-767-005 NOT FO	UND UNTIL REMOVAL OF PART. THIS FITTING IS KNOWN TO CRACK AT THE RIVET HOLE LOCATIONS, BUT IN THIS INSTANCE, IT WAS CRAC	KED ON THE AFT SIDE OF THE BOLT HOLE LOCATION. LONGERON AND FITTING WERE REPLACED WITH NEW PARTS.  (TC# 20070126007)			1	G	7	1 	4U				H1SW    					 
2007053000006	20070530	00006	NM  	2007	5	30	CA070126008      	1	20070117	G	2611		SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LAVATORY	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) ON GOING REPORTS OF LAVATORY SMOKE DETECTOR ACTIVATION. PROBLEM APPEARS TO HAVE BEGUN ON JANUARY 17, 2007 WITH A P	ILOT REPORT OF THE NR 2 ENGINE WILL NOT START AFTER (3) ATTEMPTS AND THEN AN OIL LEAK. MAINTENANCE REPLACED THE ENGINE I	GNITERS AND CLEANED THE RESIDUAL OIL. ENGINE WAS THEN STARTED SUCCESSFULLY AND RUN TO TROUBLESHOOT THE OIL LEAK. NO OIL 	LEAK COULD BE FOUND AND IT WAS SUSPECTED TO BE AS A RESULT OF THE NO START CONDITION. ON JANUARY 18, 2007 LAVATORY SMOKE	 DETECTOR ACTIVATED ON FINAL APPROACH. FLIGHT ATTENDANT DETECTED ODOR ON GROUND. MAINTENANCE REPLACED DETECTOR (P/N 46-0	083-4) AND SYSTEM CHECKED SERVICEABLE. ON NEXT FLIGHT, DETECTOR ACTIVATED AGAIN WITH NO SMOKE OR ODOR. LOW BATTERY (TC N	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100174	20070511	00174	SO  	2007	5	11	CA070126009      	1	20070118	G	3246	402377	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING, THE UPPER TORQUE LINK BOLT BROKE WHICH ALLOWED THE LT MAIN WHEEL TO TURN SIDEWAYS. (TC NR 200701260	09)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007051100175	20070511	00175	CE  	2007	5	11	CA070126010      	1	20070123	G	2110	206SZZC	BEARING         	BEECH       	115555024   	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COMPRESSOR	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING WITHIN RT ENGINE AIR CONDITIONING COMPRESSOR DRIVE PULLEY DISINTEGRATED WHICH GREATLY CAUSED FURTHER HARM 	TO ITS ASSOCIATED PARTS.  THE QUILL SHAFT, COMPRESSOR DRIVE PULLEY, COMPRESSOR MOUNT ASSEMBLY, DRIVE SUPPORT, BEARING SH	IMS AND SPACER, AND DUAL BELT (COMPRESSOR DRIVE BELT) HAVE HAD IRREVOCABLE DAMAGE. QUILL SHAFT DID NOT SHEAR. (TC NR 200	70126010)			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007080800131	20070808	00131	CE  	2007	8	8	CA070126011      	1	20070118	G	3213	50411148	TORQUE LINK     			CESSNA	401   	401         	207590C	CE  										RT MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT WAS DOING TOUCH AND GO`S ON THE 2ND LANDING PILOT REPORTED ABNORMAL LANDING AND NO GEAR UP INDICATION.  G	EAR CYCLED AND ONLY 2 OUT OF 3 INDICATOR LIGHTS ILUMINATED. RT MAIN, NO INDICATION. GEAR CYCLED AGAIN NO UP INDICATION A	ND NO RT GREEN DOWN INDICATION. AIRCRAFT COMPLETED FLY BY CONTROL TOWER WHEN PILOT WAS INFORMED OF HIS RT MAIN WHEEL AT 	A 45 DEGREE ANGLE. AIRCRAFT CARRIED OUT A FLY OVER OF MORGAN AIR`S FACILITY WHERE WITH BINOCULARS, I COULD SEE THE RT MA	IN GEAR OVER CENTER DOWN AND LOCK WAS OVER CENTERED. PILOT CARRIED OUT SUCCESSFUL LANDING AND AIRCRAFT WAS REMOVED FROM 	RUNWAY WITHIN 10 MINUTES. (TC NR 20070126011)	1	L	7	2 	3O				A7CE    					 
2007051100178	20070511	00178		2007	5	11	CA070126012      	4	20070124	G	2300		FEEDER CABLE    			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	RADIO	LOOSE           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) TOTAL LOSS OF CAPT`S RADIO COMMUNICATIONS. TROUBLESHOOTING FOUND MAIN POWER FEED CONNECTION NOT TIGHTEN ON TERMINA	L BLOCK T5GA CAUSING CONNECTOR TERMINAL RING TO FLOAT AND REMOVE POWER SUPPLY TO CAPT`S AUDIO STATION BOX (TC NR 2007012	6012)				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2007051100179	20070511	00179	NE  	2007	5	11	CA070126013      	2	20070126	G	7220		FAN             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	DISLODGED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D	T	Y	INFLIGHT SEPARATION       	ENGINE CASE PENETRATION   	ENGINE STOPPAGE           	CL	CLIMB          	1			CA											(CAN) THE NR 1 ENGINE FAN DISLODGED ITSELF FROM THE ENGINE AND TORE OFF THE INLET AND FAN CASING.  IT ALSO DID EXTENSIVE	 DAMAGE TO THE PYLON AND THE FUSELAGE. NTSB IS ON SITE FOR THE INVESTIGATION. MORE INFORMATIOON TO FOLLOW ONCE AVAILABLE	. (TC NR 20070126013)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100180	20070511	00180	SO  	2007	5	11	CA070127002      	1	20070123	G	6120	454254	CONTROL CABLE   			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							317512033				(CAN) LT PROPELLER CONTROL CABLE FAILURE. THE PILOT NOTED THAT THE LT PROPELLER CONTROL WAS STIFF ON APPROACH. THE LT EN	GINE AND PROPELLER CONTROLS WERE INSPECTED, MAINTENANCE DETERMINED THE LT PROPELLER CONTROL CABLE IN THE CABIN PEDESTAL 	HAD FAILED. THE PROPELLER CONTROL CABLE WIRES HAD TWISTED AND SEVERED APPROXIMATELY .2500 FROM THE SWAGED PORTION OF THE	 ROD END.  THE LT PROPELLER CONTROL CABLE PN: 454-254 (ALT P/N: 24894-08) WAS REPLACED. THE AIRCRAFT RETURNED TO SERVICE	. (TC NR 20070127002)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007051600133	20070516	00133	NE  	2007	5	16	CA070128001      	2	20070125	G	7250		BEARING SEAL    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	LEAKING         	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA			11811	11811				872974			(CAN) REPORTS OF LAV SMOKE CAUTION MSG COMING ON. PROBLEM APPEARS TO HAVE BEGUN ON DEC 5,2006 FLT. 8620, ON CLIMB-OUT, C	REW RECEIVED A LAV SMOKE DETECT CAUTION LIGHT, FA CHECKED LAV NO SMOKE WAS EVIDENT, FLIGHT RETURNED TO DEPARTURE. A/C WA	S DE-ICED PRIOR TO DEPARTURE AND DE-ICE FLUID WAS THE SUSPECTED CAUSE.  BOTH COALESER BAGS WERE REPLACED AND GROUND RUNS	 WERE CARRIED OUT.  A 2ND EVENT OCCURRED ON THE GROUND , DEC 5,2006, LAV SMOKE MSG CAME ON FOR 30 SECS THEN DID NOT COM	E ON AGAIN, C/BS WERE RESET AND A/C WAS POWERED DOWN AND RESET, FUNCTION CHECKED SERVICEABLE.  3RD EVENT, JANUARY 17, 2	007, FLT. 7690,  SHORTLY AFTER ROTATION, FLIGHT CREW RECEIVED A SMOKE IN THE LAV INDICATION AND FA CONFIRMED LAV SMOKE D	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100183	20070511	00183	EA  	2007	5	11	CA070128002      	1	20070126	G	4900		APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						CONTAMINATED    	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER DEPARTURE, THE CREW NOTICED A LAV SMOKE WARNING AND SMOKE WAS VISIBLE IN THE CABIN FOR 3-4 MINUTES  	THEN IT DISSIPATED. SMOKE WAS BLUISH IN COLOR AND OILY SMELLING. (2) MAINTENANCE PERSONNEL WERE ON BOARD, INITIALLY THEY	 THOUGHT SINCE THE AIRCRAFT HAD JUST BEEN DE-ICED WITH ENGINES AND APU RUNNING THAT DE-ICE FLUID WAS THE CAUSE SO A DECI	SION WAS MADE TO CONTINUE. THE COALESER BAGS WERE INSPECTED AND REPLACED. AFTER ENGINE RUNS AND FURTHER TROUBLESHOOTING 	IT WAS NOTICED THAT NR 2 PRSOV IS RUNNING AT 38 TO 41 PSI AND MAY HAVE CAUSED DAMAGE TO NR 2 ACM.  FURTHER TROUBLESHOOTI	NG ON GOING. (TC NR 20070128002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100184	20070511	00184	EU  	2007	5	11	CA070129001      	1	20070127	G	3800		LINE            			EMB   	ERJ190	ERJ190100IGW	3260408	EU  										WATER	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			2865 								(CAN) REPORTED STIFF AILERONS IN FLIGHT AND IT APPEARS THE ROOT CAUSE WAS A WATER LEAK RESULTING IN WATER POOLING IN THE	 BILGE AND BINDING THE AILERON CABLES. AN INVESTIGATION IS STILL TAKING PLACE. (TC NR 20070129001)					2	L	7	2 	4F			RT	A57NM   					 
2007051100185	20070511	00185	EU  	2007	5	11	CA070129002      	1	20070125	G	3244		TIRE            			EMB   	ERJ190	ERJ190100IGW	3260408	EU  										MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING, RT OB MAIN WHEEL TIRE FAILED, DUE TO BRAKE SEIZING. INVESTIGATION STILL UNDERWAY ON CAUSE. (TC NR 2007	0129002)					2	L	7	2 	4F			RT	A57NM   					 
2007053000007	20070530	00007	GL  	2007	5	30	CA070129003      	1	20070122	G	3810	4E32612	VALVE           	BFGOODRICH  		BOMBDR	BD700 	BD7001A10   	1390006	GL  										WATER SYSTEM	OPEN            	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) OVER AN HOUR INTO THE FLIGHT, A SPOILER MOMENTARY DEPLOYMENT WITH WING ROLL AFTER SPOILER FAULT CAS OCCURRED.  FLI	GHT SPOILER FAIL CAS POSTED SHORTLY AFTERWARDS.  SEVERAL CABIN SYSTEM MALFUNCTIONS OCCURRING NEXT FOLLOWED BY HAVING NO 	WATER FROM ANY FAUCET AVAILABLE. A/C LANDED AT FINAL DESTINATION AND SPOILER/STAB IN BIT CAS POSTED. WATER NOTED TO BE D	RAINING FROM FORWARD FUSELAGE BELLY SKIN DRAINS WITH WATER TANK QUANTITY SHOWING EMPTY.  GALLEY CARPET FOUND WET WITH GA	LLEY UNDER SINK AREA WET AS WELL. VISUAL INSPECTION OF AVIONICS BAY CARRIED OUT WITH FCU RESET PROCEDURE CARRIED OUT. SP	OILER FAIL CAS CLEARED WITH SPOILER/STAB IN BIT ONLY THAT WAS MMEL`D . WATER SYSTEM LEFT EMPTY AND TURNED OFF FOR UNEVEN	2	L	7	2 	4F			RT	T00003NY					 
2007051100186	20070511	00186	EA  	2007	5	11	CA070129004      	1	20070115	G	2560	11011200	BUCKLE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CREW SEATBELT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SPECIAL INSPECTION OF CREW SEAT BELT ROTORY LATCH SYSTEM PERFORMED. BOTH LT AND RT CREW SEATBELT BUCKLE ASSEMBLIES	 WERE CAPABLE OF BEING UNLATCHED WHEN CONTACTED BY THE CONTROL YOKE WHEN ROTATED LT OR RT WITH THE YOKE FULL AFT AND THE	 SEAT IN THE MOST FORWARD POSITION. THIS SPECIAL INSPECTION WAS MANDATED BY A COMPANY CAMPAIGN NOTICE TO INSPECT AIRCRAF	T IAW FAA SPECIAL AIRWORTHINESS INFORMATION BULLETIN (NM-06-39)TO DATE, NO RECTIFICATION FOR THIS PROBLEM HAS BEEN PUBLI	SHED. (TC NR20070129004)		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007051100188	20070511	00188	NM  	2007	5	11	CA070129005      	1	20070128	G	3230	83221002003	LOCK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE NOSE LANDING GEAR FAILED TO RETRACT.  FLIGHT CONTINUED AND LANDED TO THE DESTINATION AIRPORT WIT	HOUT FURTHER INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AFTER ARRIVAL AND FOUND THE NOSE GEAR GROUND LOCK OUT, AND IN 	LOCK POSITION.  (TC NR 20070129005)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100191	20070511	00191	SW  	2007	5	11	CA070129007      	1	20070125	G	6510		DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE A/C WAS BEING LANDED TO DROP OFF SKIERS AND REPORTEDLY HAD A T/R DRIVE SHAFT BREAK BETWEEN THE ENGINE AND THE 	OIL COOLER. THE A/C WAS LANDED WITHOUT DAMAGE. THERE WAS NO INDICATION OF A T/R STRIKE. (TC NR 20070129007)					1	G	7	1 	3U			O	H2SW    					 
2007051500188	20070515	00188	NM  	2007	5	15	CA070129008      	1	20070126	G	3230	483023	VALVE           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LT NACELLE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			215  								(CAN) CREW REPORTED THAT THE GEAR WENT UP BUT THE LT MAIN LANDING GEAR DOORS REMAINED OPEN.  JACKED AIRCRAFT AND PERFORM	ED A GEAR SWING. GEAR WENT UP BUT THE LT DOORS REMAINED OPEN AFTER SYSTEM WENT TO BYPASS MODE.  ON SELECTION OF GEAR DOW	N THE LT MAIN GEAR DOORS CLOSED AND THE GEAR CAME DOWN WITH THE LT UPLOCK RELEASING.  RETRACTED THE GEAR AND TURNED OFF 	THE HYDRAULICS.  PERFORMED AN ALTERNATE GEAR EXTENSION TO GET THE GEAR DOWN. (TC NR 20070129008)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007051100194	20070511	00194	EA  	2007	5	11	CA070130001      	1	20070129	G	2820		LINE            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL VACUUM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT CREWS REPORTED THAT FUEL FLOW FLUCTUATES WHEN BOOST PUMPS ARE SELECTED OFF. SEVERAL VACUUM LEAKS WHERE FOUN	D IN THE FUEL LINES IN THE NACELLE AREA. SYSTEM SEALED AS REQUIRED, ENGINE GROUND RUNS CARRIED OUT AND NO FLUCTUATIONS N	OTED AT TAKEOFF POWER WITH BOOST PUMPS OFF. (TC NR 20070130001)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007051600134	20070516	00134		2007	5	16	CA070130002      	4	20070123	G	3414		INDICATOR       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	AIRSPEED	INOPERATIVE     	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL THE CREW REJECTED THE TAKEOFF AT 85 KTS WITH NO INDICATION ON FIRST OFFICERS SIDE. MAINTENANCE CON	DUCTED A PURGE OF THE SYSTEM AND CARRIED OUT A PITOT/STATIC SYSTEM TEST.THE SYSTEM WAS VERIFIED SERVICEABLE AND THE AIRC	RAFT RETURNED TO SERVICE. (TC NR 20070130002)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007051100195	20070511	00195	CE  	2007	5	11	CA070130003      	1	20070129	G	7600	5052456849	CONDITION LEVER 			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	CONTROL PEDESTAL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOTS REPORTED LT FUEL CONDITION LEVER CRACKED HALF WAY DOWN LEVER.  AIRCRAFT REMOVED FROM SERVICE.  RT CONDITION	 LEVER INSPECTED AND SHOWED SIGNS OF WEAR.  LT AND RT CONDITION LEVERS ON ORDER. (TC NR 20070130003)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007051100196	20070511	00196	NM  	2007	5	11	CA070130004      	1	20070126	G	2820		O-RING          			BOEING	767   	767306      	1385148	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					FUEL SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) AC LANDED WITH LOW HYD FLUID IN CENTER SYS FOUND ACMP NR 2 CENTER FILTER MODULE PRESSURE DELTA P POP-UP LEAKING DU	E TO A FAILED O-RING.  O-RING REPLACED AND HYD SYSTEM SERVICED (37 QTS). (TC NR 20070130004)					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2007051100198	20070511	00198	EA  	2007	5	11	CA070131001      	2	20070129	G	7397		CONNECTOR       	BENDIX      		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 1 TRANSMITTER	SEPARATED       	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA				4801 		812141					(CAN) AIRCREW REPORTED THAT THE NR 1 FUEL FLOW WAS FLUCTUATING WITH NO OTHER ENGINE PARAMETERS BEING AFFECTED. MAINTENAN	CE TROUBLESHOT THE SYSTEM, SWAPPED GAUGES FROM SIDE TO SIDE, PERFORMED ENGINE RUNS AND COULD NOT FAULT THE SYSTEM.  AIRC	RAFT WAS RELEASED FOR FLIGHT. WHEN AIRCRAFT RETURNED TO BASE THE AIRCREW REPORTED THAT THE SNAG WAS STILL PRESENT. MAINT	ENANCE BEGAN INVESTIGATING DEEPER INTO SYSTEM. WHEN THE NR 1 FUEL FLOW TRANSMITTER WAS LOOKED AT, IT WAS FOUND THAT THE 	CONNECTOR PLUG BOSS HAD SEPARATED FROM THE MAIN BODY, THIS ALLOWED THE WIRES TO STRIKE THE HOUSING SIDES DURING FLIGHT D	UE TO NORMAL VIBRATIONS, SHORTING OUT THE TRANSMITTER. THIS COMPONENT HAS BEEN INSTALLED ON THE AIRCRAFT SINCE WE TOOK P	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007080800132	20070808	00132	EA  	2007	8	8	CA070131002      	1	20070131	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) THE CREW REPORTED THAT ON APPROACH THAT THEY RECEIVED AN INITIAL FLAP HALFSPEED MESSAGE FOLLOWED BY A (FLAP FAIL) 	MESSAGE WHEN FLAPS SELECTED ON APPROACH.  ZERO FLAP LANDING WAS COMPLETED. THE AIRCRAFT IS CURRENTLY WITH LINE MAINTENAN	CE TROUBELSHOOTING THE INCIDENT. (TC NR 20070131002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100200	20070511	00200	EA  	2007	5	11	CA070131003      	1	20070130	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED THAT UPON APPROACH FLAPS 8 DEGREES WERE SELECTED OKAY. UPON FLAP 20 DEGREE SELECTION, THE FLAPS 	DID NOT MOVE AND THE FLAP FAIL CAUTION LIGHT ILLUMINATED. THE FLAPS LOCKED AT 8 DEGREES. THE AIRCRAFT IS CURRENTLY IN LI	NE, MAINTENANCE IS TROUBLESHOOTING.(TC NR 20070131003)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100202	20070511	00202	SW  	2007	5	11	CA070131004      	1	20070122	G	6210	206010200133	BLADES          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	OUT OF BALANCE  	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) COULD NOT ACHEIVE DYNAMIC BALANCE OF A/C. (TC NR 20070131004)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007080800133	20070808	00133	EA  	2007	8	8	CA070131005      	1	20070124	G	3230		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MAINS	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE AIRCRAFT LANDED WITH ALL LANDING GEAR UP. BA FSR ON SITE. FSR REPORTED THAT THE ADG WAS DEPLOYED, AND FLAPS RE	TRACTED. AIRPORT AUTHORITIES ARE PRESENTLY IN THE PROCESS OF LIFTING THE A/C IAW THE AIRCRAFT RECOVERY MANUAL USING CRAN	ES. AIRCRAFT CONDITION APPEARS TO BE GOOD.   CONFIRMATION OF A WHEELS UP LANDING HAS BEEN RECEIVED. BA AIR SAFETY IS IN 	CONTACT WITH THE TSBC TO ESTABLISH WHAT ACTUALLY OCCURRED. IT IS NOT KNOWN IF THERE WERE ANY INJURIES. AN UPDATE WILL BE	 ISSUED SHORTLY. THE TSBC HAS CONTACTED THE CIAIC (SAFETY BOARD) OF SPAIN. THE BA RESPONSE WILL BE BASED ON THE NEXT UPD	ATE FROM BARCELONA.   THE FOLLOWING COULD BE OBSERVED IN THE COCKPIT (VERY LIMITED TIME ALLOWED): LANDING GEAR CONTROL H	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051100203	20070511	00203	EU  	2007	5	11	CA070131007      	1	20070128	G	5610	1379628C401	WINDSHIELD      			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE INSPECTION, WINDOW WAS FOUND TO BE DELAMINATING AT THE CENTER OF THE BOTTOM EDGE. WINDOW WAS RE	PLACED. (TC NR 20070131007)					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2007051100204	20070511	00204	EU  	2007	5	11	CA070131008      	1	20070131	G	2910	373Q2277	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	HYDRAULIC SYS	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT (30 MINUTES AFTER DEPARTURE THE FLIGHT CREW OBSERVED NR 1 AND NR 2 LOW HYDRAULIC PRESSURE LIGHTS 	ILLUMINATED. THE FLIGHT CREW RETURNED TO DEPARTURE, USED ALTERNATE MEANS FOR EXTENDING THE LANDING GEAR AND LANDED UNEVE	NTFUL.  MAINTENANCE FOUND INSUFFICENT FLUID IN THE HYDRAULIC SYSTEM. A LEAK IN HYDRAULIC LINE P/N 373Q2277, CAUSED BY CH	AFING WAS FOUND IN THE LT MAIN LANDING GEAR WHEEL WELL.   THE LINE WAS REPLACED, SYSTEM BLEED AND FUNCTION CHECKED OK.  	 (TC NR 20070131008)		2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007051400004	20070514	00004	NM  	2007	5	14	CA070201003      	1	20070201	G	3246	31573	WHEEL           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 3	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) AN AIRCRAFT EXPERIENCED NR 3 WHEEL AND TIRE SEPARATION UPON LANDING DUE TO WHEEL BEARING FAILURE. DETERIORATION OF	 THE MAIN LANDING GEAR WHEEL BEARINGS, RESULTING IN DAMAGE TO THE WHEEL, AXLE, AND BRAKE UNITS.    (TC NR 20070201003)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007051400005	20070514	00005	EA  	2007	5	14	CA070201004      	1	20070201	G	2797		WIRE            	CNDAIR      		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FLAP SYSTEM	BROKEN          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) APPROX 1 MILE OUTSIDE THE OUTER MARKER AT 3000 AGL, THE AMBER FLAP CAUTION LIGHT ILLUMINATED.  THE CREW SELECTED F	LAP 20 AND THE FLAPS WENT TO 20. WHEN THE LIGHT ILLUMINATED THE CREW WENT THROUGH THEIR EMERGENCY CHECKLIST AND CARRIED 	OUT AN UNEVENTFUL LANDING.  THE AIRCRAFT WAS THEN FERRIED FOR MAINTENANCE.  ALL FLAP ACTUATORS WERE PURGED AND SERVICED 	WITH FRESH GREASE IAW MM TASK 12-20-29-640-805.  BOTH BPSUS WERE REPLACED IAW MM TASK 27-51-10-000-80.  FLAP OPERATIONA	L TESTS AND A TEST FLIGHT WERE CARRIED OUT WITH NO FAULTS FOUND. JANUARY 29/2007 IN HOUSE TASK RJ2-275002 FLAP MOISTURE 	PREVENTION PROGRAM WAS CARRIED OUT.  JANUARY 30/2007 THE AIRCRAFT FLEW FOUR LEGS AND ON THE FORTH LEG, THE FLAPS FAILED 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400006	20070514	00006	EU  	2007	5	14	CA070201005      	1	20070130	G	2710	S27010022120100	WASHER          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	AILERON	SPLIT           	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE CREW OBSERVED BINDING IN THE AILERON SYSTEM WHILE EXECUTING A RT TURN DURING DEPARTURE. THE AIRCRAFT RETURNED 	TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. POST FLIGHT INSPECTION DETECTED A LOCATION IN THE SYSTEM WHICH EXHIBITED 	AN INCREASED RESISTANCE TO TRAVEL WHEN CYCLING THE SYSTEM BUT THERE WAS NO RESTRICTION TO FULL MOVEMENT. MAINTENANCE FOU	ND A SPLIT TEFLON WASHER FOULING THE BEARING AT THE SWING LINK BETWEEN RIBS 8 AND 9. THE WASHER WAS REPLACED AND THE AIR	CRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER PROBLEM. (TC NR 20070201005)		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008032000001	20080320	00001	CE  	2008	3	20	CA070201007      	1	20070123	G	3244	0283353	TIRE            			BEECH 	200   	B200        	1152922	CE  										SIDEWALL	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18   								(CAN) DURING MAINT WALK AROUND INSP, IT WAS NOTED THAT ALL (4) MLG LOCATIONS RECEIVED SIDE WALL DAMAGE ON FIRST 20 HRS O	F FLIGHT ON A FACTORY NEW AC DUE TO INTERFERENCE FIT.  AC HAS (2) STCS INCLUDED IN THE MLG. THEY ARE AS FOLLOWS:  AC EQ	UIPPED WITH  (P/N:028-335-3) (WILDERNESS TIRES):  STC SA00184LA.   AC ALSO EQUIPPED WITH WHEEL AND BRAKE CONVERSION KIT:	  STC SA757GL BY STC HOLDER - MFG WAS CONTACTED AND STATED THAT THEY WERE AWARE OF THE PROBLEM SOME SIX MONTHS AGO. IM 	TOLD THE PROBLEM HAS ARISEN WITH THE (19.5X6.75-8/10/190 P/N:028335-3) WHEN MFG OUTSOURCED ITS MANUFACTURE TO FROM THE E	XISTING USA FACILITY. THE OUT OF COUNTRY MFG TIRES ARE BUILT TO A WIDER TOLERANCE FOR SOME REASON. NOTE: ALL AFFECTED TI	1	L	7	2 	4T				A24CE   					 
2007051400007	20070514	00007	GL  	2007	5	14	CA070201008      	2	20070127	G	7321	23034702	FCU             			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20      	03013	GL  					THROTTLE LEVER	FAILED          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA				2719 				CAE820727			(CAN) AFTER THE AIRCRAFT WAS STARTED, THE PILOT DECIDED TO DO A WALK AROUND THE AIRCRAFT. FUEL WAS NOTICED FLOWING FROM 	THE ENGINE BAY TO THE GROUND. FURTHER INVESTIGATION REVEALED A MASSIVE FUEL LEAK AT THE FUEL CONTROL THROTTLE LEVER SHAF	T SEAL. FUEL WAS FLOWING FROM THE FUEL CONTROL AND SATURATING THE STARTER GENERATOR WITH FUEL. THE ENGINE WAS SHUTDOWN A	ND THE AIRCRAFT EVACUATED. FCU REPLACED WITH SERVICABLE UNIT, STARTER VISUALLY INSPECTED AIRCRAFT GROUND RUN, LEAK CHECK	ED AND TEST FLOWN. AIRCRAFT RELEASED. THIS COULD HAVE BEEN A DIFFERENT STORY.  NORMALLY THE PILOT WOULD HAVE JUST TAKEN 	OFF AFTER STARTING THE AIRCRAFT. HIS DECISION TO PERFORM A WALK AROUND MAY HAVE SAVED LIVES AS THE AMOUNT OF FUEL LEAKIN	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007051400011	20070514	00011	SW  	2007	5	14	CA070201009      	1	20070201	G	2410		BRACKET         	LYC         	LW11147     	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ALTERNATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ALTERNATOR ADJUSTING BRACKET BOLT HOLE THAT ATTACHES THE BRACKET TO THE ENGINE WAS FOUND CRACKED ALL THE WAY T	HROUGH. THE BRACKET WAS ONLY BEING HELD IN PLACE BY THE TENSION OF THE BELT. THERE IS SEVERAL OTHER REPORTS OF CRACKS IN	 THE BOLT HOLE OF THIS BRACKET ON OUR ENGINES. (TC NR 20070201009)				1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P25EA	 
2007080800135	20070808	00135	EU  	2007	8	8	CA070202001      	1	20070130	G	7110	5711012091	COWLING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		DAMAGED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			14281								(CAN) AFTER TAKEOFF THE PILOTS NOTICED THAT THE TOP FRONT COWLING WAS LIFTING OFF AT THE REAR. THEY RETURNED TO THE FIEL	D AND DURING THE FLARE THE COWLING DEPARTED THE AIRCRAFT, STRIKING AND DAMAGING THE PROP REQUIRING ITS DISASSEMBLY AND R	T WING DAMAGING THE OB DEICE BOOT. THE POWER SECTION WAS REMOVED FOR A PROP STRIKE INSPECTION. MAINTENANCE HAD BEEN ACCO	MPLISHED THE PREVIOUS EVENING WHERE THAT COWLING HAD BEEN REMOVED AND REINSTALLED. THE (4) LATCHES APPEARED SECURE TO TH	E AME AND THE PILOTS ON THEIR WALK AROUND. THERE IS NO VISUAL AID ON THIS COWLING DESIGN OTHER THEN THE LATCH BEING (FLU	SH) TO INDICATE TO THE PILOT OR TECHNICIAN THAT THE LATCH IS SECURED. PREVIOUS EXPERIENCE HAS SHOWN THAT THE DIFFERENCE 	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007051400013	20070514	00013	EA  	2007	5	14	CA070202002      	1	20070126	G	4930	38834491	LINE            	HONEYWELL   	38004883    	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU FUEL	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA						P160					(CAN) JANUARY 296/2007 DEFECT 591259,  THERE WAS A FUEL SMELL COMING FROM THE APU BLEED. THE APU WAS DEFERRED AND INHIBI	TED IAW MEL 49-10-01-1.  JANUARY 29/2007 MAINTENANCE REPLACED THE ECU FOR TROUBLESHOOTING, BUT THERE WAS NO FIX. FEBRUAR	Y 01/2007 FURTHER TROUBLESHOOTING CARRIED OUT BY MAINTENANCE AND APU FUEL LINE FOUND TO BE LEAKING ABOVE THE EXCITER BOX	.  THE ADEL CLAMP HAD CHAFED THROUGH THE LINE.  FUEL LINE PN 3883449-1  WAS REPLACED, NEW CLAMPS INSTALLED AND APU LEAK 	AND FUNCTION CHECKED SERVICEABLE.  APU HOUR SINCE OVERHAUL ARE 3254 AND CYCLES 2660. (TC NR 20070202002)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400015	20070514	00015	NM  	2007	5	14	CA070202003      	1	20070116	G	5210		SEAL            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  						FAILED          	W				G				O2 MASK DEPLOYED        				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL320, CABIN RATE STARTED TO CLIMB AT 1500 FPM. CREW (CARGO FIT) DONED O2 MASKS. PRESSURIZATION C	ONTROLLER SELECTED TO (MANUAL) AND (STBY), NO CHANGE. CARGO HEAT OUTFLOW VALVE CLOSED, RECOVERED PRESSURE. O2 REMOVED, F	LIGHT CONTINUED WITHOUT FURTHER INCIDENT.  MAINTENANCE CLEANED DOOR SEALS OF DEBRIS AND CARRIED OUT PRESSURIZATION CONTR	OL TEST IAW MM 21-31-00 AND FOUND SERVICEABLE. (TC NR 20070202003)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051400016	20070514	00016	NM  	2007	5	14	CA070202004      	1	20070117	G	2697	W27260718	WIRE            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					FIRE DETECTION	SHORTED         	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AT FL120, APU FIRE LIGHT AND BELL ILLUMINATED. APU FIRE DRILL CARRIED OUT, REMAINED (ON). DECLARED EM	ERGENCY, RETURNED TO AIRPORT WITHOUT INCIDENT.  UPON INSPECTION NO FIRE DETECTED.  MAINTENANCE FOUND (FIRE WARNING) WIRE	  NR W272-607-18 SHORTED TO GROUND. WIRE REPLACED, FUNCTIONED CHECKED SERVICEABLE IAW MM 26-15-01.  (TC NR 20070202004)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051400017	20070514	00017	NM  	2007	5	14	CA070202005      	1	20070130	G	7110		DUCT            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					ENGINE COWLING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON ARRIVAL, MAINTENANCE NOTICED AN APPROXIMATELY 6 INCH HOLE IN NR 1 ENGINE COWL. FURTHER INVESTIGATION DETERMIN	ED THE CAP ON THE 6TH STAGE SADDLE DUCT MISSING, LOCATED IN COWL. CAP INSTALLED AND SECURED IAW MM AND COWL REPAIRED. (T	C NR 20070202005)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051400018	20070514	00018	SW  	2007	5	14	CA070202006      	1	20070124	G	2432	301265AA	DIODE           	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					BATTERY RELAY	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA						81640					(CAN) SINCE THE DIODE FAILED, A DIRECT SHORT TO GROUND OCCURED.  CAUSING THE BATTERY CIRCUIT WIRING TO BURN OFF ITS SHIE	LDING AND THE DIODE PIG TAIL FROM X1 TO X2 ON THE RELAY HEATED UP TO THE POINT OF BREAKING, FLAME WAS PRESENT.  THE BATT	ERY SWITCH WAS NOT DAMAGED, NOR WAS THE RELAY. (TC NR 20070202006)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007051600135	20070516	00135	NM  	2007	5	16	CA070202007      	1	20070201	G	7500	311269001	ADAPTER         			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	P3 BLEED AIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9051 	9051 				PCE123291			(CAN) DURING ENGINE OIL SERVICING, TECHNICIAN NOTICED HEAT BLANKET WAS DAMAGED ON HP DUCT, BLANKET WAS REMOVED AND CRACK	 WAS FOUND ON DUCT. (TC NR 20070202007)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007080800136	20070808	00136	EU  	2007	8	8	CA070202008      	1	20070130	G	3251	NB046547R	COLLAR          			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NLG STEERING	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) NOSE LANDING GEAR STEERING COLLAR, BROKE IN TWO PIECES DURING GROUND HANDLING. COLLAR CRACKED AFT GREASE FITTING H	OLE ANF FWD RT RELEASE DOG SLOT. (TC NR 20070202008)					1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
2007051400079	20070514	00079	NE  	2007	5	14	CA070202009      	2	20070114	G	7313	311992001	FUEL NOZZLE     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE FUEL NOZZLE CLEANING AND FLOW TEST IT WAS NOTICED THAT ONE FUEL NOZZLE SHEATH WAS CRACKED FROM THE 	AIR BLEED SLOT AT A 45 DEGREE ANGLE TOWARDS THE NOZZLE HOLE. THE SHEATH HAD 400 HOURS TIME IN SERVICE SINCE LAST INSPECT	ION. (TC NR 20070202009)				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007080800137	20070808	00137	CE  	2007	8	8	CA070202010      	1	20070202	G	5540	12310231920	HINGE BRACKET   	CESSNA      		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			*    								(CAN) DURING A 200 HR INSPECTION THE RUDDER WAS REMOVED FROM THE AIRCRAFT TO REPLACE THE RUDDER HINGE BEARINGS. INSPECTI	ON OF THE RUDDER HINGE PIONT BRACKETS FOUND THE UPPER BRACKET P/N 1231023-19 OF THE LOWER HINGE POINT WORN COMPLETLY THR	OUGH BY THE BEARING, AND UPPER BRACKET P/N 1231023-20 HAD GROVES WORN INTO IT BY THE BEARING. THE BRACKETS WERE REPLACED	 WITH NEW PARTS AND THE RUDDER WAS REINSTALLED ON THE AIRCRAFT. (TC NR 20070202010)			1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
2007080800138	20070808	00138	EU  	2007	8	8	CA070202011      	1	20070201	G	3222	5322012165	BARREL NUT      	PILATS      	532201203   	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5232 			IL192					(CAN) PILOT REPORTED THAT ON OCCASION DURING EXTENSION OF LANDING GEAR THAT A LOUD CLUNK WAS HEARD IN NOSE GEAR AREA.DUR	ING A TEARDOWN OF NOSE LANDING GEAR TO REPLACE INTERNAL SEALS ,IT WAS NOTED THAT ON THE INNER GROOVE OF BARREL NUT ,THAT	 SUPPORTS A PHENOLIC GUIDE RING THAT CORROSION WAS OCCURING IN THE ALUMINIUM BARRLE NUT.THIS CORROSION PUT SO MUCH PRESS	URE ON BACKSIDE OF GUIDE RING THAT THE RING WAS CLAMPING TO OLEO STRUT NOT ALLOWING THE STRUT TO FULLY EXTEND PRIOR TO R	ETRACTION OF GEAR. WHEN GEAR WAS LOWERED IN COLD FLIGHT CONDITIONS THE NOSE FORK WOULD CONTACT GEAR RETRACT MECHANISM ON	 EXITING GEAR WELL CAUSING CLUNK.  REMOVAL AND TREATMENT OF CORROSION, CLEANING OF GUIDE RING ALLOWED FREE MOVEMENT OF O	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061300154	20070613	00154	NM  	2007	6	13	CA070202012      	1	20070131	G	2410		BEARING         	LUCAS       		DHAV  	DHC5  	DHC5A       	2803018	NM  										DC GENERATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1850 	102  		1093					(CAN) AIRCRAFT WAS RETURNING TO BASE WHEN THE NR 1 GENERATOR FAILED. FLIGHT WAS CONTINUED WITHOUT FURTHER PROBLEMS. WHEN	 MAINTENANCE REMOVED THE GENERATOR FOR REPLACEMENT THE QUILL SHAFT WAS FOUND SHEARED AND THE FORWARD BEARING ON THE GENE	RATOR SUFFERED A CATASTROPHIC FAILURE AND WAS COMPLETELY DESTROYED. THE GENERATOR HAD JUST BEEN INSTALLED 102 HOURS PREV	IOUSLY FRESH FROM OVERHAUL FACILITY. ANOTHER GENERATOR WAS INSTALLED AND CHECKED SERVICEABLE. (TC  20070202012)			2	H	7	2 	4T			RT	        					 
2007051400081	20070514	00081	EA  	2007	5	14	CA070202013      	1	20070202	G	2913	65WE01042	PUMP            			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	HYDRAULIC SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				763  							(CAN) PUMP INSIDES COUPLING SPLINES BADLY WORN, OUT OF LIMITS.  (TC NR 20070202013)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007051400082	20070514	00082	NM  	2007	5	14	CA070202014      	1	20070118	G	5610	NP15790114	WINDSHIELD      			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			11448								(CAN) DURING FLIGHT, SMOKE AND FLAMES STARTING COMING FROM THE TOP OF FO`S WINDSCREEN.  SECONDS LATER WINDSCREEN SHOWED 	SEVERAL CRACKS. FOUND TERMINAL END L2 BURNED, REMOVED AND REPLACED TERMINAL END AND F/O`S WINDSHIELD.   (TC NR 200702020	14)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051400083	20070514	00083	CE  	2007	5	14	CA070202015      	1	20070202	G	2612	473275	FIRE DETECTOR   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCE4N	HCE4N3      	NE  	RT NACELLE	MALFUNCTIONED   	W				E	F	A		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		N			FALSE WARNING             			CR	CRUISE         	1			CA			289  								(CAN) DURING A ROUTINE MISSION, THE RT FIRE WARNING ANNUNCIATOR LIGHTS ILLUMINATED. THERE WAS NO VISUAL INDICATION OF FI	RE. THE PILOT`S SECURED THE ENGINE IAW PUBLISHED PROCEDURES, ACTIVATED THE FIRE SUPPRESSION SYSTEM AND RETURNED TO THE B	ASE. MAINTENANCE WAS ABLE TO FAULT THE FIRE DETECTION SYSTEM FWD OF THE RT ENGINE FIREWALL, BUT WERE UNABLE TO PINPOINT 	THE EXACT CAUSE TO EITHER OF THE UPPER FIRE DETECTORS OR THE CONNECTING HARNESS. BOTH DETECTORS AND THE HARNESS WERE REP	LACED.  THE ENGINE WAS INSPECTED FOR DAMAGE FROM THE RELEASE OF FIRE SUPPRESSION AGENT. NO DAMAGE WAS EVIDENT. THE FIRE 	BOTTLE AND SQUIB WERE REPLACED. AIRCRAFT WAS RELEASED INTO SERVICE. (TC NR 20070202015)	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	P10NE	 
2007051400084	20070514	00084	CE  	2007	5	14	CA070202016      	1	20070202	G	2810	509215873	GASKET          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCE4N	HCE4N3      	NE  	RT ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			166  								(CAN) PILOTS NOTICED FUEL (STREAMING) FROM THE RT NACELLE TOP COVER SHORTLY AFTER TAKEOFF. THE AIRCRAFT RETURNED TO BASE	 WITHOUT INCIDENT. THIS HAPPENED (3) TIMES BEFORE THE PROBLEM WAS CORRECTED. 1ST NOTICE, AFT 86.9 HRS. MAINTENANCE ATTRI	BUTED THE EXCESS FUEL FOUND UNDER THE NACELLE COVER TO A PROBABLE FAULTY FUEL VENT CHECK VALVE ATTACHED TO THE FUEL FILL	ER NECK IN THIS AREA. THIS AREA OF THE AIRCRAFT WAS REINSPECTED DURING SCHEDULED MAINTENANCE AND MINIMAL FUEL WAS NOTICE	D.  2ND NOTICE - AFT 157.6 HRS. MAINTENANCE CHECKED THE AREA, PLUGGED THE VENT LINES AND FILLED THE FUEL CELL COMPLETELY	. NO FAULTS WERE NOTED, SO ANOTHER CHECK VALVE WAS INSTALLED. 3RD NOTICE -- AFT 165.9 HRS. MAINTENANCE REMOVED THE RT NA	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	P10NE	 
2007051400086	20070514	00086	CE  	2007	5	14	CA070202017      	1	20070201	G	2497		CONNECTOR       			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	POWER JUNCTION	CORRODED        	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA			3758 								(CAN) DURING A PREFLIGHT INSPECTION WHEN THE FLAPS WERE SELECTED TO LOWER A COMPLETE POWER FAILURE RESULTED. UPON INSPEC	TION BY THE AMO THE POWER JUNCTION BOX PLUG WAS FOUND CORRODED RESULTING IN PINS BREAKING WHEN PLUG WAS PULLED APART FOR	 INSPECTION. THIS PLUG FAILURE RESULTED IN A POOR CONTINUITY FROM THE MASTER SOLENOID AND THE MASTER SWITCH RESULTING IN	 A 12+ VOLTAGE LOSS AND THE HOMINOID FAILING TO ENGAGE. (TC NR 20070202017)			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2007051400088	20070514	00088	EA  	2007	5	14	CA070202018      	1	20070201	G	3246	50105711	WHEEL           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  			            		MLG	DAMAGED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			6836 								(CAN) DURING ROTATION THE A/C PULLED TO THE LT ON CLIMB OUT , ASSOCIATED WITH SEVERE VIBRATION. THE FLIGHT CREW DECIDED 	TO DIVERT THE A/C. UPON LANDING THE ROB TIRE DEFLATED.  UPON INVESTIGATION, THE FOLLOWING WAS FOUND . THE INNER RT MAIN 	WHEEL CORD WAS DAMAGED AND DEFLATED. ( FROM ORIGINAL REPORT ON T/O. BOTH MAIN WHEEL`S WERE REPLACED . THE OUTER RT MAIN 	WHEEL WAS DAMAGED ON LANDING.  THE RT INNER FLAP WAS DAMAGED BY THE TIRE SEPARATION NR REPLACED . THE AFT FUSELAGE BODY 	FAIRING WAS SLIGHTLY DAMAGED AND REPAIRED UNDER REO 601R-53-82-267( 500 FT/HRS )  (TC NR 20070202018)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400090	20070514	00090	EA  	2007	5	14	CA070202019      	1	20070131	G	5610	601R3303031	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			8520 								(CAN) CREW NOTED ON DESCENT, CAPT SIDE WINDOW CRACKED HOWEVER CABIN PRESS REMAINED NORMAL AND A.C LANDED SAFELY.  C/A--	-REMOVED AND REPLACED CAPT SIDE WINDOW IAW CRJ AMM 56-10-05 AND OPS CK GOOD   MX REPORT CAPT SIDE WINDOW SHATTERED (TC N	R 20070202019)				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007051400100	20070514	00100	EU  	2007	5	14	CA070204001      	1	20070201	G	5320		CHANNEL         			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN UNSCHEDULED MAINTENANCE PROCEDURE OF THE VIBRATION DAMPER ASSEMBLIES UNDER THE CABIN FLOOR, IT WAS FOUND	 THROUGH THE USE OF A BOROSCOPE THAT THE IB CHANNELS OF THE LATERAL SUPPORT STRUCTURE WERE CRACKED AT THE UPPER ENDS.  S	UBSEQUENT INSPECTION OF ALL OUR AIRCRAFT REVEALED SIMILAR DISCREPANCIES. (TC NR 20070204001)				1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2007051400101	20070514	00101	EU  	2007	5	14	CA070205001      	1	20070202	G	6220	704A33341003	SPRING          			SNIAS 	350   	AS350*      	       	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ANTI VIBRATION	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11359	1460 							(CAN) WE ARE DOING A 12 YEAR INSPECTION ON AIRCRAFT, AS WELL AS SEND IT OUT FOR PAINT. THE MAIN ROTOR ANTI-VIBRATOR WAS 	REMOVED FOR CHECK AND MODIFICATION. WHEN SPRINGS WERE REMOVED, ONE WAS FOUND TO BE BROKEN 40 MM FROM OB END. THIS AREA I	S HIDDEN BEHIND SIDE COVERS. (TC NR 20070205001)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007051400103	20070514	00103		2007	5	14	CA070205002      	4	20070203	G	3418	0861HB	VANE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					AOA	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			1428 	1428 							(CAN) DURING CLIMB OUT STALL FAIL CAUTION MESSAGE ILLUMINATED. CREW UNABLE TO RESET DURING FLIGHT. CREW ELECTED TO LAND 	AT ENROUTE MAINTENANCE BASE. MAINTENANCE REPLACED RT AOA VANE, FUNCTION CHECKED AND AIRCRAFT RETURNED TO SERVICE (TC NR 	20070205002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400105	20070514	00105	EA  	2007	5	14	CA070205003      	1	20070203	G	2752		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAP	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, CREW SELECTED FLAP 8 AND RECEIVED A (FLAP FAIL) MESSAGE. FLAP FAILED AT 0. CREW ADVISED ATC AND DECLA	RED EMERGENCY. LANDING WAS UNEVENTFUL. (TC NR 20070205003)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051600136	20070516	00136	NM  	2007	5	16	CA070205004      	1	20070121	G	3231	83232013003	BELLCRANK       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG DOOR	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3000 								(CAN) AN OPERATOR MADE AIR TURN BACK DUE TO NOSE GEAR DOOR MALFUNCTION. THE NLG DOORS WONT CLOSE WHEN SELECTED. THE AMB	ER NOSE GEAR DOOR LIGHT SHOWED ON LANDING GEAR CONTROL PANEL. MAINTENANCE FOUND THE NOSE GEAR BELLCRANK BROKEN AT ONE OF	 THE LUGS. (TC NR 20070205004)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051400107	20070514	00107	CE  	2007	5	14	CA070205005      	1	20070205	G	2560	497900312	BUCKLE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ROTARY SEAT BELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) REF FAA SPECIAL AIRWORTHINESS INFORMATION BULLETIN NM-06-29 AND MFG CAMPAIGN NOTICE 010-25-10-011 REV 1 FIXED WING	 AIRCRAFT EQUIPPED WITH ROTARY CREW SEAT BELT BUCKLES.  WHEN THE CONTROL COLUMN IS PULLED FULLY AFT THE SEAT BELT BUCKLE	 CAN BE RELEASED BY ROTATING THE CONTROL WHEEL IN BOTH THE PILOT AND CO-PILOT POSITIONS. (TC NR 20070205005)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007051400110	20070514	00110	NM  	2007	5	14	CA070205007      	1	20070130	G	2741	651948218	GEARBOX         			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					HORIZONTAL STAB	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, CREW EXPERIENCED STAB TRIM FAILURE.  A/C RETURNED TO AIRPORT WITHOUT INCIDENT.  MAINTENANCE CREWS	 FOUND THE STAB TRIM GEARBOX TO BE QUITE STIFF TO OPERATE AND REPLACED IT.  A/C RETURNED TO SERVICE.  THE STAB TRIM GEAR	BOX AND JACKSCREW WERE INSPECTED AND LUBED ON A 2A CHECK NOV 19/2006. (TC NR 20070205007)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051400112	20070514	00112	CE  	2007	5	14	CA070206002      	1	20070205	G	3260		LANDING GEAR    			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	MAINS	UNKNOWN         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LANDING GEAR (IN TRANSIT) LIGHT STAYED ON AFTER GEAR UP SELECTION AFTER TAKEOFF. GEAR DOWN SELECTED AND GEAR WENT 	DOWN AND LOCKED NORMALLY (3 GREEN LIGHTS) FOR LANDING BACK TO DEPARTURE AIRPORT.  AIRCRAFT JACKED, RETRACTIONS DONE, LAN	DING GEARS INSPECTED, CLEANED AND LUBED, NO DEFAULT FOUND, SYSTEM FOUND SERVICEABLE. (TC NR 20070206002)				1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007051400115	20070514	00115		2007	5	14	CA070206003      	4	20070204	G	8300		COVER           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					AGB	DISLODGED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) APPROX 10 MINS INTO THEIR DESCENT, THE NR 1 OIL PRESSURE WARNING LIGHT ILLUMINATED. THE NR 1 OIL PRESSURE READ 0. 	 THE CREW REFERENCED THEIR CHECKLIST AND SHUTDOWN THE ENGINE. THE CREW ANNOUNCED TO THE PAX THAT DUE TO LOW OIL PRESSURE	 THEY WERE GOING TO SHUT DOWN AN ENGINE. MAINTENANCE CHECKED AND CLEANED TRANSDUCER CONNECTOR PLUGS, OIL TANK AND ASSOCI	ATED PLUMBING. THE ONLY ANOMALY NOTED WAS THE PLUG ON THE ACCESSORY GEAR BOX WAS NOT PROPERLY SECURED. THE CIRCLIP WAS O	FF AND THE PLUG DISLODGED SOMEWHAT. THERE WAS NO EVIDENCE OF MASSIVE OIL LOSS, BUT SUSPECT WITH CAP OFF ENGINE WAS PROBA	BLY SUCKING AIR, AND NOT PRESSURIZING ACCESSORY GEAR BOX PROPERLY. CIRCLIP SECURED. IDLE AND HIGH POWER RUNS COMPLETED S	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400117	20070514	00117	CE  	2007	5	14	CA070207001      	1	20070203	G	3230	MC815A51	RELAY           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				484  							(CAN) LANDING GEAR IN TRANSIT LIGHT STAYED ON AFTER GEAR WAS SELECTED UP AND AN ALTERNATE GEAR EXTENSION WAS DONE AND TH	E A/C RETURNED TO BASE. THE LANDING GEAR CONTROL RELAY BOX WAS REPLACED AND LANDING GEAR SYSTEM FUNCTION CHECKED SERVICE	ABLE. (TC NR 20070207001)				1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007051400119	20070514	00119	EA  	2007	5	14	CA070207002      	1	20070131	G	5210	600315351001	STRIKER         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					DOOR SEAL	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING A TYPE III REPAIR (MFG REO 601R-53-22-033) DUE TO A CRACK FOUND ON THE OUTER FLANGE OF THE PASSENGER DOOR F	WD SEAL STRIKER, THE FORWARD SEAL STRIKER FLANGE WAS FOUND CRACKED IN THE RADIUS  (OVER 3INCHES IN LENGTH) UNDER AN EXIS	TING REPAIR (REPAIR TYPE I, REO 601R-53-22-033). AFTER A VISUAL CHECK, THE AFT PASSENGER DOOR SEAL STRIKER (ALSO PREVIOU	SLY REPAIRED TYPE I) WAS FOUND CRACKED IN THE RADIUS. (TC NR 20070207002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400121	20070514	00121	CE  	2007	5	14	CA070207003      	1	20070206	G	2560	1101983	BUCKLE          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CREW SEATBELTS	DAMAGED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) CAMPAIGN NOTICE 010-25-10-011 / FAA SAIB NM-06-29.  CREW SEAT BELT ROTARY LATCH IS CONTACED BY THE CONTROL YOKE AN	D THE POSSIBLITY EXISTS TO RELEASE THE BELT WITH ROTATION OF THE CONTROL YOKE WHEN FUNCTIONAL TEST WAS CARRIED OUT IAW S	AIB. (TC NR 20070207003)				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2007051400131	20070514	00131	CE  	2007	5	14	CA070207007      	1	20070206	G	3310		LIGHT           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	CABIN	INOPERATIVE     	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA			8862 	8862 							(CAN) WHILE ON FINAL APPROACH, SMOKE WAS OBSERVED IN COCKPIT COMING FROM THE LOWER LT C/B PANEL. SIDE LIGHT C/B POPPED A	ND SMOKE STOPPED. LANDING COMPLETED WITHOUT FURTHER INCIDENT.  MAINTENANCE WAS CONTACTED AND IN CONVERSATION WITH FLIGHT	 CREW SMOKE PROBLEM WAS ISOLATED TO EDGE OF PANEL LIGHTING, C/B WAS PULLED AND POWER FUNCTION TEST REVEALED NO FURTHER S	MOKE ISSUES. RETURN FLIGHT WITH ESSENTIAL CREW WAS CARRIED OUT. MAINTENANCE STAFF CONFIRMED PROBLEM AND SHORTED PANEL WA	S REPAIRED. (TC NR 20070207007)		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007051400133	20070514	00133	WP  	2007	5	14	CA070207008      	1	20070202	G	6710	A9182	BUNGEE          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FLT CONTROLS	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			87   								(CAN) UPON INSPECTION, BUNGEE FOUND HANGING DOWN AND DISCONNECTED FROM THE FLIGHT CONTROL. THERE WERE NO FLIGHT PERFORMA	NCE ISSUES REPORTED. MINOR SCRAPES FOUND IN CONTROL TUBE PAINT. CORDS WERE CHECKED FOR DAMAGE AND RECONNECTED. (TC NR 20	070207008)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007051400136	20070514	00136	EA  	2007	5	14	CA070208001      	1	20070207	G	2750	7805013	CONTROL LEVER   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAP CONTROL	DAMAGED         	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) AFTER LANDING WITH FLAPS SELECTED TO 45 DEGREES, THE CREW SELECTED FLAPS FROM 45 TO 20 DEGREES AND THE FLAPS DID N	OT MOVE. CAPTAIN PUT THE FLAPS BACK TO 45 DEGREES. FECU (FLAPS ELECTRONIC CONTROL UNIT) CODES RETRIEVED BY MAINTENANCE P	OINTED OUT TO THE FLAP CONTROL LEVER WHICH WAS REPLACED. (TC NR 20070208001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051400139	20070514	00139	CE  	2007	5	14	CA070208002      	1	20070128	G	5610	50420066137	WINDOW          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	COCKPIT	DEPARTED        	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			10639								(CAN) AFTER TAKEOFF AND CLIMB TO APPROXIMATELY 10,000 FEET, THE LT.   (TC NR 20070208002)						1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007051400157	20070514	00157	SO  	2007	5	14	CA070208003      	1	20070117	G	7603	30205002	THROTTLE CABLE  			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  		FAILED          	W				E				ENGINE SHUTDOWN         				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		DE	DESCENT        	1			CA											(CAN) DURING DESCENT THE RT THROTTLE DID NOT RESPOND. THE ENGINE WAS SHUTDOWN AND PROPELLER FEATHERED. UPON RETURN TO TH	E HANGAR, CABLE 30205-002 WAS REPLACED AND DUAL INSPECTION CARRIED OUT. (TC NR 20070208003)					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2007051400160	20070514	00160	CE  	2007	5	14	CA070208004      	1	20070207	G	2497	S21351	WIRE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CONNECTOR	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION IT WAS DISCOVERED THAT ONE WIRE GOING TO THE OVER VOLTAGE WARNING LIGHT WAS FOUND BURN	ED.  CAUSE OF THE BURNED WIRE WAS DUE TO FAILURE OF A BUTT SPLICE IN THE WIRE WHICH HAD EXPOSED THE BARE WIRE CAUSING IT	 TO SHORT OUT. THE BURNED SECTION OF WIRE WAS REPLACED. THE AIRCRAFT WAS GROUND CHECKED SERVICEABLE AND RETURNED TO SERV	ICE. (TC NR 20070208004)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007051400164	20070514	00164	SW  	2007	5	14	CA070208005      	1	20070205	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				2415 							(CAN) DURING TAXI WITH THE WINDSHEILD HEAT SELECTED ON THE RT COCKPIT HEATED WINDSHEILD CRACKED. THE FLIGHTCREW RETURNED	 TO THE TERMINAL AND THE AIRCRAFT WINDOW HAS BEEN REPALCED BY MAINTENANCE. NO CAUSE OF THE CRACKED GLASS COULD BE DETERM	INED. THIS IS THE THIRD FAILURE OF A HEATED WINDSHEID THIS COMPANY HAS INCURRED SINCE JAN 1, 2007. 12 WERE REPORTED IN 2	006. OTHER AIRCRAFT OPERATORS OF THIS TYPE OF AIRCRAFT HAVE BEEN CONTACTED AND ARE INCURRING SIMILAR FAILURE RATES. (TC 	NR 20070208005)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2007051400161	20070514	00161	CE  	2007	5	14	CA070209001      	1	20070207	G	2560	110198301	BUCKLE          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SEAT BELT ASSY	DAMAGED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL 	COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSI	BILITY EXISTS THAT THE SEAT BELT ROTARY BUCKLE COULD BE INADVERTENTLY RELEASED DURING EXTREME FLIGHT CONTROL MOVEMENTS. 	THIS CONDITION WAS VERIFIED WHILE PERFORMING THE PROCEDURE AS DESCIBED IN FAA SAIB NM-06-29. A GUARDED BUCKLE WOULD NEGA	TE THE POSSIBILITY OF ACCIDENTAL RELEASE (TC NR 20070209001)		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2007051400158	20070514	00158	CE  	2007	5	14	CA070209002      	1	20070207	G	2560	110193201	BUCKLE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT BELT	MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL 	COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSI	BILITY EXISTS THAT THE SEAT BELT ROTARY BUCKLE COULD BE INADVERTENTLY RELEASED DURING EXTREME FLIGHT CONTROL MOVEMENTS. 	THIS CONDITION WAS VERIFIED WHILE PERFORMING THE PROCEDURE AS DESCIBED IN FAA SAIB NM-06-29. A GUARDED BUCKLE WOULD NEGA	TE THE POSSIBILITY OF ACCIDENTAL RELEASE (TC NR 20070209002)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007051400159	20070514	00159	CE  	2007	5	14	CA070209003      	1	20070207	G	2560	110193201	BUCKLE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CREW SEATS	INTERFERENCE    	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL 	COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSI	BILITY EXISTS THAT THE SEAT BELT ROTARY BUCKLE COULD BE INADVERTENTLY RELEASED DURING EXTREME FLIGHT CONTROL MOVEMENTS. 	THIS CONDITION WAS VERIFIED WHILE PERFORMING THE PROCEDURE AS DESCIBED IN FAA SAIB NM-06-29. A GUARDED BUCKLE WOULD NEGA	TE THE POSSIBILITY OF ACCIDENTAL RELEASE.  (TC NR 20070209003)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007051400162	20070514	00162	GL  	2007	5	14	CA070209004      	3	20070203	G	6110	HCE4A3D	PROPELLER       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			3188 	3188 					HJ1517		(CAN) DURING FLIGHT OIL WAS NOTICED ON THE WINDSCREEN WHILE ON ROUTE. UPON INSPECTION AFTER LANDING, MAINTENANCE FOUND E	XCESSIVE OIL ON ENGINE COWLING. PROP WAS REMOVED AND SENT FOR REPAIRS. REPAIR SHOP CHANGED ALL THE INTERNAL SEALS AND RE	TURNED THE PROP. REPAIRED PROP WAS RE-INSTALLED. AFTER 6 HRS IN OPERATION FLUID WAS NOTICED LEAKING FROM PROP AGAIN ALTH	OUGH NOT TO THE DEGREE THAT OCCURRED ON THE FIRST OCCASION. AFTER CLEANING AND GROUND RUNS IT WAS DETERMINED THAT THE PR	OP WAS LEAKING OIL AGAIN.  PROP WAS REMOVED AND SENT FOR REPAIR AGAIN. REPAIR SHOP FINDINGS HAVE YET TO BE DETERMINED. (	TC NR 20070209004)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007051400163	20070514	00163	GL  	2007	5	14	CA070209005      	1	20070209	G	2720	C2TR445	BELLCRANK       			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23428								(CAN) ON REMOVAL OF RUDDER FOR BEARING REPLACEMENT CORROSION WAS PRESENT ON THE OB ATTACH POINTS OF THE RUDDER BELLCRANK	 NR C2TR445 (PICTURE ATTACHED) CORROSION WAS NOT EVIDENT BEFORE THE REMOVAL OF THE RUDDER AS THE DAMAGED AREA WAS COVERE	D BY THE RUDDER CONNECTING RODS NR C2UT233. THE AIRCRAFT NOTED ABOVE HAS BEEN OPERATED EXTENSIVELY FROM SALT WATER. (TC 	NR 20070209005)			1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007051400173	20070514	00173	NE  	2007	5	14	CA070209008      	2	20070111	G	7200		ENGINE          			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  						OVERSPEED       	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								BF0116			(CAN) THE ENGINE WENT TO AN OVERSPEED CONDITION ON TAKE-OFF AND THE TAKE-OFF WAS ABORTED.  MFG WILL INVESTIGATE THE INCI	DENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209008)					1	G	7	1 	3U	3	U		R00001RC	E42NE				 
2007051500189	20070515	00189	NE  	2007	5	15	CA070209009      	2	20070112	G	7532	31J285704	MOTOR           			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					BLEED VALVE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY VIBRATION, AN EEC REVERSION AND A LACK OF THROTTLE RES	PONSE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A UNSERVICEABLE BLEED VALVE TORQUE MOTOR. (TC	 NR 20070209009)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007051500190	20070515	00190	EA  	2007	5	15	CA070209010      	2	20070103	G	7321	3027791	TUBE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FCU P3	FRACTURED       	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			5581 								(CAN) ON CLIMB, ENGINE POWER REDUCED TO IDLE UNCOMMANDED.  THE ENGINE WAS SHUTDOWN IN FLIGHT. INSPECTION REVEALED A FRAC	TURED FCU P3 DELIVERY TUBE. (TC NR 20070209010)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007051500191	20070515	00191	NE  	2007	5	15	CA070209011      	2	20070118	G	7310	3026779	LINE            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					FUEL SYSTEM	FRACTURED       	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION FOLLOWING A REPORT OF FUEL ODOR IN THE CABIN, THE ENGINE HIGH PRESSURE FUEL DELIVERY TUBE WAS FOUND 	CRACKED. (TC NR 20070209011)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007051500192	20070515	00192	NE  	2007	5	15	CA070209012      	2	20070116	G	7260		DRIVE GEAR      			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PW120 	PW127       	 	NE  					GEARBOX	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE FLAMED OUT ON DESCENT.  SUBSQUENT INSPECTION REVEALED DAMAGE TO THE ANGLE DRIVE GEARBOX GEARING. (TC NR	 20070209012)					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007051500193	20070515	00193	NE  	2007	5	15	CA070209013      	2	20070118	G	7260		GEAR            			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					GEARBOX	DAMAGED         	W				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA											(CAN) THE ENGINE FLAMED OUT IN CRUISE.  SUBSEQUENT INVESTIGATION REVEALED DAMAGED TOWERSHAFT DRIVE BEVEL GEARS. (TC NR 2	0070209013)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007051500194	20070515	00194	NE  	2007	5	15	CA070209014      	2	20070119	G	7321	8237007	HMU             			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA						F51037					(CAN) THE ENGINE FLAMED OUT IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED AN UNSERVICEABLE HYDROMECHANICAL FCU. (TC NR 2007	0209014)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007051500195	20070515	00195	NE  	2007	5	15	CA070209015      	2	20070121	G	7261		TUBE            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       	 	NE  					ENGINE OIL	FRACTURED       	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE ENGINE OIL PRESSURE REDUCED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALE	D A FRACTURED NR 6 AND 7 BEARING OIL TRANSFER TUBE. (TC NR 20070209015)					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2007051500196	20070515	00196	NE  	2007	5	15	CA070209016      	2	20070123	G	7200		ENGINE          			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  						FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								116011			(CAN) DURING CRUISE THE ENGINE CHIP DETECTOR AND LOW OIL PRESSURE WARNINGS ACTIVATED AND THE ENGINE FLAMED OUT IN FLIGHT	.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAU	SE ONCE DETERMINED. (TC NR 20070209016)				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE				 
2007051500198	20070515	00198	CE  	2007	5	15	CA070209019      	1	20070131	G	5711	5016000355	SPAR            			BEECH 	100   	100BEECH    	1152916	CE  										RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17018								(CAN) RT IB FLAP P/N 50-160003-97 REMOVED FOR HINGE BRACKET REPLACEMENT.  UPON TEARDOWN OF FLAP FOR HINGE BRACKET REMOVA	L, AN 8 INCH CRACK WAS NOTED ON THE SPAR UPPER RADIUS.  THE CRACK EXTENDED 4 INCHES EITHER SIDE OF THE FLAP ACTUATOR BRA	CKET ATTACH AREA. PROBABLY CRACKED DUE TO CYCLING OF THE FLAP OVER TIME AND THE LOCALIZED STRESSES IN THAT AREA OF THE F	LAP, AROUND THE ACTUATOR BRACKET. CRACK IN SPAR CANNOT BE SEEN WITHOUT DISASSEMBLY OF FLAP. (TC NR 20070209019)			1	L	7	2 	3T				A14CE   					 
2007051500199	20070515	00199	SO  	2007	5	15	CA070209020      	1	20070207	G	2424	B002861	VOLT REGULATOR  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ALTERNATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT, THE LT ALTERNATOR FAIL LIGHT CAME ON, AIRCRAFT RETURNED TO BASE FOR REPAIRS. VOLTAGE REGULATORS 	REPLACED WITH NEW, RT ALTERNATOR P/N ALU8521 REPLACED WITH OVERHAULED UNIT. GROUND RUNS CARRIED OUT TO CHECK FUNCTION, C	HECKED OK.  TEST FLIGHT CARRIED OUT AND SYSTEM CHECKED NORMAL. (TC NR 20070209020)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007051500200	20070515	00200	NE  	2007	5	15	CA070209021      	2	20070207	G	7250		BLADE           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	TURBINE DISK	SEPARATED       	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			12458	12458				785590			(CAN) AFTER REACHING CRUISING ALTITUDE OF 23000 FT THE LT ENGINE SURGED AND THE LOW OIL PRESSURE LIGHT ILLUMINATED. THE 	ENGINE WAS SHUTDOWN AND THE FLIGHT CONTINUED TO WHERE AN UNEVENTFULL LANDING WAS MADE. THE ENGINE STRIP SHOWED THAT THE 	COMPRESSOR STAGE ONE TURBINE DISK HAD LOST A BLADE. THE REMAINING BLADES HAD SUFFERED EXTENSIVE DAMAGE, AS TOO HAD THE S	TATOR ASSY. THE ENGINE AND COMPONENTS HAVE BEEN RETURNED TO GE (ENGINE OEM) FOR INVESTIGATION. (TC NR 20070209021)			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2007051500201	20070515	00201	EU  	2007	5	15	CA070209022      	1	20070209	G	2750		FLAP SYSTEM     			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  						FROZEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			261  								(CAN) THE COLD WEATHER HAS AFFECTED SEVERAL AIRCRAFT IN THE FLEET OF 9. IN -25 C OR COLDER TEMPERATURES, THE CIRCUIT BRE	AKERS POP AFTER LANDING WHEN THE FLAPS ARE SELECTED (TC NR 20070209022)					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2007051600137	20070516	00137	EA  	2007	5	16	CA070209023      	1	20070207	G	5610	6003303026	WINDSHIELD      			CNDAIR	CL601 	CL6013A     	8070802	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				Z			SIGNIFICANT FAILURE REPORT			CR	CRUISE         	1			CA			1167 								(CAN) RT WINDSHIELD OUTER LAYER CRACKED DURING FLIGHT, A SINGLE CRACK LOCATED IN THE CENTER OF THE WINDSHIELD AND IS VER	TICAL FROM TOP TO BOTTOM. AIRCRAFT PRESSURIZATION WAS NOT AFFECTED AND AIRCRAFT RETURNED TO BASE. (TC NR  20070209023)					2	L	7	2 	4F			RT	A21EA   					 
2007051600138	20070516	00138	EU  	2007	5	16	CA070212001      	1	20070201	G	2711	978731813	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AILERON TRIM TAB	INTERMITTENT    	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AILERON TRIM INTERMITTENT. TRIM TAB ACTUATOR REPLACED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20070212001)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007051600139	20070516	00139	EU  	2007	5	16	CA070212002      	1	20070208	G	7600	941941141	CONDITION LEVER 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6263 								(CAN) DURING INSPECTION, IT WAS FOUND THAT THE CONDITION LEVER WAS EXTREMELY HARD TO MOVE.  THE CONDITION LEVER CABLE WA	S REPLACED. (TC NR 20070212002)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007051600140	20070516	00140	EU  	2007	5	16	CA070212003      	1	20070207	G	3250		STEERING SYS    			BAG   	JETSTM	JETSTM3212  	1500217	EU  										NLG	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				4808 							(CAN) INTERNAL STEERING MECHANISM SLOPPY. A/C HARD TO CONTROL DURING TAXI. NOSE LANDING GEAR REMOVED AND REPLACED WITH O	VERHAULED UNIT, GROUND TEST CARRIED OUT AND FOUND SERVICEABLE. DEFECTIVE LANDING GEAR HAS NOT BEEN SHIPPED FOR OVERHAUL 	AT THIS TIME. (TC NR 20070212003)				2	L	7	2 	4T			RT	BA15CAA 					 
2007051600141	20070516	00141	GL  	2007	5	16	CA070212004      	1	20070208	G	5340	C2FS5487A	FITTING         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT SCHEDULED INSPECTION THE PORK CHOP FITTINGS WERE FOUND CORRODED. THESE C2FS5487A LT AND RT WERE BOTH REPLACED. 	DEPTH OF CORROSION WAS APPROX 20 PERCENT OF OVERALL PART THICKNESS. THE MANUFACTURE WAS CONTACTED AND REPORTED SEVERAL S	ERVICE DIFFICULTY REPORTS HAVE BEEN FILED BY OEM. (TC NR 20070212004)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2007051600142	20070516	00142	WP  	2007	5	16	CA070212005      	2	20070207	G	7200	TPE33110UG	ENGINE          			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  						UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17244	4760 							(CAN) DURING PRE FLIGHT INSPECTION FLIGHT CREW HEARD ABNORMAL NOISE COMING FROM ENGINE WHILE THEY TURNED THE PROPELLER. 	MAINTENANCE WAS NOTIFIED AND ENGINE WAS INSPECTED, SUSPECT REAR BEARING FAILURE, OIL SYSTEM INSPECTED AND FOUND TO HAVE 	NO METAL CONTAMINATION. ENGINE REMOVED AND HAS NOT YET BEEN SENT FOR REPAIR. (TC NR 20070212005)				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE				 
2007051600143	20070516	00143	EU  	2007	5	16	CA070212006      	1	20070211	G	5210		MECHANISM       			EMB   	ERJ190	ERJ190100IGW	3260408	EU  										L2 DOOR	FROZEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1243 								(CAN) F/A ADVISED L2 DOOR FROZEN UNABLE TO OPEN VENT FLAP.  L2 DOOR THAWED OUT IN HANGAR, GVI CARRIED OUT ON DOOR, CHECK	ED SERVICEABLE. NOTE:  SINCE NOV 1 2006, HAVE FOUND 8 OTHER SNAGS RELATED TO E190 FROZEN DOORS.  COULD BE A CONCERN IN T	HE EVENT OF AN EMERGENCY SITUATION. (TC NR 20070212006)				2	L	7	2 	4F			RT	A57NM   					 
2007051600144	20070516	00144	CE  	2007	5	16	CA070212007      	1	20070129	G	2730	1155240465	TORQUE TUBE     			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE TAIL CONE WAS REMOVED FOR OTHER SCHEDULED MAINTENANCE.  IT WAS NOTICED THAT THE ELEVATOR BELLCRANK TORQUE TUBE	 WAS CRACKED. THE CRACK STARTED AT THE HORN ATTACH TAPER PIN AND SPIRALED AROUND THE TORQUE TUBE APPROX 270 DEGREES. THE	 ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE (TC 20070212007)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007051600145	20070516	00145	EU  	2007	5	16	CA070212008      	1	20070127	G	3800		LINE            			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					WATER SYS	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE ENROUTE TO DESTINATION CREW REPORTED TO MAINTENANCE THAT AILERON CONTROL COLUMN FREEZES AND TAKES EXCESSIVE 	FORCE TO FREE UP, UPON INSPECTION AT DESTINATION MAINTENANCE FOUND AILERON CONTROLS COVERED IN ICE CAUSED BY A BROKEN WA	TER LINE.  A MAINTENANCE INVESTIGATION FOUND THAT A CLAMP HAD COME OFF FROM THE FORWARD WATER SYSTEM DRAIN PLUMBING.  (T	C NR 20070212008)			2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2007051600146	20070516	00146	CE  	2007	5	16	CA070212010      	1	20070201	G	3246		BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	MAIN WHEEL	DESTROYED       	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN THE AIRCRAFT LANDED ALL OF PASSENGERS WERE UNLOADED FOR REFUELING.  THE CAPTAIN OF THE AIRCRAFT WALKED AROUND	 THE RT SIDE OF THE AIRCRAFT TO TALK TO THE FUELER AND NOTICED THAT THE RT MAIN GEAR ONLY HAD ONE MAIN WHEEL ASSEMBLY AT	TACHED.  HE IMMEDIATELY CONTACTED MAINTENANCE AND GROUNDED THE AIRCRAFT. UPON INSPECTION OF THE AXLE STUB IT WAS FOUND T	HAT THE INNER RACES OF THE BEARINGS, NUT AND SAFETY HARDWARE WAS STILL ATTACHED.  THE OTHER 3 WHEEL ASSEMBLIES WERE REMO	VED AND INSPECTED FOR CONDITION AND SECURITY.  ONE OF THE 3 HAD BEEN CHANGED BY US ALREADY AND WAS FINE.  THE LAST TWO W	ERE FOUND TO HAVE GREASE COATED ON THE OUTSIDE OF THE BEARINGS BUT NOT (PACKED) INSIDE.   NOTE:  THE AIRCRAFT IS NEW TO 	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007051600147	20070516	00147	EA  	2007	5	16	CA070213001      	1	20070212	G	2750		FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FLAP FAIL MESSAGE RECEIVED IN-FLIGHT. AIRCRAFT LANDED UNEVENTFUL WITH FLAPS ZERO (FLAPS WOULD NOT MOVE). (TC NR 20	070213001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051600148	20070516	00148	CE  	2007	5	16	CA070213002      	1	20070131	G	2910	991242339	VALVE           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					HYD SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1409 								(CAN) POST INSPECTION RUN REVEALED HYDRAULIC PRESSURE ON ANNUNCIATOR LIGHT DID NOT EXTINGUISH WHEN SYSTEM SHOULD HAVE BE	EN AT REST. HYDAULIC LOADING VALVE FOUND FAILED.  BLEED ORIFICE RECOVERED FROM HYDRAULIC MANIFOLD UNDER RELIEF VALVE (3R	D FROM LOADING VALVE). LOADING VALVE MAY HAVE FALLEN APART DURING EMERGENCY GEAR EXTENSION TEST.  LOADING VALVE REPLACED	. ALL TESTS NORMAL. FAILED VALVE SENT TO MFG FOR ANALYSIS.  (TC NR 20070213002)			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2007051600149	20070516	00149	NM  	2007	5	16	CA070213003      	1	20070206	G	2497	50086003	CONTACT         			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					GENERATOR	BURNED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT ALL 4 CB`S POPPED FOR TANK 2 FUEL BOOST PUMPS, AIRCRAFT RETURNED TO AIRPORT. DETERMINED NR 3 GENE	RATOR VOLTAGE FLUCTUATING, (THE PUMP FAULT WAS ATTRIBUTED TO THE POWER FLUCTUATION WHICH WAS POWERING THE (ESSENTIAL POW	ER) AND THE (SYNC BUSS POWERING THESE PUMPS).  INSPECTION OF NR 3 GENERATOR CB FOUND BURNED CONTACTS. CB REPLACED, CONTA	CTS CLEANED NO FURTHER REPORTS. (TC NR 20070213003)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007051600150	20070516	00150	CE  	2007	5	16	CA070213005      	1	20070213	G	3510	510010951	LINE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	CREW O2 SYS	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FOUND LT SIDE CABIN OXYGEN LINE P/N 5100109-51 CORRODED WHERE IT CROSSES THE OVERHEAD CABIN AIR DUCT P/N CM3212-2 	(WL 103.10) AT FS 160.0. (TC NR 20070213005)					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
2007051600151	20070516	00151		2007	5	16	CA070213006      	4	20070206	G	3444	401020101	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT MLG WOW 1	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			369  								(CAN) ON TAKEOFF CREW GOT (WT ON WHEELS) CAUTION LIGHT MOMENTARILY.  LIGHT CAME ON AGAIN IN FLIGHT, QRH ACTIONED AND RET	URN TO BASE.  PSEU SHOWED THAT RT MLG WOW 1 SENSOR PROXIMITY SHOWED  (UNREASONABLY NEAR). COULD ADJUST OUT SO THAT MILLI	HENERYS WERE IN SPEC BUT THE GAP WAS OUT.  REPLACED SENSOR PROXIMITY. (TC NR 20070213006)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007061300155	20070613	00155	NM  	2007	6	13	CA070213007      	1	20070206	G	3230	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG	FAILED          	W				A				UNSCHED LANDING         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			CA			654  								(CAN) NOSE LANDING GEAR DOORS WOULD NOT CLOSE ON GEAR RETRACTION. GEAR WOULD NOT EXTEND NORMALLY SO CREW DID AN ALTERNAT	E GEAR EXTENSION.  REPLACED VALVE,SOLENOID SEQUENCE AS WE HAD DEALT WITH THIS ISSUE A WEEK EARLIER ON ANOTHER AIRCRAFT (	TC# 20070213007).				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007051600152	20070516	00152	WP  	2007	5	16	CA070213008      	1	20070204	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											(CAN) RT LATERAL SERVO FOUND LEAKING BY ENGINEER DURING DI.  SERVO REMOVED FOR REPAIR AND SERVICABLE UNIT INSTALLED. (TC	 NR 20070213008)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007051600153	20070516	00153	EU  	2007	5	16	CA070213009      	1	20070113	G	6730	704A44831142	SERVO           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			6258 	2996 							(CAN) SERVO FOUND LEAKING BY ENGINEER ON POST FLIGHT INSP.  SERVO REPLACED WITH SERVICABLE UNIT.  SERVO WAS SENT OUT FOR	 REPAIR.  THE SERVO WAS OVERHAULED AND IS BEING SHIPPED BACK TO US FOR INSTALLATION. (TC NR 20070213009)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007051600154	20070516	00154	EA  	2007	5	16	CA070214001      	1	20070214	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	JAMMED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, WHEN THE CREW SELECTED FLAP 8, THE FLAPS DID NOT MOVE AND THEY STAYED AT 0. CREW LANDED FLAPLESS WITH	OUT INCIDENT. NO MORE DETAILS. INFORMATION WILL BE UPDATED AS SOON AS IS AVAILABLE.  (TC NR 20070214001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051600155	20070516	00155	EU  	2007	5	16	CA070214002      	1	20070207	G	7603	55CF8891	CABLE           			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					THROTTLE	FAILED          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			4461 	4461 							(CAN) THROTTLE FROZEN IN THE FULL OPEN POSITION. FUEL FIRE WALL SHUT OFF USED TO CONTAIN ENGINE.  (TC NR 20070214002)						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2007051600156	20070516	00156	SO  	2007	5	16	CA070214004      	2	20070203	G	8530	5A10204	EXHAUST VALVE   			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	CYLINDER HEAD	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			1541 								(CAN) DURING TAKEOFF, AN ENGINE VIBRATION WAS FELT. A PRIORITY LANDING WAS REQUESTED. CYLINDER EXHAUST VALVE NR 3 FOUND 	BROKEN AT THE VALVE HEAD. CYLINDER SA10200, S/N AM1376 INSTALLED. OTHER VALVES INSPECTED AND REPLACED VALVES SA10204 ON 	CYLINDER NR 4 AND NR 2.  (TC NR 20070214004)				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007051600157	20070516	00157	EA  	2007	5	16	CA070214005      	1	20070212	G	3610	3035279	LINE            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	PNEUMATIC SYS	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFTER LANDING THE NR 1 PROP RPM WAS LOWER THAN NORMAL. MAINTENANCE FOUND THAT THE P3 LINE FROM THE P3 FILTER BOWL 	TO THE ENGINE WAS BROKEN PN 3035279. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.   (TC NR 20070214005)					2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2007080800140	20070808	00140	CE  	2007	8	8	CA070215001      	1	20070213	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	LANDING LIGHT	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			2364 								(CAN) LANDING LIGHT SWITCH GAVE OFF ODOR OF SMOKE, WHEN PILOT WENT TO TURN OFF, THE SWITCH WAS HOT AND THE SHUTOFF THE S	WITCH WAS REPLACED WITH A NEW UNIT (TC NR 20070215001)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007051600158	20070516	00158	WP  	2007	5	16	CA070215002      	2	20070213	G	7260		HOUSING         	ALIDSG      		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ACCESSORY DRIVE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						P63269C					(CAN) ACCESSORY DRIVE HOUSING BOTTOM CASE DRAIN THREADED MOUNTING BOSS DISCOVERED BROKEN. ENGINE REMOVED AND LOANER ENGI	NE INSTALLED. (TC NR 20070215002)					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2007051600159	20070516	00159	CE  	2007	5	16	CA070215003      	1	20070215	G	2435		SPLINE          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STARTER GEN	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				624  		19360					(CAN) START ATTEMPTED ON ENGINE. STARTER/GENERATOR ROTATED BUT ENGINE DID NOT. S/G REMOVED AND INSPECTED. S/G SHAFT SPLI	NE NOTED AS EXTREMELY WORN. ENGINE ACCESSORY HOUSING INTERNAL SPLINE CHECKED FOR WEAR WITH WEAR CHECK TOOL. DIMENSIONS W	ITHIN ACCEPTABLE LIMITS. S/G REPLACED WITH NEW UNIT. (TC NR 20070215003)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007080800141	20070808	00141	CE  	2007	8	8	CA070215004      	1	20070210	G	2434	10300B	ALTERNATOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT A LOW VOLTAGE LIGHT INDICATION. PILOT RECYCLED ALTERNATOR, LOW VOLTAGE INDICATION WAS NOT CORRECTED A	ND PILOT RETURNED FOR LANDING (TC NR 20070215004)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007080800142	20070808	00142	CE  	2007	8	8	CA070215007      	1	20070214	G	3221	NAS464P4A10	BOLT            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			7092 								(CAN) AFTER GEAR WERE RETRACTED A VIBRATION IN THE NOSE OF THE AIRCRAFT WAS NOTICED.  THE AIRCRAFT RETURNED TO BASE WITH	 NO INCIDENT. AN INSPECTION WAS CONDUCTED AND THE NOSE GEAR DOOR TORQUE TUBE ATTACH BOLT WAS FOUND BROKEN.  THIS BOLT AT	TACHES THE TORQUE TUBE TO THE WHEEL WELL STRUCTURE AND THE TORQUE TUBE ROTATES AROUND THIS BOLT. THE TORQUE TUBE WAS INS	PECTED AND REINSTALLED. (TC NR 20070215007)			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007051600160	20070516	00160	SW  	2007	5	16	CA070216001      	1	20070214	G	2820	206040525101	HOUSING         			BELL  	206   	206L4       	1182110	SW  										FUEL  SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BYPASS INDICATOR BORE MISSING ONE 0.062 INCH DIA OIL PASSAGE AT BOTTOM OF BORE BREAKING THROUGH THE SMALLEST RECES	SED BORE DIAMETER OF .375 INCH. PICTURE OF PART WITH THE MISSING HOLE ATTACHED. (TC NR 20070216001)					1	G	7	1 	3U			NC	H2SW    					 
2007051600168	20070516	00168	CE  	2007	5	16	CA070216002      	1	20070214	G	2750	100984040	MOTOR           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAP	FAILED          	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH, THE PILOT SELECTED FLAPS DOWN, WHEN THE FLAPS REACHED 5 DEGREES, THE ASSOCIATED CIRCUIT BREAKER	 POPPED. THE PILOT OVERSHOT TO EVALUATE THE SITUATION AND THEN CARRIED OUT AN UNEVENTFUL LANDING WITH 5 DEGREE OF FLAP. 	UPON INVESTIGATION BY MAINTENANCE, IT WAS FOUND THAT THE BEARING IN THE FLAP MOTOR HAD FAILED. THE MOTOR WAS REPLACED AN	D THE AIRCRAFT RETURNED TO SERVICE. AS THE FLAP MOTOR IS NOT CONTROLLED FOR HARD TIME, THE OPERATORS HAVE INDUCED A MAND	ATORY OVERHAUL OF THE MOTOR AND GEARBOX EVERY 5000 CYCLES. (TC NR 20070216002)		1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007051600169	20070516	00169	SO  	2007	5	16	CA070216003      	1	20070216	G	2730	AN17422A	BOLT            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION FOUND BOLTS (AN174-22A (6EA)) IN ELEVATOR TORQUE TUBE ASSEMBLY (40070-05) CORRODED. (TC NR 200702160	03)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2008031900133	20080319	00133	CE  	2008	3	19	CA070216004      	1	20070209	G	7120	829	SPACER          			CESSNA	172   	172E        	2072412	CE  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1000 			15182					(CAN) A RATTLE NOISE WAS HEARD AT ENGINE START. CLOSE INSP OF THE ENGINE MOUNT ASSY REVEALED ALL 4 MOUNT SPACERS, P/N 82	9, HAD SHEARED THEIR ATTACHMENT RIVET HEADS. THIS AC WAS MODIFIED IN THE PAST WITH 180HP CONVERSION. DISASSEMBLY REVEALE	D THE USE OF VERY SOFT ALUMINUM ALLOY RIVETS TO ATTACH THE ALUMINUM SPACERS TO THE STEEL TUBE MOUNT STRUCTURE, PN 17201-	1, WEAR DAMAGE PREVENTED POSITIVE VISUAL ID OF THE RIVET TYPE.  IT IS UNKNOWN IF THESE RIVETS ARE A FACTORY OR A FIELD I	NSTALLATION. FAILURE OF THESE RIVETS ALLOW  SPACER TO OSCILLATE LATERALLY ON THEIR MOUNTING PADS.  SUBMITTER RECOMMENDS 	TO EXAMINE THIS ENGINE MOUNT SPACER CLOSELY FOR SMOKING OR LOOSE RIVET HEADS AT INSP. (TC NR 20070216004)	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	C	P920	 
2007051600170	20070516	00170	GL  	2007	5	16	CA070216005      	2	20070210	G	7261		OIL SYSTEM      	ALLSN       		LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2 ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA				9453 							(CAN) IN CRUISE FLIGHT, THE CREW OBSERVED THAT THE OIL QUANTITY WAS DROPPING ON NR 2 ENGINE. AFTER VISUAL CONFIRMATION T	HAT OIL WAS EXITING THE OVERBOARD DRAIN, THE ENGINE WAS SHUTDOWN. THE AIRCRAFT LANDED WITHOUT FURTHER PROBLEM.  MAINTENA	NCE REPLACED THE ENGINE SCAVENGE SYSTEM FILTER, THE ENGINE OIL COOLER, CHECKED THE ENGINE MAGNETIC DRAIN PLUGS AND REFIL	LED THE ENGINE WITH FRESH OIL. NO CONTAMINATION WAS OBSERVED OTHER THAN SOME CARBON IN THE SCAVENGE FILTER. THE AIRCRAFT	 WAS GROUND RUN AND THE RETURNED TO SERVICE. (TC NR 20070216005)		2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007051600171	20070516	00171	SW  	2007	5	16	CA070216006      	1	20070207	G	6320		GEARBOX         	BELL        		BELL  	427   	427         	1182207	SW  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1623 			A37					(CAN) FOUND A CRACK IN MAIN ROTOR TRANSMISSION, ON THE LT SIDE INPUT SHAFT. OIL STARTED TO SIP OUT OF THE TRANSMISSION. 	(TC NR 20070216006)					1	G	7	1 	3U				R00001RC					 
2007053000010	20070530	00010	NE  	2007	5	30	CA070216008      	2	20070216	G	7230	5009T34P01	BLADE           	GE          							GE    	CT58  	CT581401    	30011	NE  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3971 		258					(CAN) ON INSPECTION, A STAGE 4 BLADE WAS FOUND TO HAVE A 0.080 INCH CRACK THROUGH THE DOVE TAIL AREA ON THE TRAILING EDG	E SIDE.  OUR FILE NR SQID 07-00588 (TC NR 20070216008)										4	U			1E3				 
2007051600173	20070516	00173	NE  	2007	5	16	CA070219001      	2	20070216	G	7230		FAN BLADE       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 2 ENGINE	BENT            	W				A				UNSCHED LANDING         				C			F.O.D.                    			CL	CLIMB          	1			CA			25204	25204				807217			(CAN) FEB 16/07, AIR TURN BACK. THE CREW REPORTED THAT AFTER TAKEOFF A LOUD RUMBLING NOISE WAS HEARD.  CREW BELIEVED THA	T ICE MAY HAVE BEEN INGESTED INTO THE RT ENGINE DURING LANDING ON THE PREVIOUS LEG INBOUND TO DESTINATION. MAINTENANCE C	ONFIRMED SEVERAL FAN BLADES WERE DAMAGED AT OUTER TIPS.  THE FAN BLADES WERE REMOVED AND REPLACED AND A COMPRESSOR INSPE	CTION WAS CARRIED OUT WITH NFF.  ENGINE RUNS WERE CARRIED OUT AND ALL PARAMETERS FOUND WITHIN LIMITS AND AIRCRAFT WAS RE	TURNED TO SERVICE. (TC NR 20070219001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051600174	20070516	00174	EA  	2007	5	16	CA070219003      	1	20070218	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL600*      	       	EA  										TE FLAPS	JAMMED          	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH, CREW RECEIVED SLATS FAIL MESSAGE, ALSO, FLAPS  STOPPED AT 8 DEGREES. FLIGHT LANDED WITHOUT INCIDENT. 	INFORMATION WILL BE UPDATED AS SOON AS IS AVAILABLE.   (TC NR 20070219003)					2	L	7	2 	4F			RT	A21EA   					 
2007051600175	20070516	00175	SW  	2007	5	16	CA070219004      	1	20070204	G	5610	2719442003	WINDSHIELD      			SWRNGN	SA227 	SA227AC     	8780603	SW  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA				3829 							(CAN) WHILE IN CRUISE FLIGHT ENROUTE, THE CAPTAINS WINDSCREEN CRACKED IN THE OUTER PANE. THE AIRCRAFT CONTINUED ON AND 	LANDED WITHOUT INCIDENT. THE WINDSHIELD WAS REPLACED WITH AN OVERHAULED ASSEMBLY AND THE AIRCRAFT RELEASED.   (TC 200702	19004)				2	L	7	2 	4T			RT	A8SW    					 
2007051600176	20070516	00176	SW  	2007	5	16	CA070219005      	1	20070218	G	7120	276211497	MOUNT           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				8945 							(CAN) DURING INSPECTION A CRACK WAS DISCOVERED IN THE UPPER AFT OUTBOARD WELD ASSEMBLY ON THE ENGINE MOUNT TRUSS REQUIRI	NG REPLACEMENT OF THE MOUNT ASSEMBLY. (TC NR 20070219005)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2007051600177	20070516	00177	EA  	2007	5	16	CA070219006      	2	20070208	G	7321	34475523	FCU             			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING GROUND RUN, RT POWER LEVER FOUND NOT CONTOLLING FCU. INSPECTED THROTLE LEVER LINKAGES AND CABLE TO FCU AND 	NO FAULTS FOUND. AFTER TROUBLESHOOTING WITH MFG TECH SUPPORT, SUSPECTED FAULTY FUEL CONTROL UNIT. FCU HAS BEEN REPLACED 	AND FAULT ELIMINATED. (TC NR 20070219006)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007051700116	20070517	00116	EA  	2007	5	17	CA070219008      	1	20070218	G	5551	C6TPM102228	BRACKET         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE FLIGHT CREW WHERE CONDUCTING A GROUND RUN, MAINTENANCE ON THE GROUND NOTED THE RT ELEVATOR WAS MOVING UP AND	 DOWN EXCESSIVELY. UPON INVESTIGATION, MAINTENANCE FOUND BRACKET P/N C6TPM1022-28 WITH RIVETS WORKING AND SEVERAL WHERE 	ACTUALLY MISSING. THIS BRACKET IS THE PART OF THE ELEVATOR HINGE THAT IS RIVETED TO THE HORIZONTAL STABILIZER. ALL MISSI	NG, LOOSE OR DAMAGED FASTNERS WHERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE COMPANY HAS ISSUED A FLEET INSPEC	TION OF ALL OTHER TWIN OTTERS. (TC NR 20070219008)		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000011	20070530	00011	EA  	2007	5	30	CA070219009      	1	20070216	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			17589	13354							(CAN) DURING APPROACH WHEN FLAP SELECTED TO 8 DEG, CREW RECEIVED (FLAP FAIL) CAUTION MESSAGE ON EICAS, CONTROL POSITION 	DISPLAY SHOWED 2DEG ON LT FLAP AND 0 DEG ON RT FLAP. ZERO DEG FLAP LANDING CARRIED OUT.  AFTER LANDING CREW PERFORMED VI	SUAL INSPECTION OF THE FLAPS AND NOTED THAT LT FLAPS APPEARED TO BE AT 2 DEG AND RT FLAP LOOKED LIKE 2 DEG ON THE IB AND	 0 DEG ON THE OB. FLAP CIRCUIT BREAKER RESET PROCEDURE CARRIED OUT. FLAPS FUNCTION CHECKED NORMAL. AIRCRAFT POSITIONED T	O MAINTENANCE BASE. MAINTENANCE FOUND NO OBVIOUS FAULTS. ALL FLAP ACTUATORS REPLACED WITH REPLACEMENT UNITS, ALL FLAP DR	IVE CABLES REMOVED AND INSPECTED AND RE-LUBRICATED. BOTH BPSU`S (FLAP BRAKE AND POSITION SENSOR UNITS) REPLACED. MAINTEN	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051700117	20070517	00117	EU  	2007	5	17	CA070219010      	1	20070219	G	5497		WIRE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	NR 2 NACELLE	DAMAGED         	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) CREW REPORTED THAT THE AIRCRAFT NR 2 ENGINE STARTED TO SURGE AND THE TORQUE INDICATION FLUCTUATED BETWEEN 0-120 PE	RCENT. TTL AND SRL COMPUTERS TURNED OFF AND ENGINE SURGE STABILIZED AND CONTINUED TO RUN NORMALLY. INDICATION CONTINUED 	TO FLUCTUATE. TROUBLESHOOTING INDICATED DAMAGED WIRING IN THE NR 2 ENGINE COMPARTMENT. WIRING REPAIRED. INDICATION CALIB	RATED AND NO FURTHER FAULTS FOUND. (TC NR 20070219010)			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2007051700118	20070517	00118		2007	5	17	CA070219011      	4	20070217	G	2397	M2430823F	CONNECTOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					P1RU	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			5121 	5121 							(CAN) CREW REPORTED PASSENGER ADDRESS CIRCUIT BREAKER 1Q5 POPPED , NON PA/CHIMES/CALL FUNCTION. MAINTENANCE INSPECTION F	OUND STOWED CONNECTOR P1RU CORRODED AND SHORTING , CONNECTOR IS FOR AFT CABIN PA HANDSET ( NOT INSTALLED ON THIS TAIL) ,	 CONNECTOR HAD BEEN BAGGED AND STOWED ABOVE CEILING PANEL. MAINTENANCE REMOVED CONNECTOR AND HEAT SHRUNK AND STOWED WIRI	NG IAW AMM 20-17-10 . (TC NR 20070219011)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900134	20080319	00134	SW  	2008	3	19	CA070220001      	1	20070215	G	2913	297037	SPLINE          	VICKERS     		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD PUMP	STRIPPED        	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA						MX433286C					(CAN) LT HYD LIGHT ILLUMINATED BEFORE LANDING. THE DRIVE SPLINE ON THE PUMP WAS FOUND TO BE STRIPPED. IT IS MADE OF SOFT	ER MATERIAL AND MADE TO WEAR INSTEAD OF THE ENGINE. PUMP ASSY WAS REPLACED AND AC RETURNED TO SERVICE. THIS IS THE 3RD S	PLINE REPLACED. ONE IN OCT- 06, ONE IN DC-06 AND NOW THIS ONE FEB-07. (TC NR 20070220001)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007051700119	20070517	00119	EA  	2007	5	17	CA070220002      	2	20070212	G	7200		ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA				285  				40812100			(CAN) CREW CALLED IN ON LANDING TO INFORM MAINTENANCE THAT THE RT CHIP LIGHT HAD ILLUMINATED.  MAINTENANCE FOUND ENGINE 	HAD METAL IN OIL.  ENGINE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.  THIS ENGINE WILL REQUIRE FURTHER INVESTIGATION	 AS TO THE CAUSE OF THE MIO.  IT IS A LOW TIME POWER SECTION THAT IS ON IT`S SECOND MIO.  THE FIRST TIME WAS 183 HOURS A	ND 341 CYCLES (TC NR 20070220002)			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007051700120	20070517	00120	WP  	2007	5	17	CA070220003      	1	20070218	G	6510	C04111	BEARING         	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					DRIVESHAFT	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			85   			1062					(CAN) DAMPER HANGAR BEARING INNER RACE ROTATED ON DRIVESHAFT ASSY.  BEARING REPLACED ON DRIVE SHAFT ASSY WITH SERVICABLE	 UNIT. (TC NR 20070220003)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2007051700121	20070517	00121	NE  	2007	5	17	CA070220004      	2	20070213	G	7200		ENGINE          			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  						UNKNOWN         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA								731587			(CAN) EARLY INVESTIGATIONS POINT TO A NR 4 BEARING FAILURE, AT THIS TIME THE ENGINE HAS NOT BEEN DISSASSEMBLED FOR CONFI	RMATION OF FAILURE, PRESENTLY ENROUTE TO SHOP. (TC NR 20070220004)					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007051700122	20070517	00122	NM  	2007	5	17	CA070220005      	1	20070216	G	3230	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			8173 								(CAN) ON GEAR EXTENSION GOT 3 GREEN AND DOOR AMBER.  TROUBLESHOOTING POINTED TO THE NOSE VALVE SOLENOID SEQUENCE.  VALVE	 REPLACED. (TC NR 20070220005)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008031900135	20080319	00135	NE  	2008	3	19	CA070220006      	2	20070216	G	7230	31B525501	ACTUATOR        			GULSTM	200   	200         	4500308	NM  	PWC   	PW306 	PW306A      	52165	NE  					IGV	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			525  					PCECC02423			(CAN) AC PERFORMED NORMALLY FOR THE TAKEOFF AND INITIAL CLIMB TO 5000 FEET. APPROX (2) MINUTES INTO THE FLIGHT AFTER CLE	ARANCE TO 17000 FT WITH CLIMB PWR REAPPLIED TO COMMENCE THE CLIMB, THE RT ENG EXPERIENCED A COMPRESSOR STALL. AFTER (2) 	OR (3) SURGES THE ENGINE ROLLED BACK TO AROUND 50 PERCENT, N1 WITH FLUCTUATING RPM AND ITT. ROLLBACK WAS FOLLOWED BY A F	ADEC MAJOR FAIL FAULT LIGHT. THE PILOT REDUCED POWER ON THE RT ENGINE AND THE N1 STABILIZED AT FLIGHT IDLE. CHECKLIST WA	S CALLED FOR AND THE RT ENG WAS SHUTDOWN IAW MFG CHECKLIST. FUEL DUMP WAS COMPLETED WITH CLEARANCE FROM THE DEPARTURE CO	NTROLLER AND THE AC WAS REDUCED TO LANDING WEIGHT AND RETURNED FOR LANDING AT AIRPORT WITH NO FURTHER INCIDENT.   THE AC	2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2007051700123	20070517	00123	CE  	2007	5	17	CA070220007      	1	20070219	G	3233		SHAFT           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	MLG ACTUATOR	FRACTURED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			DE	DESCENT        	1			CA			1329 	1329 							(CAN) MAIN LANDING GEAR ACTUATOR SHAFT FRACTURED AT LAST THREAD FARTHEST FROM ROD END BEARING JAM NUT. SHAFT BENT SLIGHT	LY THROUGHOUT ITS FULL LENGTH WITH AN APPROXIMATELY 40 DEGREE BEND AT FRACTURE POINT. (TC NR 20070220007)					1	L	7	2 	3O	3	O		A29CE   	1E10	5	C	P43GL	 
2007051700124	20070517	00124	EA  	2007	5	17	CA070221001      	1	20070219	G	2720	600902461	BUSHING         			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF348E5A1   	30015	NE  					RUDDER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			7326 	7326 							(CAN) DURING FLIGHT THE CO-PILOTS RUDDER PEDAL ADJUSTMENT MECHANISM FAILED ALLOWING THE RUDDER PEDALS TO FALL FORWARD TO	 THE LIMIT OF THEIR TRAVEL. INSPECTION REVEALED THAT THE THREADED BUSHING IN THE ADJUSTMENT MECHANISM HAD FAILED ALLOWIN	G THE SYSTEM TO DICONNECT. NOTE: RUDDER CONTROL WAS STILL AVAILIBLE THOUGH RUDDER PEDAL POSITION ADJUSTMENT WAS NOT. (TC	 NR 20070221001)			2	L	7	2 	4F	4	F	RT	A21AE   	E00063EN				 
2007051700125	20070517	00125	EA  	2007	5	17	CA070221002      	1	20070218	G	2782	7663854	ACTUATOR        			CNDAIR	CL600 	CL600*      	       	EA  										SLATS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) SLAT FAIL MESSAGE, UNABLE TO MOVE SLATS AND FLAPS ONLY MOVED TO 8 DEGREES. MDC CODE B1-007772 INDICATES JAMMED SLA	T ACTUATOR AND AIRCRAFT REMOVED FROM SERVICE FOR INVESTIGATION. BOTH LEFT HAND OUTBOARD ACTUATORS NR 5 AND NR 6 REPLACED	 AND TEST COMPLETED SUCCESSFULLY. WILL ASK FOR STRIP REPORTS FROM MANUFACTURER. INFORMATION WILL BE UPDATED AS SOON AS I	S AVAILABLE. (TC NR 20070221002)			2	L	7	2 	4F			RT	A21EA   					 
2007051700126	20070517	00126	CE  	2007	5	17	CA070221003      	1	20070205	G	2560	1101983	BUCKLE          	PACIFICSCIEN		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SEAT BELT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 NM-06-29.  THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTED WIT	H THE CONTROL YOKE WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING 	THE YOKE AND MAKING CONTACT WITH THE BUCKLE. THE FUNCTION TEST WAS CARRIED OUT IAW THE INSTRUCTIONS GIVEN IN NM-06-29.  	(TC NR 20070221003)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2007051700127	20070517	00127	CE  	2007	5	17	CA070221004      	1	20070210	G	2560	1101983	BUCKLE          	PACIFICSCIEN		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SEAT BELT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011, NM-06-29.  THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTED WI	TH THE CONTROL YOKE WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING	 THE YOKE AND MAKING CONTACT WITH THE BUCKLE. THE FUNCTION TEST WAS CARRIED OUT IAW THE INSTRUCTIONS GIVEN IN NM-06-29. 	 (TC NR 20070221004)			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2007080800143	20070808	00143	CE  	2007	8	8	CA070221005      	1	20070206	G	2560		BUCKLE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEATBELT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011/SAIB NM-06-29.  THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTE	D WITH THE CONTROL YOKE LET DOWN HOLDER WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE 	SEATBELT BY ROTATING THE YOKE AND MAKING CONTACT WITH THE BUCKLE. THE FUNCTION TEST WAS CARRIED OUT IAW THE INSTRUCTIONS	 GIVEN IN SAIB NM-06-29.   (TC NR 20070221005)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007051700128	20070517	00128	NE  	2007	5	17	CA070221006      	1	20070213	G	3230	4546A	MOTOR           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					LANDING GEAR	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			10618	1192 		A019					(CAN) ON PRELANDING CHECK, MAIN LANGDNG GEAR FAILED TO EXTEND. EMERGENCY BLOW DOWN PROCEDURE WAS FOLLOWED AND AIRCRAFT L	ANDED WITHOUT FURTHER INCIDENT. INVESTIGATION  DETERMINED THAT THE ELECTRIC MOTOR THAT DRIVES THE MLG HYDRAULIC PUMP HAD	 FAILED AND TRIPPED THE CIRCUIT BREAKER. (TC NR 20070221006)				2	G	7	2 	4U	4	U		1H15    	1E3				 
2007051700129	20070517	00129	NM  	2007	5	17	CA070221007      	1	20070220	G	2133	14C3308	COUPLER         	HYDROFLOW   		BOEING	737   	737*        	       	NM  										FS 967 S23R	LEAKING         	W				A				UNSCHED LANDING         				K	G		FLUID LOSS                	MULTIPLE FAILURE          		CR	CRUISE         	1			CA											(CAN) ALMOST AN HOUR INTO THE FIRST FLIGHT OF THE DAY, AIRCRAFT EXPERIENCED AUTOMATIC PRESSURIZATION FAULT WITH (AUTO-FA	IL) LIGHT ON (WITH BOTH CPC`S FAIL). CREW RESORT TO MANUAL PRESSURIZATION CONTROL. AIRCRAFT ADVISED TO DIVERT TO MAIN BA	SE FOR RECTIFICATION.  UPON INVESTIGATION THE AFT OUT FLOW VALVE FOUND BLOCKED WITH ICE AND WATER SYSTEM QUANTITY LOW.  	THIS WAS THE SECOND SIMILAR INCIDENT ON THIS AIRCRAFT.  FURTHER INVESTIGATION REVEALED WATER LEAKING FROM THE COUPLING (	SIMILAR TO COUPLING) AT THE FITTING RT ABOVE THE AFT OUTFLOW VALVE. (SIMILAR TO PREVIOUS FINDING).  FITTING/LINES RE-ALI	GNED TO RELIEVE POSSIBLE STRESS ON COUPLING. COUPLING TIGHTENED AND RESECURED WITH NEW PACKING. NO FURTHER LEAKS AND AIR	2	L	7	2 	4F			RT	A16WE   					 
2007051700131	20070517	00131	EA  	2007	5	17	CA070222001      	1	20070212	G	7897	22858222801	WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1 ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22696	22696							(CAN) DURING ROUTINE MAINTENANCE INSPECTION , FOUND WIRING HARNESS ON NR1 ENGINE FOR THRUST REVERSER STOW SWITCH WIRING 	CHAFING ON EDGE OF LIGHTENING HOLE OF MOUNTING BRACKET. DAMAGED WIRING CUT OFF AND END RE-TERMINATED. MFG ILLUSTRATED PA	RTS CATALOG (CSP A-006) 78-37-01 FIG 1A PG 0 , ITEM 40 (BRACKET ASSY, STOW SWITCH MOUNTING). LIGHTNING HOLE ON THIS BRAC	KET CHAFED ON HARNESS FOR STOW SWITCH  (TC NR 20070222001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007051700132	20070517	00132	EA  	2007	5	17	CA070222002      	1	20070212	G	5730	6001201687S	SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT WING	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25955	25955							(CAN) CREW REPORTED BIRDSTRIKE ON APPROACH, MAINTENANCE INSPECTION FOUND DENT IN LT WING LEADING EDGE APPROX 6 FT OB FRO	M FUSELAGE. DENT ALLOWABLE IAW SRM LIMITS. (TC NR 20070222002)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007080800144	20070808	00144	CE  	2007	8	8	CA070222003      	1	20070222	G	5514	07321014	BRACKET         			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2383 								(CAN) HORIZONTAL STABILIZERS REMOVED FOR REPAIR.  AFT ATTACHMENT POINT REINFORCEMENT BRACKETS PN 0732101-4 REPLACED WITH	 NEW.  ADJACENT RIVETS REPLACED.  TAIL RE-ASSEMBLED.  DUAL INSPECTED. (TC NR 20070222003)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007051700133	20070517	00133	NE  	2007	5	17	CA070222004      	2	20070219	G	7200	70BM031090	MODULE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) POSSIBLE T1 OR T2 MO3 TURBINE RUB. REMOVED MO3 AND SEND TO MFG FOR INVESTIGATION. THE TURBINE RUB WAS NOTICED AFTE	R SHUTDOWN OF THE ENGINE. (TC NR 20070222004)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2007080800145	20070808	00145	CE  	2007	8	8	CA070223001      	1	20070220	G	2130	6621000000037	CHECK VALVE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN PRESSURE	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			2491 								(CAN) SHORTLY AFTER TAKEOFF, DURING INITIAL CLIMBOUT, THE CREW NOTICED THAT THE CABIN ALTITUDE RATE OF CLIMB INDICATOR S	HOWED 600FT/MIN CLIMB.  USUALLY, THE CONTROLLER IS SET TO 400FT/MIN.  THEY CONTINUED TO CLIMB AND TO MONITOR THE PRESSUR	IZATION SYSTEM. A FEW MOMENTS LATER, THE INDICATOR SHOWED A 1500-2000FT/MIN CLIMB.  THE CABIN ALTITUDE FOLLOWED THE AIRP	LANE ALTITUDE.  THE AIRPLANE WAS NOT PRESSURIZING THE CABIN. THE CREW CARRIED OUT THE APPROPRIATE CHECKLIST AND DECIDED 	TO DIVERT TO THEIR ALTERNATE AIRPORT.  MEANWHILE, NO WARNING OR CAUTION INDICATIONS/MESSAGES APPEARED ON EICAS AND THE C	REW COULD NOW SMELL KIND OF ODOR OF A OVERHEATED DUCT.  THEY NOTICED ALSO THAT NO HEATED/CONDITIONED AIR WAS COMING FROM	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007053000012	20070530	00012	CE  	2007	5	30	CA070223002      	1	20070220	G	7797	8975294	WIRE HARNESS    			BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ENGINE ITT	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA				495  				P27035			(CAN) FLIGHT CREW DID ATTEMPTED AN ENGINE START NR 2 ENGINE WITH NO SUCCESS. AFTER MAINTENANCE HAD CORRECTED THE PROBLEM	 ASSOCIATED WITH THE FAILED START, THE CREW PROCEEDED TO CARRY OUT ANOTHER ENGINE START. ONCE THE ENGINE LIT OFF THE CRE	W NOTED THAT THE ITT WAS CLIMBING RAPIDLY TOWARDS THE RED BUT THEN WOULD DROP AND RISE AGAIN. THEY DECIDED TO CONTINUE W	ITH THE START. ONCE THE ENGINE HAD SETTLED AT IDLE, THE ITT BEGAN TO FLUCTUATE AND SLOWLY CLIMB TO THE REDLINE. THE CREW	 DECIDED AT THIS TIME TO SHUTDOWN THE ENGINE.  MAINTENANCE TROUBLESHOT THE SYSTEM AND FOUND THAT THE ITT HARNESS WAS U/S	. DUE TO THE FACT THAT THEY COULD NOT SPECIFICALLY STATE THAT THE PROBLEM WAS THE HARNESS AND NOT THAT THE HARNESS AND T	1	L	7	2 	3T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007053000013	20070530	00013	EA  	2007	5	30	CA070223003      	2	20070221	G	8520	UNK	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	CRANKSHAFT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			7000 	1365 				L327861A			(CAN) DURING A NORMAL WALK AROUND, OIL WAS OBSERVED ON THE COWLING. AN INVESTIGATION INTO THE OIL LEAK REVEALED THE CRAN	KSHAFT SEAL WAS BLOWN OUT. THE OIL SUMPS WERE DRAINED AND OIL FILTER CHECKED AND FOUND TO CONTAIN LARGE QUANTITIES OF ME	TAL FILINGS. THE ENGINE WAS REMOVED FOR TEARDOWN REPORT AND OVERHAULED ENGINE INSTALLED. (TC NR 20070223003)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	 	 
2007051700160	20070517	00160	EA  	2007	5	17	CA070223004      	1	20070222	G	5330		SKIN            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35713								(CAN) AIRCRAFT IS IN THE PROCESS OF GOING THROUGH ITS (5) YEAR CORROSION INSPECTION. DURING INSPECTION, SEVERAL AREAS OF	 CORROSION WERE NOTED IN AREAS WHERE CORROSION IS USUALLY NOT FOUND. THE HORIZONTAL STAB LOWER SKIN (CENTER) WAS CORRODE	D AROUND SOME ANCHOR NUTS (FOR THE FAIRINGS), THE SUPPORT BRACKET FOR THE LOWER RUDDER ATTACH POINT, AND AROUND ALL THE 	PASSENGER WINDOW FRAMES (WHERE SPOT WELDS ARE). THE SUPPORT BRACKET IS BEING REPLACED AND WE ARE WAITING FOR RD`S FROM V	IKING FOR THE OTHER AREAS. (TC NR741 20070223004)		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007051700161	20070517	00161	SW  	2007	5	17	CA070223005      	1	20070220	G	6510	204040608001	SPRING          	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A512					(CAN) ENGINEER CARRYING OUT REQUIREMENTS OF CAMP CODE NR 650121 (INSPECT/LUBE T/R DRIVESHAFT FLEX COUPLING).  WHEN DISAS	SEMBLING THE T/R QUILL OUTPUT COUPLING IN SITU ON THE M/R TRANSMISSION.  UPON REMOVAL OF RETAINER AND PLATE, A SMALL SEC	TION OF SPRING PN 204-040-608-001 FELL INTO THE HAND OF THE ENGINEER.  REMAINDER OF SPRING WAS IN CORRECT POSITION.  FUR	THER DISASSEMBLY OF COUPLING REVEALED DAMAGE TO COUPLING P/N 204-040-603-009.  NEW SPRING P/N 204-040-608-001 AND SERVIC	EABLE COUPLING P/N 204-040-603-009 S/N A12-42482 INSTALLED.  COMPLETE COUPLING ASSEMBLY LUBED AND REASSEMBLED IAW CHAPTE	R 65 OF MM, AND REASSEMBLED ONTO THE M/R TRANSMISSION. (TC NR 20070223005)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007051700162	20070517	00162	SW  	2007	5	17	CA070223007      	1	20070222	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	DENTED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3224 								(CAN) WHILE IN HANGAR, METAL PIECE OUT OF HANGAR OVERHEAD HEATER FELL ON M/R BLADE AND DENTED THE BLADE. BLADE WAS REMOV	ED AND SENT FOR INSPECTION. HANGAR STAFF AND MANAGER WERE NOTIFIED AND REQUESTED TO INSPECT ALL OVERHEAD ACCESSORIES INC	LUDING HEATERS FOR LOOSE OBJECTS.  (TC NR 20070223007)				1	G	7	1 	3U				H2SW    					 
2007080800146	20070808	00146	CE  	2007	8	8	CA070223008      	1	20070214	G	3245	0923150	TUBE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	MAIN TIRE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			1000 								(CAN) THE PILOT REPORTED A FLAT TIRE ON THE RUNWAY.  MAINTENANCE REMOVED THE AIRCRAFT FROM THE RUNWAY. FOUND NO DAMAGE T	O THE TIRE, THE TUBE WAS FOUND SPLIT IN TWO PLACES AROUND THE OUTER CIRCUMFERENCE.  PART HAD BEEN INSTALLED APPROX 1000 	HOURS AND APPROX 15 MONTHS.  REPLACED THE TUBE AND TIRE AND RETURNED TO SERVICE. (TC NR 20070223008)				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2007053000017	20070530	00017	EA  	2007	5	30	CA070225001      	1	20070212	G	5610	1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			10130								(CAN) INNER CORE OF CAPTAINS WINDSHIELD SHATTERED AT FL 330. MX REPLACED CAPTAINS WINSHIELD IAW 56-11-01. (TC NR 2007022	5001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007053000020	20070530	00020		2007	5	30	CA070226001      	4	20070221	G	3497		CONNECTOR       	HONEYWELL   		BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					DRIVE UNIT	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						4531					(CAN) CREW REPORTED EICAS STATUS MESSAGE, WXR SYSTEM. ON REPLACEMENT OF WXR DRIVE UNIT, FOUND BURNED ELECTRICAL CONNECTO	RS. (TC NR 20070226001)					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2007053000021	20070530	00021	NM  	2007	5	30	CA070226002      	1	20070223	G	5610	5717623133	WINDSCREEN      			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAIN`S NR 2 WINDOW OUTER LAYER SHATTERED IN FLIGHT. WINDOW WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. REPOR	TED AS AN SDR DUE TO A SUSPECTED RELIABILITY ISSUE WITH SUBJECT WINDOWS. (TC NR 20070226002)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2007053000024	20070530	00024	CE  	2007	5	30	CA070226005      	1	20070208	G	5210	1014300327	PLATE           			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1328 	1328 							(CAN) DISCOVERED DOOR MAKING NOISE WHEN RAISING OR LOWERING DOOR. INVESTIGATED FOR LOOSE HARDWARE INSIDE DOOR AND DETERM	INED PIN AND ROLLER ASSY MIGRATED OUT OF LOWER AFT LATCH ASSY. THE DEFECTIVE PART IN QUESTION IS THE PLATE P/N 101-43003	2-7. THE PLATE IS THE FIXTURE FOR A PIN P/N 101-430032-9 AND ROLLER P/N 50-430037-7. THESE PARTS (PIN/ROLLER)ARE CONTAIN	ED IN THE PLATE BY MEANS OF STAKING WAS NOT PROPERLY SET WHEN MFG CAUSING THE PIN MIGRATING OUT OF THE PLATE. ALL OTHER 	PLATES WERE INSPECTED TO ENSURE EACH PLATE`S SECURITY. THESE PLATES/LATCHES ARE CRUCIAL TO THE STRUCTURAL INTEGRITY OF T	HE DOOR AND FUSELAGE FRAME UNDER PRESSURIZATION LOADS. IPI REFERENCE 52-10-00 PG.16 ITEM 280, 285, 290 ILLUSTRATION SHEE	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007053000025	20070530	00025	SO  	2007	5	30	CA070226006      	2	20070219	G	8520	626608	CAMSHAFT        			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1294 							(CAN) EXCESSIVE WEAR ON NR 1 AND NR 2 INTAKE LOBE.  CAUSED EXCESSIVE PITTING ON ALL LIFTER BODY ASSEMBLIES. (TC NR 20070	226006)					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007053000027	20070530	00027	EA  	2007	5	30	CA070226008      	1	20070226	G	5711	2151003268	SPAR CAP        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43D	43D50       	NE  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4124 								(CAN) WHILE PERFORMING AD CF92-26R1, A CRACK WAS DETECTED ON THE RT REAR LOWER SPAR CAP JUST OB OF RBL 51.00.  WORK COMM	ENCED ON REPAIR IAW THE MFG SPEC. UPON REMOVAL OF REINFORCING STRIP (P/N 215-10032-76) AN ADDITIONAL CRACK WAS FOUND ON 	THE LOWER SPAR CAP AT RBL 49.50. FOLLOWING REMOVAL OF THE DAMAGED SPAR CAP AN ADDITIONAL CRACK WAS NOTICED ON THE WING S	PAR WEB (P/N 215-10032-242) AT RBL 50.00 THAT EXTENDED FROM THE SECOND LOWER, WING TO FUSELAGE PICK UP ANGLE FASTENER HO	LE THROUGH TO THE LOWER FASTENER HOLE AND OUT THE EDGE OF THE WEB. THESE CRACKS ARE BOTH LOCATED OUTSIDE OF THE DESIGNAT	ED INSPECTION AREA. (TC NR 20070226008)	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P8879	 
2007053000028	20070530	00028	EU  	2007	5	30	CA070226009      	1	20070131	G	5310	350A3821003	CROSSBEAM       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				373  							(CAN) IAW THE AD 96-156-071 (B) R1 VISUAL INSPECTION EVERY 30 HOURS OR 150 LANDINGS. THE CRACKS WERE FOUND ON THE VISUAL	. (TC NR 20070226009)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007053000029	20070530	00029	CE  	2007	5	30	CA070226010      	1	20070225	G	3297		CONNECTOR       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) CREW REPORTED THAT THE GEAR INDICATION WOULD NOT INDICATE DOWN AND LOCKED ON APPROACH.   MAINTENANCE PERSONNEL LAT	ER CARRIED OUT AIRCRAFT LANDING GEAR SWINGS AND FOUND RT SQUAT SWITCH CONNECTOR PLUG LOOSE ON BULKHEAD. CLEANED, SECURED	 AND GEAR SWINGS FUNCTION CHECKS CARRIED OUT.  NO FAULTS FOUND (TC NR 20070226010)				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007053000030	20070530	00030	WP  	2007	5	30	CA070226011      	1	20070224	G	6310	C1664	RETAINER        	ROBSIN      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			895  			2043					(CAN) CRACKS AT OUTER RING BOLT HOLES. CLUTCH ASSY REMOVED AND IS BEING SENT TO MFG FOR WARRANTY. (TC NR 20070226011)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008021900141	20080219	00141	SW  	2008	2	19	CA070227001      	1	20070222	G	6220	204011121121	GRIP            			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) M/R GRIP TANG FOUND CRACK. COMPONENT ACCUMULATE 111 HRS SINCE LAST 150HRS NDT INSPECTION. (TC NR 20070227001)						1	G	7	1 	4U				H4SW    					 
2007053000031	20070530	00031		2007	5	30	CA070227002      	4	20070225	G	3442	20414440406	DRIVE UNIT      			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					WX RADAR ANTENNA	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WXR RADAR DRIVE UNIT FOUND WITH TERMINAL 15 AND 16 BURNED (TC NR 20070227002)						2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2007053000032	20070530	00032	NE  	2007	5	30	CA070227003      	2	20070215	G	7210		GEARBOX         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	REDUCTION	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								PCEPR0089			(CAN) SHORTLY AFTER TAKEOFF THE ENGINE CHIP LIGHT ILLUMINATED. THE PILOT RETURNED TO BASE. THE REDUCTION GEARBOX CHIP DE	TECTOR WAS INSPECTED AND A FERROUS METAL FLAKE WAS FOUND ON THE DETECTOR, NO CONTAMINATION WAS FOUND IN ANY SCREENS OR T	HE MAIN OIL FILTER. THE ENGINE WAS RETURNED TO SERVICE AFTER COMPLETING THE MAINTENANCE REQUIREMENTS SPECIFIED IN MM CH.	 79-20-02. AFTER 10 HRS OF OPERATION THE OIL FILTER WAS PULLED AND NO CONTAMINATION WAS FOUND. THE ENGINE HAS ACCUMULATE	D 101 HRS SINCE THE INCIDENT WITH NO FURTHER PROBLEMS. THE POWER SECTION NOW HAS 8788.3 TSN AND 652.9 TSO. (TC NR 200702	27003)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000033	20070530	00033	EA  	2007	5	30	CA070227004      	2	20070221	G	8550		TRANSFER TUBE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	OIL SYSTEM	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CRANKSHAFT FWD CAVITY OIL TRANSFER TUBE LOOSE LATERALLY AND ROTATIONALLY. CRANKSHAFT WAS REPAIRED APPROX 500 HOURS	 AGO.   (TC NR 20070227004)					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2007080800147	20070808	00147	EU  	2007	8	8	CA070227006      	1	20070222	G	3234	GH115TAREVE	HANDLE          			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  	HARTZL	HCC3Y	HCC3Y*      	GL  	LANDING GEAR	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA				97   							(CAN) LANDING GEAR HANDLE FAILED TO GIVE GEAR POSITION LIGHT AND IN-TRANSIT LIGHT INDICATIONS DURING A TRAINING MISSION.	 THE PILOT ELECTED TO FLY BY THE TOWER FOR ALL GEAR IN EXTENDED POSITION CONFIRMATION BEFORE AN UNEVENTFUL LANDING.  AFT	ER SHUTDOWN, THE LANDING GEAR POSITION LIGHTS BEGAN TO FUNCTION NORMALLY. MAINTENANCE PERSONNEL PLACED THE AIRCRAFT ON J	ACK AND TRIED UNSUCCESSFULLY TO DUPLICATE THE SNAG. THE WIRING AND TERMINALS WERE INSPECTED FOR FAULTS. NUMEROUS GEAR SW	INGS WERE PERFORMED. THE AIRCRAFT WAS RELEASED SERVICEABLE. HISTORICALLY, THE LANDING GEAR HANDLE UNIT POSITION LIGHTS H	AVE FAILED ON GROUND CHECKS AND THE UNITS (A FLEET OF 9 NEW (2006) AIRCRAFT) WERE SYSTEMATICALLY UPGRADED TO REVISION (E	1	L	7	1 	3O	3	O	RT	A49CE   	1E4	5	C	P25EA	 
2007053000035	20070530	00035	GL  	2007	5	30	CA070227008      	3	20070223	G	6111		BLADE           	HARTZL      	HCE4A3D     	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				2234 					KX130		(CAN) EXCESSIVE GREASE WAS NOTED LEAKING FROM PROPELLER BLADE ROOT ON ALL (4) BLADES. PROPELLER REMOVED AND SENT FOR REP	AIR. (TC NR 20070227008)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007080800148	20070808	00148		2007	8	8	CA070227010      	4	20070223	G	3160	0710143931	CONTROL PANEL   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EFIS	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) MOVING THE HEADING KNOB ON THE CONTROL PANEL WOULD CAUSE A FAILURE INDICATION (RED X) THROUGH THE HEADING BUG, AND	 A TD WARNING ON THE BOTTOM RT CORNER OF THE EFIS SCREEN. THE CONTROL PANEL WAS REPLACED. (TC NR 20070227010)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007080800149	20070808	00149		2007	8	8	CA070227012      	4	20070223	G	3455	066107214	RECEIVER        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ADF	ERRATIC         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) THE VOLUME ON THE ADF WAS VERY HARD TO ADJUST AND ERRATIC.  ADF RECEIVER REPLACED (TC NR 20070227012)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000038	20070530	00038		2007	5	30	CA070227013      	4	20070223	G	3100	973321920	LIGHT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CAUTION LIGHT	STUCK           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHEN RESETING THE CAUTION LIGHT, IT WOULD OCCASIONALY STICK ON. THE CAUTION LIGHT ASSY WAS REPLACED WITH NEW. (TC 	NR 20070227013)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000039	20070530	00039	NE  	2007	5	30	CA070227015      	2	20070126	G	7210	PT6T3B	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					REDUCTION GB	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			16983	1182 							(CAN) ENGINE NR 1 CHIP DETECTOR CAUTION LIGHT ILLUMINATED WHILE IN CRUISE FLIGHT AND PILOT RETURNED TO BASE. REDUCTION G	EARBOX NR 1 SIDE CHIP DETECTOR FOUND WITH SMALL AMOUNT OF METAL. CHIP DETECTOR WAS CLEANED AND AIRCRAFT FLEW ANOTHER 2 H	OURS BEFORE SECOND CHIP LIGHT AND RETURNED TO BASE.  SLIGHTLY MORE METAL FOUND ON PLUG. OIL WAS CHANGED AND AIRCRAFT WAS	 GROUND RUN 1 MINUTE BEFORE CHIP LIGHT ILLUMINATED. CHIP DETECTOR AND OIL FILTER CONTAINED MASSIVE AMOUNT OF METAL. REDU	CTION GEARBOX WAS REPLACED AND SENT TO MFG FOR INVESTIGATION. NO REPORT HAS BEEN ISSUED AS YET. (TC NR 20070227015)		1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007053000040	20070530	00040		2007	5	30	CA070228002      	4	20070221	G	6122	89741016	ARM             	WOODWARD    		MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	GOVENOR	STIFF           	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			875  	875  		2131212					(CAN) WHEN AIRCRAFT LANDED IT WOULD PULL TO THE LT.   MAINTENANCE FOUND THAT THE PROP GOVERNOR ARM WAS STIFF AND WOULD N	OT RETURN TO THE STOP. NOTE THIS GOVERNOR HAS SB TPE331-72-0567 RETURN SPRING INCORPORATED ON IT.  GOVERNOR WAS REPLACED	 AND CHECKED SERVICEABLE.  (TC NR 20070228002)				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2007053000041	20070530	00041		2007	5	30	CA070228003      	4	20070228	G	6122	AT210937	CONTROL ARM     			CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	GOVERNOR	DEFECTIVE       	W				A				UNSCHED LANDING         				F	R	J	FLT CONT AFFECTED         	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) THE SUBJECT AIRCRAFT WAS CLIMBING OUT AFTER TAKEOFF AND EXPERIENCED A SIGNIFICANT LOSS OF CLIMB POWER RELATED TO A	 DROP IN ENGINE RPM FROM 2700 RPM TO 1600 RPM. THE PILOT EXECUTED ALL APPROPRIATE EMERGENCY PROCEDURES/ACTIONS WITH NO  	IMPROVEMENT. THE PILOT DECLARED AN EMERGENCY AND WAS ABLE TO MANEUVER THE AIRCRAFT BACK TO THE AIRPORT,  LANDED WITHOUT 	FURTHER INCIDENT. UPON EXAMINATION, IT WAS DETERMINED THAT THE INTENTION OF THE DESIGN OF THE PROP GOVERNOR ARM ATTACHME	NT WAS TO HAVE THE BOLT THAT COMPRESSES THE ARM ON TO THE SPLINED SHAFT WAS TO PASS THROUGH THE GROVE IN THE SHAFT THUS 	PREVENTING THE ARM FROM SEPARATING EVEN IF THE BOLT DOES NOT HAVE SUFFICIENT TORQUE. IN THIS CASE THE ARM IS MANUFACTURE	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA	 
2007053000044	20070530	00044	CE  	2007	5	30	CA070228006      	1	20070228	G	7120	1299100471	MOUNT           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE A BLEED AIR LINE WAS FOUND CHAFING AN ENGINE TRUSS MOUNT TUBE. BLEED AIR LINE PN: 118-9	10033-93 TRUSS MOUNT PN: 129-910047-17. THE DAMAGE WAS FOUND TO BE WITHIN REPAIRABLE LIMITS IAW THE AIRCRAFT SRM. THE MO	UNT WAS REPAIRED BY A QUALIFIED WELDER AND THE AIRCRAFT WAS RELEASED BACK INTO SERVICE. A FLEET CAMPAIGN WAS CONDUCTED A	ND ONE OTHER AIRCRAFT WAS FOUND WITH THE SAME PROBLEM WITH BOTH INCIDENTS ON THE LT ENGINE TRUSS MOUNT.  (TC NR 20070228	006)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007053000045	20070530	00045		2007	5	30	CA070228007      	4	20070215	G	3452	KT76A	TRANSPONDER     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  		INTERMITTENT    	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CIRCUIT FLYING, TOWER REPORTED TO PILOT THAT HIS TRANSPONDER WAS INTERMITTENT.  PILOT CANCELLED REMAINDER O	F FLIGHT AND RETURNED TO AIRPORT. DEFECT WAS NOT DUPLICATED ON THE GROUND. DEFECT OCCURED THE NEXT DAY WHILE AIRCRAFT WA	S AGAIN IN THE CIRCUIT, PILOT CANCELLED AND RETURNED TO AIRPORT. MAINTENANCE REMOVED TRANSPONDER, CLEANED CONTACTS AND R	E-RACKED TRANSPONDER. AIRCRAFT RETURNED TO SERVICE AND HAS NOT HAD ANOTHER OCCURANCE IN OVER 50 HOURS. (TC NR 2007022800	7)		1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007053000046	20070530	00046	CE  	2007	5	30	CA070228008      	1	20070208	G	5630	51116052	WINDOW          			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	EMERGENCY EXIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAJOR INSPECTION OF AIRCRAFT, REMOVED PLASTIC UPHOLSTERY COVER ON THE EMREGENCY EXIT HATCH. WINDOW FOUND CR	ACKED AT ALL LOWER ATTACH SCREW HOLES, ONLY THE SEALANT KEEPING THE WINDOW IN PLACE. (TC NR 20070228008)					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
2007053000047	20070530	00047		2007	5	30	CA070228009      	4	20070227	G	3400		SWITCH          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					AVIONICS	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING TRAINING FLIGHT, PILOT EXPERIENCED COMPLETE AVIONICS FAILURE WHEN DEPRESSING THE PTT SWITCH. AIRCRAFT RETUR	NED TO BASE, MAINTENANCE DUPLICATED THE SNAG, DISCOVERED THE AVIONICS SWITCH DEFECTIVE AND REPLACED IT WITH NEW ONE, NO 	FURTHER FAULTS FOUND. (TC NR 20070228009)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007053000048	20070530	00048	EA  	2007	5	30	CA070301001      	2	20070301	G	8530	LW11901	INTAKE VALVE    			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA			29   								(CAN) INVESTIGATING LOW COMPRESSION REVEALED SMALL CHUNK (ONE QUARTER INCH SQUARE) OF INTAKE VALVE MISSING ON EDGE, AND 	A CRACK IN ANOTHER AREA. (TC NR 20070301001)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007053000049	20070530	00049	EA  	2007	5	30	CA070301002      	1	20070228	G	5343		FITTING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH MAIN LANDING GEAR FITTING FOUND CRACKED ON NDT INSPECTION IAW ADCF-1999-32R3. MAIN LANDING GEAR WILL BE REPLA	CED. LT P/N 5321103  S/N PO-422V5Q, RT P/N 3521104  S/N PO-BBBB10. (TC NR 20070301002)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007052400194	20070524	00194	NM  	2007	5	24	CA070301003      	1	20070223	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) WHILE DOING A PRE-FLIGHT WALK AROUND THE PILOT NOTICED HYDRAULIC FLUID DRIPPING FROM THE RT FLAP TRACK NR 3 FAIRIN	G. THE LEAK WAS FOUND TO BE COMING FROM THE OB ROLL SPOILER ACTUATOR. UPON REMOVAL OF THE ACTUATOR IT WAS FOUND THAT THE	 HOUSING HAD CRACKED IN THE AREA SUROUNDING ONE OF THE PLUGS CAUSING THE PLUG TO DISLODGE. THE CRACK EXTENDED AROUND THE	 ENTIRE CIRCUMFERENCE OF THE THREADED PORTION OF THE ACTUATOR BODY WHERE THE PLUG IS THREADED IN. THE ACTUATOR WAS REPLA	CED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070301003)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007052400208	20070524	00208	EA  	2007	5	24	CA070301004      	1	20070301	G	2760	6009260273	ROD             			CNDAIR	CL601 	CL6012A12   	1900303	EA  										SPOILER	CORRODED        	W				O				OTHER                   				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			10927								(CAN) DURING THE PILOT PRE-FLIGHT CHECKS THE LT FLIGHT SPOILER INDICATED DEPLOYED WHEN STOW WAS SELECTED. THE FLIGHT SPO	ILER STOW/DEPLOY HANDLE WAS STIFF AT THE STOW EXTREMELY. VISUAL CONFIRMATION REVEALED THAT THE FLIGHT SPOILER WAS NOT FU	LLY STOWED BUT THE RT SPOILER WAS. INVESTIGATION REVEALED THAT THE ROD ENDS OF THE 15 DEGREE CONTROL ROD WERE CORRODED W	ITH RED RUST AND WERE NOT ABLE TO MOVE RESTRICTING THE FEEDBACK OF THE FLIGHT SPOILER CONTROL UNITS ON THE LT SIDE. OPER	ATIONS USING TYPE 4 ANTI-ICING FLUIDS HAVE SHOWN TO CAUSE RED RUST CORROSION ON UNPROTECTED STEEL. THERE CURRENTLY IS NO	 REQUIREMENT TO TREAT THE SURFACES WITH A CORROSION INHIBITOR. THE USE OF TYPE 4 ANTI-ICING FLUIDS CONTRIBUTING TO CORRO	2	L	7	2 	4F			RT	A21AE   					 
2007053000050	20070530	00050	EA  	2007	5	30	CA070302001      	1	20070228	G	2497		WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						DAMAGED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER A NORMAL LANDING AND WHILE TAXING TO THE GATE, THE FLT CREW REPORTED INTERMITTENT ARCING AND SMOKE COMING FR	OM BEHIND THE CAPTAINS SIDE CB PANEL.  AIRCRAFT DEPLANED NORMALLY.  ELECTRICAL POWER WAS SHUT DOWN AND FIRE CREW WERE CA	LLED TO CHECK OF FIRE.  NO FURTHER REPORTS OF SMOKE/FIRE AFTER POWER WAS REMOVED FROM THE AIRCRAFT.   UPON FURTHER INVES	TIGATION, MAINTENANCE NOTED THAT (2) BUS FEEDER WIRES BECAME UNSECURED AND ARCED ON THE BULKHEAD WHICH RUNS PARALLEL TO 	B SCREEN TRAILING EDGE ON CAPTAINS SIDE AND APPROX FS280.  DAMAGE WAS NOTED TO WIRE TERMINAL ENDS AND WIRE INSULATION AN	D WELL AS BURN MARKS ON BULKHEAD/STRINGER AND 2 RIVETS.  NO DAMAGE TO EXTERNAL FUSELAGE SKIN.  BURN ON BULKHEAD IS 1 INC	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007053000051	20070530	00051	EA  	2007	5	30	CA070302002      	1	20070225	G	5410		COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT NACELLE	DEPARTED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) FLIGHT 3808, REPORTED A LOUD NOISE SHORTLY AFTER DEPARTURE, ON LANDING DISCOVERED COWLING MISSING AND UNKNOWN DAMA	GE TO HORIZONTAL  STABILIZER, NO REPORTED INJURIES, SN 7849 (REG N456ZW).  WHAT COLLATERAL DAMAGE TO HZ STAB AND OTHER A	REAS? HZ STAB LEADING EDGE AND HZ STAB CENTER BULLET CAP SIGNIFICANT IMPACT DAMAGE ASSUMED FROM LT UPPER FAN COWL DEPART	ING THE AIRCRAFT.   WHAT POINT IN DEPARTURE WAS (LOAD NOISE) HEARD? (LOUD NOISE) ASSUMED TO BE (CARGO SHIFT) NOW SUSPECT	ED AS COWL DEPARTURE AT 2800 FEET ON INITIAL CLIMB OUT, ENROUTE.  BECAUSE PILOTS ASSESSED NOISE TO BE (CARGO SHIFT) THEY	 ELECTED TO CONTINUE.  LT UPPER FAN COWL WAS RECOVERED BY AND CURRENTLY RETAINED BY US COAST GUARD FROM LOCATION OUTSIDE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007053000052	20070530	00052	SW  	2007	5	30	CA070302004      	1	20070228	G	6230	206010003001	CONE SET        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN ROTOR TORQUE CHECK WAS PERFORMED ON M/R MAST NUT BETWEEN 3 TO 8 FLIGHT HOURS IAW THE MM CHAPTER 5, AND MM, SE	CTION 62-7, PARAGRAPH 5.    INITIAL TORQUE CHECK OF MAST NUT TORQUE WAS FOUND BELOW MINIMUM SPECIFIED TORQUE OF 250 FT/L	BS, IAW MM.  A SUBSEQUENT TORQUE CHECK WAS PERFORMED AFTER SECOND FLIGHT OF 3 HOURS WITH THE SAME RESULTS, MAST NUT TORQ	UE FALLING BELOW MINIMUM TORQUE VALUE OF 250FT/LBS.    UPON VISUAL INSPECTION IN THE AREA OF THE CONE SET TO TRUNNION,  	IT WAS FOUND THAT ONE OF THE SPLIT CONES HALVES HAD MOVED.   THEREFORE DID NOT PROVIDE A TRUE SEAT FOR THE SPLIT CONES T	O THE M/R TRUNNION AS CONE SET AND WAS PARTIALLY COCKED.    IT IS SUSPECTED THAT EACH OF THE 2 TORQUE CHECK ADJUSTMENTS 	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007053000053	20070530	00053	NM  	2007	5	30	CA070305001      	1	20070303	G	2752	NAS1611130	O-RING          	BOEING      		BOEING	727   	727247      	138408F	NM  										DIRVE MOTOR	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA			69942			84630D					(CAN) AIRCRAFT EXPERIENCED LOW PRESSURE WARNING LIGHT FROM THE (A)  HYD SYSTEM.  DUE TO WEATHER THE CREW DECIDED THAT A 	RETURN TO DEPARTURE POINT WOULD BE THE BEST OPTION. THE CREW DECLARED AN EMERGENCY AND RETURNED WHERE THEY HAD A SAFE LA	NDING AND THE AIRCRAFT WAS TOWED OFF THE RUNWAY TO THE RAMP.  MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THAT THE OB F	LAP DRIVE HYD MOTOR WAS LEAKING HYD FLUID FROM THE CASE DRAIN TUBE. DUE TO WEATHER THE OB FLAP DRIVE HYD MOTOR WAS REPLA	CED THE NEXT DAY. SYSTEM WAS SERVICED AND THE SYSTEM WAS LEAK AND FUNCTION TESTED SERVICEABLE. THE AIRCRAFT DEPARTED ON 	MAR.3, 2007 WITH NO FURTHER FAULTS. (TC NR 20070305001)	2	L	7	3 	4F				A3WE    					 
2007053000054	20070530	00054	EA  	2007	5	30	CA070305002      	1	20070305	G	3233	MS2125004012	BOLT            			DHAV  	DHC8  	DHC8311     	1386006	EA  										ACTUATOR FITTING	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ACCOMPLISHMENT OF C-CHECK, THE NOSE ACTUATOR FUSELAGE FITTING WAS FOUND WITH (2) BOLTS SHEARED. SB 8-53	-50 FOR THIS FAILURE. THE CUT IN S/N WAS 403 AND OUR A/C WAS S/N:410. THE MODIFICATION 8/2140 WAS TRULY ACCOMPLISHED. TH	E FITTING WAS INSTALLED WITH BIGGER BOLTS BUT (2) OF THOSE BOLTS WERE SHEARED.  (TC NR 20070305002)				2	H	7	2 	4T			RT	A13NM   					 
2007053000055	20070530	00055	NM  	2007	5	30	CA070305003      	1	20070305	G	2497	CL12068161	RELAY           			DHAV  	DHC8  	DHC8102     	2809003	NM  										ECU	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ACCOMPLISHMENT OF THE INSPECTION TASK 7320/02, BOTH RELAY (RELAYS 7611-K3 AND K4) BASES WERE FOUND BROK	EN AND BARELY MAKING CONTACT. SHOULD BOTH OF THEM HAVE FALLEN OFF AND DISCONNECTED IN FLIGHT, BOTH ECU`S WOULD HAVE HAD 	A COMPLETE POWER FAILURE. ECU SYSTEMS ARE DESIGNED TO HAVE POWER FED FROM NR 1 AND NR 2 ESSENTIAL BUSES. BOTH POWER SOUR	CES GO THROUGH THEIR RESPECTIVE RELAYS K3 AND K4, A BROKEN BASE WOULD COMPROMISE THE 2 POWER SOURCES SIMULTANEOUSLY, RES	ULTING IN EACH ECU REVERTING TO MANUAL MODE. THIS RELAY BASE PROBLEM WAS REPORTED BY ME FEW TIME FOR DIFFERENT SYSTEM ON	 DIFFERENT A/C AND DIFFERENT OPERATOR. (TC NR 20070305003)	2	H	7	2 	4T			RT	A13NM   					 
2007053000056	20070530	00056	CE  	2007	5	30	CA070305004      	1	20070228	G	5610	11438402522	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	FAILED          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			21017								(CAN) CO-PILOTS WINDSHIELD SHATTERED IN CRUISE.  AIRCRAFT DESCENDED IAW ABNORMAL OCCURRENCE CHECKLIST AND BROUGHT CABIN 	DIFF DOWN TO BELOW 2PSI.  AIRCRAFT DESCENDED TO 11000 FT LOWERED CABIN ALTITUDE AT 500 FPM TO 11000FT.  PUT CABIN INTO D	UMP MODE AND CONTINUED FLIGHT WITHOUT INCIDENT. WINDSHIELD WAS REPLACED WITH IMPROVED PART. (TC NR 20070305004)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007053000057	20070530	00057	WP  	2007	5	30	CA070306001      	1	20070223	G	2916		RESERVOIR       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION HYDRAULIC FLUID FOUND VERY LOW, DETERMINED FLUID WAS LEAKING OUT OF THE VENT CAP ON HYDRAULIC RE	SERVOIR. FLUID TOPPED UP TO CENTER OF SIGHT GLASS. AIRCRAFT GROUND RAN, DETERMINED FLUID WAS RISING IN RESERVOIR AND VEN	TING OUT OF VENT CAP. RESERVOIR SENT TO MFG. REINSTALLED AFTER REPAIR, GROUND RAN AND FOUND HYDRAULIC LEVEL TO STAY AT C	ENTER OF SIGHT GLASS. (TC NR 20070306001)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007053000058	20070530	00058	SW  	2007	5	30	CA070306002      	1	20070226	G	6310	206040118001	COUPLING        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) C-GELT`S MAIN DRIVESHAFT P/N 206-040-015-103, S/N A-1331, 600 HR INSPECTION AND REPACK C/W FEB 22/07 AT 13635.5 HR	S. TEST FLOWN 0.3 HRS, FLEW 7.1 HRS FEB 24 AND 25, ENGINEER FOUND TRANS. SIDE LEAKING GREASE AND COUPLING OVERHEATED. DR	IVE SHAFT S/N A-2441 REMOVED FROM AC WITH FRESH 600 HR INSP. AND REPACK INSTALLED ON C-GELT. WHICH FAILED IN 11.7 HRS. W	ITH THE SAME PROBLEM. DRIVE SHAFT S/N A1331 OVERHAULED WITH NEW INNER GEAR, NEW OUTER COUPLING, NEW O-RINGS, AND GREASE 	(PN 204-040-755-5 EXP. NOV 2/08) INSTALLED ON YHY, FAILED IN 23 MINUTES FLYING TIME, SAME PROBLEM (TRANSMISSION SIDE) TH	E SAME TUBE OF GREASE WAS USED FOR ALL THE REPACKS. (TC NR 20070306002)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007053000059	20070530	00059	NM  	2007	5	30	CA070306003      	1	20070308	G	2150	20405010	ACM             			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					LEFT	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER DERPARTING, A SMOKE SMELL/HAZE WAS NOTICED IN THE CABIN AREA. THE AIRCRAFT RETURNED TO POINT OF DEPA	RTURE AND LANDED WITHOUT FURTHER PROBLEM. THE CREW ADVISED MAINTENANCE THEY SUSPECTED THE LT PACK. THE SMOKE SMELL SOURC	E WAS VERIFIED AS THE THE LT AIR CYCLE MACHINE. THE AIRCRAFT WAS RELEASED UNDER THE MEL. THE AIR CYCLE MACHINE WAS REPLA	CED THE FOLLOWING DAY. (TC NR 20070306003)			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2007053000060	20070530	00060	EU  	2007	5	30	CA070306004      	1	20070308	G	5610		WINDSHIELD      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ON DESCENT THE LT WINDSHIELD OUTER PANE FAILED. THE AIRCRAFT LANDED AT DESTINATION WITHOUT FURTHER PROBLEM. MAINTE	NANCE INSPECTED THE AIRCRAFT PRIOR TO RETURN UNDER MEL, WHERE THE WINDSHIELD WAS REPLACED. (TC NR 20070306004)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007053000061	20070530	00061	NE  	2007	5	30	CA070306005      	2	20070305	G	7510	82110588003	DUCT            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	BLEED AIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			38233	38233							(CAN) DURING MAINTENANCE, TROUBLESHOOTING FOR LOW FLOW FROM CABIN GASPERS, MAINTENANCE, WHILE INSIDE THE AFT CARGO COMPA	RTMENT FELT THE REAR PRESSURE BULKHEAD AS BEING WARM/HOT. INVESTIGATION IN THE AFT EQUIPMENT BAY, FOUND THE ENGINE BLEED	 AIR / APU / AIR-CONDITIONING PACKS JUNCTION DUCT CRACKED, CRACK EXTENDED AT LEAST 50 PERCENT OF CIRCUMFERENCE AND WAS O	PEN BY APPROX .2500 INCH.  DUCT ASSEMBLY REPLACED, FUNCTION CHECKS CARRIED OUT.  AIRCRAFT RETURNED TO SERVICE. (TC NR 20	070306005)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007053000062	20070530	00062	EA  	2007	5	30	CA070306006      	1	20070304	G	3220	498003	DAMPER          			CNDAIR	CL600 	CL6002C10   	1390015	EA  										NLG	MALFUNCTIONED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			3750 								(CAN) ON LANDING CREW REPORTED AN AIRFRAME VIBRATION.  CREW INDICATED THAT THE VIBRATION DEMINISHED AS THE AIRCRAFT SPEE	D REDUCED.  AIRCRAFT TAXIIED TO GATE WITHOUT FURTHER INCIDENT.  MAINTENANCE INSPECTION REVEALED LOOSE APEX NUT ON LT SHI	MMY DAMPER.  NEW SHIMMY DAMPER AND ASSOCIATED PARTS ARE BEING REPLACED. (TC NR 20070306006)				2	L	7	2 	4F			RT	A21EA   					 
2007053000063	20070530	00063	EU  	2007	5	30	CA070307001      	1	20070302	G	3240	90002340PR	BRAKE ASSY      			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E6    	30015	NE  					MLG	ICED            	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) ON LANDING, AT 90 KNOTS THE LT OB TIRE BLEW, DAMAGING PART OF THE GEAR DOOR ASSEMBLY. ACFT DEPARTED WHERE A SEVERE	 SNOW STORM WAS TAKING PLACE, IT WAS NOTED THAT WATER WAS RUNNING FROM THE BRAKE ASSEMBLY AND DRIPPING FOR HOURS, SUSPEC	T BRAKE BECAME PACKED WITH SNOW AND ICE. (TC NR 20070307001)				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2007053000064	20070530	00064	EA  	2007	5	30	CA070307002      	1	20070305	G	2560	110124007	BUCKLE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SEAT BELT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 AN INSPECTION FOR INTERFERENCE BETWEEN THE YOKE AND SEAT	BELT BUCKLE WAS CARRIED OUT IAW NM-06-29.THE RESTRAINT RELEASE MECHANISM ON PILOT AND COPILOTS SEAT BELTS CAN BE OPERATE	D UNINTENTIONALLY BY EXTREME NOSE UP AND ROLL COMMANDS OF THE CONTROL COLUMN. (TC NR 20070307002)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000065	20070530	00065	EA  	2007	5	30	CA070307003      	1	20070305	G	5730	C6W1017	SKIN PANEL      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17756								(CAN) DEBONDING OF UPPER WING SKIN, OB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR	 CARRIED OUT IAW REO6-57-30-V013 REV A. (TC NR 20070307003)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000066	20070530	00066	EA  	2007	5	30	CA070307004      	1	20070305	G	5730	C6W1017	SKIN PANEL      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RWS 72-97	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17756								(CAN) DEBONDING OF UPPER WING SKIN, IB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR	 CARRIED OUT IAW REO6-57-30-V012 REV A. (TC NR 20070307004)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000067	20070530	00067		2007	5	30	CA070307005      	4	20070306	G	3160	0660312525	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EFIS	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, A (DU) WARNING APPEARED ON THE CO-PILOTS EADI DISPLAY INDICATING INSUFFICENT COOLING. THE DISPLAY U	NIT WAS REPLACED. (TC NR 20070307005)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000068	20070530	00068	EA  	2007	5	30	CA070307006      	1	20070305	G	5730		SKIN            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17756								(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM T	HE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V017 (YW 85-91.25) AND REO6-57-30-V018 (YW 127-146). (TC NR 200703	07006)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000069	20070530	00069	EA  	2007	5	30	CA070307007      	1	20070305	G	5730	MS20470AD	SKIN            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17756								(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM T	HE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V019 (YW 85-91.25) AND REO6-57-30-V020 (YW 122-135). (TC NR 200703	07007)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000070	20070530	00070	EA  	2007	5	30	CA070307008      	1	20070305	G	5730	C6W101427	SKIN PANEL      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17756								(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM T	HE EXHAUST STACKS. REPAIRS TO CORRODED RIVETS WAS INITIATED AND REVEALED CORROSION UNDER THE RIVET HEADS EXISTED TO A DE	PTH OF 0.011. REPAIRS CARRIED OUT I.A.W. VIKING REO6-57-30-V025 (YW 85-97.25). I.C.A.`S PENDING D.T.A. BY VIKING. (TC NR	 20070307008)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007053000071	20070530	00071	SW  	2007	5	30	CA070307009      	1	20070305	G	2910	66D44	REGULATOR       			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AC DEPARTED BASE AND UPON GEAR RETRACTION BOTH LT AND RT HYD PRESSURE LIGHTS ILLUMINATED FOR 3-4 SECONDS THEN WENT	 OUT.  AIRCRAFT RETURNED TO BASE AND UPON INVESTIGATION IT WAS FOUND THAT NO RESIDUAL HYD PRESSURE WAS PRESENT AFTER ENG	INE SHUTDOWN.  UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE 31 PSI REGULATOR WAS CONTAMINATED WITH HYD FLUID.  	THE REGULATOR CHECK VALVE HAD BEEN INSTALLED INCORRECTLY.  THE CHECK VALVE WAS REPOSITIONED AND THE REGULATOR WAS REPLAC	ED.  GEAR WINGS WERE CARRIED OUT SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070307009)		2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007053000072	20070530	00072	NE  	2007	5	30	CA070307010      	2	20070307	G	7497	WIRE	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			286  			E051A254					(CAN) GOVERNOR WAS LAZY AND SNAGGED BY PILOT.  UPON FURTHER INVESTIGATION, THE MAGNETO WAS REMOVED AND PRIMARY COIL WIRE	 WAS TOUCHING AND CHAFING ON TACH POINT CONNECTOR. THIS MAY BE THE POSSIBLE CAUSE FOR LAZY GOVERNOR.  NEW MAGNETO INSTAL	LED PROBLEM RECTIFIED. MAGNETO SENT BACK FOR WARRANTY. (TC NR 20070307010)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008032400412	20080324	00412	EU  	2008	3	24	CA070307011      	1	20070307	G	6710		CYCLIC CONTROL  			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					MAIN ROTOR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) CYCLIC CONTROLS JAMMED IN NEUTRAL POSITION, CYCLIC WAS ABLE TO MOVE AFT, FWD, AND LT BUT WAS UNABLE TO MOVE CYCLIC	 TO THE RT DURING LEVEL CRUISE AT 2500 FT AGL. REDUCED AIRSPEED TO 65 KNOTS AND CONTROLS BROKE FREE AND OPERATED NORMALL	Y.  THEN FLEW BACK TO THE HANGER AT AN AIRSPEED OF 65 KNOTS AND CONTROLS FELT NORMAL UNTIL AT ABOUT 200 FT AGL AND AIRSP	EED AT ABOUT 40 KNOTS WITH 300 FT IAW MINUTE DESCENT RATE THE CYCLIC JAMMED ON THE RT SIDE AGAIN. THE AC SLOWLY STARTED 	A BANK AND AN OVERSHOOT AND PROCEEDED TO THE RUNWAY. DURING THE OVERSHOOT, BROUGHT AIRSPEED BACK UP TO AROUND 65 KNOTS A	ND JOINED A RT DOWNWIND FOR RUNWAY 13. ON A BASE LEG, SHUTOFF HYD AND PERFORMED A NORMAL HYD FAILURE APPROACH. CONTROLS 	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2007053000073	20070530	00073	SO  	2007	5	30	CA070308001      	1	20070302	G	2842	68101002	FLOAT           			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC3Y	HCC3YF1     	GL  	FUEL CELL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7968 								(CAN) HOLE IN FLOAT WAS EXTREMELY WORN AND FLOAT FELL OFF. (TC NR 20070308001)						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P25EA	 
2007053000074	20070530	00074		2007	5	30	CA070308002      	4	20070306	G	2397	J176037	WIRE            	COLLINS     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	NR 2 COMM HEAD	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			16604			14617					(CAN) FLIGHT CARRIED OUT MAR. 5, 2007, NR 2 COMM DISPLAY WENT BLANK.  CONTROL HEAD REPLACED WITH LOANER UNIT, GROUND TES	TED OK. NEXT FLIGHT AIRCRAFT TOOK OFF AND UPON ROTATION THE CREW SMELLED SOMETHING BURNING AND SAW SMOKE COMING FROM THE	  NR 2 COMM CONTROL HEAD. AIRCRAFT RETURNED TO BASE.  CONTROL HEAD REMOVED FOR REPAIR AND INVESTIGATION. FOUND WIRE P/N 	J176037 IN NOSE AVIONICS BAY GOING FROM RELAY J304 TO TRANSCEIVER TRAY WITH CONTINUITY TO GROUND.  WIRE REPAIRED AND ORI	GINAL CONTROL HEAD INSTALLED AFTER REPAIR, COMM OPERATED FOR 2 HOURS ON THE GROUND WITHOUT FAULT. NO PROBLEMS REPORTED T	HE SUBSEQUENT FLIGHT. (TC NR 20070308002)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007053000075	20070530	00075	EA  	2007	5	30	CA070308003      	1	20070307	G	7603	2100140007	GEARBOX         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			1740 								(CAN) DURING CLIMB, THE RT ENGINE WAS NOT ABLE TO ACHIEVE CLIMB POWER. THE AIRCRAFT DIVERTED TO ANOTHER AIRPORT AND LAND	ED UNEVENTFULLY. INVESTIGATION REVEALED THAT THE THROTTLE GEARBOX HAS AN AREA WHERE MOVEMENT OF THE THROTTLE HAS NO EFFE	CT ON THE MFC. THIS CONDITION WOULD NOT ALLOW THE MFC TO REACH THE MAX POWER STOP. MFG SB 604-76-004 HAD NOT BEEN COMPLI	ED WITH AT THIS TIME NOR WAS IT REQUIRED AT THIS TIME BUT WAS PLANNED TO BE COMPLETED. THERE ARE (2) AD`S FOR THROTTLE G	EARBOX WEAR ON THE RJ FLEET.  REF: AD 2005-06-04, AD 2004-05-12.  AFTER REPAIR AND RETURN OF THE AIRCRAFT TO THE MAIN BA	SE AND EXAMINATION OF THE FAILED PART THEN MORE INFORMATION WILL BE PROVIDED. (TC NR 20070308003)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007053000076	20070530	00076	WP  	2007	5	30	CA070308004      	1	20070306	G	2430		CONTROL SWITCH  			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  		SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WHILE CARRYING OUT FLIGHT TRAINING THE LT GENERATOR WAS TURNED OFF. WHEN SELECTED BACK ON, IT WAS NOTED THAT SMOKE	 WAS COMING FROM THE VOLTAGE REGULATOR. THE GANG BAR WAS SELECTED TO SHUTOFF DC POWER. DURING TROUBLESHOOTING THE MAINTE	NANCE CREW DISCOVERED AN AN960-10L WASHER HAD SHORTED OUT THE WIRE ATTACHMENT LUGS ON THE BACK OF THE GENERATOR CONTROL 	SWITCH. A REPLACEMENT VOLTAGE REGULATOR WAS INSTALLED AND THE WIRING SYSTEM WAS INSPECTED. NO FURTHER DAMAGE WAS NOTED. 	THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070308004)		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2007053000077	20070530	00077	EU  	2007	5	30	CA070309001      	1	20070303	G	2820	110BR02	VALVE           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R408	CR4086123F17	EU  	FUEL CROSSFEED	MALFUNCTIONED   	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AC WAS IN CRUISE FLIGHT, WHEN THE FLIGHT CREW OPENED THE FUEL CROSSFEED VALVE TO BALANCE THE FUEL LOAD. WHEN THE F	LIGHT CREW SELECTED THE LT BOOST PUMPS TO OFF, THE NR 1 ENGINE FLAMED OUT. THE FLIGHT CREW FEATHERED ENGINE NR 1. THE PI	LOT THEN CLOSED THE FUEL CROSSFEED VALVE, SWITCHED THE LT FUEL BOOST PUMPS TO ON AND SUCCESSFULLY RELIT ENGINE NR 1. THE	 AIRCRAFT CONTINUED WITH OUT FURTHER DIFFICULTY.  UPON ARRIVAL, MAINTENANCE BLED THE FUEL SYSTEM, CHECKED FOR FUEL CONTA	MINATION AND EXTENSIVELY GROUND RAN ENGINE NR 1. NO FAULTS WERE FOUND. FURTHER INVESTIGATION HAS DETERMINED HS SB 28/27 	WHICH PREVENTS ACCUMULATION OF AIR IN THE CROSSFEED LINE HAS NOT BEEN ACCOMPLISHED ON THIS AIRCRAFT. IT IS BELIEVED AIR 	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P17BO	 
2008021900147	20080219	00147	EU  	2008	2	19	CA070309002      	1	20070308	G	6210	C621A1006103	BLADE           			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			995  	995  							(CAN) BLADE CRACKED BY TRAILING EDGE OF TRIM TAB, IB SIDE. (TC NR 20070309002)						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2007053000078	20070530	00078	WP  	2007	5	30	CA070309003      	1	20070302	G	6210	500P2100101	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			2597 								(CAN) PILOT FELT A VIBRATION AND UPON LANDING CHECKED MAIN ROTOR BLADES. A CRACK APPROXIMATELY 18 INCHES FROM THE ROOT, 	RUNNING PERPENDICULAR TO THE TRAILING EDGE WAS DISCOVERED. IT APPEARS AS IF THE BLADE DEBONDED AT A RIB, AS THE CRACK FO	LLOWS STRAIGHT FROM THE RIB TOWARD THE C-CHANNEL BEFORE IT TRAILS OFF TO THE SIDE.  MDHI )OEM) HAS SUGGESTED THAT THE CA	USE WAS TOO MUCH TENSION ON THE BLADES AT TIE-DOWN, OIL-CANNING BETWEEN THE RIBS PUTTING PRESSURE ON THE BOND. (TC NR 20	070309003)		1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007053000079	20070530	00079	EU  	2007	5	30	CA070310001      	1	20070302	G	2752	9787320309	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			2242 	2242 							(CAN) FLAPS WOULD WORK AS NORMAL, EVEN AFTER 4 HOUR FLIGHT AT -45. AFTER LANDING & SELECTING FLAPS UP,  (FLAPS) CAUTION 	WOULD COME ON NR FLAPS WOULD NOT MOVE. NORMAL GROUND RESET WOULD NOT WORK. FLAP CONTROL 1 AMP C/B APPEARED TO BE (BLOWN)	 BUT NOT POPPED. AFTER RESETTING C/B, NORMAL FLAP RESET WOULD WORK. TRYING TO MOVE FLAPS AGAIN WOULD CAUSE THE SAME PROB	LEM. NOTE THIS DEFECT WOULD ONLY OCCUR IF THE GROUND TEMP WAS -5 TO -12. AFTER WARMING THE AIRCRAFT IN A HANGAR FLAPS WO	ULD RESET NR WORK. UPON INSPECTION OF THE ACTUATORS IT WAS DISCOVERED THAT 3 OF THE 4 ACTUATORS WERE HEATING UP. +40 TO 	+50 C. ACTUATORS WERE REMOVED FROM SERVICE. ALSO NOTED WAS FLAP CONTROL WARNING UNIT FAILURE CODES INCLUDED TOO HIGH CUR	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000080	20070530	00080	EU  	2007	5	30	CA070310002      	1	20070302	G	2752	97897320309	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			2242 	2242 							(CAN) FLAPS WOULD WORK AS NORMAL, EVEN AFTER 4 HOUR FLIGHT AT -45. AFTER LANDING AND SHUTDOWN (FLAPS) CAUTION WOULD COME	 ON AND FLAPS WOULD NOT MOVE. NORMAL GROUND RESET WOULD NOT WORK. FLAP CONTROL 1 AMP C/B APPEARED TO BE (BLOWN) BUT NOT 	POPPED. AFTER RESETTING C/B, NORMAL FLAP RESET WOULD WORK. TRYING TO MOVE FLAPS AGAIN WOULD CAUSE THE SAME PROBLEM. NOTE	 THIS DEFECT WOULD ONLY OCCUR IF THE GROUND TEMP WAS -5 TO -12. AFTER WARMING THE AIRCRAFT IN A HANGAR FLAPS WOULD RESET	 AND WORK. UPON INSPECTION OF THE ACTUATORS IT WAS DISCOVERED THAT 3 OF THE 4 ACTUATORS WERE HEATING UP. +40 - +50 C. AC	TUATORS WERE REMOVED FROM SERVICE. ALSO NOTED WAS FLAP CONTROL WARNING UNIT FAILURE CODES INCLUDED TOO HIGH CURRENT DRAW	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000081	20070530	00081	EU  	2007	5	30	CA070310003      	1	20070302	G	2752	9787320309	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			2242 	2242 							(CAN) FLAPS WOULD WORK AS NORMAL, EVEN AFTER 4 HOUR FLIGHT AT -45. AFTER LANDING AND SHUTDOWN (FLAPS) CAUTION WOULD COME	 ON AND FLAPS WOULD NOT MOVE. NORMAL GROUND RESET WOULD NOT WORK. FLAP CONTROL 1 AMP C/B APPEARED TO BE (BLOWN) BUT NOT 	POPPED. AFTER RESETTING C/B, NORMAL FLAP RESET WOULD WORK. TRYING TO MOVE FLAPS AGAIN WOULD CAUSE THE SAME PROBLEM. NOTE	 THIS DEFECT WOULD ONLY OCCUR IF THE GROUND TEMP WAS -5 TO -12. AFTER WARMING THE AIRCRAFT IN A HANGAR, FLAPS WOULD RESE	T AND WORK. UPON INSPECTION OF THE ACTUATORS IT WAS DISCOVERED THAT 3 OF THE 4 ACTUATORS WERE HEATING UP. +40 - +50 C. A	CTUATORS WERE REMOVED FROM SERVICE. ALSO NOTED WAS FLAP CONTROL WARNING UNIT FAILURE CODES INCLUDED TOO HIGH CURRENT DRA	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007053000082	20070530	00082	NM  	2007	5	30	CA070312001      	1	20070220	G	2913		SHAFT           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD PUMP	SHEARED         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			20954	8792 		MX422697					(CAN) AFTER START OF THE NR 1 ENGINE, THE HYDRAULIC PUMP CAUTION LIGHT REMAINED ON WITH ZERO PRESSURE INDICATED ON THE A	SSOCIATED HYDRAULIC SYSTEM PRESSURE GAUGE. AIRCRAFT ENGINES WERE SUBSEQUENTLY SHUTDOWN AND ENGINEERING CONTACTED TO COND	UCT DEFECT RECTIFICATION PRIOR TO RETURNING THE AIRCRAFT TO SERVICE. ENGINEERING DEFECT INVESTIGATION REVEALED THAT THE 	NR 1 ENGINE DRIVEN HYDRAULIC PUMP DRIVE SHAFT WAS SHEARED. THE HYDRAULIC PUMP WAS REPLACED WITH A SERVICEABLE ASSY IAW A	MM 29-10-11 AND THE AIRCRAFT SUBSEQUENTLY RETURNED TO SERVICE.  (TC NR 20070312001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007053000083	20070530	00083	NE  	2007	5	30	CA070312002      	2	20070306	G	7230		BLADES          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					COMPRESSOR	DAMAGED         	W				A				UNSCHED LANDING         				R	A		PARTIAL RPM/PWR LOSS      	FLAME/FIRE                		CL	CLIMB          	1			CA			40214	18251				731775			(CAN) ON TAKEOFF AT 500 AGL, 3 TO 4 STALLS ON NR 2 ENGINE, LOUD POPPING NOISE, ATC SAW FLAMES COMING OUT. AIRCRAFT RETUR	NED TO DEPARTURE, ENGINE BOROSCOPE FOUND DAMAGED COMPRESSOR BLADES FROM STAGE 6 TO STAGE 9. ENGINE REMOVED FROM AIRCRAFT	 AND SENT TO SHOP FOR INVESTIGATION. (L-4298804) (TC NR 20070312002)				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007053000084	20070530	00084	NM  	2007	5	30	CA070312003      	1	20070312	G	4940	360581217	STARTER         			BOEING	737   	73735B      	13844BM	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					APU	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) APU SHUTDOWN ON ITS OWN AND WOULD NOT RE-START. NEW STARTER INSTALLED. NEW STARTER BLEW APART ON FIRST START ATTEM	PT. SECOND STARTER INSTALLED AND OPERATED SERVICEABLE. (TC NR 20070312003)					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007053000085	20070530	00085	NM  	2007	5	30	CA070312004      	1	20070307	G	3810		LINE            			BOEING	767   	767306      	1385148	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					POTABLE WATER	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING NORMAL WALK AROUND FOUND WATER LEAKING OUT OF THE BELLY OF THE AIRCRAFT, FORWARD AREA. SUBSEQUENT INVESTIGA	TION FOUND CLAMSHELL (CLAMP) P/N CA62505-56BL HOLDING POTABLE WATER LINE THAT RUNS OVER FWD. E&E COMPARTMENT TOWARD THE 	FWD. LAVATORY FAILED RESULTING IN THE TWO EICAS COMPUTERS BEING SOAKED WITH WATER.  BOTH COMPUTERS CHANGED, CLAMP REPLAC	ED WITH APPROVED P/N 14C33-08, METAL NOT  THE ORIGINAL PLASTIC. (TC NR 20070312004)			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2007053000086	20070530	00086	EA  	2007	5	30	CA070312005      	1	20070225	G	5220	1196411	HOUSING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ECAPE HATCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11157								(CAN) CREW ESCAPE HATCH HANDLE HOUSING FOUND CRACKED AND OUTER HANDLE WAS CORRODED. THE PART OF THE HOUSING THAT FITS IN	SIDE OF THE INNER HANDLE WAS CRACKED COMPLETELY OFF. (TC NR 20070312005)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008021900156	20080219	00156	CE  	2008	2	19	CA070312006      	1	20070222	G	3230	1225P363	PRESSURE SWITCH 		ADI7999001  	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING LANDING GEAR SWINGS IT WAS NOTICED THAT THE LANDING GEAR PUMP WAS HESITATING. PROBLEM WAS TRACED BACK TO TH	E PRESSURE SWITCH. SWITCH WAS REPLACED AND GEAR SWUNG, FAULT FEE. (TC NR 20070312006)					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2008021900171	20080219	00171	SO  	2008	2	19	CA070312007      	1	20070303	G	3246	16102100	WHEEL HALF      			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	LANDING GEAR	DESTROYED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			2203 								(CAN) SUSPECT HARD LANDING WITH SIDE MOVEMENT STRESSED WHEEL HALF CASTING. THE BACK STOP PORTION OF HUB CASTING HAS A NE	W CLEAN BREAK. WITH RACE BROKEN, BEARING CONE FAILED. WHEEL ASSEMBLY TIPPED IN MOUNTING FORK AND RODE ON BRAKE CALIBER T	ORQUE PLATE. BRAKE DISK WORE ON INSIDE OF MOUNTING FORK. (TC NR 20070312007)				1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
2007053000087	20070530	00087	NM  	2007	5	30	CA070312008      	1	20070222	G	3230	10134501	TORQUE LINK     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT MLG	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			5304 								(CAN) DURING TAKEOFF A SEVERE VIBRATION WAS NOTICED ON THE ENTIRE AC, THE CREW ABORTED THE TAKEOFF SUCCESSFULLY. MAINTEN	ANCE FOUND THE LT MLG TORQUE LINK BROKE INTO 2 PARTS ALONG WITH DAMAGE TO LT IB AND LT OB TIRES, BRAKE UNITS NR 1 AND 2,	 WIRING AND BRAKE LINES, AND STRUCTURE DAMAGE TO THE NACELLE. MFG TO CARRY OUT INVESTIGATION AS TO THE CAUSE OF TORQUE L	INK FAILURE.  (TC NR 20070312008)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008021900187	20080219	00187	SO  	2008	2	19	CA070312009      	1	20070220	G	2420	587857	ALTERNATOR      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LEFT	FAILED          	W				O				OTHER                   				H	P		ELECT. POWER LOSS-50 PC   	NO WARNING INDICATION     		CR	CRUISE         	1			CA											(CAN) LT ALTERNATOR FAILED AT CRUISE, FAULT-FIELD POWER FUSE BLOWER.  RT ALTERNATOR FAILED/NOT ON LINE, FAULT, BAD ALTER	NATOR MASTER SWITCH OR NOT ON.  RT INOP ALTERNATOR SWITCH/RELAY FAILED SO NO COCKPIT INOP LIGHT.  AC CONTINUED FLIGHT ON	 BATTERY POWER TO DESTINATION.  FLIGHT AT NIGHT -30C AND IFR CONDITIONS.  CONCLUSIONS/RECTIFICATIONS:  LT FIELD FUSE REP	LACED. RT ALTERNATOR INOP SWITCH REPLACED. ALTERNATOR MASTER SWITCH CLEANED/TESTED.  BATTERY CHARGED AND TESTED.  AC AND	 ALTERNATOR SYS OPS CHECKED AND AC RETURNED TO SERVICE. (TC NR 20070312009)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007053000088	20070530	00088	EA  	2007	5	30	CA070312010      	2	20070307	G	7320		COTTER PIN      	HONEYWELL   		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL CONTROL	MISINSTALLED    	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			DE	DESCENT        	1			CA				2504 		A63002					(CAN) ON DESCENT FROM 21000 FEET, THE RT POWER LEVER WAS PULLED BACK BUT THE ENGINE DID NOT RESPOND TO THE COMMAND. ENGI	NE WAS THEN SHUTDOWN TO PREVENT OVERTORQUING.   ON INSPECTION OF FCU LINKAGES, MECHANICS FOUND THE COTTER PIN GOING THRO	UGH INPUT SHAFT AFT OF MAX STOP ARM HAD ONLY ONE LEG BENT OVER.  OTHER LEG, IN CERTAIN POSITIONS WOULD HANG UP ON MIN ST	OP SCREW, PREVENTING FCU ARM FROM RETURNING TO IDLE.  COTTER PIN WAS PROPERLY SECURED AND AIRCRAFT WAS TEST FLOWN WITH N	O FURTHER INCIDENTS. (TC NR 20070312010)		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007053000089	20070530	00089	EA  	2007	5	30	CA070313001      	2	20070312	G	8530	LW16812	LIFTER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	INTAKE	UNLOCKED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1778 	1778 				RL326476T			(CAN) DURING THE REAMING OF A STICKY EXHAUST VALVE GUIDE IN CYLINDER NR 4, IT WAS FOUND THAT THE NR 4 CYLINDER INTAKE HY	DRAULIC LIFTER HAD LOST ITS SNAP RING.  THE WEAR PATTERN SHOWED THAT THE SNAP RING HAD MIGRATED ALONG BETWEEN THE PUSHRO	D AND THE SHROUD TUBE (THE SNAP RING SHOWED WEAR ON ITS INSIDE DIAMETER WERE IT HAD MOVED ALONG THE PUSHROD, AND WEAR ON	 ITS OUTSIDE DIAMETER, WHERE IT HAD WORN ALONG THE INSIDE OF THE PUSHROD SHROUD TUBE). THE SNAP RING WAS FOUND INTACT (S	AME SHAPE), IN THE NR 4 CYLINDER ROCKER BOX.  ONE EXPLANATION IS THAT WHEN THE CYLINDER WAS CHANGED 525.0 HRS PREVIOUS, 	THE SNAP RING WAS NOT PROPERLY INSTALLED IN THE HYDRAULIC LIFTER WHEN IT WAS BLED DOWN BEFORE INSTALLATION, AND IT POPPE	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007053000090	20070530	00090		2007	5	30	CA070313002      	4	20070312	G	6113	05503214	BULKHEAD        	CESSNA      		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			373  								(CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATES	T SB. CRACKS WERE FOUND FORMING PARALLEL FROM THE PROP BOLT HEAD CONTACT SURFACE ON (3) OF THE (6) HOLES. YOU HAVE TO LO	OK VERY CAREFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND HIDE UNDER THE FACTORY PRIMER.  THE	 TORQUE OF THE PROP BOLTS IS SHEAR STRESSING THE BULKHEAD. A COVER PLATE IS NEEDED TO OFFSET THE BOLTS FROM THE THIN ALU	MINUM SHEET METAL BULKHEAD. THIS PROBLEM IS RE-OCCURRING WITH THIS SPINNER ASSY ON SEVERAL OF OUR AC THAT WE MAINTAIN. (	TC NR 20070313002)	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007060100117	20070601	00117	EU  	2007	6	1	CA070313003      	1	20070312	G	3320	8ES00375200	POWER SUPPLY    			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					CABIN LIGHTS	OVERHEATED      	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, FLIGHT CREW OBSERVED WHAT APPEARED TO BE WHITE SMOKE EMANATING FROM READING LIGHT (PSU) PANEL ASSEM	BLY ABOVE SEAT 30 AB. CREW SWITCHED OFF READING LIGHTS AND SMOKE STOPPED. ON ARRIVAL TO THE STATION, MAINTENANCE FOUND O	NE TRANSFORMER PRINTED CIRCUIT BORD SEVERELY OVERHEATED. POWER SUPPLY REPLACED AND SYSTEM TESTED SERVICEABLE.   (TC NR 2	0070313003)			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2007060100118	20070601	00118	NM  	2007	6	1	CA070313004      	1	20070313	G	3230		LANDING GEAR    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NOSE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH TO BASE, THE NLG DOORS DID NOT OPEN AND THE NLG DID NOT EXTEND.  APPROACH CANCELLED, AIRCRAFT ENTE	RED HOLDING PATTERN. GEAR CYCLED WITHOUT SUCCESS NLG EXTENSION. MLG OPERATED NORMALLY. ALTERNATE EXTENSION PROCEDURE CON	DUCTED. NLG REMAINED RETRACTED AND NLG DOORS REMAINED CLOSED. AIRCRAFT PERFORMED A TOUCH AND GO TO SHOCK THE NLG DOWN, W	ITHOUT SUCCESS.  AIRCRAFT CONDUCTED A 60-DEGREE BANK TO APPLY POSITIVE G IN AN EFFORT TO EXTEND THE NLG WITHOUT SUCCESS.	 AIRCRAFT LANDED WITH NLG RETRACTED.  TO COMPLETE FULL INVESTIGATION. AOM NR 210 ISSUED. (TC NR 20070313004)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007060100119	20070601	00119	CE  	2007	6	1	CA070313005      	1	20070312	G	5340	05521335	SUPPORT         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LANDING LIGHT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2647 								(CAN) THE SUPPORT WAS CRACKING AT THE MOUNTING FLANGE BEND RADII AT THE (4) AND (8) O`CLOCK POSITIONS. THE CRACKS HAD PR	EVIOUSLY BEEN STOPDRILLED BUT HAD CONTINUED PAST THE STOPDRILLING.  SUSPECT THAT CRACKING STARTS AT SHARP/ROUGH ALUMINUM	 EDGES AND IS AGGRAVATED BY THE PROPELLERS PROXIMITY CAUSING PULSATION AGAINST THE LIGHT. (TC NR 20070313005)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007060100120	20070601	00120	EA  	2007	6	1	CA070313006      	2	20070308	G	8520	13F1773585	CRANKSHAFT      			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	BROKEN          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA				1289 				RL352361A			(CAN) APPROXIMATELY 45 MILES OUT, THE CREW NOTED A VIBRATION FROM THE LT ENGINE. THE CREW SECURED THE ENGINE AND FEATHER	ED THE PROP IAW THE CHECK LIST.  THE FLIGHT CONTINUED TO DESTINATION WITHOUT INCIDENT.   WITH COWLINGS REMOVED,  NOTED 	THE CASE HAD BEEN BREACHED AND THE CAMSHAFT HAD BROKEN.  WITH NR 5 CYL. REMOVED WE COULD SEE THAT THE CRANKSHAFT WAS BRO	KEN AFT OF THE MAIN BEARING BETWEEN CYLINDER BANKS 2-4 AND 5-6.  THIS PERMITTED THE CRANK SEGMENT WITH CONNECTING RODS F	OR CYL`S 5 AND 6 TO FLAIL AROUND, BREAKING THE CRANKCASE AND CAMSHAFT.   THE ENGINE WILL BE SENT OUT FOR FURTHER TEARDOW	N. PARTS AVAILABLE FOR INSPECTION. (TC NR 20070313006)	1	L	7	2 	3O	3	O		A12SW   	E14EA	5	C	P33EA	 
2007060100121	20070601	00121	NE  	2007	6	1	CA070313008      	2	20070313	G	7530	3024606	FITTING         			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1761 					PCE107017			(CAN) UPON INSPECTION OF THE P3 AIR LINES, IT WAS DISCOVERED THAT THERE WAS NO CLEARANCE BETWEEN THE P3 FILTER HOUSING N	IPPLE FITTING (P/N 3024606) AND THE ENGINE REAR FIRE SEAL PLATES (P/N 3031003 AND 3031004).  UPON REPOSITIONING OF THE F	IRE SEAL PLATES, IT WAS DISCOVERED THAT THE PLATES HAD CHAFED INTO THE NIPPLE FITTING APPROXIMATELY 0.020 INCH. THE FITT	ING WAS REMOVED AND REPLACED.  THE OTHER AIRCRAFT IN OUR FLEET WERE INSPECTED WITH NO OTHER DEFECTS NOTED. (TC NR 200703	13008)		1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008021900194	20080219	00194	SW  	2008	2	19	CA070313009      	1	20070313	G	5411	804501	FRAME           			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	FIREGATE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			568  								(CAN) DURING ANNUAL INSPECTION, THE LOWER LONGITUDINAL FRAME OF THE STAINLESS STEEL FIREGATE P/N 80450-1 WAS NOTED TO BE	 CRACKED AT THE FWD END AND BULGED AT THE AFT END.  (2) OTHER AC HAVE SIMILAR DAMAGE. WATER WAS FOUND IN THE TUBE AND TH	E DAMAGE APPEARS TO BE CAUSED BY WATER FREEZING. (TC NR 20070313009)				1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL	 
2008012900013	20080129	00013	SO  	2008	1	29	CA070314001      	1	20070314	G	3233	WTC21151	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACTUATOR BROKEN, FOUND DURING REPAIRS TO AIRCRAFT. (TC NR 20070314001)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007060100122	20070601	00122	EA  	2007	6	1	CA070314002      	2	20070117	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			CL	CLIMB          	1			CA								114390			(CAN) ON CLIMB FOLLOWING TAKE-OFF, FLAMES WERE SEEN EXITING THE ENGINE EXHAUST ACCOMPANIED BY A LOUD NOISE.  THE ENGINE 	WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND ROTOR SEIZURE.  MFG WILL INVE	STIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314002)				2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2007060100123	20070601	00123	NE  	2007	6	1	CA070314004      	2	20070125	G	7321	311717804	FUEL CONTROL    			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA			9077 								(CAN) ON APPROACH, ENGINE TORQUE FELL TO ZERO WHEN POWER LEVER WAS RETARDED. SUBSQUENT THROTTLE INPUT RESULTED IN TORQUE	 FLUCTUATION AND THE ENGINE WAS SUBSEQUENTLY SHUTDOWN IN FLIGHT.  TROUBLESHOOTING LED TO REPLACEMENT OF THE ENGINE FUEL 	CONTROL UNIT. (TC NR 20070314004)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007060100124	20070601	00124	WP  	2007	6	1	CA070314005      	2	20070217	G	7200	FE73121C	ENGINE          			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					NR 1	VIBRATION       	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								P73114			(CAN)  NR1 ENGINE FAILED, TEMPERATURE SPIKE ABOVE 1000 DEGREES C. AS VIBRATION INCREASED, THEN INDICATIONS (ITT, FIFY N2	) DECREASED. N1 TURNED, SECURITY, PULLED FIRE HANDLE.  ON ARRIVAL, COULD NOT TURN N1, FOUND OIL AND METAL PIECES IN EXHA	UST, ENGINE REMOVED FROM AIRCRAFT.  PRIOR OIL ANALYSIS WERE NORMAL (16 DEC.2006 AND 21 SEPT, 2005).  NO METAL ON MAG PLU	G.  A FEW SLIVERS IN FILTER.  (TC NR 20070314005)			2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2008013100014	20080131	00014	SO  	2008	1	31	CA070314006      	1	20070307	G	5720		STRUCTURE       			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	RT WING ROOT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			8000 								(CAN) RT FORWARD WING WALK ASSEMBLY, P/N 62061-002. RT ROOT WAS CRACKED. (TC NR 20070314006)						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007061300123	20070613	00123	EU  	2007	6	13	CA070314007      	1	20070130	G	7930	310595801	RELIEF VALVE    			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE OIL	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSP	ECTION LED TO REPLACEMENT OF THE ENGINE COLD-OIL PRESSURE RELIEF VALVE. (TC NR 20070314007)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007060100125	20070601	00125	EU  	2007	6	1	CA070314008      	1	20070313	G	2752	9787320309	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			2259 	2259 							(CAN) FLAP ACTUATOR WOULD TEMPORARILY FREEZE/SEIZE AT THE END OF A FLIGHT WHILE WAITING ON THE GROUND AT OAT-5-12C. AFTE	R WARMING A/C, FLAPS WOULD RESET AND FUNCTION NORMALLY. ACTUATOR REMOVED FROM SERVICE.  FLAP WARNING UNIT FAILURE CODES 	INDICATED HIGH CURRENT DRAW. FLAPS SYSTEM TESTED WITHIN CURRENT DRAW LIMITS AFTER REPLACEMENT OF ACTUATOR. MFG TECH REP 	HAS REQUESTED TEARDOWN REPORTS. (TC NR 20070314008)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061300124	20070613	00124	EA  	2007	6	13	CA070314009      	2	20070129	G	7200		ENGINE          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A6       	52043	EA  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								103238			(CAN) DURING ATTITUDE RECOVERY TRAINING, THE ENGINE FLAMED OUT.  THE ENGINE WAS SUCCESSFULLY RE-STARTED IN FLIGHT BUT SU	FFERED AN OVER TEMPERATURE DURING THE RE-LIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE	D. (TC NR 20070314009)				1	L	7	1 	3T	3	T	RT	A78EU   	E4EA				 
2007060100126	20070601	00126	EU  	2007	6	1	CA070314010      	1	20070313	G	2752		ROD END         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ACTUATOR	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA				17   							(CAN) ROD END WAS FOUND LOOSE/WORN OUT ON OVERHAULED ACTUATOR. TEMPORARILY INSTALLED IN AIRCRAFT WHILE AWAITING REPLACEM	ENT. REMOVED WITH 16.8 HRS TSO BEFORE RETURNING TO SUPPLIER. (TC NR 20070314010)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061300125	20070613	00125	NE  	2007	6	13	CA070314011      	2	20070208	G	7260		SHAFT           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					ACCESSORY DRIVE	DAMAGED         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA								12383			(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION	 REVEALED ACCESSORY DRIVE TOWER SHAFT DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 	(TC NR 20070314011)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007061500188	20070615	00188	NE  	2007	6	15	CA070314012      	2	20070213	G	7261	PW545B	ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWC   	545   	PW545B      		NE  						OIL CONSUMPTION 	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								DD0351			(CAN) THE ENGINE LOW-OIL-PRESSURE WARNING ACTIVATED IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED HIGH OIL CONSUMPTION. 	 MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314012)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007061300126	20070613	00126	NE  	2007	6	13	CA070314013      	2	20070213	G	7250		BLADES          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					POWER TURBINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								121276			(CAN) DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE ENGINE WAS SH	UTDOWN IN FLIGHT.   GROUND INSPECTION REVEALED A SEIZED PROPELLER AND DAMAGED POWER TURBINE BLADES.  MFG WILL INVESTIGAT	E THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC  20070314013)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007061300127	20070613	00127	NE  	2007	6	13	CA070314014      	2	20070202	G	7230		COMPRESSOR      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	SEIZED          	W				E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			CR	CRUISE         	1			CA								114109			(CAN) FLAMES WERE SEEN EXITING THE ENGINE EXHAUST AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALE	D COMPRESSOR SEIZURE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314014)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007061300128	20070613	00128	NE  	2007	6	13	CA070314015      	2	20070210	G	7250		TURBINE BLADES  			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								124662			(CAN) THE ENGINE FLAMED OUT OUT FOLLOWING TAKEOFF.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES AND META	L DEBRIS IN THE ENGINE OIL SYSTEM.   MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20	070314015)				2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2007061300129	20070613	00129	NE  	2007	6	13	CA070314016      	2	20070215	G	7200		ENGINE          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  						VIBRATION       	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								100180			(CAN) ENGINE EXHIBITED HEAVY VIBRATION DURING CRUISE AND WAS SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADV	ISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070314016)					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007060100127	20070601	00127	NM  	2007	6	1	CA070314017      	1	20070312	G	4900	4503067A	APU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	APU BAY	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CREW MADE A NORMAL APU START REQUEST, A FEW SECONDS LATER HEARD A LOUD BANG AND GOT THE APU FAIL ADVISORY LIGHT. A	PU ENCLOSURE SUFFERED STRUCTURAL DAMAGE AFTER FUEL VAPOR IGNITED. NO FIRE LIGHT OR FIRE NOTED.  EXAMINATION OF APU COMPA	RTMENT AREA REVEALED THAT APU ACCESS DOORS DEPARTED THE TAILCONE. TAIL CONE TO BE REPLACED.  (TC NR 20070314017)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007061300130	20070613	00130	NE  	2007	6	13	CA070314018      	2	20070216	G	7230		ACTUATOR        			GULSTM	200   	200         	4500308	NM  	PWC   	PW306 	PW306A      	52165	NE  					INLET GUIDE VANE	FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON APPLICATION OF POWER IN CLIMB, THE ENGINE EXPERIENCED A COMPRESSOR STALL ACCOMPANIED BY AN UNCOMMANDED POWER RE	DUCTION, PARAMETER FLUCTUATIONS AND A FADEC FAULT INDICATION.  SUBSEQUENT INVESTIGATION LED TO REPLACEMENT OF THE ENGINE	 INLET GUIDE VANE ACTUATOR. (TC NR 20070314018)				2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2007061300131	20070613	00131	NE  	2007	6	13	CA070314019      	2	20070216	G	7310	3033981	LINE            			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					FCU	FRACTURED       	W				O				OTHER                   				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN FLIGHT AND FLAMED OUT ON LANDING ROLL-OUT.   SUBSEQUENT I	NSPECTION REVEALED A FRACTURED FUEL DELIVERY TUBE. (TC NR 20070314019)					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2007061300132	20070613	00132	EA  	2007	6	13	CA070314020      	2	20070122	G	7250		TURBINE BLADES  			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				O			OTHER                     			LD	LANDING        	1			CA								TH0727			(CAN) ON LANDING FOLLOWING A TRAINING FLIGHT, THE ENGINE EMITTED A LOUD NOISE.  SUBSEQUENT INSPECTION REVEALED FRACTURED	 POWER TURBINE BLADES.   MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314020)					1	G	7	2 	3U	4	U		H7EU    	E22EA				 
2007061300133	20070613	00133	NE  	2007	6	13	CA070314021      	2	20070223	G	7200		ENGINE          			RAYTHN	36    	G36         	7150061	CE  	PWA   	PT6   	PT6A68      	 	NE  						MAKING METAL    	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING A TRAINING MISSION, THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER ACCOMPANIED BY A NOISE AND A C	HIP DETECTOR INDICATION.  SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS IN THE ENGINE OIL SYSTEM.  MFG WILL INVESTIGATE	 THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314021)				1	L	7	1 	3O	4	T	RT	3A15    	E26NE				 
2007061300134	20070613	00134	NE  	2007	6	13	CA070314022      	2	20070222	G	7200		ENGINE          			AYRES 	S2    	S2RHGT65    	0970110	SO  	PWA   	PT6   	PT6A65AG    	52043	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE FLAMED OUT IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONC	E DETERMINED. (TC NR 20070314022)					1	L	7	1 	3T	4	T	NC	        	E4EA				 
2007060100128	20070601	00128	EU  	2007	6	1	CA070315001      	1	20070306	G	3000		HEATER          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					CCAS PROBE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DEPARTING, THE CREW OBSERVED A STICK PUSHER/ STICK SHAKER FAULT. AFTER A FAILED, RESET THE AIRCRAFT, RETURNED TO P	OINT OF DEPARTURE WITH OUT FURTHER PROBLEM. MAINTENANCE VERIFIED THE NR 1 CCAS ALPHA PROBE HEAT FUNCTION HAD FAILED. THE	 PROBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE (TC NR 20070315001)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007060100129	20070601	00129	EA  	2007	6	1	CA070315002      	1	20070313	G	3320	BB100200258	SOCKET          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CABIN LIGHTS	BURNED          	W				H	K			DEACTIVATE SYST/CIRCUITS	NONE                    			B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) REF LOG PAGE NR 593976. F/A REPORTS ELECTRICAL SMELL IN FORWARD CABIN, AROUND ROW 2 AND 3. 4FD SIDEWALL LIGHT HOLD	ER FOUND AT FAULT, CBP2 C/B S5 OPENED AND SECURED.  SIDEWALL LIGHT INOP, DEFERRED IAW MEL 33-21-01 CAT (C). SOCKET ASSY 	P/N BB1-0020-02-58 (TC NR 20070315002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007060400003	20070604	00003	EU  	2007	6	4	CA070315003      	1	20070310	G	3297		CONNECTOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					MLG	UNSECURE        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DEPARTING, THE CREW OBSERVED A FAIL TO RETRACT INDICATION ON THE RT MAIN LANDING GEAR. THE AIRCRAFT RETURNED TO PO	INT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM.  MAINTENANCE FOUND A CONNECTOR IN THE INDICATION SIGNAL HARNESS WIT	H A CONNECTOR NOT FULLY LOCKED. THE CONNECTOR WAS SECURED SYSTEM INTEGRITY VERIFIED AND THE AIRCRAFT RETURNED TO SERVICE	. (TC NR 20070315003)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007060400004	20070604	00004		2007	6	4	CA070315004      	4	20070312	G	3410	7004544713	HSI             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					NR 1	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DEPARTING THE CREW OBSERVED A CIRCUIT BREAKER TRIP ON THE NR 1 EADI, RESET SUCCESSFUL. THIS WAS FOLLOWED BY A CIRC	UIT BREAKER TRIP ON THE NR 1 EHSI. THE RESET ATTEMPT FAILED AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURT	HER PROBLEM. MAINTENANCE REPLACED THE NR 1 SYMBOL GENERATOR UNIT.  THE SYSTEM FUNCTION CHECKED SATISFACTORY AND THE AIRC	RAFT WAS RETURNED TO SERVICE. (TC NR 20070315004)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007060400005	20070604	00005	NM  	2007	6	4	CA070315005      	1	20070215	G	3246	29685	BEARING         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 4 MAIN WHEEL	DAMAGED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, A PIECE OF NR4 BRAKE DISK WAS FOUND AT THE SPOT WHERE THE A/C WAS PARKED. A/C WAS INSPECTED AND THE	 FOLLOWING ARE REPORTED. FOUND DAMAGE AT INNER BEARING AFTER THE INSPECTION WITH NR 4 WHEEL ASSEMBLY WAS REMOVED. WHEEL 	BRAKE AND AXLE ASSYS REPLACED. (TC NR				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008013100015	20080131	00015	EU  	2008	1	31	CA070316001      	1	20070315	G	6340	MS2771923	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					LOW ROTOR	INTERMITTENT    	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			8171 								(CAN) LOW ROTOR HORN NOT WORKING BUT LIGHT ON 4ALPHA PANEL WOULD COME ON.  SYSTEM TROUBLESHOT AND FOUND SWITCH TO BE INT	ERMITENT.  A/C GROUNDED TILL NEW SWITCH HAD BEEN REPLACED. THE POTENTIAL FOR GIVING A FALSE READ TO THE PILOT DURING FLI	GHT MAY HAVE OCCURED.  AIRCRAFT WAS GROUNDED. SWITCH HAS BEEN REPACED AND A/C RETURN TO SERVICE. (TC NR 20070316001)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008013100016	20080131	00016	SW  	2008	1	31	CA070316002      	1	20070316	G	3610		LINE            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	BLEED AIR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1437 								(CAN) DURING ANNUAL INSPECTION, THE BLEED AIR LINE FOR THE CABIN HEATER WAS FOUND UNSECURED UNDER THE COCKPIT FLOOR. FUR	THER INVESTIGATION FOUND THE MUFFLER FOR THE LINE BROKEN IN (2) PIECES AT THE FWD END. THE PARTS WERE REPLACED. THE REMA	INING AIRCRAFT IN THE FLEET WERE INSPECTED. ONE ADDITIONAL AIRCRAFT WAS FOUND WITH THE SAME DEFECT. THE PARTS WERE REPLA	CED WITH SERVICEABLE UNITS. (TC# 20070316002)			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008020100099	20080201	00099	CE  	2008	2	1	CA070316003      	1	20070313	G	7714	MS250384	TACH GENERATOR  			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  		FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) N1 TACH GENERATOR FAILED IN FLIGHT. (TC NR 20070316003)						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007061300136	20070613	00136	EA  	2007	6	13	CA070316004      	2	20070212	G	7322		CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	OUT OF ADJUST   	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA				455  							(CAN) ENGINE WAS RUNNING ROUGH, UNABLE TO ADJUST IDLE ON CARBURETOR.  ENGINE WANTED TO SHUTDOWN ON APPROACH WHEN THROTTL	E WAS RETARDED. (TC NR 20070316004)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007060400006	20070604	00006	EU  	2007	6	4	CA070319001      	1	20070312	G	2140	BAS30198	PRESSURE SWITCH 			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R408	CR4086123F17	EU  	HEATER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE THE AIRCRAFT`S HEATER FAILED AND THE CREW WAS UNABLE TO RESTART THE HEATER. THE AIRCRAFT RETURNED	 TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE HEATER PRESSURE SWITCH AND THE AIRCR	AFT RETURNED TO SERVICE AFTER SATIFACTORY GROUND CHECK. (TC NR 20070319001)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P17BO	 
2007060400007	20070604	00007	NE  	2007	6	4	CA070319004      	2	20070316	G	7310	263451	DUMP VALVE      			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	FLOW DIVIDER	LEAKING         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			4065 	1179 							(CAN) AFTER TAKEOFF DURING CLIMB, NR1 ENGINE LOST POWER AND TRQ ROLL BACK, CREW ELECTED TO SHUT ENGINE DOWN AND RETURN T	O DEPARTURE AIRPORT. MAINTENANCE INSPECTION FOUND FUEL SUPPLY LINE TO FLOW DIVIDER/DUMP VALVE (B-NUT) NOT LOCKWIRED AND 	BACKED OFF, ALLOWING HIGH PRESSURE FUEL LEAK. O-RINGS REPLACED, FUEL LINE (B-NUT) TIGHTENED AND LOCKWIRED. ENGINE RUNS C	ARRIED OUT, AIRCRAFT RETURNED TO SERVICE. (TC NR 20070319004)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007060400008	20070604	00008	WP  	2007	6	4	CA070319005      	2	20070316	G	7230	8934825	IMPELLER        			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	FRACTURED       	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			20650	20650				P44721C			(CAN) ENGINE WAS REMOVED DUE TO NOT MAKING TARGET TAKEOFF TORQUE.  UPON DISASSEMBLY THE 2ND STAGE COMPRESSOR IMPELLER FA	ILED AND HAS EXPERIENCED A FATIGUE TYPE FAILURE. THE PRESENT TIME ON THE IMPELLER IS 20,650.2 HOURS AND 28,175 CYCLES.  	A LARGE PIECE OF THE LEADING EDGE BROKE OFF AND WAS DISCOVERED FURTHER DOWN IN THE ENGINE.  IT HAS BEEN RETAINED.  IT HA	S EXTENSIVE DAMAGE DUE TO SECONDARY IMPACT DAMAGE.  NO RUB DAMAGE, AS WOULD TYPICALLY CAUSE A PROBLEM, FOR THE IMPELLER 	WAS FOUND SUGGESTING THAT THE COMPRESSOR WAS BUILT PROPERLY. THE DAMAGE NOTED IN PHOTOGRAPH IS BELIEVED TO BE SECONDARY 	RUB DAMAGE DUE TO THE CRACKED PIECE GETTING LODGED BETWEEN THE SHROUD AND THE IMPELLER.  ALL DIMENSIONS FOR ENGINE SHIMM	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007060400009	20070604	00009	EA  	2007	6	4	CA070319006      	2	20070314	G	8530	77672	TAPPET          			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			443  								(CAN) ENGINE MODIFIED IAW FIREWALL FORWARD CENTRILUBE STC. PREVIOUS EXPERIENCE WITH THIS ENGINE SERIES PROMPTS REGULAR T	APPET INSPECTIONS. TAPPETS INSPECTED AND SPALLING WAS FOUND, EVEN ON THIS STC`D ENGINE.  TAPPETS SENT TO FIREWALL FORWAR	D FOR EXAMINATION, AND ONLY 3 OF THE 12 TAPPETS WERE JUDGED REUSABLE.  THIS TAPPET-BODY MANUFACTURING PROCESS HAS BEEN H	IGHLY SUSPECT FOR MANY YEARS BY THIS SUBMITTER. (TC NR 20070319006)			1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
2007060400010	20070604	00010	EA  	2007	6	4	CA070319008      	2	20070315	G	8520		CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				136  				L521861A			(CAN) THIS ENGINE WAS JUST PUT ON WING TO REPLACE AN ENGINE THAT HAD CAMSHAFT WEAR. DURING A ROUTINE INSPECTION THE OIL 	WAS DRAINED AND A SUBSTANTIAL AMOUNT OF FERROUS METAL WAS DISCOVERED IN THE FILTER. AN OIL SAMPLE WAS SENT IMMEDIATELY T	O PROGRESSIVE FOR ANALYSIS. THEY REPORTED BACK THAT IT WAS THE CAMSHAFT FAILING. WE ARE SENDING THE ENGINE TO THEM FOR T	EARDOWN AND WILL NOT KNOW UNTIL THEN WHETHER IT IS AN OPERATIONAL PROBLEM OR A COMPONENT PROBLEM. (TC NR 20070319008)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007060400011	20070604	00011	NM  	2007	6	4	CA070319009      	1	20070209	G	3297		WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG WOW	DAMAGED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, ALL THREE GEAR FAILED TO RETRACT. (3) RED AND (3) GREEN LIGHTS REMAINED ILLUMINATED.  RAN CHECKLIS	T, NO HELP.  HANDLE DID ILLUMINATE AMBER. FLIGHT WAS DIVERTED BACK TO BASE.  MAINTENANCE REMOVED AND REPLACED NLG WOW 2 	CENTERING WIRING HARNESS. (TC NR 20070319009)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007060400012	20070604	00012	NM  	2007	6	4	CA070320001      	1	20070207	G	5610	80260006	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			12216								(CAN) RT WINDSHIELD SPIDER WEBBED AT 24,000 FT CRUISE. WINDSHIELD HEAT ON. NO CAUTION LIGHTS. FLIGHT WAS DIVERTED BACK T	O BASE. MAINTENANCE REPLACED RT WINDSHIELD IAW AMM 56-10-01. (TC NR 20070320001)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007060400013	20070604	00013	NE  	2007	6	4	CA070320002      	2	20070317	G	7313	3038589	STUD            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL NOZZLE	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			349  	349  				PCEPC0700			(CAN) DURING FIRST FUEL NOZZLE INSPECTION FROM OVERHAUL -9 OF 28 FUEL NOZZLE STUDS WERE REMOVED WITH NUTS ON STUDS P/N 3	038589.  HAVE A CODE H19 STAMPED ON THE END -DURING A PHONE CONVERSATION WITH AN EMPLOYEE AT MFG, THEY INDICATED THAT OV	ERSIZED STUDS WERE PROBABLY NOT USED AT THE OVERHAUL. MFG ACKNOWLEDGED THE PROBLEM, AND ARE INTERNALLY LOOKING INTO IT, 	AND PROVIDING THE PROPER HARDWARE TO BE INSTALLED. (TC NR 20070320002)			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2007060400014	20070604	00014	EA  	2007	6	4	CA070320003      	1	20070317	G	2120	X8905	MANIFOLD        			CNDAIR	CL600 	CL6002B19   	1900309	EA  										CABIN AIR	SPLIT           	W				O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			CA											(CAN)  A/C IS UNDERGOING MODIFICATION TO FREIGHTER CONFIGURATION,AND WAS BEING TEST FLOWN FOR COLLECTING CABIN VENTILATI	ON SYSTEM PRESSURES, UNDER VARIOUS OPERATIONAL CONDITIONS.THE A/C WAS CONFIGURED FOR THE TEST; SPECIFICALLY (2) TEST POR	TS WERE FITTED TO THE A/C VENTILATION SYSTEM DUCTING TO MEASURE DUCT PRESSURE IN FLIGHT. THE DUCT PRESSURES WERE MEASURE	D SUCCESSFULLY UNDER SEVERAL OPERATING CONDITIONS, BUT IT WAS NOTED THAT THE DISTRIBUTION MAIN FEED MANIFOLD WOULD NOT W	ITHSTAND THE PRESSURE FROM THE PACK FLOW, WITH MAX CLIMB POWER APPLIED. THE FLIGHT WAS CONCLUDED AND THE A/C RETURNED UN	EVENTFULLY. UPON INSPECTION OF THE SYSTEM,THE THE MAINFEED MANIFOLD WAS FOUND TO HAVE A SPLIT AT ONE OF THE JOINTS.  (TC	2	L	7	2 	4F			RT	A21EA   					 
2007060400016	20070604	00016	EA  	2007	6	4	CA070320005      	1	20070319	G	7830		THRUST REVERSER 			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C1     		NE  						UNKNOWN         	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AFTER TAKEOFF AND CLIMBING THROUGH 25000 FEET, CREW RECEIVED RED THRUSTER REVERSER ICON IN THEIR N1 GAUGE. SHORTLY	 THEREAFTER CREW RECEIVED REVERSER STATUS MESSAGE. AFTER DISCUSSION WITH MTC, ELECTED TO RETURN TO DEPARTURE TO LOCK OUT	 THRUST REVERSER. THRUST REVERSER DEFERRED IAW MEL 78-30-01 WILL PROVIDE MORE INFORMATION WHEN IT BECOMES AVAILABLE.  WI	TH THE SUPPORT OF MFG WE HAVE CONCLUDED THAT THE CAUSE OF THE INDICATION PROBLEMS IS RELATED TO A PYLON CONNECTOR THAT I	S BEING CONTAMINATED WITH MOISTURE. THE IMMEDIATE SHORT TERM FIX IS TO APPLY A WATER RESISTANCE FILLER TO THE BACK OF TH	E CONNECTOR TO PREVENT WATER INGRESS. THE LONG TERM FIX IS TO REPLACE THE CONNECTOR WITH A NEW WATER TIGHT CONNECTOR. MF	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007060400017	20070604	00017	SW  	2007	6	4	CA070320006      	1	20070226	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	LT WING TE DLAP	FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			535  								(CAN) FLAP CABLE FOUND FRAYED AT ALLUMINUM PULLEY IN LT WING GAP AREA.  (TC NR 20070320006)						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2007060400018	20070604	00018	CE  	2007	6	4	CA070320007      	1	20070316	G	3245	7008006	TUBE            			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	TIRE	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			374  								(CAN) MAINTENANCE WAS DISPATCHED AND THE WHEEL ASSEMBLY WAS REPLACED UPON INSPECTION, VALVE STEM FOUND CRACKED DUE TO EX	TREME COLD.  (TC NR 20070320007)					1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P25EA	 
2007060400019	20070604	00019	SW  	2007	6	4	CA070320008      	1	20070226	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	RT WING TE FLAP	FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			535  								(CAN) FLAP CABLE FOUND FRAYED AT ALLUMINUM PULLEY IN RT WING GAP AREA.  (TC NR 20070320008)						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2007060400020	20070604	00020		2007	6	4	CA070320009      	4	20070320	G	8300	9408308902	BEARING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ACCESSORY DRIVE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			477  								(CAN) TRYING TO DIAGNOSE A NR 2 GENERATOR HOUSING DRAIN LINE OIL LEAK ,THE NR 2 GEN  HOUSING ASSY WAS REMOVED TO REPLACE	 THE ENGINE ACCESSORY DRIVE SEAL WHICH WAS SUSPECT LEAKING. UPON REASSEMBLY OF NR 2 GEN HOUSING PLAY WAS NOTED ON PULLEY	 END OF DRIVE SHAFT. DISASSEMBLY REVEALED THAT THE OUTER BEARING P/N:940.83.08.902 OR P202PP/FS5000 HAD BEGUN TO DISINTE	GRATE. THERE WERE 3 BALLS MISSING AND THE REMAINING BALLS STILL WERE CARRYING LOAD. THERE WAS ENOUGH SIDE PLAY IN THE SH	AFT WHICH WOULD CAUSE THE SHAFT NOT TO RUN TRUE WHICH IN TURN CAUSED THE ENGINE ACCESSORY SEAL TO FAIL. ALL AFFECTED PAR	TS REPLACED WITH NEW AND OIL LEAK IS GONE. (TC NR 20070320009)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007060400021	20070604	00021	EA  	2007	6	4	CA070320010      	1	20070314	G	5350	CL6002D15	RADOME          			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF34*       	 	NE  					FUSELAGE	BURNED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			4522 	4522 							(CAN) DURING CRUISE AIRCRAFT STRUCK BY LIGHTENING. MAINTENANCE INSPECTION FOUND SCORCH MARKS ON RADOME, ALONG CENTER EDG	ES OF NLG DOORS, AND ALONG FORWARD FUSELAGE UP TO WING ROOT FAIRINGS. ALSO MINOR BURN MARK ON RT WINGLET TIP. NO DAMAGE 	TO ANY STATIC DISCHARGE WICKS. ADF WILL NOT POINT, ADF LOOP ANTENNA REPLACED. FUSELAGE BURN MARKS REPAIRED IAW MFG INSTR	UCTIONS. WINGLET DAMAGE ALLOWABLE AS IAW MFG REO. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070320010)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007060400022	20070604	00022	CE  	2007	6	4	CA070321001      	1	20070307	G	3230	115811020651	GEARBOX         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA			9220 	2576 							(CAN) GEAR WOULD NOT COME UP WHEN SELECTED, LANDING GEAR GEARBOX REPLACED. OVERHAUL FACILITY REPORTED THAT A INTERNAL GE	AR MAY HAVE BEEN SHIMMED IMPROPERLY THAT CAUSED PREMATURE WEAR (TC# 20070321001)					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2007060400023	20070604	00023	SO  	2007	6	4	CA070321002      	1	20070320	G	8120		BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			2110 					L147768A			(CAN) RT ENGINE LOST BOOST AT ALTITUDE. PILOT ELECTED TO DESCEND TO LOWER ALTITUDE.  AT LOWER ALTITUDE, RT ENGINE HAD NO	RMAL POWER.  APPROXIMATELY 20 MINUTES LATER, RT OIL PRESSURE WAS OBSERVED LOWER THAN NORMAL.  ENGINE WAS SECURED AND SHU	TDOWN.  UNEVENTFUL SINGLE-ENGINE LANDING WAS CARRIED OUT. (TC NR 20070321002)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007060400024	20070604	00024	NE  	2007	6	4	CA070321003      	3	20070320	G	6114	S8462	BARREL          													HAMSTD	2D	2D30        	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				855  					112779		(CAN) LOWER BARREL HALF FOUND WITH 5.5 INCH CRACK AT FLANGE AREA. (TC NR 20070321003)																5	C	P206	 
2007060400025	20070604	00025	EA  	2007	6	4	CA070321004      	2	20070316	G	8510		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				1033 				L11868AA			(CAN) THE AIRCRAFT WAS BROUGHT INTO THE HANGAR DURING AN INTERMEDIATE STOP TO WORK ON SOME SNAGS.  THE ENGINEER NOTICED 	A QUANTITY OF OIL ON THE OUTSIDE OF THE IB NACELLE OF THE RT ENGINE.  AFTER CLEANING THE ENGINE AND RUNNING IT AGAIN A C	RACK WAS NOTICED EMANATING FROM THE LOWER FORWARD STUD OF THE NR 2 CYLINDER.  IT RAN FORWARD TO THE THREADED HOLE FOR TH	E PROP GOVERNOR BRACE.  THE CRACK WAS NDT`D AND FOUND TO ALSO BE RUNNING BACKWARDS ALONG THE CASE UNDER THE STARTER AREA	.  IT ALSO RAN HALFWAY UP THE EDGE OF THE CYLINDER BOSS.  THE ENGINE HAS GONE FOR REPLACEMENT OF THE CASE. (TC NR 200703	21004)	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007060400026	20070604	00026	EA  	2007	6	4	CA070321005      	1	20070228	G	2497	PA204D8	WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			26799	26799							(CAN) AFTER LANDING ELECTRICAL SHORT/ARCING BEHIND CAPTAINS SEAT IN CIRCUIT BREAKER PANEL. SOME SMOKE OBSERVED. AC TAXIE	D CLEAR OF ACTIVE RUNWAY. SMOKE AND SPARKS STOPPED, AIRCRAFT TAXIED TO RAMP, PRIOR TO ARRIVAL AT GATE SPARKS RE-OCCURRED	. AIRCRAFT STOPPED AND DEPLANED. MAINTENANCE INSPECTION FOUND BUSS FEEDER JUMPER WIRE DISCONNECTED AND HAD MADE CONTACT 	WITH BULKHEAD BEHIND CB PANEL. ARCING DAMAGE BURNED THROUGH STRINGER AND BULKHEAD SKIN. BULKHEAD BURN THROUGH APPROX 1 I	NCH BY .5 INCH . (2) FEEDER WIRES BURNED INSULATION. FEEDER WIRES PA204D8 AND PA204E8 REPLACED. WIRE PA204C8 CONNECTION 	FOUND LOOSE AT CB 1-H2, ALL SCREWS ON BUS BAR H FROM H2 TO H13 FOUND NOT TIGHT. SB601R-34-096 (PROVISIONAL GPS INSTALLAT	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007060400027	20070604	00027	CE  	2007	6	4	CA070321006      	1	20070320	G	5410	S32471	LATCH           			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	LT NACELLE	LOOSE           	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			14254								(CAN) LT ENGINE UPPER COWL OPENED IN FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. AIRCRAFT WAS FLYING THROUGH TURBULENCE WH	EN THE COWL OPENED. DURING THE INSPECTION OF THE COWL, IT WAS FOUND THAT ALL 3 LATCHES WERE LOOSE. THE LATCHES WERE RE-A	DJUSTED.   (TC NR 20070321006)				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2007060400028	20070604	00028	NM  	2007	6	4	CA070321007      	1	20070320	G	3260		PSEU            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) DURING APPROACH TO AIRPORT, THE PILOTS SELECTED GEAR DOWN AND HAD A GEAR (UNSAFE) LIGHT BUT NO GEAR EXTENSION. ALT	ERNATE EXTENSION WAS PERFORMED IAW CHECK LIST WITHOUT FURTHER REMARKS.   PSEU (PROXIMITY SWITCHING ELECTRONIC UNIT) REPL	ACED AS PRECAUTION.   FURTHER INVESTIGATION FOUND OUT THE MAIN CAUSE OF THE EVENT WAS LOOSE WIRING/TERMINAL ON THE MLG I	NHIBIT SWITCH.  MFG ISSUED DASH 8 Q100/200/300 AOM 828 TO PROVIDE DETAILS OF THIS EVENT. (TC NR 20070321007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007060400029	20070604	00029	SW  	2007	6	4	CA070321008      	1	20070321	G	5310	205030163395	BEAM            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					FUSELAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1231 								(CAN) WEB P/N 205-030-163-395 FOUND CRACKED AT INDUCTION BAFFLE SUPPORT WL 80.13. THE CRACK WAS APPROX 1 INCH IN LENGTH 	AND .5 INCH DOWN . REPAIR SCHEME IN PROGRESS THROUGH MFG. (TC NR 20070321008)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007060400030	20070604	00030	EU  	2007	6	4	CA070321009      	3	20070305	G	6197	697070212	BUSS BAR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROP HUB	SHORTED         	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) NR 2 ENGINE SHUTDOWN MANUALLY IN FLT DUE PEC FAIL CAUTION AND PROP SPEED AT 1060 RPM. FAULT CODES RT CH A/B 160 AN	D 162. MAINT DISPATCHED TO T/S. FOUND BUSBAR FOR PROPELLER DEICE CHAFFING ON MPU BRACKET, CAUSING MPU TO PICKUP SENS FRO	M BUSBAR. MPU ADJUSTED AND NEW BUSBAR INSTALLED. ENGINE GROUND RUNS C/O NORMAL. (TC NR 20070321009)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007061300137	20070613	00137	NE  	2007	6	13	CA070321010      	2	20070316	G	7321	430109817	FCU             			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA				1082 							(CAN) THE ENGINE FLAMED OUT WHILE THE THROTTLE WAS BEING RETARDED DURING A PRACTICE AUTOROTATION. THE POSITION OF THE TH	ROTTLE AT THE TIME OF THE FLAME OUT WAS NO WHERE NEAR THE POSITION IT NORMALLY CUTS OFF THE FUEL DURING NORMAL SHUTDOWN.	 AFTER CONDUCTING A NORMAL AUTOROTATION, THE PILOTS RESTARTED THE ENGINE AND PERFORMED A TEST HOVER AND FLIGHT. THEY PER	FORMED (3) MORE PRACTICE AUTOROTATIONS WITHOUT ANY MORE INCIDENT OR SYMPTOMS.  NO FUEL LEAKS OR VISIBLE MECHANICAL ISSUE	S WERE FOUND.  THE FCU WAS REPLACED AS A PRECAUTION AND IS BEING SENT TO AN APPROVED FACILITY FOR BENCH TESTING.     (TC	 NR 20070321010)	1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2007060400031	20070604	00031	SW  	2007	6	4	CA070321011      	1	20070321	G	6230	206010332121	MAST            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2213 							(CAN) DURING ANNUAL INPECTION OF INTERIOR OF MAST, CORROSION AND PITTING WERE DISCOVERED.  MAST WAS REMOVED AND SENT TO 	AN OVERHAUL FACILITY FOR REPAIR. (TC NR 20070321011)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007060400032	20070604	00032	EA  	2007	6	4	CA070321012      	1	20070321	G	5330		SKIN            			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	FS 388	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3765 								(CAN) DURING A REGULAR SCHEDULED MAINTENANCE B-CHECK, THE MAINTENANCE GUIDE CHECKLIST CALLED FOR A VISUAL INSPECTION IN 	ZONE 330/340 FUSELAGE TO WING AREA, BS 388-434.  A SMALL 1 INCH CRACK WAS FOUND STEMMING FROM UNDERNEATH THE SHEAR PLATE	 AT BS 388. AFTER REMOVAL OF THE PRC, PAINT STRIPPING, AND COMPLETING A LIQUID DYE PENETRANT INSPECTION, (2) CRACKS AT S	TA 388 BETWEEN WL216 AND WL210 WERE IDENTIFIED. ONE CRACK WAS APPROXIMATELY 3.5 INCH AND THE OTHER APPROXIMATELY 0.5 INC	H.  PICTURES AND INFORMATION SENT TO THE MFG FOR DIRECTION TO COMPLETE THIS REPAIR. (TC NR 20070321012)		2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2007060400033	20070604	00033	EA  	2007	6	4	CA070321013      	1	20070319	G	4930	21188002	ECU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU	MALFUNCTIONED   	W				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA			5330 	5330 							(CAN) GROUND CREW REPORTED FLAMES FROM APU EXHAUST DURING PUSHBACK. COCKPIT HAD NO FIRE INDICATIONS. CREW SHUTDOWN AND P	ASSENGERS DEPLANED. MAINTENANCE INSPECTED AND APU MEL`D. LATER MAINTENANCE TROUBLESHOOTING FOUND APU ECU WITH FAULT/ERRO	R CODES. APU ECU REPLACED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070321013)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007060400034	20070604	00034	CE  	2007	6	4	CA070322001      	1	20070321	G	5414	1019800013	PANEL           			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	NACELLE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1375 	1375 							(CAN) PANEL IS INSTALLED ON RT IB SIDE OF NACELLE. IT COVERS THE FUEL FIREWALL SHUTOFF VALVE. THE PANEL IS MANUFACTURED 	WITH A BULGE TO ACCOMMODATE THE VALVE.  IN THIS INSTALLATION THE VALVE CONNECTOR PLUG CHAFFED AGAINST THE PANEL CAUSING 	A STRESS RISER RESULTING IN A 1.5 CRACK VISIBLE FROM THE OUTSIDE OF THE PANEL.  PANEL WAS REPAIRED IAW THE SRM 54-00-01.	  A NEW PANEL P/N 101-980001-41 WAS ORDERED.  THIS ALTERNATE PANEL HAS A LARGER/DEEPER DEPRESSION TO BETTER ACCOMMODATE 	THE VALVE. (TC NR 20070322001)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007060400037	20070604	00037	EA  	2007	6	4	CA070322004      	1	20070321	G	7897		CONNECTOR       			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C1     		NE  					THRUST REVERSER	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENROUTE, CREW RECEIVED RED THRUST REVERSER ICON IN THEIR N1 GAUGE. AFTER DISCUSSIONS WITH MAINTENANCE AND DISPATCH	, ELECTED TO DIVERT FOR MAINTENANCE TO LOCK OUT THE THRUST REVERSER. LANDED WITHOUT INCIDENT AND MAINTENANCE CARRIED OUT	 THE PROCEDURE. RT THRUST REVERSER LOCKED OUT. MEL 78-30-01 APPLIED WILL PROVIDE MORE INFORMATION WHEN IT BECOMES AVAILA	BLE  CORRECTIVE ACTION, DATED 29 MARCH 2007: WITH THE SUPPORT OF MFG WE HAVE CONCLUDED THAT THE CAUSE OF THE INDICATION 	PROBLEMS IS RELATED TO A PYLON CONNECTOR THAT IS BEING CONTAMINATED WITH MOISTURE. THE IMMEDIATE SHORT TERM FIX IS TO AP	PLY A WATER RESISTANCE FILLER TO THE BACK OF THE CONNECTOR TO PREVENT WATER INGRESS. THE LONG TERM FIX IS TO REPLACE THE	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007060400038	20070604	00038		2007	6	4	CA070322005      	4	20070313	G	6122	8210410	GOVERNOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED FOR DESTINATION, WHEN THE CREW ATTEMPTED TO SET CLIMB POWER, THE RT PROP DROPPED TO 1200 RPM AND	 THE TORQUE WENT TO 2200 LBS.  THE CREW DECLARED AN EMERGENCY AND LANDED UNEVENTLY .   MAINTENANCE WENT TO SITE THE FOLL	OWING DAY AND CHANGED THE RT PROPELLER, RIGGED IT AND PERFORMED GROUND RUNS .THE AIRCRAFT WAS RETURNED TO SERVICE WITH N	O FURTHER PROBLEMS. (TC NR 20070322005)			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007060400039	20070604	00039	SO  	2007	6	4	CA070322006      	2	20070128	G	7314	64936849A1	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FUEL SYSTEM	OUT OF ADJUST   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			69   					806498			(CAN) PILOT REPORTED ENGINE STOPPED DURING POWER OFF STALL.  RECORDS INDICATED (2) SID97-3C FUEL SET UP ADJUSTMENTS CARR	IED OUT IN THE PREVIOUS FIVE DAYS OR 13.1 HRS PRIOR TO THE INCIDENT. SID CHECK REVEALED UNMETERED PRESSURE OUT OF LIMITS	 BY -1.1 PSI, LIMIT IS +/- 0.2 PSI.  MECHANICAL FUEL PUMP REPLACED, PUMP OFF S/N B06LA110, NEW PUMP S/N B06LA111 INSTALL	ED, FUEL INJECTORS, INLINE FILTER AND ALL FUEL LINE REMOVED CLEANED INSPECTED AND RE-INSTALLED. AIRCRAFT RELEASED CONDIT	IONAL TO SATISFACTORY TEST FLIGHT AND TEST FLOWN UNSATISFACTORY. EITHER PUMP WAS UNABLE TO BE ADJUSTED TO OBTAIN LEANING	 SCHEDULE LIMITS OR UNABLE TO RE-ADJUST  TO MEET SID SPEC AFTER TEST FLIGHT.  MECHANICAL FUEL PUMP REPLACED ONCE AGAIN W	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081107		GL  	2008	11	7	CA070322007      	1	20070108	G	3245		TIRE            			DIAMON	DA20  	DA20C1      	2990001	GL  										MLG	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN)  AFTER 2 FLAT TIRES WITHIN APPROX. 30 HRS. ASSOCIATED WITH A SMALL MANUFACTURE LABEL ADHERED TO THE INSIDE OF THE 	TIRE DURING THE MANUFACTURING PROCESS.  THE GLUE OR LABEL MATERIAL WAS REACTING WITH THE TUBE AND CAUSING SMALL CRACKS A	ND EVENTUALLY ALLOWING AIR TO ESCAPE.  FAILURES DID NOT SEEM TO BE RELATED TO ANY PARTICULAR FLIGHT SEGMENT AS SOME WERE	 GOING FLAT OVERNIGHT, OTHERS WERE GOING FLAT WHILE TAXIING AND SOME SHORTLY AFTER LANDING ON ROLL OUT. SINCE THE TIRE R	EPLACEMENTS TO DATE WE HAVE HAD NO RECURRENT ISSUES DUE TO THE LABEL. APPROX. 35 TIRES AND TUBES HAVE BEEN REPLACED, SOM	E WERE REPLACED AS A PRECAUTION NOT NECESSARILY A FAILURE.	1	L	7	1 	3O			NT	TA4CH   					 
	20081113		GL  	2008	11	13	CA070322008      	1	20070309	G	3245	500X56PLY	TIRE            	CLEVELANDPNU	4078E       	DIAMON	DA20  	DA20C1      	2990001	GL  										LANDING GEAR	SPLIT           	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SINCE OUR PLAGUED REPORTED UNDER SDR 20070322007, WE HAVE ENCOUNTERED MORE FLAT TIRES. THIS TIME WE ARE FINDING SP	LITS IN THE TUBE OUTER EDGE CENTRE LINE. NOT THE SAME PROBLEM WE WERE HAVING WITH THE MCCREARY TIRES. THE COMMONALITY IN	 THESE FAILURES SEEMS TO BE RELATED TO MICHELIN TUBES. WE HAVE SINCE RETURNED 5 TUBES TO MICHELIN FOR THEIR INSPECTION. 	A CONVERSATION WITH AN AVIALL REPRESENTATIVE WHO HAS BEEN IN CONTACT WITH MICHELIN TODAY CONFIRMS THEY HAVE RECEIVED THE	 TUBE AND HAVE BEGUN PRELIMINARY INSPECTION. THEY HAVE INDICATED THAT THEY ARE ALSO DEALING WITH ANOTHER CUSTOMER WITH S	IMILAR PROBLEMS AND WILL GET BACK TO US WITH THE DETAILS OF THE ANALYSIS. WE HAVE SINCE PURCHASED TUBES FROM A DIFFERENT	1	L	7	1 	3O			NT	TA4CH   					 
2007060400040	20070604	00040	EA  	2007	6	4	CA070322009      	3	20070314	G	6111		TAPE            													SNSNCH	W69EK	W69EK63     	EA  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			71   			AG7471					(CAN) DURING VISUAL INSPECTION, IT WAS FOUND THAT THE TAPE USED ON THE LEADING EDGE OF THIS PROP WHICH WAS INSTALLED BY 	THE MFG, UNDER SPEC SP-127, WAS STARTING TO BLISTER AND SEPARATE FROM THE LEADING EDGE, WORSE AT THE TIPS. TAPE WAS REMO	VED AND LOG ENTRIES CARRIED OUT. NO WEIGHT AND BALANCE CHANGES AND THOUGH DISCUSSIONS WITH BOTH MFGS.  THERE IS NO ILL E	FFECT ON BALANCE AS LONG AS BOTH BLADE TAPES ON BOTH BLADES ARE REMOVED.  COULD NOT SEEM TO ENTER THAT THIS IS A W69EK-6	3 MODEL PROP. (TC NR 20070322009)												5	N	TA4CH	 
	20081104		EA  	2008	11	4	CA070322010      	3	20070314	G	6110		TAPE            													SNSNCH	W69EK	W69EK63     	EA  	PROPELLER	BLISTERED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48   								(CAN) DURING VISUAL INSP, IT WAS FOUND THAT THE TAPE USED ON THE L/E OF THIS PROP WHICH WAS INSTALLED BY THE MFG UNDER S	PECIFICATION SP-127 WAS STARTING TO BLISTER AND SEPERATE FROM THE L/E, WORSE AT THE TIPS. TAPE WAS REMOVED AND LOG ENTRI	ES CARRIED OUT. NO WEIGHT AND BALANCE CHANGES AND THOUGH DISCUSSIONS WITH BOTH PROP MFG AND ACFT MFG, THEIR IS NO ILL EF	FECT ON BALANCE AS LONG AS BOTH BLADE TAPES ON BOTH BLADES ARE REMOVED.. (TC NR 20070322010)													5	N	TA4CH	 
2007060400041	20070604	00041	CE  	2007	6	4	CA070322011      	1	20070322	G	5610	35410291652	WINDOW          			BEECH 	95    	E95         	1153410	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	COCKPIT	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT, AT 6000 FT, THE MAJORITY OF THE LT SIDE COCKPIT WINDOW DEPARTED THE AC. THE AC BEING CLOSE TO IT	S INTENDED DESTINATION CONTINUED ON AND LANDED WITHOUT INCIDENT. A FLIGHT PERMIT WAS ISSUED AND THE AIRCRAFT FLOWN TO MA	IN BASE FOR EVALUATION AND REPAIR. SPEAKING WITH THE PILOT THE WINDOW DID NOT APPEAR DAMAGED OR CRACKED PRIOR TO THE EVE	NT. THE SAME PILOT WHO FLEW THE SAME AIRCRAFT DAYS EARLIER MENTIONED HIS HEAD HIT THE WINDOW DURING AN ENCOUNTER WITH TU	RBULENT AIR BUT DID NOT FEEL IT WAS SEVERE ENOUGH TO CAUSE DAMAGE TO THE WINDOW. THE ONLY SUBSEQUENT DAMAGE TO THE AIRCR	AFT WAS A SMALL CUT IN THE LT HORIZONTAL STABILIZER DE-ICE BOOT. THE AIRCRAFT IS AN UNPRESSURIZED AIRCRAFT. (TC NR 20070	1	L	7	2 	3O	3	O		3A16    	1E10	5	C	P920	 
2007060400042	20070604	00042	EU  	2007	6	4	CA070323001      	2	20070301	G	7240	RK47289	COMBUST CHAMBER 								RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				2479 							(CAN) PILOTS NOTICED THE LT ENGINE OPERATING APPROX. 100 POUNDS OF TORQUE LOW.  UPON LANDING MAINTENANCE WAS NOTIFIED.  	IT WAS FOUND THAT THE NR 2 COMBUSTION CAN ASSEMBLY HAD LOST A SECTION OF ITS OUTSIDE AIR CASING. A GENERAL INSPECTION OF	 THE AREA GAVE NO CLUES AS TO WHY THIS HAPPENED. IAW THE MM ALL APPLICABLE INSPECTIONS WERE COMPLETED TO ENSURE THE ENGI	NE WOULD BE SAFE TO CONTINUE IN SERVICE.  FURTHERMORE, DUE TO A HOT SECTION INSPECTION COMING DUE ALL OTHER COMBUSTION C	ANS WERE REPLACED.  THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO ISSUES SINCE. (TC NR 20070323001)							4	T			A196	6	C	P899	 
	20081104		NM  	2008	11	4	CA070323002      	1	20070321	G	5280	8233101003	PUSHROD         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NR 1 MLG, AFT DOOR OPEN IN FLIGHT. FOUND BOTH GEAR DOOR PUSH ROD, P/N: 8323101-003 AND SPRING, P/N: 83231020-003, 	BROKEN. PUSH ROD AND SPRING REPLACED. (TC NR 20070323002)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007060400043	20070604	00043	NE  	2007	6	4	CA070323003      	2	20070321	G	7261	4115T43PO3	CARBON SEAL     			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF34*       	 	NE  					NR 1 ENGINE	MISSING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			5302 								(CAN) AFTER DEPARTURE AND CLIMBING THOUGH 16,000 FT, CREW RECEIVED (OIL LEVEL LOW) MESSAGE FOR NR 1 ENGINE. QUANTITY WAS	 50 PERCENT AND DROPPING. AFTER DISCUSSION WITH MAINTENANCE ELECTED TO RETURN TO BASE.  ANNOUNCED TO PASSENGERS THAT THE	Y WERE RETURNING DUE TO OIL QUANTITY INDICATION. JUST PAST THE OUTER MARKER CREW RECEIVED RED OIL LEVEL WARNING AND SHUT	DOWN NR 1 ENGINE.  NO EMERGENCY WAS DECLARED AS THEY WERE SO CLOSE TO LANDING AT THIS POINT. DID A FLAP 20 LANDING WITHO	UT INCIDENT AND ADVISED PASSENGERS THAT THEY DID HAVE TO SHUTDOWN ENGINE DUE OIL LEVEL. NO ADVERSE PASSENGER REACTION.  	FDR READOUT WAS TAKEN AND NO HEAVY LANDING INSPECTION WAS REQUIRED.  EARLIER THAT DAY THE NR 1 EDP HYDRAULIC PUMP HAD BE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007060400044	20070604	00044	NM  	2007	6	4	CA070323004      	1	20070322	G	3260	387	BULB            			BOEING	727   	727247      	138408F	NM  										MLG INDICATOR	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) AIRCRAFT ON MARCH 22, 2007 WAS ON APPROACH WHEN THE CREW EXTENDED THE LANDING GEAR FOR LANDING. WHEN THE GEAR WAS 	DOWN, THE CREW NOTICED THAT THE LT MAIN GEAR GREEN LOCKED LIGHT WAS NOT ILLUMINATED. THE CREW REJECTED THE LANDING AND C	ONTACTED ATC FOR A NEW APPROACH LINE-UP. THE SECOND APPROACH REVEALED THE SAME RESULTS. THE CREW REMOVED AND REPLACED A 	FAULTY BULB AND THE AIRCRAFT LANDED WITH NO FURTHER INCIDENTS. MAINTENANCE CHECKED THE SYSTEM AND CHECKED THAT THE CORRE	CT BULB WAS USED. NO FURTHER PROBLEMS. (TC NR 20070323004)		2	L	7	3 	4F				A3WE    					 
2007061300138	20070613	00138	EA  	2007	6	13	CA070323005      	2	20070322	G	7300		CONTROLLER      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	E	R	FLUID LOSS                	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			CA				1069 				L91568A			(CAN) DURING A TRAINING FLIGHT WHEN POWER WAS APPLIED, THE RT ENGINE ACCELERATED NORMALLY TO 40 INCHES AND THEN STARTED 	TO SURGE BETWEEN 20 AND FORTY INCHES.  THE PILOT WAS ABLE TO STABILIZE THE ENGINE AT ABOUT 25 INCHES OF MANIFOLD PRESSUR	E.  ALL GAUGES WERE NORMAL ALTHOUGH THEY COULD NOT GAIN ANY MORE THAN 30 INCHES OF MANIFOLD PRESSURE.   A LOT OF BLACK S	MOKE WAS OBSERVED UNDER THE WING OF THE AIRCRAFT. AS THE AIRCRAFT LANDED, THE RIGHT ENGINE QUIT. A QUANTITY OF FUEL WAS 	POURING OUT THE `SNIFFLE` VALVE OF THE ENGINE.    MAINTENANCE REMOVED THE DENSITY AND DIFFERENTIAL CONTROLLERS.  THE DEN	SITY CONTROLLER APPEARED TO HAVE AN INTERNAL LEAKAGE WHICH HAD CONTAMINATED BOTH THE DIFFERENTIAL CONTROLLER AND THE FCU	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2007060400045	20070604	00045	NM  	2007	6	4	CA070326001      	1	20070322	G	2497		WIRE HARNESS    			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  		CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			13589								(CAN) AN OPERATOR HAS REPORTED FINDING SOME WIRE LOOMS THAT WE HAVE DAMAGED DUE TO CHAFING. THIS CHAFING IS OCCURRING WI	TH THE CABIN FLOOR WIRE TROUGH ON AN A/C THAT IS POST MOD 8/2705, S/B 8-53-66. THE BULK OF THE CHAFING HAS BEEN OBSERVED	 IN THE REAR OF THE FUSELAGE WHERE THE LOOM TIE MOUNTS ARE GREATLY REDUCED.  MFG IS REVIEWING WIRING INSTALLATION. (TC N	R 20070326001)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007060400046	20070604	00046	EU  	2007	6	4	CA070326002      	1	20070322	G	2741		RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TRIM SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) A/C WAS CLIMBING OUT. THE PILOT MADE A MANUAL TRIM UP SELECTION WHEN A HZ STAB TRIM RUNAWAY OCCURRED. THE PILOT SE	LECTED THE TRIM INTERRUPT SWITCH TO STOP THE RUNAWAY AND RETURNED. THE TRIM RELAY K 022 WAS REPLACED AND SYSTEM WAS GROU	ND CHECKED SERVICEABLE AND THE A/C RETURNED TO SERVICE. NO FURTHER PROBLEMS HAVE BEEN REPORTED. (TC NR 20070326002)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007060400047	20070604	00047	CE  	2007	6	4	CA070326003      	1	20070214	G	5311	11543008435	FRAME           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FRAME SEGMENT P/N 115-43008-35 CRACKED AT OB ENDS. AIRCRAFT IS AN EMS MACHINE. DEFECT APPEARS TO BE RELATED TO HIG	H FLOOR LOADING.  (TC NR 20070326003)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007060400048	20070604	00048	CE  	2007	6	4	CA070327001      	1	20070326	G	3010		BOOT            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DE ICE SYSTEM	ARCED           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PILOTS REPORTED THAT THE IB LEADING EDGE DEICE BOOT WAS NOT FUNCTIONING.  THE DEICE SYSTEM WAS TESTED AND THE SNAG	 WAS CONFIRMED.   WHEN THE LEADING EDGE WAS REMOVED TO CHECK THE BOOT SYSTEM EVIDENCE OF SEVERE ARCING WAS FOUND IN THE 	VICINITY OF THE START RELAYS.  IT IS SUSPECTED THAT THE DEICE HOSE WAS ROUTED IMPROPERLY TO THE LEADING EDGE.  OVER TIME	 THE HOSE CHAFED ON THE WIRING FROM THE RELAYS.    MAINTENANCE REPLACED THE LEADING EDGE AS WELL AS ANY CONNECTORS THAT 	WERE DAMAGED.  (TC NR 20070327001)		1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007060400049	20070604	00049	NM  	2007	6	4	CA070327002      	1	20070322	G	3810	6BS10011	DRAIN VALVE     			AMD   	FALC50	FALCON2000  	2730170	NM  	HNYWL 	AS907 	AS90711A    	33908	WP  					POTABLE WATER	DAMAGED         	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA			3626 	3626 							(CAN) THE AIRCRAFT POTABLE WATER SYSTEM WAS DAMAGED DUE TO HAVING THE WATER SYSTEM FULL OF WATER. THEN HAVING THE AIRCRA	FT LEFT ON THE RAMP FOR 8 HOURS AT -14C WITH NO ADDITIONAL HEAT TO KEEP THE WATER SYSTEM FROM FREEZING. UPON ARRIVAL THE	 PILOTS REPORTED (WATER APPEARS TO BE LEAKING FROM THE BELLY). THE MAINTENANCE PERSONNEL INVESIGATED THE SNAG AND FOUND 	THE WATER SYSTEM DRAIN VALVE WAS DAMAGED DUE TO THE SEVERE FREEZING. A REMINDER TO ALL CORPORATE PILOTS TO MONITOR THE P	OTABLE WATER SYSTEM AND THE OAT IN WINTER.  (TC NR 20070327002)		2	K	7	2 	4F	4	F	RT	A50NM   	E00010LA				 
2007060400050	20070604	00050	SW  	2007	6	4	CA070327003      	1	20070319	G	2435	230321910	FRICTION CUP    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STARTER GEN	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				660  		10481					(CAN) DURING INSPECTON STARTER-GENERATOR FRICTION CUP PLATE WAS FOUND TO BE CRACKED. NEW PART ORDERED AND INSTALLED WHEM	 IT ARRIVED. (TC NR 20070327003)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007060400052	20070604	00052	SO  	2007	6	4	CA070327005      	1	20070322	G	3260	487862	PROXIMITY SWITCH			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	FAILED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN)  MAINTENANCE COULD NOT DUPLICATE FAULT ON GROUND WITH AIRCRAFT ON JACKS. CYCLED GEAR 20 TIMES FAULT FREE. WIRING C	HECKED,OK, RIGGING CHECKED OK, HYDRAULIC POWER PACK CHECKED, OK. CORRECTIVE ACTION TO REPLACE ALL 6 LANDING GEAR PROXIMI	TY SWITCHES. (TC NR 20070327005)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081104		EA  	2008	11	4	CA070327006      	2	20070323	G	7414	10391584	DISTRIBUTOR BLK 	BENDIX      		PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	MAGNETO	UNSERVICEABLE   	W				D				RETURN TO BLOCK         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA				1130 							(CAN) DISTURBER BLOCK CENTER BUSHING WAS LOOSE IN THE PLASTIC MOLDING. (TC NR 20070327006)						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P25EA	 
2007060400054	20070604	00054	EA  	2007	6	4	CA070327008      	2	20070312	G	8500		ENGINE          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  		FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			2145 								(CAN) ENGINE FAILURE, PROP STOPPED IN FLIGHT. NO EXTERNAL DAMAGE TO ENGINE.  SUSPECT CRANKSHAFT FAILURE. (TC NR 20070327	008)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007060400055	20070604	00055	SW  	2007	6	4	CA070327009      	1	20070313	G	6520	206040402003	GEARBOX         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  						LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			5118 								(CAN) OIL LEAK. SHIPPED TO AUTHORIZED SERVICE CENTER FOR REPAIR AND RE-INSTALLATION.  (TC NR 20070327009)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007060400056	20070604	00056	CE  	2007	6	4	CA070327010      	1	20070208	G	2730	1260505406	CONTROL CABLE   			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	3A32C	D3A32C*     	GL  	ELEVATOR	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2664 								(CAN) A SCREW FROM THE AVIONIC EQUIPMENT LOOSENED, FELL AND LODGED  BETWEEN THE PULLEY AND CABLE FOR THE ELEVATOR FLIGHT	 CONTROL. WITH TIME, THE CABLE WAS DAMAGED AS IT ROLLED OVER THE SCREW. (TC NR 20070327010)					1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P21EA	 
2007060400057	20070604	00057	EU  	2007	6	4	CA070327011      	1	20070327	G	3500	D2475	COUPLING        			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	BLEED AIR SYS	DAMAGED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE A BLEED AIR LEAK INDICATION WAS OBSERVED FOR THE RT ENGINE. THE ENGINE WAS SHUTDOWN AS A PRECAUTIONARY M	EASURE. AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE INSPECTION FOUND NO EVIDENCE OF A BLEED AIR LEAK. FURTHER INVESTIGAT	ION SHOWED THAT A FIRE WIRE COUPLING WAS LOOSE IN THE RT WING. WHEN THE COUPLING WAS REMOVED IT WAS FOUND THAT A CRUSH W	ASHER WAS MISSING FROM THE ASSEMBLY. THE COUPLING WAS CLEANED, INSPECTED AND REASSEMBLED CORRECTLY WITH (2) CRUSH WASHER	S. AFTER INSTALLATION THE FIRE WIRE ELECTRICALLY TESTED SATISFACTORY. THE AIRCRAFT WAS SUBJECT TO FULL ENGINE RUNS AND N	O BLEED AIR LEAK WAS EVIDENT. ALL COCKPIT INDICATIONS WERE NORMAL. (TC NR 20070327011)	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2007060400058	20070604	00058		2007	6	4	CA070328001      	4	20070325	G	3418	350A230083	COMPUTER        			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	STALL WARNING	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) FOLLOWING DEPARTURE, THE CREW OBSERVED A STICK PUSHER/ STICK SHAKER FAULT. THE AIRCRAFT RETURNED TO POINT OF DEPAR	TURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE CREW ALERTING COMPUTER, SYSTEM GROUND CHECKED AND THE 	AIRCRAFT RETURNED TO SERVICE. (TC NR 20070328001)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007060400059	20070604	00059	CE  	2007	6	4	CA070328002      	1	20070312	G	2120	651510314	DUCT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN AIR SYS	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPANY CAMPAIGN NOTICE 851-21-20-034 WAS CARRIED OUT. INSPECTION FOUND THE CLAMP PORTION OF THE BLEED AIR WELD AS	SEMBLY LOOSE. THE WELD ASSEMBLY WAS REPAIRED BY COLD BONDING IAW INSTRUCTIONS RECEIVED FROM MFG CUSTOMER SUPPORT. UNIT R	ETURNED TO SERVICE. (TC NR 20070328002)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007060400060	20070604	00060	EA  	2007	6	4	CA070328003      	1	20070323	G	2910	600752406	LINE            			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF348E5A1   	30015	NE  					HYD SYSTEM	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			15054	15054							(CAN) DURING ROUTINE SERVICING AFTER A/C ARRIVAL, HYD FLUID WAS NOTICED LEAKING OUT OF THE BOTTOM OF THE RUDDER AND RUNN	ING DOWN THE TAILCONE AND TO THE GROUND. PANELS WERE REMOVED TO LOCATE THE LEAK, FIGURING THAT THERE WAS A BAD RUDDER PC	U LEAKING. WHAT WAS FOUND IT WAS THE NR 3 HYDRAULIC RETURN SYSTEM LINE P/N 600-75240-6 CHAFED THREW AT THE BOTTOM OF THE	 HORIZONTAL STAB REAR SPAR. 3 MONTH PREVIOUS A 15,000 HOUR INSP WAS C/O AND THE CENTER BOTTOM HINGE BEARING WAS FOUND WO	RN OUT, SO THE HOLE BRACKET ASSY WAS REPLACED. TO REPLACED THIS BRACKET THE HYD LINE OF THE NR 3 RETURN SYSTEM HAD TO BE	 DISASSEMBLE TO GAIN ACCESS TO THE BRACKET. WHEN THE RUDDER WAS REMOVED TO DO THE REPAIR, AS THIS LINE IS ON THE REAR SP	2	L	7	2 	4F	4	F	RT	A21AE   	E00063EN				 
	20081104		CE  	2008	11	4	CA070328004      	1	20070327	G	7921	10656D	OIL COOLER      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LT ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) EXCESSIVE OIL NOTED ON LT ENGINE NACELLE. OIL LEAK TRACED TO LT ENGINE OIL COOLER. NEW OIL COOLER INSTALLED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20081104		NM  	2008	11	4	CA070328005      	1	20070317	G	2520	VL200307A	ACTUATOR        	BOEING      		BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					LEG REST	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) SEAT LOCATION ON THE ACFT WAS 7F, AND FAILED IN FLIGHT. LEG REST ACTUATOR KEPT DRIVING THE FOOTREST BACKWARD, AND 	PUNCTURED THE REAR SPAR OF THE SEAT. THERE IS A CONCERN THAT ECU SOFTWARE 2.8 MAY BE TO BLAME, BUT INVESTIGATION IS ON G	OING. THERE HAS BEEN A PREVIOUS CASE OF A BENT SPAR, PRIOR TO THIS LEVEL OF SOFTWARE, SO IT IS POSSIBLE THAT THERE IS ST	ILL AN UNKNOWN FAILURE MODE THAT CAUSES THE FEEDBACK FROM THE FOOTREST POSITION TO BE LOST, AND DRIVE THE FOOTREST UNTIL	 FAILURE.		2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2007050300001	20070503	00001	EU  	2007	5	3	CA070329001      	1	20070326	G	6310	350A35105901	COUPLING        	SNIAS       		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					M/R DRIVESHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK IN DISC LAMINATE FOUND DURING POST FLIGHT (DAILY) INSPECTION. (TC NR 20070329001)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007051100001	20070511	00001	EA  	2007	5	11	CA070329002      	1	20070323	G	5340	CN6272017203	BRACKET         			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					HYD LINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			5723 								(CAN) AC EXPERIENCED A COMMANDED IFSD DUE TO OIL PRESSURE LOSS DURING CRUISE. DURING FLIGHT, PILOT NOTICED OIL PRESSURE 	DECREASING STEADILY DURING CRUISE. AT 36 PSI OIL PRESSURE, PILOT INITIATED A COMMANDED SHUTDOWN OF THE NR 2 ENGINE AND D	IVERTED INTO BILLINGS FOR AN UNEVENTFUL SINGLE ENGINE LANDING.  UPON INSPECTION OF ENGINE, MECHANICS NOTICED A STATIC OI	L LEAK FROM THE BOTTOM OF GEARBOX. AFTER FURTHER INSPECTION, IT WAS NOTICED THAT THE BRACKET HOLDING THE HYD LINE TO GEA	RBOX AT 6:30 ON THE AFT AGB FLANGE HAD BROKEN OFF, AND CONTACTED THE BOTTOM OF THE GEARBOX JUST ABOVE THE BRACKET LOCATI	ON, HAD WORN A HOLE IN THE AGB HOUSING, RESULTING IN THE OIL LOSS. ENGINE IS BEING REMOVED AND REPLACED, ANOTHER ENGINE 	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007050300002	20070503	00002	CE  	2007	5	3	CA070329005      	1	20070329	G	2560	110195203	BUCKLE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEATBELT	INTERFERENCE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CONTROL YOKE INTERFERENCE WITH ROTORY SEAT BUCKLES INSPECTED IAW INTERNAL CAMPAIGN NOTICE 010-25-10-011. OPERATION	 OF EITHER PILOTS AND CO-PILOTS YOKES WITH SEATS FULL FORWARD CONFIRMS THAT INTERFERENCE CAN CAUSE UNLATCHING OF THE SEA	TBELT ROTARY BUCKLES. (TC NR 20070329005)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007050300003	20070503	00003	SO  	2007	5	3	CA070329006      	2	20070313	G	8530		CYLINDER        			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	NR 4	DETACHED        	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			1587 								(CAN) ENGINE VIBRATION AND POWER LOSS IN FLIGHT, ENGINE CAME TO TOTAL STOP ON TAXIWAY. CYLINDER NR 4 FOUND DETACHED. ENG	INE (2587.4 HOURS). ENGINE REMOVED FOR OVERHAULED. (TC NR 20070329006)					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007061300139	20070613	00139		2007	6	13	CA070329007      	4	20070314	G	6122	8210004	GOVERNOR        			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA				2862 				PCE40320			(CAN) A GROUND INCIDENT OCCURRED WHERE ONE AC TAXIED INTO ANOTHER.  BOTH AIRCRAFT WERE ON STRAIGHT SKIS. AFTER START-UP 	THE AC  MOVED FORWARD FROM ITS PARKING SPOT, THEN WHEN THE PILOT MOVED THE POWER LEVER INTO REVERSE THE NR 2 PROP WENT I	NTO REVERSE MOMENTARILY BUT THEN WENT INTO FORWARD PITCH WITH THE POWER LEVER STILL IN REVERSE.  AS A CONSEQUENCE THE RT	 WING MOVED FORWARD CAUSING THE AIRCRAFT TO SWING TO THE LT AND THE AIRCRAFT ENDED UP WITH ITS LT WING UNDER THE RT WIN	G OF THE PARKED AC, ITS LT SPINNER INTO THE RT WINDSHIELD OF THE PARKED AC, AND THE NR 1 PROP DAMAGED THE NOSE OF THE P	ARKED AIRCRAFT. AFTER TEMPORARY REPAIRS WERE COMPLETED AND THE NR 1 PROP AND ENGINE WERE CHANGED ON THE AIRCRAFT THAT HA	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007050400083	20070504	00083	CE  	2007	5	4	CA070329008      	1	20070327	G	3250	1018100327	TORQUE KNEE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	WORN            	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			7020 	7020 							(CAN) WHILE TAXING BACK TO THE RAMP, THE PILOT NOTICED THAT THE STEERING WAS MORE DIFFICULT AND INEFFECTIVE. HE SHUTDOWN	 BOTH ENGINES AND ON INVESTIGATION FOUND THE LT LANDING GEAR TORQUE KNEE BOLT DISCONNECTED. THE CAUSE OF THE DISCONNECTI	ON WAS A WORN OUT RETAINING WASHER. MAINTENANCE REPLACED THE WASHER AND RETURNED THE AIRCRAFT TO SERVICE. THIS AREA WAS 	RECENTLY INSPECTED. THE MM DOES NOT SPECIFY DISASSEMBLING THIS AREA TO INSPECT. THE ONLY WAY THIS COULD HAVE BEEN DETECT	ED WAS BY DISASSEMBLY.  OUR MAINTENANCE PROGRAM TRACKING SHEETS HAVE BEEN AMENDED TO INCLUDE DISASSEMBLY OF THE TORQUE K	NEES EACH 800 HOURS. (TC NR 20070329008)	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007050300004	20070503	00004	CE  	2007	5	3	CA070329009      	1	20070329	G	2897		WIRE            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	SHUTOFF VALVE	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA			434  								(CAN) 5 AMP ANNUNCIATOR INDICATION (CB4) POPPED IN FLIGHT AND THE CREW LOST THE GREEN AND WHITE ANNUNCIATOR LIGHTS. THE 	CREW ATTEMPTED TO RESET THE 5 AMP CIRCUIT BREAKER, BUT COULD NOT BE RESET.  PROBLEM WAS IN FOUND ON WIRE PIN D WIRE NR Q	62A20 ON THE RT FUEL SHUTOFF VALVE HAD CHAFED TO GROUND ON ONE OF THE SCREWS THAT HOLDS ON THE INSPECTION PANEL ON. DID 	A REPAIR ON WIRE NR Q62A20 AND THE SYSTEM WAS FUNCTION TESTED NORMAL. (TC NR 20070329009)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007050400086	20070504	00086	NE  	2007	5	4	CA070330002      	3	20070216	G	6114	58462	BARREL          	HAMSTD      		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				855  		112779					(CAN) PROPELLER HISTORY  - AUG 28 06 TTSOH 712.8 PROPELLER REPAIRED. - JAN 19 07 TTSOH 839.6 PROPELLER FLY WEIGHT ROLLER	 STIFF, ROLLER LUBRICATED AND RETURNED TO SERVICE. - FEB 16 07 TTSOH 854.9 PROPELLER REMOVED FROM SERVICE AND RETURNED T	O O/H SHOP FOR REPAIR, SLOW TO CHANGE PITCH. - MAR 13 07 TTSOH 854.9 PROPELLER REPAIRED BY O/H SHOP, NEW CYLINDER AND CO	UNTER WEIGHT ROLLER KITS INSTALLED. - MAR 15 07 TTSOH 854.9 PROPELLER INSPECTED BEFORE INSTALLATION ON AIRCRAFT AND THE 	REAR PORTION OF THE PROPELLER BARREL (HUB) WAS FOUND TO BE CRACKED FROM THE BOLT BOSS 90` TO THE REAR OF THE BARREL ALON	G THE OUTSIDE RADIUS.  CONTINUED OPERATION OF THE UNIT IN THIS CONDITION WOULD HAVE LED TO A CATASTROPHIC FAILURE.  THIS	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007050400092	20070504	00092	WP  	2007	5	4	CA070330003      	1	20070329	G	2780	N547E	RELAY           			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	TE FLAP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, THE FLAPS WERE SELECTED DOWN. THEY STOPPED  MOVING APPROXIMATELY HALF WAY DOWN. THE FLAP SOLENO	ID CIRCUIT BREAKER WAS OBSERVED TO BE OPEN. UPON INVESTIGATION  THE FLAP RELAY LOCATED IN THE GENERAL RELAY PANEL WAS FO	UND TO HAVE FAILED. THE RELAY WILL BE REPLACED WITH A SERVICEABLE UNIT. (TC NR 20070330003)				2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2007050400094	20070504	00094	NM  	2007	5	4	CA070330004      	1	20070329	G	3230		LANDING GEAR    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  		MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			48007	48007							(CAN) DURING CRUISE CREW RECEIVED INTERMITTENT LANDING GEAR INOP CAUTION LIGHT. CREW ELECTED TO RETURN TO ORIGINATING AI	RPORT. ALTERNATE GEAR EXTENSION USED TO LOWER LANDING GEAR.  NORMAL LANDING.  MAINTENANCE INSPECTION FOUND NO FAULTS. AI	RCRAFT WILL BE RETURNED TO SERVICE SUBJECT TO A SATISFACTORY TEST FLIGHT. (TC NR 20070330004)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050300005	20070503	00005	NE  	2007	5	3	CA070330005      	2	20070326	G	7261		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RIGHT	MAKING METAL    	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			14491	6131 				PS0149			(CAN) PILOTS LOADED PAX DEPARTED THE GATE. AFTER RECEIVING TAXI CLEARANCE THE PILOT NOTICED THE RIGHT LOW OIL PRESSURE W	ARNING LIGHT,THE AIRCRAFT WAS TURNED AROUND AND THE ENGINE SHUTDOWN. THE AIRCRAFT RETURNED TO THE GATE AND THE PASSENGER	S UNLOADED. THE AIRCRAFT WAS TOWED BACK TO THE MAINTENANCE HANGER AND INSPECTED. WHEN THE OIL FILTER WAS REMOVED THERE W	AS A LARGE AMOUNT OF SILVER COLORED MAGNETIC PARTICLES IN THE FILTER. THE ENGINE HAS BEEN REMOVED AND WILL BE SENT BACK 	TO MFG FOR INSPECTION/OVERHAUL, (TC NR 20070330005)		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007050300008	20070503	00008	NM  	2007	5	3	CA070402001      	1	20070329	G	6120	666000459	CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 PROPELLER	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING LEVEL FLIGHT FL. 250, ENGINE NR 2 PROPELLER SPEED WENT TO 1051 RPM, FOLLOWED BY POWERPLANT ON ED. THIS CASE	 WAS TREATED AS AN OVERSPEED AND QRH CONSULTED, ENDING UP WITH ENGINE SHUTDOWN, ON NR 2 ENGINE. EMERGENCY DECLEARED AND 	A NORMAL DESCENT TOWARDS BASE WAS INITIATED. LANDING PERFORMED AND TAXI TO REMOTE GATE WAS DONE.  MAINTENANCE ARRIVED AN	D FOUND FAULT CODE 160 CH A AND B. FIM TASK 61-20-04-810-813 PERFORMED. NO CONTACT WITH MPU AND BUSS BARS. REMOVE AND RE	PLACED MPU.  (TC NR 20070402001)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007050300010	20070503	00010	EU  	2007	5	3	CA070402002      	1	20070402	G	2910	7229160003	LINE            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FLUID WAS NOTICED ROUND ACCESS PANEL 151CB RT. INVESTIGATION REVEALED A WEAR MARK AND PIN HOLE IN A HYDR	AULIC LINE UNDER THE PANEL. FURTHER INVESTIGATION INDICATED THAT AN AJACENT PANEL BONDING STRAP HAD LOOPED WHEN THE PANE	L WAS CLOSED AND HAD BEEN RUBBING ON THE HYDRAULIC LINE. THAT THE STRAP WOULD CHAFE ON THE HYDRAULIC LINE WAS NOT OBVIOU	S WHEN THE PANEL WAS CLOSED. (TC NR 20070402002)			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2007050300019	20070503	00019	EU  	2007	5	3	CA070402003      	1	20070322	G	2917	973811430	PRESSURE SWITCH 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			165  								(CAN) DURING INSPECTION IT WAS NOTED THAT THIS HYDRAULIC PRESSURE SWITCH WAS LEAKING FLUID AT THE SWAGED SEEM OF THE SWI	TCH. THE SWITCH WAS REPLACED WITH NEW. (TC NR 20070402003)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007050300023	20070503	00023	EU  	2007	5	3	CA070402004      	1	20070330	G	7700	304544902	CHIP DETECTOR   			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6574 								(CAN) WHEN THE CONNECTOR WAS REMOVED FROM THE CHIP DETECTOR AT INSPECTION, IT WAS NOTED THAT ONE OF THE PINS OF THE CHIP	 DETECTOR HAD BROKE, AND STAYED IN THE CONNECTOR. THE CHIP DETECTOR WAS REPLACED. (TC NR 20070402004)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007050300026	20070503	00026	SW  	2007	5	3	CA070402006      	1	20070315	G	5610	36004314SS	WINDSHIELD      			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			6350 								(CAN) DURING A ROUTINE MEDIVAC FLIGHT AT AN ALTITUDE OF 12,000 FEET, THE FLIGHT CREW VISUALLY NOTED THAT THE RT WINDSHIE	LD WAS CRACKED ACROSS THE UPPER OB CORNER.  AIRCRAFT RETURNED TO BASE. INSPECTION OF THE WINDSHIELD FOUND THE OUTER WIND	OW PANE CRACKED APPROXIMATELY 2.5 INCHES LENGTH ACROSS THE CORNER.  NEW WINDSHIELD INSTALLED AND AIRCRAFT RETURNED TO SE	RVICE.  (TC NR 20070402006)			1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
2007050300030	20070503	00030	CE  	2007	5	3	CA070403001      	1	20070328	G	5740	SPS8178510	BOLT            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WING ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7540 								(CAN) DURING A SCHEDULED NDT INSPECTION OF THE WING ATTACHMENT BOLTS THE FWD UPPER BOLT ON THE RT SIDE WAS REJECTED AFTE	R THE LIQUID PENETRANT INSPECTION REVEALED A CRACK AT THE HEAD OF THE BOLT. THE BOLT HAD 7540.5 TSN. THIS INSPECTION IS 	DUE EVERY 1000 HRS. (TC NR 20070403001)				1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007050300031	20070503	00031	SW  	2007	5	3	CA070403002      	1	20070401	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA				5049 							(CAN) THE FLIGHT CREW OBSERVED THE LT HEATED WINDSHEILD DELAMINATE AND CRACK DURING FLIGHT. THEY CARRIED OUT THEIR EMERG	ENCY PROCEDURES AND LANDED AT THEIR POINT OF DESTINATION. MAINTENANCE REPLACED THE WINDSHEILD. NO REASON FOR THE FAILURE	 (IE IMPACT) COULD BE DETERMINED. THIS IS ONE OF MANY FAILURES OF THIS WINDSHEILD PN INCURRED BY THIS OPERATOR. MULTIPLE	 ATTEMPTS TO CONTACT THE MFG HAS RESULTED IN NO RESPONSE. (TC NR 20070403002)			2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P15EA	 
2007050300033	20070503	00033		2007	5	3	CA070403003      	4	20070321	G	6122	3020094	DRIVE GEAR      	WOODWARD    							GARRTT	TPE331	TPE331*     	01514	WP  					PROPELLER GOV	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1754695					(CAN) CONSTANT SPEED, SINGLE ACTING PROPELLER GOVERNOR P/N 895490-10 WAS RECEIVED AT MFG WITH REPORTED PROBLEM CUSTOMER 	RETURNED ON IN TRANSIT B69894 AND IRR NR 5170 STATING PROP GOVERNOR HAS NO RESET PRESSURE AND SHAFT STICKS AND WILL NOT 	RETURN TO MINIMUM STOP. THE FAULT WAS NOT CONFIRMED BY AN EXTERNAL VISUAL INSPECTION. A (RUN AS RECEIVED) WAS PERFORMED 	AND THE FOLLOWING WAS NOTED: ( PUMP CAPACITY WAS 7.8 QPM, SHOULD HAVE BEEN 9.0 QPM ) RELIEF VALVE PRESSURE WAS 440 PSI, 	SHOULD HAVE BEEN 465 +/- 20 PSI  MAGNETIC PICKUP WAS 3.2 VOLTS AT 3700 RPM, SHOULD HAVE BEE 4.5 +/- 0.2 VOLTS THE UNIT W	AS SYSTEMATICALLY DISASSEMBLED IAW COMPONENT MM (CMM 33091C, 1986), AND SIGNIFICANT DAMAGE WAS FOUND TO SEVERAL INTERNAL						3	T			E2WE				 
2007050300034	20070503	00034	SO  	2007	5	3	CA070403004      	1	20070331	G	3250	AN3H7A	ATTACH BOLT     	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	STEERING ARM	SHEARED         	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) DURING T/O ROLL DEPARTING CREW ABORTED T/O DUE A VIBRATION AND PULLING TO THE RIGHT. A/C TAXIED OFF RUNWAY, SHUTDO	WN AND CREW VISUALLY INSPECTED A/C, NO DEFECTS NOTED. TAXIED BACK TO HANGER, MTCE WAS NOTIFIED.  MAINTENANCE INSPECTION 	REVEALED (2) STEERING ARM ATTACH BOLTS SHEARED. NLG INSPECTED FOR OVER STEERAGE FROM GROUND HANDLING, NO OBSERVED DEFECT	S NOTED.  STEERING BOLTS REPLACED WITH NEW AND SYSTEM/TRAVEL/LANDING GEAR FUNCTION TESTS C/W .  (TC NR 20070403004)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007050300035	20070503	00035	EA  	2007	5	3	CA070403005      	1	20070331	G	3820	060150C1	WATER HEATER    			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					LAVATORY	ODOR            	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			5057 								(CAN) WHILE EN ROUTE, A BURNING ODOR WAS NOTICED BY THE CREW AND PASSENGERS.  NO SMOKE WAS APPARENT IN THE CABIN OR COCK	PIT.  THEN SEARCHED THE LAVATORY AND BAGGAGE COMPARTMENT.  A TRACE OF SMOKE WAS FOUND IN THE BAGGAGE COMPARTMENT.  A QUI	CK VISUAL INSPECTION OF THE LUGGAGE WAS CARRIED OUT TO SEE IF THIS WAS THE SOURCE OF THE SMOKE.  IT WAS NOT.  UPON EXITI	NG THE LUGGAGE COMPARTMENT THE SMOKE WAS SEEN SLOWLY ADVANCING TO THE PASSENGER CABIN.  CLOSED THE DOOR TO THE BAGGAGE A	REA AS WELL AS TO THE LAVATORY.  BRIEFED THE PASSENGERS TO NOT OPEN THE DOORS AND MOVED THEM TO THE MOST FORWARD SEATING	 POSITIONS.  DECLARED AN EMERGENCY AND REQUESTED TO LAND.  A RAPID DESCENT WAS INITIATED AND THE QRH PROCEDURE FOR SMOKE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050300036	20070503	00036	CE  	2007	5	3	CA070404001      	1	20070325	G	5610	10138402521	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE L/H OUTER WINDSHIELD PANE CRACKED IN SEVERAL PLACES. THE CREW CARRIED OUT THE APPLICABLE 	PROCEDURES AND LANDED AT THE NEAREST AIRPORT. THE WINDSHIELD WAS INSPECTED BY MAINTENANCE AND THE AIRCRAFT WAS FERRIED T	O A MAINTENANCE FACILITY WHERE THE WINDSHIELD WAS REPLACED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. (TC NR 2007040400	1)			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007050300037	20070503	00037	GL  	2007	5	3	CA070404002      	1	20070402	G	5511	C2TP39ND	RIB             	DHAV        		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						112					(CAN) DURING MAIN SPAR REPLACEMENT AFTER COMPLETION OF SB 2/47, A SINGLE NOSE RIB WAS FOUND TO BE HEAVILY CORRODED.  AIR	CRAFT TT 22235.0. THE AIRCRAFT OPERATES ON FLOATS IN A CORROSIVE ENVIRONMENT.  PREVIOUS CORROSION TREATMENT WAS NOT IN E	VIDENCE (TC NR 20070404002)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2007050300038	20070503	00038	EA  	2007	5	3	CA070404003      	1	20070403	G	2797	UK	WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RUDDER POSITION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			30222								(CAN) DURING AN INSPECTION, THE RUDDER POSITION TRANSMITTER HARNESS WAS FOUND TO BE DAMAGED. THE CAUSE OF THE DAMAGE WAS	 FOUND TO BE IMPROPER ROUTING BY COMPARING WITH ANOTHER A/C S/N 7163. THE ACTUAL ROUTING DRAWING WHERE REQUESTED FROM BO	MBARDIER AND THE HARNESS WILL BE REPAIRED AND REROUTED PROPERLY. (TC NR 20070404003)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050300040	20070503	00040	EU  	2007	5	3	CA070404004      	1	20070404	G	2910	AE2463774G0164	HOSE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					HYD SYSTEM	PUNCTURED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) GREEN HYDRAULIC ECAM MESSAGE LOW LEVER WARNING CAME ON AFTER TAKE OFF. ON ARRIVAL, MAINTENANCE FOUND THE RT MAIN L	ANDING GEAR DOWN LOCK ACTUATOR FLEX LINE HOSE LEAKING. FOUND HOLE IN FLEX LINE. FLEX LINE WAS REPLACED WITH BOTH HYDRAUL	IC PUMPS, CASE DRAIN FILTERS AND GREEN SERVO CONTROL MANIFOLD FILTERS.   (TC NR 20070404004)				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2007050400107	20070504	00107	NM  	2007	5	4	CA070404006      	1	20070329	G	2781	H1010262	SWITCH          			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 3 KRUGER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON FLAP RETRACTION THE CREW NOTICED THE NR 3 KRUGER FLAP INDICATED (IN TRANSIT).  CREW RETURNED TO BASE. NR 3 KRUG	ER FLAP RETRACT SWITCH WAS REPLACED AND A/C RETURNED TO SERVICE.  (TC NR 20070404006)					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007050400109	20070504	00109	SW  	2007	5	4	CA070404007      	1	20070404	G	2810	2060636321	FUEL CELL       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					LEFT	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) RETURNING FROM A FLIGHT IT WAS NOTED THERE WAS A FUEL ODOR IN THE REAR CABIN. INVESTIGATING DETERMED THE LT FWD FU	EL CELL HAD A SMALL LEAK. FUEL CELL WAS CHANGED OUT. (TC NR 20070404007)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007050400112	20070504	00112	CE  	2007	5	4	CA070404008      	1	20070329	G	5710	97430000150	CROSS TIE       			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	BS 187	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10546								(CAN) THE STRUCTURAL PIECE CALLED A CROSSTIE P/N 97-430000-150 WAS FOUND CRACKED DURING INSPECTION. IPC / REF: 53-10-20 	FIG. 20 ITEM NR 26. THE CRACK IS LOCATED LT SIDE OF AIRCRAFT AT FS 187.383 AND WL 119 ( LOWER LONGERON ). REPLACED WITH 	NEW. (TC NR 20070404008)				2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2007050700076	20070507	00076	EA  	2007	5	7	CA070404009      	1	20070401	G	2740	706010	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	MALFUNCTIONED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, FLIGHT EXPERIENCED A HSTA RUNAWAY. ACFT HAD JUST DEPARTED RUNWAY  AND FLAPS WERE RETRACTED 	TO 0 DEGREES. AUTOPILOT DISENGAGED. TRIM SELECTION INPUT MADE.  STABILIZER TRIM CONTINUED TO RUN & ASSOCIATED AURAL ALER	T SOUNDED.  IMMEDIATE ACTION CHECKLIST WAS COMPLETED, AS WAS QRH PROCEDURE.   MODERATE CONTROL PULL FORCES WERE REQUIRED	 TO FLY ACFT AT 10,000 & 250 KNOTS. CREW USED ACARS SYSTEM TO CALCULATE A WEIGHT & BALANCE, & REDISTRIBUTED CABIN LOAD T	O ALLEVIATE CONTROL FORCES. ICE ENCOUNTERED AT 10,000 FT & REQUIRED DESCENT TO 8,000 FT.   EMERGENCY DECLARED.  ACFT RET	URNED.    FLAPS SELECTED TO 20 DEGREES WHILE BETWEEN 8000 & 6000 FT.   CONTROL FORCES WERE SIGNIFICANTLY LIGHTER ONCE FL	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050400114	20070504	00114	EA  	2007	5	4	CA070404010      	1	20070328	G	5610	NP13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				B				EMER. DESCENT           				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THROUGH 11000` PILOTS WINDSHIELD SHATTERED.  REMARKS FROM PILOT (TOOK OFF CLIMBING THROUGH 11000 OR 1	2000) THE LT FRONT PILOT WINDSHIELD SPIDERWEBBED AND SHATTERED.  IT SPIDERWEBBED ALL AT ONCE VERY QUICKLY.  WE DECLARED 	AN EMERGENCY, DESCENDED TO 8000 FT AND SLOWED THE AIRCRAFT DOWN TO 190 KNOTS.  COMPLETED THE QRH FOR LT WINDSHIELD HEAT.	  TRANSFERRED THE CONTROLS TO THE FIRST OFFICER AND PREPARED FOR AN EMERGENCY LANDING.  BRIEFED THE FLIGHT ATTENDANTS AN	D SENT A MESSAGE TO DISPATCH VIA ACARS.  NEXT WE ADVISED OPS WE WERE RETURNING AND WERE ASSIGNED GATE.  FIRST OFFICER AN	D BRIEFED AN OVERWEIGHT LANDING AND COMPLETED IN RANGE AND BEFORE LANDING CHECKLIST.  CONDITIONS WERE GUSTY WINDS GUSTIN	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007050400118	20070504	00118	EA  	2007	5	4	CA070404011      	1	20070330	G	4900	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						FAILED          	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			4510 								(CAN) TECHNICIAN WAS TROUBLESHOOTING THE APU FOR APU AUTO SHUTDOWN, LOSS OF APU DOOR POSITION ON STATUS PAGE.  ECU CODE:	 109,224,91  MAINTENANCE FOUND THE ELECTRICAL CONNECTOR FOR OIL TEMP SENSOR PARTIALLY INSTALLED ( CODE 91). RESECURED TH	E CONNECTOR AND PROCEEDED TO START THE APU. AT THAT TIME NO FUEL LEAK / OIL LEAK WERE NOTED IN THE APU ENCLOSURE.  START	 THE APU WITH NO PROBLEM AND WITH BOTH A/C PACKS RUNNING, A STRONG SMELL OF FUEL IN THE COCKPIT AND GALLEY AREA WAS NOTE	D. SOME FUEL ON THE GROUND AT THE DRAIN AREA WAS NOTED.  SHUTDOWN THE APU, CLIMBED IN THE AFT EQUIPMENT BAY, START TO OP	EN THE OIL SERVICING PANEL ONCE A FEW FASTENERS WERE LOOSE THEN A FIRE FLARED UP. ASKED THE CREW TO DISCHARGE THE ONBOAR	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007061300141	20070613	00141	CE  	2007	6	13	CA070405001      	1	20070404	G	7830	LA7139A	BEARING         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					THRUST REVERSER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7285 			2537					(CAN) WATER INFILTRATED BETWEEN SLEEVE P/N LA7140 AND BEARING P/N  LA7139A CAUSING PIN HOLE CORROSION IN THE BEARING JAC	KET, ALLOWING WATER TO COME IN CONTACT WITH THE DRIVER LINK P/N 202-0007-3 PIVOT POINT CORRODING IT BEYOND REPAIR. (TC N	R 20070405001)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007080800150	20070808	00150	CE  	2007	8	8	CA070405003      	1	20070215	G	2720	04310031	BELLCRANK       			CESSNA	150   	150         	2071802	CE  	CONT  	O200  	O200A       	17020	SO  	SNSNCH	69CK	M69CK       	EA  	RUDDER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			10000								(CAN) FOLLOWING ITEMS FOUND INSTALLED: TRIANGLE DOUBLERS IAW SL 150-27; ANGLE STIFFENER NOT INSTALLED IAW SL 65-10. ANGL	E STIFFENER MIGHT BE INSTALLED IAW PERSONAL PLANE SERVICE LTD (OTTAWA). DRAWING NR PPS.161. HAVE NOT BEEN ABLE TO FIND A	 COPY OF PPS 161, AT THIS TIME (MARCH 29, 2007). IF CRACKED PART IS A NON CONFORMING PART, NO FURTHER ACTION IS NEEDED. 	MY CONCERNS IS THIS: IF PART IS IAW PPS 161, AND NO FURTHER ACTION IS REQUIRED AFTER INSTALLATION (A VERY LONG TIME AGO)	 AND THEY ARE CRACKING IN SERVICE IT COULD BE QUITE SERIOUS, IN MY OPINION TO LOSE RUDDER CONTROL. THE AREA IN QUESTION 	IS ALSO VERY DIRTY AND HARD TO LOOK AT DUE TO OIL ACCUMULATION AND DIRT. (TC NR 20070405003)	1	H	7	1 	3O	3	O	NT	3A19    	E252	5	N	P9045	 
2007050400120	20070504	00120	EA  	2007	5	4	CA070405005      	1	20070405	G	2120	C6VF11531	FLAPPER VALVE   	DHAV        		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RAM AIR DUCT	OBSTRUCTED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			14   								(CAN) THE RAM AIR FLAPPER VALVE, P/N C6VF1153-1, BECAME JAMMED IN IT`S DUCT. ATTEMPTS BY THE PILOT TO RECTIFY THE PROBLE	M BY MOVING THE CONTROL LEVER BACK AND FORTH RESULTED IN THE CONTROL CABLE, P/N 130-032A22.75B29.0, BECOMING KINKED AND 	UNSERVICEABLE.  DIS-ASSEMBLY OF THE SYSTEM REVEALED THAT THE RUBBER-LIKE MATERIAL USED TO SEAL THE PERIMETER OF THE FLAP	PER VALVE HAD BECOME DISTORTED AND ENLARGED, POSSIBLY DUE TO EXPOSURE TO HEAT. THIS CAUSED THE SEAL TO CONTACT THE INNER	 WALLS OF THE DUCT BEFORE THE FLAPPER WAS AT A 90-DEGREE ANGLE TO THE DUCT, IE: BEFORE THE FLAPPER WAS IN THE CLOSED POS	ITION.  REMOVAL AND REPLACEMENT OF THE DAMAGED CABLE AND FLAPPER VALVE REQUIRED REMOVAL AND REPLACEMENT OF MUCH OF THE A	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2007050400122	20070504	00122	EA  	2007	5	4	CA070405006      	1	20070405	G	3250	7116111	COLLAR          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STEERING SYS	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) STEERING COLLAR CRACKED AT RADIUSED AREA OF ATTACH STUD TO STEERING ACTUATOR. FOUND AT ROUTINE MAINTENANCE INSPECT	ION (TC NR 20070405006)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008022100003	20080221	00003	CE  	2008	2	21	CA070405007      	1	20070321	G	7603	565549012	THROTTLE CONTROL			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A105	1A105*      	GL  		BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			4475 								(CAN) PILOT REPORTED STRANGE, SPRINGY FEELING TO THROTTLE CONTROL. IT WAS DISCOVERED THAT THE OUTER PART OF THE CONTROL 	HAD SEPARATED WHERE IT WAS SWAGED TO THE FLEXIBLE, SPIRAL ROUND PART OF THE CONTROL. (TC NR 20070405007)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P918	 
2007050400123	20070504	00123	EA  	2007	5	4	CA070405008      	1	20070405	G	3220	713381	TORQUE LINK     			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOWER TORQUE LINK CRACKED AT ATTACHMENT LUG TO UPPER TORQUE LINK. CRACK FOUND ON ROUTINE MAINTENANCE INSPECTION (T	C NR 20070405008)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007051100002	20070511	00002	EA  	2007	5	11	CA070405009      	1	20070403	G	2450	VS643	RELAY           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					JUNCTION BOX NR6	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE IB, FLIGHT CREW NOTICED AN AC ESSENTIAL BUS MESSAGE FOLLOWED BY A POPPING SOUND AND A BURNED ODOR ON	 THE FLT DECK. LOOKED AT AC ELECTRICAL SYNOPTIC PAGE AND EVERYTHINGS WAS NORMAL BUT THE F/A NOTICED THAT THE EMERGENCY L	IGHTS WERE ON. FLIGHT CREW APPLIED QRH AND CARRIED ON FLIGHT.  ON ARRIVAL AT THE GATE, BURNED ODOR WAS STRONGER AND THEY	 SHUTDOWN EVERYTHING INCLUDING THE APU.  AFTER INVESTIGATION, MAINTENANCE FOUND AC ESSENTIAL RELAY K1XD BURNED IN JB6 AN	D CARBON TRACES WERE FOUND ON THE RELAY SOCKET AND JB6 BRACKET/CASING.  REF LOG NR 565535 AC ESSENTIAL SENSE RELAY K1XD 	P/N VS 643 AND RELAY SOCKET PN S0-1021-7127 WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070405009)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050400124	20070504	00124	SO  	2007	5	4	CA070405010      	1	20070405	G	3220	203601042	AXLE            	CURTIS      		CURTIS	C46   	C46DAIRLIFT 	       	SO  	PWA   	R2800 	R280051     	52026	NE  	HAMSTD	23E	23E50       	NE  	TAIL GEAR	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TAXI TO RUNWAY POSITION, TAIL WHEEL AXEL FRACTURED RESULTING IN TAIL WHEEL DEPARTING TAIL GEAR ASSEMBLY.  T	AXI WAS AT SLOW SPEED BUT TAIL FORK DAMAGED DURING AXEL FAILURE.  TAIL WHEEL FORK AND AXEL ASSEMBLY, WERE REPLACED AND A	IRCRAFT RETURNED TO SERVICE. (TC NR 20070405010)				2	L	7	2 	4R	4	R		3A2     	5E8	6	C	P603	 
	20080520		CE  	2008	5	20	CA070405011      	1	20070403	G	7110	05521335	SUPPORT         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48   								(CAN) THE ORIGINAL PART WAS FOUND CRACKED AND WAS REPLACED LESS THAN 50 HOURS AGO. THE CRACKS ORIGINATE AT THE 4 OCLOCK	 AND 8 OCLOCK POSITIONS, AT THE END OF THE FLANGED SECTION OF THE SUPPORT. SUBMITTER SUSPECTS THAT THE PULSATING AIRFLO	W FROM THE PROPELLER, WHICH IS IMMEDIATELY IN FRONT OF THIS ASSEMBLY, IS RESPONSIBLE FOR THE FATIGUE CRACKING.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007050400125	20070504	00125	NM  	2007	5	4	CA070407001      	1	20070404	G	5280		DOOR            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			44803	44803							(CAN) MAINTENANCE CARRIED OUT A LIGHTENING STRIKE INSPECTION IAW AMM 05-50-31 AND DAMAGE WAS NOTED ON THE RT FWD NOSE GE	AR DOOR, BURN AND PITTING MARKS ON BELLY FUSELAGE AND LT ELEVATOR STATIC WICK WAS BURNED OFF.  NDT WAS CARRIED OUT AND T	HE BELLY SKIN WAS REPAIRED IAW MFG RD8-53-9556 ISSUE 1, TEMP REPAIR FOR 1000 HRS.  THE ELEVATOR TIP FAIRING FASTENERS WE	RE REPLACED IAW SRM AND THE STATIC WICK WAS REPLACED AND BONDING CHECKS WERE CARRIED OUT.  RT NOSE GEAR DOOR A SCREW WAS	 REPLACED.  ALL SYSTEMS AND FLIGHT CONTROLS FUNCTION CHECKED SERVICEABLE AND THE A/C WAS RETURNED TO SERVICE. (TC NR 200	70407001)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007051100101	20070511	00101	NE  	2007	5	11	CA070409001      	2	20070330	G	7200		ENGINE          			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348E5     	30015	NE  					NR 1	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								194243			(CAN) ON TAKEOFF ROLL, 1ST OFFICER NOTICE A MOMENTARY FLUCTUATION OF ABOUT 2% ON NR 1 N1 GAGE JUST AFTER THE 80 KNOTS CA	LL.  N1 THEN STABILIZED UNTIL REACHING JUST OVER 100 KNOTS, FLUCTUATED AGAIN.  DID NOT HEAR OR FEEL ANY CHANGES IN ENGIN	E.  THERE WERE NO EICAS MSG AND ALL OTHER ENGINE READOUTS WERE STABLE AND NORMAL.  THIS WAS POSSIBLY A ERRONEOUS N1 READ	OUT, ELECTED TO CONTINUE TAKEOFF.  EVERYTHING NORMAL ON CLIMB UNTIL SHORTLY AFTER ACCELERATION ALTITUDE WHEN NR 1 N1 BEG	AN TO FLUCTUATE MORE SIGNIFICANTLY.   COULD NOW HEAR AND FEEL NR 1 ENGINE SURGING. WITHIN SECONDS, ENGINE WENT INTO AN O	VERSPEED CONDITION ACCOMPANIED BY A FADEC FAULT 1 STATUS MSG. BROUGHT THRUST LEVER TO IDLE, NO EFFECT.  DECLARED AN EMER	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2007050700176	20070507	00176	EA  	2007	5	7	CA070409002      	1	20070404	G	2913	R1309P216	PLUG            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT EDP	MISSING         	W				B				EMER. DESCENT           				K	J	Y	FLUID LOSS                	WARNING INDICATION        	ENGINE STOPPAGE           	CR	CRUISE         	1			CA			8717 								(CAN)  AFTER TAKEOFF FROM SOUTH BEND (SBN), THE AIRCRAFT CLIMBED TO FL 290. SHORTLY AFTER REACHING CRUISE ALTITUDE, THE 	RT ENGINE OIL PRESS WARNING ILLUMINATED FOLLOWED BY A DROP IN THE OIL PRESSURE ON THE RT OIL PRESSURE GAUGE. THE FLIGHT 	CREW PERFORMED THE QRH PROCEDURES AND REDUCED POWER ON THE RT ENGINE. SEEING THAT THE OIL PRESSURE CONTINUED TO DROP, TH	E CAPTAIN ELECTED TO SHUTDOWN THE ENGINE. AN EMERGENCY WAS DECLARED AND AN UNEVENTFUL APPROACH AND LANDING WAS MADE AT M	SP.  UPON LANDING, MAINTENANCE FOUND THAT THE AIRCRAFT HAD A MEL OPENED FOR NR 2 ENGINE DRIVEN HYDRAULIC PUMP. FURTHER I	NVESTIGATION REVEALED THE RT EDP HAD NOT BEEN PROPERLY MEL`D AND THAT THE OIL LOSS WAS THE RESULT OF A MISSING SPLINE PL	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050400126	20070504	00126	CE  	2007	5	4	CA070409003      	1	20070404	G	2910	25800	SELECTOR VALVE  			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA				2    							(CAN) VALVE WAS OVERHAULED BY VENDOR. AFTER OVERHAUL IT WAS INSTALLED IN THE AIRCRAFT. AFTER 2 HOURS OF OPERATION A LEAK	 DEVELOPED. THE VALVE WAS REMOVED AND DISTRIBUTION MANIFOLD DISASSEMBLED. WHEN CHECKING THE IPC IT WAS NOTED THAT AT OVE	RHAUL, THE OVERHAUL FACILITY FAILED TO INSTALL 2 O-RINGS. THE O-RINGS WERE INSTALLED AND RE-ASSEMBLED, THE AIRCRAFT GEAR	 SWING CARRIED OUT SATISFACTORY (TC NR 20070409003)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007080800151	20070808	00151	CE  	2007	8	8	CA070409004      	1	20070402	G	5610	551127517	WINDOW          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT`S STORM WINDOW DELAMINATED AT UPPER EDGE, RESULTING IN A CRACK FROM ATTACH HOLE RADIUS TO AFT EDGE. (TC NR 2	0070409004)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007050400221	20070504	00221	SO  	2007	5	4	CA070409005      	1	20070406	G	2823		SELECTOR        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	FUEL	FAILED          	W				D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING FUNCTIONAL TEST PRIOR TO TAKEOFF, WHEN MOVING FUEL SELECTOR FROM OB TO IB TANKS THE ROLL PIN CONNECTING THE	 FUEL SELECTOR HANDLE TO THE LINKAGE FAILED.  THIS FAILURE LEFT THE RT ENGINE FUEL SELECTOR IN THE OFF  POSITION, STARVI	NG THE ENGINE FOR FUEL.  THE AIRCRAFT RETURNED TO THE RAMP FOR REPAIRS.    (TC NR 20070409005)				1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2008021900367	20080219	00367	CE  	2008	2	19	CA070409006      	1	20070405	G	3230	508103385	DRAG BRACE      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	LT MLG	FAILED          	W				O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			TX	TAXI/GRND HDL  	1			CA											(CAN) AC WAS DISCOVERD OUTSIDE HANGER WITH THE LT MLG COLLAPSED.  THE FAULT OF THE PROBLEM WAS THE LT MLG DRAG BRACE. IT	 WAS REPLACED RECENTLY WHEN A SIMILIAR INCIDENT OCCURED TO THE RT MLG DRAG BRACE CAUSING THE LT MLG TO COLLAPSE WHILE BE	ING TOWED. DAMAGE CAUSED FROM THIS INCIDENT WAS AS FOLLOWS, DAMAGE TO LT WING TIP, LT MLG DOORS, LT MLG ACTUATOR, VHF AN	TENNA. THE AIRCRAFT WAS LIFTED AND JACKED AND A LOCALLY MFG DOWNLOCK WAS INSTALLED. THE AIRCRAFT IS IN THE PROCESS OF BE	ING INSPECTED FOR OTHER DAMAGE. THIS IS ONLY A PRELIMINARY REPORT, A MORE CONCLUSIVE REPORT WILL BE ADDED WHEN FINDINGS 	ARE COMPLETE. (TC NR 20070409006)	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007050700077	20070507	00077	WP  	2007	5	7	CA070409007      	2	20070228	G	7314		GEAR            								GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	FUEL PUMP	UNKNOWN         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								P63259			(CAN) GEARS DRIVING THE FUEL PUMP FAILED CAUSING THE ENGINE TO SHUTDOWN IN FLIGHT. (TC NR 20070409007)											4	T			E4WE	6	C	P61GL	 
2007050700078	20070507	00078	NE  	2007	5	7	CA070410001      	2	20070408	G	7260		CASE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	ACC GEARBOX	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			30198	10612				PW123150			(CAN) ON MARCH 28TH/07 IT WAS REPORTED AN OIL LEAK ON NR 2 ENGINE. THE OIL LEVEL WHEN DOWN 2L IN 5.55 HOURS OF FLIGHT TI	ME. THE PROPELLER ASSY AND THE LT SIDE OF THE ENGINE WAS REPORTED TO HAVE BEING WASHED WITH OIL AND BOTH THEY WERE INSPE	CTED FOR LEAKAGE. NO SIGNS OF DETERIORATION FOUND AT THE TIME AND IT WAS DECIDED TO DO A POWER RUN CHECK. AGAIN NO SIGNS	 OF LEAKAGE FOUND. ON MARCH 29TH/07 WAS REPORTED ANOTHER OIL LEAKAGE FROM NR 2 ENGINE. PERSONNEL INVESTIGATED THE PROPEL	LER AND THE ENGINE AND IT WAS FOUND AN APPROXIMATE 2. (TC NR 20070410001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050700079	20070507	00079	EU  	2007	5	7	CA070410002      	1	20070408	G	2750	1700637	DRIVE SHAFT     			EMB   	ERJ170	ERJ170100   	       	EU  	GE    	CF34  	CF348E5A1   	30015	NE  					FLAP DRIVE	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, THERE WAS A FLAP FAIL MSG. ACFT LANDED WITH FLAPS LOCKED OUT.  TROUBLESHOOTING REVEALED THAT GEAR	BOX SPLINED SHAFT AND DRIVE SHAFT WERE NOT LOCKED INTO PLACE BY LOCK SCREW.  SIMILAR SCENARIO OCCURRED ON RHS, WHERE THE	 IB MOST FLAP ACTUATOR DISCONNECTED WITH THE SPLINE IN THE SAME WAY.  THE LOCKBOLT WAS IN PLACE AND SAFETIED, BUT WAS NO	T INSTALLED THROUGH THE HOLE IN THE SPLINED SHAFT. ANGLED GEARBOX PN IS AS ABOVE, BUT FLAP ACTUATOR PN IS C154814-2. (TC	 NR 20070410002)		2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2007080800152	20070808	00152	CE  	2007	8	8	CA070410003      	1	20070327	G	3233	NAS464P4A29	BOLT            			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	LT MLG ACTUATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON SCHEDULED INSPECTION APPRENTICE FOUND ONE ATTACH BOLT BACKED OUT OF HOLE. ON REMOVING THE BOLT FULLY HE FOUND T	HE BOLT TO BE BROKEN. THE AIRCRAFT WAS JACKED UP AND THE ACTUATOR WAS REMOVED. THE OTHER 2 ATTACH BOLTS WERE INSPECTED A	ND FOUND WORN. THE ACTUATOR WAS INSPECTED FOR CRACKS. NONE FOUND. THE ATTACH BULKHEAD WAS INSPECTED ALSO. NO FAULTS WERE	 FOUND. THE ACTUATOR WAS REINSTALLED WITH NEW BOLTS. GEAR WAS SWUNG AND AIRCRAFT RETURNED TO SERVICE. SUSPECT THAT AS TH	ERE ARE NO LOCKING DEVICES OTHER THAN TORQUE, BOLTS LOOSENED OVER TIME AND BOLT BROKE DUE TO GEAR TRANSIT FORCES. (TC NR	 20070410003)	1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P36EA	 
2007050700178	20070507	00178	EU  	2007	5	7	CA070410004      	1	20070406	G	5753		BELLCRANK       			PZLWAR	WILGA 	PZL104W35A  	7360104	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			276  								(CAN) LOWER LT FLAP ACTUATOR BELLCRANK SUPPORT BRACKET CRACKED AT UPPER END. WHEN FLAP IS SUBJECTED TO A SIMULATED AIR L	OAD, THE SUPPORT BRACKET FLEXES AND THE CRACK VISIBLY OPENS.  THIS BRACKET HAS EVIDENCE OF PREVIOUS REPAIR (A DOUBLER IS	 PRESENT AT THE LOWER END). NONE OF THE OTHER (3) SUPPORT BRACKETS HAVE ANY DOUBLERS OR SHOW ANY EVIDENCE OF CRACKS. (TC	 NR 20070410004)			1	H	7	1 	3R	3	O	NC	EXPA1H71	1E4	5	C	P33EA	 
2007050700180	20070507	00180	SW  	2007	5	7	CA070411001      	1	20070409	G	6310	209340265103	SEAL            			BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			395  								(CAN) TRANSMISSION OIL PRESSURE DROP (2) BARS BELOW THE GREEN.  ON ROUTE BACK TO BASE THE TRANSMISSION OIL LOW PRESSURE 	LIGHT CAME ON UPON LANDING.  THE ENGINE DECK IS COVERED WITH OIL. THE FREEWHEEL AFT SEAL HAD POPPED OUT OF ITS BORE, RES	ULTING IN A LOSS OF OIL. (TC NR 20070411001)				1	G	7	1 	3U			O	H2SW    					 
2007050700080	20070507	00080	EU  	2007	5	7	CA070411002      	1	20070405	G	3230	A2757040500200	SWITCH          			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					MLG	STICKING        	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE AIRCRAFT HAD A (KRUGER) FAULT ECAM WARNING.QAH CARRIED OUT BUT WARNING REMAINED ON. AIRCRAFT RETU	RNED TO THE STATION. DURING TROUBLESHOOTING THE BITE TEST ON THE SFCC 1 AND 2 FAULTED THE RT RETRACT SWITCH. THE SWITCH 	WAS FOUND DIRTY AND STICKING AND TARGET WAS FOUND WORN. SWITCH WAS CLEANED AND TARGET ADJUSTED IAW MM. SYSTEM WAS TESTED	 SERVICEABLE.  (TC NR 20070411002)			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2008022000007	20080220	00007	SW  	2008	2	20	CA070411003      	1	20070317	G	6320		DRIVE GEAR      	KAMAN       	K974002103  	KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A1LYC  	41615	NE  					TRANSMISSION	DAMAGED         	W				E				ENGINE SHUTDOWN         				J	Z		WARNING INDICATION        	SIGNIFICANT FAILURE REPORT		IN	INSP/MAINT     	1			CA			7556 	2748 		AA1825					(CAN) DURING THE INITIAL START UP OF THE DAY, AT APPROX 10 PERCENT ROTOR RPM, AN ABNORMAL NOISE WAS HEARD COMING FROM TH	E POWER TRAIN AND A TRANSMISSION CHIP WARNING LIGHT INDICATION. THE START WAS THEN ABORTED. THE ATTENDING AME INSPECTED 	THE TRANSMISSION SYS CHIP PLUGS AND FOUND AN ABUNDANCE OF PARTICLES OF ON THE LT SUMP CHIP PLUG.  PRODUCT SUPPORT WAS CO	NTACTED AND WANTED US TO REMOVE THE OIL PUMP AND THE OIL PUMP DRIVE ASSY AND INSPECT THE OIL PUMP DRIVE GEAR FOR DAMAGE.	 THIS INSPECTION REVEALED THE DRIVE GEAR HAD SUSTAINED SIGNIFICANT DAMAGE. THIS GEAR IS INSIDE THE TRANSMISSION MAIN HOU	SING AND IS NOT FIELD REPAIRABLE ITEM. THE TRANSMISSION WAS SUBSEQUENTLY REPLACED ON LOCATION WITH TSO 0.0 UNIT INSTALLE	1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
	20081104		WP  	2008	11	4	CA070411004      	1	20070408	G	6310	V31001	SWITCH          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH ASSY	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			507  								(CAN) DURING GROUND RUN AND PRE-TAKEOFF CHECKS, THE CLUTCH FAILED TO ENGAGE. SWITCH V3-1001 IS SPRING LOADED AND BREAKS 	AND THE CLUTCH WILL NOT ENGAGE. THESE SWITCHES ARE A WEAK PART OF THE SYSTEM. (TC NR 20070411004)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007050700081	20070507	00081	EA  	2007	5	7	CA070411005      	1	20070410	G	5310	C3FS249	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	WINDSCREEN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REPLACEMENT OF THE LT WINDSCREEN, CORROSION WAS FOUND ON THE STRUT PN C3FS2-49.  AFTER REMOVAL OF SEALANT I	T WAS NOTED THE STRUT WAS CORRODED COMPLETELY THROUGH ONE OF THE WALLS OF THE STRUT.   RT STRUT INSPECTED AND NO FAULT F	OUND (TC NR 20070411005)				1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2007050700082	20070507	00082		2007	5	7	CA070411006      	4	20070411	G	2300	52611	CONTROL PANEL   			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AUDIO CONTROL	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			32513	4328 							(CAN) ENROUTE CREW NOTICED SMOKE COMING FROM AUDIO CNTRL PANEL, PULLED CIRCUIT BREAKER, SMOKE STOPPED. CREW DONNED O2 MA	SKS AND ELECTED TO RETURN TO ORIGINATING AIRPORT FOR NORMAL LANDING. MAINTENANCE REPLACED LT AUDIO CNTRL PANEL AND AIRCR	AFT RETURNED TO SERVICE (TC NR 20070411006)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050700083	20070507	00083	SW  	2007	5	7	CA070412001      	1	20070320	G	7120	206062102001	MOUNT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A ROUTINE ENGINE REPLACEMENT, IT WAS FOUND THAT THE LT LOWER ENGINE MOUNT WAS CRACKED AT THE ATTACH POINT. AFTE	R CLOSER INSPECTION THE MOUNT WAS COMPLETELY SEPARATED FROM THE AIRFRAME. THERE WAS NO INITIAL INDICATION OF A PROBLEM. 	IT WAS FOUND THAT THERE WAS EXCESSIVE TORQUE ON THE ATTACH BOLT TO THE AIRFRAME. THE ATTACH POINT WAS ALSO CUPPED TO IND	ICATE THAT THE PROPER PROCEDURE WAS NOT USED TO REMOVE THE ENGINE IE; LOOSENING THE ENGINE MOUNTS FIRST. (TC NR 20070412	001)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081104		EA  	2008	11	4	CA070412002      	1	20070411	G	3246	50105844	WHEEL           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6421 	1492 							(CAN) DURING ROUTINE NDT HFEC INSP OF MAIN WHEELS, ACCORDING TO ABSC NDT MANUAL PART 1, CH. 32-42-03, CRACKS WERE FOUND 	IN THE LOCKING RING GROOVE. THE DEPTH OF 3 CRACKS IS GREATER THAN .040 INCH AND THE LENGTH OF THE CRACKS ARE 30MM, 20MM 	AND 5MM. ONE CRACK HAS A DEPTH OF .020 INCH AND A LENGTH OF 20MM. COMPONENT COULD BE SENT FOR MACHINING, BUT THE DEFECT 	DEPTH IS ALREADY GREATER THAN THE MACHINING LIMITS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081104		EA  	2008	11	4	CA070412003      	1	20070411	G	3246	50105844	WHEEL           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6421 	1492 							(CAN) DURING ROUTINE NDT HFEC INSP OF RJ MAIN WHEELS, ACCORDING TO NDT MANUAL PART 1, CH. 32-42-03, CRACKS WERE FOUND IN	 THE LOCKING RING GROOVE. THE DEPTH OF 3 CRACKS IS GREATER THAN .040 INCH AND THE LENGTH OF THE CRACKS ARE 30MM, 20MM AN	D 5MM. ONE CRACK HAS A DEPTH OF .020 INCH AND A LENGTH OF 20MM. COMPONENT COULD BE SENT FOR MACHINING, BUT THE DEFECT DE	PTH IS ALREADY GREATER THAT THE MACHINING LIMITS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050700084	20070507	00084	NE  	2007	5	7	CA070412004      	2	20070330	G	7323	116085023	GOVERNOR        			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2920 	1160 				LE07576			(CAN) DURING THE DAILY INSPECTION PERFORMED BY THE ENGINEER, THE SCREW HOLDING THE GOV SERVO LEVER PLATE IN PLACE WAS EN	TIRELY BACKED OUT OF THE HOLE.  THIS PART HAD BEEN REPLACED, TESTED AND ADJUSTED AT TSN 2346.3 FOR LOOSE SCREWS.  THE SC	REWS ARE STAKED IN PLACE AND YET WERE STILL ABLE TO BACK OUT. THE GOVENOR WAS SENT FOR REPAIR. THE SCREW MAY POISE A RIS	K IN JAMMING THE SERVO LEVER. (TC NR 20070412004)			1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007050700085	20070507	00085	NM  	2007	5	7	CA070412005      	1	20070407	G	3110	B030302104C94	HOSE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	INSTRUMENT PANEL	CUT             	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			908  								(CAN) CREW REPORTED THAT THE INTEGRATED STANDBY ELECTRONIC INSTRUMENT WAS NOT READING THE SAME AS THE PRIMARY FLYING DIS	PLAYS.  INVESTIGATION REVEALED THAT THE LINES TO THE INSTRUMENT HAVE TO BE REMOVED TO PERFORM AD CF2005-15 PART B.  ON R	EASSEMBLY IF THE LINES ARE NOT ORIENTED PROPERLY THAT WILL CHAFE ON STRUCTURE. (TC NR 20070412005)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007050700097	20070507	00097	EA  	2007	5	7	CA070413001      	1	20070407	G	7830		COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THRUST REVERSER	DEPARTED        	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) A/C EXPERIENCED A THRUST REVERSER UNLOCK IN FLIGHT AT A CRUISE FLIGHT LEVEL OF 16000 FEET WITH AN APPROXIMATE SPEE	D OF 280 KNOTS.  A SMALL VIBRATION IN THE AIRFRAME WAS FELT BY THE CREW PRIOR TO RECEIVING THE (REVERSER UNLOCK) MSG, FO	LLOWED BY A LOUD BANG, WITH THE AIRCRAFT PITCHING UP AND ROLLING LT. THE CREW STOWED THE REVERSER AND VIBRATIONS SUBSEQ	UENTLY STOPPED.  UPON LANDING INTO ORD UNDER A DECLARED EMERGENCY, IT WAS NOTE THAT T/R TRANSLATING COWLS WERE MISSING, 	ALONG WITH THE STRUCTURAL DAMAGE TO THE VERTICAL AND HORIZONTAL STAB.  LIST OF AFFECTED COMPONENT TO FOLLOW. (TC NR 2007	0413001)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050700098	20070507	00098	NM  	2007	5	7	CA070413002      	1	20070409	G	3230	69141061	CYLINDER        			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE CREW OBSERVED AN A SYSTEM DEPLETION CONDITION AFTER EXTENDING THE LANDING GEAR. THE AIRCRAFT LANDED WITHOUT FU	RTHER PROBLEM. MAINTENANCE FOUND THE NOSE LANDING GEAR SYSTEM TRANSFER CYLINDER HAD FAILED. THE CYLINDER HAD FAILED AT T	HE LAST END CAP THREAD. THE UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070413002)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2008021900368	20080219	00368	EA  	2008	2	19	CA070413003      	1	20070411	G	3240	B121	PEDAL           			FOUND 	FBA   	FBA2C1      	3640103	EA  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			147  								(CAN) DURING CLEAN UP AFTER THE REPLACEMENT OF THE FUEL GAUGE ON AC 52 MECHANIC NOTICED THAT THE CO-PILOTS BRAKE-PEDAL A	SSY WAS CRACKED. AFTER DISCUSSION WITH CHIEF ENGINEER HE NOTED THAT THIS WAS THE SECOND TIME, IT HAD HAPPENED PREVIOUSLY	 TO AC 53. FOUND MFG HAS INITIATED A MATERIAL REVIEW BOARD, A SB WILL BE MAILED OUT. THE SB WILL REQUIRE AN IMMEDIATE VI	SUAL INSPECTION TO THE BRAKE PEDAL AND A VISUAL INSPECTION EVERY 100 HOURS AFTERWARDS. IF A CRACK IS FOUND OR TO TERMINA	TE THE SB, A DOUBLER WILL BE INSTALLED. A TEST FIXTURE WILL BE FABRICATED TO TEST THE CRACKED BRAKE PEDAL TO FIND THE RE	SIDUAL LOAD. THE FIXTURE WILL ALSO BE USED TO TEST A REPAIRED PEDAL AND A NEW DESIGN OF BRAKE PEDAL. (TC NR 20070413003)	1	H	7	1 	3O			NC	A7EA    					 
2007050700099	20070507	00099	EA  	2007	5	7	CA070413004      	1	20070410	G	6120	C6NF1117	CONTROL BOX     			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BETA SYSTEM	FAILED          	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) THE AIRCRAFT WAS BEING USED FOR CREW TRAINING WHEN, ON TAKEOFF, THE RT PROPELLER RPM DROPPED TO 30 PERCENT. THE PI	LOTS ABORTED THE TAKEOFF AND RETURNED TO THE RAMP. THE PILOTS NOTED THAT NP WAS STILL AT 30 PERCENT WITH THE POWER LEVER	 AT IDLE. THE PROPELLER WAS FEATHERED WITH THE PROP LEVER AND IT DID SO. WHEN THE PROP LEVER WAS SELECTED FULLY FWD THE 	PROPELLER WOULD NOT UNFEATHER. TROUBLESHOOTING REVEALED THAT THERE WAS POWER TO THE BETA BACKUP SOLENOID VALVE. FURTHER 	TROUBLESHOOTING LED BACK TO THE BETA BACKUP CONTROL BOX P/N C6NF1117. THIS WAS REPLACED AND THE AIRCRAFT CHECKED SERVICE	ABLE.  IT IS SUSPECTED THAT RELAY K4 MAY HAVE MALFUNCTIONED. THE CONTROL BOX IS BEING RETURNED TO THE OEM FOR EXAMINATIO	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081104		CE  	2008	11	4	CA070416001      	1	20070413	G	8011	PM2401	HOUSING         	LAMAR       		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	STARTER	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			965  								(CAN) PILOT ATTEMPTED TO START THE ACFT. ALL THAT COULD BE HEARD WAS A CLICKING NOISE. FURTHER INVESTIGATION REVEALED TH	E FWD HSG WAS CRACKED CAUSING THE INCORRECT ENGAGEMENT OF THE STARTER BENDIX. STARTER WAS REPLACED AND ACFT RETURNED TO 	SERVICE. (TC NR 20070416001)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007050700101	20070507	00101	CE  	2007	5	7	CA070416002      	1	20070413	G	7720	3034389	PROBE           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE T5	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 7 OUT OF 8 T5 INDICATION PROBES WERE FOUND WITH LOOSE OR BROKEN TERMINALS AND MISSING CERAMIC INSULATION.  THE PRO	BES APPEAR TO QUITE FRAGILE IN COMPARISON TO THE OEM PART.  THE PARTS IN QUESTION ARE PMA PARTS, THEIR PN 26584.  PROBES	 REPLACED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20070416002)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007050700102	20070507	00102	NM  	2007	5	7	CA070416003      	1	20070415	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER T/O LANDING GEAR WOULD NOT RETRACT WHEN SELECTED.  A/C RETURNED TO BASE FOR MAINTENANCE INSPECTION. HARNESS 	WOW NR 2 REPLACED IAW AMM. A/C RTS (TC NR 20070416003)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007050700105	20070507	00105	NM  	2007	5	7	CA070416004      	1	20070413	G	6120	699018002	CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 PROP	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) CREW COMPLETED A NR 2 ENGINE SHUTDOWN MANUALLY (IFSD) DUE POWERPLANT MESSAGE AND PEC CAUTION. MAINT ARRIVED AND FC	 161 CH A AND B. FIM TASK PERFORMED. NO CONTACT WITH MPU AND BUSS BARS. REMOVED & REPLACED PEC. (TC NR 20070416004)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007050700106	20070507	00106	EA  	2007	5	7	CA070416005      	1	20070413	G	3297		CONNECTOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					SELECTOR VALVE	CONTAMINATED    	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			14977	8924 		1999					(CAN) ON APPROACH NOSE LANDING GEAR DID NOT EXTEND.  CREW CARRIED OUT A GO-AROUND AND COMPLETED A MANUAL EXTENSION.  THE	 GEAR LOWERED AND LOCKED-CREW RECEIVED 3 GREENS IN THE COCKPIT.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE WAS 	DISPATCHED TO TROUBLESHOOT.  PSEU CODES READ AND FORWARDED TO TECH OPS.  AFTER CONSULTATION WITH TECH OPS, SUSPECT THE N	LG SELECTOR VALVE AT FAULT.  AFTER FURTHER INSPECTION IT WAS NOTED THAT THE NLG SELECTOR VALVE HAD A SLIGHT LEAK NR THE 	SOLENOID CONNECTOR PLUG WAS CONTAMINATED WITH HYD FLUID.  THE SELECTOR VALVE WAS REPLACED AND GEAR SWINGS WERE CARRIED O	UT WITH NFF AND A/C WAS RETURNED TO SERVICE WITHOUT ANY FURTHER INCIDENTS.  (TC NR 20070416005)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050700107	20070507	00107	NM  	2007	5	7	CA070416006      	1	20070315	G	2750	C1486742003	CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA			1613 								(CAN) ENROUTE BASE, THE FLAP POWER CAUTION LIGHT ILLUMINATED. RESET WAS CARRIED OUT IAW QRH 10.11 HOWEVER ONE MINUTE LAT	ER THE CAUTION LIGHT RE-ILLUMINATED.  IAW THE QRH FLAPS RENDERED UNAVAILABLE FOR LANDING. FLAPLESS LANDING WAS CARRIED O	UT WITHOUT INCIDENT. ENGINEERING INVESTIGATION REVEALED FAILURE OF THE FLAP CONTROL UNIT. UNIT REPLACED AND TESTED IAW M	AINTENANCE MANUAL REQUIREMENTS. AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. AS DEFECT CONFIRMED WITH REPLACEM	ENT OF THE FCU. (TC NR 20070416006)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007050700108	20070507	00108	SO  	2007	5	7	CA070416007      	1	20070416	G	2910	OAS229307	POWERPACK       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1091 			317552010				(CAN) DURING A MAINTENANCE RUN AFTER WORK ON AN ENGINE THE MECHANICS DID A HYDRAULIC PUMP CHECK BY SELECTING HANDLE TO G	EAR DOWN POSITION.  THE HANDLE WOULD NOT RETURN TO THE NEUTRAL POSITION AS IS NORMAL.  WHEN GEAR SWINGS WERE CARRIED OUT	 IN THE HANGAR THE OB GEAR DOORS WOULD ONLY PROCEED HALFWAY AND THEN SIT AND SHUDDER.  A LOUD BANG WAS HEARD FROM THE PO	WERPAK AND THEN THE DOORS WOULD CLOSE OR OPEN AS SELECTED.  THERE WAS NO PRIOR INDICATION OF PROBLEMS WITH THE POWERPACK	. (TC NR 20070416007)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007050700109	20070507	00109		2007	5	7	CA070416008      	4	20070324	G	3460	101741111	COMPUTER        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	FMS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA			534  								(CAN) CREW REPORTED FMS FAILED THEN FLIGHT DECK EXPERIENCED SMOKE AND FUMES. CREW ELECTED TO RETURN THE AIRCRAFT TO BASE	 WHERE A LANDING WAS CARRIED OUT WITHOUT INCIDENT.  ENGINEERING REPLACED THE FMS UNIT. INITIAL INVESTIGATION OF THE REMO	VED UNIT INDICATES AN ELECTRICAL FAILURE OF AN INTERNAL CIRCUIT BOARD. UNIT HAS BEEN RETURNED TO THE MFG FOR REPAIR AND 	WITH A REQUEST TO PROVIDE A STRIP REPORT. (TC NR 20070416008)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050700110	20070507	00110	NM  	2007	5	7	CA070416009      	1	20070327	G	2421	31708001A	GENERATOR       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 AC SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON INITIAL CLIMB AFTER TAKEOFF THE AC GENERATOR `HOT` CAUTION LIGHT ILLUMINATED. CREW ELECTED TO RETURN THE AIRCRA	FT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT. ENGINEERING REPLACED THE AC GENERATOR AND RET	URNED THE AIRCRAFT TO SERVICE. (TC NR 20070416009)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061500189	20070615	00189	SW  	2007	6	15	CA070417001      	1	20070412	G	3242	A032	VALVE           	PARAMOUNT   		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					MASTER CYLINDER	STUCK           	W				O				OTHER                   				S			AFFECT SYSTEMS            			LD	LANDING        	1			CA				5282 		13026					(CAN) THE AC RT MLG TIRES WERE BLOWN UPON LANDING. DURING INSPECTION IT WAS FOUND THAT THE RT BRAKE ASSY WERE DRAGGING A	ND OVERHEATED CAUSING THE WHEELS NOT TO TURN FREELY UPON TOUCHDOWN.  TIRES, BRAKES AND AFFECTED BRAKE MASTER CYLINDERS W	ERE REPLACED. AN INITIAL TEARDOWN OF THE MASTER CYLINDERS INDICATED THAT THE CAPTAIN`S RT CYLINDER WAS AT FAULT DUE TO M	ALFUNCTIONS OF INTERNAL COMPONENTS. AD 2002-08-01 DEALS WITH A SPECIFIC FAILURE MODE OF THESE MASTER CYLINDERS AND HAVE 	A OVERHAUL LIMIT OF 15000 HRS TIS. THESE MASTER CYLINDERS HAD 5282.00 HRS TT SINCE OVERHAUL.  FURTHER INVESTIGATION REVE	ALED THAT THE COTTER PIN (AN380-2C2) WHICH HOLDS THE VALVE IN THE MASTER CYLINDER TO THE ACTUATING ARM WAS BENT NOT ALLO	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2007051100003	20070511	00003	EA  	2007	5	11	CA070417002      	1	20070417	G	5751	2151500080680	RIB             			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	AILERON	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DAMAGE FOUND TO BOTH AILERONS ON THE (2) FIRST CENTER HINGE RIBS ASSEMBLY, ADJACENT TO THE FIXED STOPS.  A/C HOURS	;  4658.7, CYCLES;   2973  (TC NR 20070417002)					2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
	20081104		EU  	2008	11	4	CA070417003      	1	20070409	G	3240	RFS1010	DISK            			BAG   	JETSTM	JETSTM3101  	1500215	EU  										MLG BRAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISC WAS FOUND BROKEN IN HALF. NEW BRAKE UNIT INSTALLED.						2	L	7	2 	4T			RT	A21EU   					 
2007050700125	20070507	00125	GL  	2007	5	7	CA070418001      	1	20070416	G	3810	4E32612	POTABLE WATER   			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					GALLEY	LEAKING         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			422  								(CAN) FOLLOWING THE ADVISORY WIRE FROM MFG, THE WATER SYSTEM VENT VALVES (6) WHERE REPLACED IN MFG. ON THE NEXT CUSTOMER	 FLIGHT, ONE VENT VALVE FROM THE GALLEY HAS STARTED TO LEAK. END RESULT, AVIONICS BAY FLOODED, BLACK BOXES FULL OF WATER	. INVESTIGATION SHOWED THAT THE 2 VALVES ARE ACTING REVERSE. AS A TEMPORARY MEASURE, MFG DRAWING NR BAS67038670 INCORPOR	ATED. (REMOVED VENT VALVES AND INSTALLED PLUGS) (TC NR 20070418001)			2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
	20081104		EA  	2008	11	4	CA070418002      	1	20070227	G	3240	0860162001	ACCUMULATOR     			DHAV  	DHC8  	DHC8311     	1386006	EA  										PARKING BRAKE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			33458	21048							(CAN) WHILE PERFORMING AN LPI ON THE LANDING GEAR (PARKING BRAKE ACCUMULATOR), (3) AXIAL CRACKS WERE FOUND IN THE BOTTOM	 PORTION OF THE INSPECTION AREA. THIS INSPECTION WAS IN SUPPORT OF SB A8-32-162. THE CRACKS EXTEND OUTSIDE THE TAPERED S	ECTION AND ARE .75, .50, AND .25 IN LENGTH. RETURNED TO STORES FOR REPAIR.				2	H	7	2 	4T			RT	A13NM   					 
	20081104		SW  	2008	11	4	CA070418003      	1	20070321	G	7120	205060105001	MOUNT           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			91   								(CAN) ENGINE MOUNT WAS INSTALLED NEW IAW  STC SH99-11. POWER PLANT WAS ALIGNED IAW MM SUPPLEMENT. THE MM SUPPLEMENT INCL	UDES AN INSP EVERY 100 HRS OR ANNUALLY. NOTE TO INSPECT ENGINE MOUNTS FOR CRACKS, DAMAGE, CORROSION AND SECURITY. THE CR	ACK STARTED BELOW THE MOUNT BETWEEN THE WELDS AND MOVES INWARD. ACFT WAS CHECKED FOR VIBRATION AND ALIGNMENT NO DEFECTS 	NOTED.			1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081104		EA  	2008	11	4	CA070418004      	1	20070301	G	3240	0860162001	ACCUMULATOR     			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	PARKING BRAKE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			34933	5783 							(CAN) WHILE PERFORMING AN LPI INSPECTION ON THE LANDING GEAR (PARK BRAKE ACCUMULATOR) IAW SB A8-32-162 A .015 CORROSION 	PIT WAS FOUND IN THE RADIUS OF THE TOP CAP,BETWEEN THE TAPERED SECTION AND THE SHAFT OF THE CAP.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050700129	20070507	00129		2007	5	7	CA070418005      	4	20070416	G	3497	M227591622	WIRE            			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	PT6   	PT6A67R     	52043	NE  	HAMSTD	23E	23E50       	NE  	AIRSPEED WARNING	ARCED           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) THE AIRSPEED AURAL WARNING CIRCUIT BREAKER WAS FOUND TO BE (POPPED).  WHEN THE UPPER PANEL WAS LOWERED EVIDENCE OF	 ARCING WAS FOUND ON AIRFRAME STRUCTURE.  THE WIRE WAS REPAIRED THROUGH PARTIAL REPLACEMENT, CHAFE PROTECTOR WAS ADDED T	O THE AIRFRAME STRUCTURE AND THE WIRE BUNDLE AND THE WIRE BUNDLE WAS RE-POSITIONED. (TC NR 20070418005)				2	L	7	2 	4R	4	T		A669    	E26NE	6	C	P603	 
2007050700130	20070507	00130	NE  	2007	5	7	CA070418006      	2	20070322	G	8530	CH90ER	CYLINDER HEAD   								PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				586  							(CAN) ON 100 HR INSPECTION DURING A DIFFERENTIAL CHECK CYLINDER WAS READING LOW. USING A SOAP SOLUTION IT WAS DETERMINED	 THAT THERE WAS A LEAK ACROSS THE HEAD DUE TO A CRACK BETWEEN THE COOLING FINS. (TC NR 20070418006)										3	R			5E1				 
2007050700133	20070507	00133	GL  	2007	5	7	CA070418007      	1	20070417	G	5341	VALTB12091	FITTING         			DHAV  	DHC1  	DHC1        	2801702	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	WING TO BODY	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			6052 								(CAN) A CURSORY INSPECTION REVEALED CORROSION ON THE LT PORK CHOP FITTING. BOTH LT AND RT FITTINGS WERE REPLACED WITH NE	W UNITS. DEPTH OF CORROSION WAS APPROX 25 PERCENT OF PART OVERALL THICKNESS. THE MANUFACTURE WAS CONTACTED. THE PART IN 	QUESTION IS APPROX 11 YEARS OLD. (TC NR 20070418007)				1	L	7	1 	3O	3	R		EXPA1L71	5E1	5	C	P28EA	 
2007080800153	20070808	00153		2007	8	8	CA070419001      	4	20070418	G	3197		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 1 FEEDER	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) DURING AN ATTEMPT TO RUN THE AIRCRAFT TO FUNCTION CHECK THE WINDSHIELD ANTI-ICE BLEED AIR (SNAG-NO BLEED AIR TO TH	E WINDSHIELD FOR ANTI-ICE UNTIL WINDSHIELD ANTI-ICE CB IS PULLED). WHEN THE BATTERY SWITCH WAS TURNED ON THE LT CB PANEL	 35 AMP CIRCUIT BREAKER (LOCATED ON THE RT HAND CB PANEL) POPPED.  IT WAS DISCOVERED THAT THE NR 1 FEEDER WIRE (P10A6) F	OR THE LT BUSS, THE INSULATION HAD ABRADED THROUGH AND MADE CONTACT WITH A SCREW ON THE BACK OF THE DE-ICE PANEL ASSY.  	THIS WAS THE DIRECT CAUSE OF THE ABOVE MENTIONED 35AMP CIRCUIT BREAKER POPPING.  WHEN THIS DE-ICE SIDE CONSOLE PANEL ASS	Y IS INSTALLED. (3) 6 GAUGE WIRES (ALL LT BUS FEED WIRES P10A6, P11A6 AND P12A6) ARE ROUTED IN BEHIND THIS PANEL.  THE F	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007050700136	20070507	00136	EA  	2007	5	7	CA070419002      	2	20070413	G	7230		BLADES          	PWC         		BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COMPRESSOR	DEPARTED        	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA				4538 				PCE51225			(CAN) LT ENGINE EXPERIENCED A SUDDEN POWER LOSS ON CLIMB OUT. THE ENGINE WAS SHUTDOWN AND THE A/C RETURNED TO BASE WITHO	UT ANY FURTHER INCIDENT. THE POWER SECTION WAS REMOVED FOR INVESTIGATION.   THE INVESTIGATION REVEALED THAT PIECES WERE 	MISSING FROM SEVERAL CT IGV`S, MULITPLE CT BLADES BEING DAMAGED (IE. MISSING PIECES) AS WELL AS DAMAGE TO SEVERAL PT BLA	DES AND GUIDE VANES. THE ENGINE HAS 4538.3 HRS AND 4622 CYCLES SINCE O/H AND IS ON CONDITION FOR HOT SECTION INSPECTIONS	. THE LAST HSI WAS COMPLETED 2068.6 HRS AND 2695 CYCLES AGO WHEN 0.0 TSO CT BLADES P/N 3039901 WERE RE-INSTALLED.  THE E	NGINE HAS BEEN SENT FOR O/H AND FURTHER INFO WILL BE AVAILABLE AFTER WHEN A TEARDOWN REPORT BECOMES AVAILABLE (TC# 20070	1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007050700137	20070507	00137	CE  	2007	5	7	CA070419003      	1	20070418	G	5540	1145240253	TORQUE SHAFT    			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15917								(CAN) DURING A PHASE INSPECTION IT WAS DISCOVERED THAT THE RUDDER TORQUE SHAFT WAS CORRODED. IT IS BELIEVED THAT THE COR	ROSION OCCURRED DUE TO WATER MIGRATION FROM THE VERTICAL STABILIZER. THE TORQUE SHAFT WAS REPLACED. (TC NR 20070419003)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007050700138	20070507	00138	SW  	2007	5	7	CA070419004      	1	20070419	G	6520	476206297	BEARING         			BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1D    	41516	EA  					TAIL ROTOR GB	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3111 	685  							(CAN) DURING ROUTINE 100 HR INSPECTION THE OIL WAS FOUND TO BE DARKER IN COLOR THAN NORMAL, AFTER CLOSER INSPECTION AND 	CHECKING FOR STEEL WITH A MAGNET THE DARKNESS IN COLOR WAS ATTRIBUTED TO METAL CONTAMINATION IN THE OIL SO FINE THAT IT 	LOOKED LIKE METALLIC PAINT. THE GEARBOX IS IN FOR TEARDOWN AND WILL ADVISE THE FINDINGS AFTER INSPECTION.  (TC NR 200704	19004)			1	G	7	1 	3O	3	O		H1      	E279				 
2007080800154	20070808	00154	CE  	2007	8	8	CA070419005      	1	20070412	G	5540	05310181	BRACKET         			CESSNA	172   	172D        	2072410	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3717 								(CAN) DURING THE ANNUAL INSPECTION, BOTH RUDDER HINGE BRACKETS WERE FOUND TO BE CRACKED.  RUDDER WAS REMOVED AND REINSTA	LLED AFTER REPAIRS.  PN 0531018-1 AND 0531018-2 WERE REPLACED WITH NEW IAW THE MM. (TC NR 20070419005)					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P920	 
2007050700140	20070507	00140	NE  	2007	5	7	CA070420001      	2	20070419	G	8530	153084	CYLINDER        			DOUG  	DC4   	DC4         	3021502	WP  	PWA   	R2000 	R20007M2    	52023	NE  					NR 4 ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) REPLACED NR 14 CYLINDER ON NR 4 ENGINE, DUE TO CRACK.  AIRCRAFT RETURNED TO SERVICE. (TC NR 20070420001)						2	L	7	4 	4R	4	R		A762    	5E5				 
2007050700142	20070507	00142	EA  	2007	5	7	CA070420002      	2	20070417	G	8520	SL12596	BOLT            								LYC   	O540  	LTIO540J2BD 	41533	EA  					CONNECTING ROD	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA			671  								(CAN) BOLT FAILED CAUSING CONNECTING ROD TO BECAME DETACHED FROM CRANKSHAFT CAUSING MAJOR DAMAGE TO LOWER END OF ENGINE.	 (TC NR 20070420002)										3	O			E14EA				 
2007050700143	20070507	00143	EA  	2007	5	7	CA070420003      	1	20070418	G	5220		DOOR            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	EMERGENCY EXIT	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			34704	34704							(CAN) ON GROUND, WHEN FLIGHT ATTENDANTS UNDERGOING RECURRENT TRAINING ATTEMPTED TO OPEN FWD RT EMERG EXIT DOOR, WERE UNA	BLE TO GET DOOR OPEN. MAINTENANCE CALLED TO ASSIST AND REQUIRED TWO ENGINEERS (ONE ON INSIDE HANDLE AND ONE ON OUTSIDE H	ANDLE) TO GET DOOR OPEN . MAINTENANCE INSPECTED AND LUBRICATED INTERNAL DOOR MECHANISM, DOOR RE-INSTALLED AND FUNCTIONED	 WITH NORMAL OPENING FORCE. (TC NR 20070420003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007050700193	20070507	00193	EU  	2007	5	7	CA070423001      	1	20070420	G	6220	601741	BEARING         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PERFORMANCE OF A 100/300 HOUR INSPECTION OF THE AIRCRAFT AND IN PARTICULAR THE MAIN ROTOR BLADES.  THE ENGI	NEER FOUND THAT THE PENDULUM ABSORBER OF THE RED MAIN ROTOR BLADE WAS EXTREMELY ROUGH.     UPON DISASSEMBLY OF THE PENDU	LUM ABSORBER IT WAS FOUND THAT THE BEARINGS WERE DRY, WITH NO TRACE OF OIL PRESENT.  ONE BEARING CAGE HAD FAILED, AND TH	E BALL BEARINGS HAD WORN TO WELL BEYOND ANY CIRCULAR SHAPE.  JUST A NOTE TO SAY THAT THERE HAD BEEN NO TRACE OF OIL ON T	HE HEAD IN PREVIOUS INSPECTIONS TO INDICATE A LEAK.     ONE BEARING AND SEAL WERE REPLACE, THE ASSEMBLY REASSEMBLED AND 	INSTALLED ONTO THE ROTOR BLADE.  AIRCRAFT RETURNED TO SERVICE UPON COMPLETION OF THE INSPECTION. (TC NR 20070423001)	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2007050700194	20070507	00194	EA  	2007	5	7	CA070423002      	2	20070423	G	8530	LW12427	CYLINDER        			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1397 								(CAN) CRACK FOUND IN CYLINDER. (TC NR 20070423002)						1	L	7	1 	3O	3	O		A1CE    	E286	5	N	P4EA	 
2007071100290	20070711	00290	NE  	2007	7	11	CA070423004      	2	20070421	G	7297	6015091017	WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT ENGINE	CHAFED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER T/O, THE RT ENGINE VIBRATION INDICATOR FLUCTUATED ERRATICALLY THE WENT TO DASHES MOMENTARILY THEN RE	TURNED TO NORMAL OPERATION.  FLIGHT RETURNED FOR MAINTENANCE TROUBLESHOOTING.  AFTER CHANGING THE ENGINE ACCELEROMETER A	ND SIGNAL CONDITIONER WITH NO FIX, THE ENGINE VIBRATION HARNESS SHIELDED WIRE WAS FOUND CHAFFING AGAINST ENGINE CLOSE TO	 THE ENGINE DISCONNECT PLUG.  THE VIBRATION HARNESS WAS REPLACED AND THE AIRCRAFT WAS FUNCTION CHECKED SERVICEABLE. (TC 	NR 20070423004)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050800197	20070508	00197	EA  	2007	5	8	CA070423005      	2	20070419	G	8530	LW12966	CYLINDER        			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				1702 				RL145668A			(CAN) OIL WAS NOTICED LEAKING FROM THE PUSHROD AREA.  THE PUSHROD WAS REMOVED TO REPLACE THE SEALS.  THE CRACK IN THE CY	LINDER HEAD WAS FOUND THEN.  THE CRACK RAN FROM THE BOTTOM OF THE CYLINDER HEAD SEAM TO ABOUT 4-5 INCHES ALONG THE HOLLO	W WHERE THE PUSHROD TUBE RESIDES.  THE CYLINDERS WERE MANUFACTURED NEW STEEL AT OVERHAUL. (TC NR 20070423005)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007080800155	20070808	00155	CE  	2007	8	8	CA070423006      	1	20070419	G	2510	05142043	SEAT            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4224 								(CAN) WHILE PERFORMING AD CF87-15R2 A CRACK WAS NOTED IN THE RADIUS OF THE MACHINED FORK AT THE LT FRONT LOCATION. THE F	ORK IS MADE OF RATHER THIN RECTANGULAR ALUMINUM TUBING AND IS SUBJECT TO SOME FLEXING AS OCCUPANTS ENTER OR EXIT THE AIR	CRAFT. (TC NR 20070423006)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007050800199	20070508	00199	CE  	2007	5	8	CA070423007      	1	20070418	G	2430	290143	PROBE           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TEMP MONITOR	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) BATTERY TEMP MONITOR WAS INDICATING HIGHER THAN NORMAL ON APPROACH.  AIRCRAFT LANDED WITHOUT INCIDENT.  BATTERY WA	S LUKEWARM TO THE TOUCH.  MONITOR WAS UNRESPONSIVE. BATTERY AND PROBE WERE REPLACED ALONG WITH WIRING INSPECTED AND AIRC	RAFT RETURNED TO SERVICE.  NO FAULTS WERE FOUND DURING DEEP CYCLE OF BATTERY AT BATTERY SHOP.  PROBE REPLACED DUE TO POS	SIBLE INTERMITTENT OPERATION. (TC NR 20070423007)			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007071100289	20070711	00289	WP  	2007	7	11	CA070423008      	2	20070416	G	7321	8978015	FUEL CONTROL    			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA				3600 							(CAN) NOTED LARGE FUEL LEAK UNDER THE AIRCRAFT IN THE HANGER.  DETERMINED THE FUEL WAS COMING FROM AN ENGINE DRAIN.  GRO	UND RAN THE ENGINE, FOUND THE FUEL CONTROL DRAIN LEAKING.  REMOVED AND REPLACED THE FUEL CONTROL WITH AN OVERHAULED UNIT	, NO FURTHER DEFECTS NOTED. (TC NR 20070423008)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007050800201	20070508	00201	CE  	2007	5	8	CA070423009      	1	20070422	G	5322	9743000015	CROSS TIE       			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7390 								(CAN) THE INTERIOR WAS REMOVED FOR REFURBISHMENT.  MAINTENANCE DISCOVERED A CRACK IN THE CROSS TIE, A STRUCTURAL MEMBER 	AROUND THE EMERGENCY EXIT ON THE LT SIDE OF THE AIRCRAFT.  CONTACTED MFG FOR A REPAIR. (TC NR 20070423009)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007061500190	20070615	00190	EU  	2007	6	15	CA070424001      	1	20070420	G	2910	571191	PTU             			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, CREW NOTICED LOSS OF GREEN SYSTEM HYDRAULIC FLUID. FLIGHT DIVERTED TO MAIN MAINTENANCE BASE FOR INV	ESTIGATION. DURING INVESTIGATION, THE GREEN/YELLOW SYSTEM PTU WAS FOUND LEAKING AT THE CHECK VALVE DUE TO A DAMAGED O RI	NG. PTU UNIT WAS REPLACED AND SYSTEM TESTS SERVICEABLE.  (TC NR 20070424001)				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2007061500191	20070615	00191	EU  	2007	6	15	CA070424002      	1	20070421	G	2121	X76451	FAN             			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					CABIN	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT CABIN CREW REPORTED ELECTRICAL BURN ODOR FROM THE AFT CABIN.  FAULT ISOLATED TO THE AFT RT FAN HEATE	R FIN NR 28HC. CBS WERE PULLED AND ODOR DISAPPEARED.  SYSTEM WAS PLACED ON MEL DUE PART IS NIL STOCK.  (TC NR 200704240	02)				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2007061800114	20070618	00114	EU  	2007	6	18	CA070424003      	1	20070412	G	2800		UNKNOWN         			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					FUEL SYSTEM	UNKNOWN         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, CREW NOTICES A FUEL DISCREPANCY OF ONE TON BETWEEN FUEL ON BOARD AND FUEL USED. AFTER RECALCULATION	 SHORTLY THEREAFTER THE FUEL DISCREPANCY HAD GROWN TO 1.4 TONS. CREW PROCEEDED WITH QRH PROCEDURES AND SPOTTED FUEL SPAY	ING FROM THE RIGHT WING TIP VENT BOX. SHORTLY THEREAFTER THE FUEL VENTING CEASED. THE FLIGHT WAS DIVERTED TO THE MAIN ST	ATION. DURING INVESTIGATION MAINTENANCE ATTEMPTED TO DUPLICATE THE PROBLEM WITH NO SUCCESS. AIRBUS WAS CONTACTED FOR THE	IR RECOMMENDATION. THE FOLLOWING UNITS WERE REPLACED AND ROUTE TO THE VENDOR FOR SHOP CHECK AND STRIP REPORT: (A) RT INN	ER TANK VENT FLOAT VALVE (B) 2 RT OB BOOST PUMP CHECK VALVES  (C) RT WING REFUEL/DEFUEL VALVE (D)  FUEL TRANSFER VALVE A	2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2008021900369	20080219	00369	CE  	2008	2	19	CA070424004      	1	20070419	G	2913	10138800517	POWERPACK       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	HYDRAULIC SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			9010 	9010 			BB1281				(CAN) DURING A ROUTINE MEDEVAC AND TEN MINUTES AFTER  DEPARTURE THE RED LIGHT IN THE IN THE LANDING GEAR HANDLE ILLUMINA	TED.VISUAL CONFIRMATION OUT CAPT SIDE WINDOW OF LANDING GEAR PARTIALLY DOWN.  A MANUAL GEAR EXTENSION WAS INITIATED AND 	A UNEVENTFUL LANDING WAS COMPLETED. TELCOM WITH MTCE. AND FLIGHT CREW CONFIRMED, LANDING GEAR MOTOR WAS NON FUNCTIONING.	 VISUAL INSP WAS C/O BY CREW FOR DAMAGE OR EXCESSIVE FLUID LOSS, WITH NONE OBSERVED.  AC WAS RETURNED WITH LANDING GEAR 	IN THE DOWN/ LOCKED POSITION, ESSENTIAL CREW ONLY ON BOARD.  MAINT INSPECTION REVEALED,THE L/G HYD POWERPACK HAD INTERNA	LLY FAILED TO MAINTAIN SYS PRESSURE,CAUSING THE PUMP TO RUN AND EXCEEDED OPERATIONAL TOLERANCE WHICH POPPED THE C/B. REP	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007050900062	20070509	00062	EA  	2007	5	9	CA070424005      	2	20070424	G	7230		COMPRESSOR WHEEL								PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OPERATOR REPORTED THAT WHEN THE ENGINE WAS STARTED, THE PROPELLER DID NOT ROTATE. AFTER SHUTDOWN, THE ENGINE AND P	ROP COULD BE ROTATED BY HAND. HOWEVER, SEVERAL SMALL PIECES OF METALLIC DEBRIS WAS REMOVED FROM THE EXHAUST AREA.  DISAS	SEMBLY OF THE ENGINE REVEALED SEVERE IMPACT DAMAGE ON THE FWD FACE OF THE CT DISC ASSY AND 4 MISSING CT VANE RETAINING B	OLTS. FURTHER INVESTIGATION REVEALED IMPACT DAMAGE ON THE CT VANE LOCK PLATE, CT VANE, CT BLADES AND PT BLADES. (TC NR 2	0070424005)							4	T			E4EA				 
2007061800115	20070618	00115	EA  	2007	6	18	CA070424006      	1	20070420	G	2497	C030722	DIODE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	LT DC ESS BUSS	MISWIRED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35404	35404							(CAN) DURING GRD RUN LEAK CHECKS, AFTER ROUTINE MAINTENANCE,  NOTED NO DISCHARGE SHOWING ON THE BATTERY MONITOR FOR THE 	AUX BATTERY. INVESTIGATION FOUND WIRING BACKWARDS AT DIODE 2431-CR5; THIS IS THE POWER SUPPLY TO THE BUS FROM THE AUX BA	TTERY.  IN THIS CONDITION NO POWER IS AVAILABLE FROM THE AUX BATTERY UNDER ANY CONDITIONS. THE ONLY INDICATION OF THIS M	ISCONNECTION WAS BATTERY MONITOR SHOWING NO DISCHARGE FROM THE AUX BATTERY, WHEN BOTH MAIN AND AUX BATTERIES WERE SELECT	ED ON.  (NORMAL OPERATING PROCEDURE IS TO HAVE BOTH BATTERIES SELECTED ON) ALL OTHER ELECTRICAL SYSTEM INDICATIONS WERE 	NORMAL. WIRING CORRECTED SYSTEM FUNCTION CHECKED NORMAL. (TC NR 20070424006)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061800116	20070618	00116	NE  	2007	6	18	CA070424007      	2	20070423	G	7230	JT8D15QM	BLADE           	PWA         		BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					COMPRESSOR	FAILED          	W				C				ABORTED TAKEOFF         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		TO	TAKEOFF        	1			CA			57339	3677 				696622			(CAN) DURING TAKEOFF ROLL AT 80KTS, THE TOWER ADVISED THE CREW THAT FLAMES WERE VISIBLE OUT OF ONE OF THE ENGINES. THE C	REW REJECTED THE TAKEOFF AND ENGINES WERE SHUTDOWN. THE AIRCRAFT WAS TOWED BACK TO THE RAMP.   MAINTENANCE INSPECTED THE	 ENGINES AND FOUND NR 2 ENGINE TO HAVE TURBINE DAMAGE. SOME INTERNAL ENGINE PARTS HAD EXITED THE ENGINE AND WERE FOUND O	N THE RUNWAY. (16 IN YYC). AT THIS TIME IT LOOKS AS THOUGH THE FAILURE STARTED WITHIN THE COMPRESSOR SECTION.  THE ENGIN	E IS CURRENTLY BEING REMOVED FROM THE AIRCRAFT AND A FOLLOW-UP TO THIS SDR SHALL BE ACCOMPLISHED ONCE THE ENGINE HAS BEE	N DISASSEMBLED FOR INSPECTION. (TC NR 20070424007)	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008021900370	20080219	00370	CE  	2008	2	19	CA070424008      	1	20070422	G	2910	124F0016CR0164	HYDRAULIC LINE  			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYDRAULIC SYSTEM	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) DURING APPROACH TO LAND THE CREW EXTENDED THE LANDING GEAR AND NOTICED THE NOSE GEAR WAS NOT DOWN AND LOCKED. THE 	EMERGENCY GEAR EXTENSION WAS ACTIVATED AND THE NOSE GEAR WAS LOCKED IN THE DOWN POSITION. THE AC LANDED WITHOUT INCEDENT	. UPON INSP BY MAINT IT WAS DETERMINED THE HYDR SYS ACCUMULATOR LINE HAD RUPTURED PURGING THE HYDRAULIC FLUID FROM THE S	YS OVERBOARD. NO DEFINITIVE CAUSE FOR THE RUPTURE OF THE LINE COULD BE DETERMINED. THE AGE OF THE LINE IS UNKNOWN. IT IS	 SUSPECTED CYCLIC FATIGUE IS THE CAUSE OF THE RUPTURE. NO LIFE LIMIT OR REPLACEMENT INTERVAL IS MANDATED BY THE AC MFG. 	(TC NR 20070424008)	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
	20081104		CE  	2008	11	4	CA070424010      	1	20070418	G	3297	973106A12SL64	CONNECTOR       	RAYTHN      	623372      	BEECH 	1900  	1900C       	1154161	CE  										SELECTOR VALVE	CORRODED        	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON (GEAR DOWN) SELECTION, CIRCUIT BREAKER FOR THE GEAR CONTROL POPPED AND THE GEAR REMAINED RETRACTED. AFTER A MIS	SED APPROACH THE NORMAL SOP`S WERE CARRIED OUT AND THE GEAR MANUALLY EXTENDED. AN UNEVENTFUL LANDING WAS THEN CARRIED OU	T. ON INVESTIGATION THE CONNECTOR TO THE GEAR SELECTOR VALVE ON THE HYDRAULIC POWER PACK WAS FOUND TO BE CORRODED AND HA	D A BROKEN WIRE. THE CONNECTOR WAS REPLACED AND THE WIRE REPAIRED. THE GEAR SWINGS WERE NORMAL AND THE ACFT HAS SINCE FL	OWN WITH NO REOCCURRENCE OF THE DEFECT.		2	L	7	2 	4T			RT	A24CE   					 
2007050800203	20070508	00203	SW  	2007	5	8	CA070424011      	1	20070418	G	7712		IDLER GEAR      			SWRNGN	SA226 	SA226*      	       	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	TORQUE SENSOR	LOOSE           	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			3115 	3115 		P8640C					(CAN) FOUND ON TAKEOFF ROLL, THE RT CHIP LIGHT CAME ON THROUGH 70 KTS. THE TAKEOFF WAS ABORTED AND THE AC TAXIED BACK TO	 THE RAMP WITHOUT ANY FURTHER INCIDENT.  AT THIS TIME MAINT HAD DONE A SOAP SAMPLE AND FOUND METAL IN THE OIL FILTER.  W	HEN THE ENGINE WAS TAKEN APART THE TORQUE SENSOR IDLER GEAR WAS NOTICED TO BE LOOSE DUE TO THE BEARING HAD FAILED ON THE	 IDLER GEAR THAT IS ATTACHED TO THE TORQUE SENSOR. (TC NR 20070424011)			2	L	7	2 	4T	4	T	RT	A56W    	E4WE	5	C	P10NE	 
2007080800156	20070808	00156	CE  	2007	8	8	CA070425001      	1	20070423	G	3233	55275042	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			DE	DESCENT        	1			CA			7518 								(CAN) AIRCRAFT EXPERIENCED UNSAFE GEAR EXTENSION WHILE DOING CIRCUITS.  GEAR SELECTION WAS MADE WHILE IN DOWNWIND TURN A	ND RT MAIN GEAR DOWN AND LOCKED LIGHT DID NOT ILLUMINATE, (GEAR UNLOCKED) AND (HYD PRESS ON) LIGHTS REMAINED ON. GEAR WA	S RECYCLED IN LEVEL FLIGHT AND NORMAL INDICATION RESULTED.  AIRCRAFT WAS FLOWN UNDER FERRY FLIGHT PERMIT WITH GEAR VERIF	IED DOWN AND LOCKED. MAINTENANCE CONDUCTED SEVERAL GEAR SWINGS TO ENSURE PROPER OPERATION AND DOWNLOCK SWITCH CONTINUITY	, WHICH REVEALED NO FAULTS.  WHEN A LOWER THAN NORMAL HYDRAULIC PRESSURE WAS APPLIED AND GEAR DOWN SELECTION MADE, THE N	OSE AND LT GEAR RELEASED BUT THE RT MAIN REMAINED IN THE UPLOCK.  PRESSURE WAS THEN INCREASED TO NORMAL WITH NO EFFECT O	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007062000002	20070620	00002	NM  	2007	6	20	CA070425002      	1	20070421	G	3213	83210301001	STRUT           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT MLG	SEPARATED       	W				O				OTHER                   				W	Z		INADEQUATE Q C            	SIGNIFICANT FAILURE REPORT		LD	LANDING        	1			CA											(CAN) LT MLG SEPARATED FROM AIRCRAFT DURING LANDING. THE LOWER OLEO STRUT WITH THE WHEELS AND AXLE DEPARTED THE AIRCRAFT	; AIRCRAFT LANDED ON DRAG STRUT WHICH THEN COLLAPSED AND SHEARED OFF. SUBSTANTIAL DAMAGE WAS DONE TO THE LOWER FUSE, LT 	NACELLE, ENGINE AND PROP, AND LT WING TIP. PILOT REPORTED THAT THERE WAS NOT A HARD LANDING. MFGS ARE INVESTIGATING THE 	EVENT.  (TC NR 20070425002)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061800117	20070618	00117	NM  	2007	6	18	CA070425003      	1	20070419	G	2421	11522184	GENERATOR       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 1	LACK OF LUBE    	W				E				ENGINE SHUTDOWN         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		AP	APPROACH       	1			CA			3760 	1620 							(CAN) DURING APPROACH TO BASE AT 1000 FEET, THE NR 1 AC GENERATOR CAUTION LIGHT ILLUMINATED. PILOT CYCLED THE NR 1 AC GE	NERATOR AND THEN THE AC GENERATOR HOT CAUTION LIGHT ILLUMINATED AS WELL AS THE AC GENERATOR CAUTION LIGHT.  AFTER TOUCHD	OWN WHEN PLA RETARDED TO DISC THE NR 1 OIL PRESS WARNING LIGHT ILLUMINATED AND THE ENGINE WAS SHUTDOWN.  GROUND INSPECTI	ON REVEALED: AC GEN OVERHEATED, AC GEN QUILL SHAFT SEPARATED, NO OIL ON THE SIGHT GAGE, NO EXTERNAL LEAK, METAL TRAPPED 	ON THE AC GEN MCD 41 SEC, LOW OIL PRESS EXCEEDED, RECORDED IN EMU.  NR 1 ENGINE REPLACED DUE TO THE EXCEEDING. (TC NR 20	070425003)	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022000008	20080220	00008	SO  	2008	2	20	CA070425004      	1	20070405	G	3221	67054803	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6D   	42305	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10636								(CAN) DURING A PREFLIGHT INSP THE PILOT NOTICED THE NOSE GEAR TRUNNION CRACKED. THE CRACK STARTS FROM THE UPPER PART OF 	THE CASTING AND GOES DOWN HALFWAY AT WHICH POINT IT SPREADS INTO 3 OTHER CRACKS. THE IDENTICAL CRACK CAN BE FOUND ON THE	 REAR SIDE OF THE CASTING .THE CRACK IS 5 INCHES LONG.  SUSPECT A HARD LANDING, A HARD LANDING INPS WAS CARRIED OUT AND 	NO FURTHER DAMAGE WAS FOUND. THE NOSE TIRE SHOWED EVIDENCE OF A HARD LANDING. THE PART IS BEING KEPT, CAN SEND A PICTURE	 OR MAKE THE PART AVAILABLE FOR INSP. (TC NR 20070425004)		1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P25EA	 
2008022000009	20080220	00009	EU  	2008	2	20	CA070425005      	1	20070425	G	2913	593733	BEARING         		350A35109223	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					HYDRAULIC PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1188 			4KMVA					(CAN) DURING DI, HYDRAULIC PUMP PULLEY WAS NOTICED TO BE LOOSE LATERALLY WHEN MOVED SIDE TO SIDE. WHEN MAIN ROTOR WAS RO	TATED HYDRAULIC PUMP PULLEY WAS FOUND NOT SPINNING SQUARE AND THE HYDRAULIC BELT WAS OFF SET FROM CENTER. HYDRAULIC PUMP	 PULLEY WAS REMOVED AND BEARING INNER RACE WAS FOUND SPINNING ON SHAFT AND WORE A SUBSTANTIAL GROOVE IN PULLEY SHAFT.  (	TC NR 20070425005)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007050800204	20070508	00204	NE  	2007	5	8	CA070426002      	2	20070424	G	7314	6078T39P04	PUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL SYSTEM	LEAKING         	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			24818	683  				872485			(CAN) DURING ENGINE START UP, GROUND CREW OBSERVED A LEAK COMING FROM BELOW THE ENGINE NR 2.  LINE MAINTENACE FOUND A FU	EL LEAK FROM A MICROSCOPIC PIN HOLE CLOSE TO A PLUGGED FITTING ADAPTOR ON ENGINE NR 2 FUEL PUMP AFT CASING. THE EXACT PI	N HOLE LOCATION WAS NOT FOUND DUE TO THE HIGH FUEL PRESSURE MIST. FUEL PUMP SN CGWT0202. (TC NR 20070426002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007050800212	20070508	00212	EA  	2007	5	8	CA070426003      	2	20070426	G	8530	72242	ROCKER COVER    			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA				24   				L633761A			(CAN) SHORTLY AFTER TAKEOFF, THE PILOTS EXPERIENCED A POWER LOSS IN THE LT ENGINE, HOWEVER THE ENGINE REMAINED RUNNING. 	 THEY RETURNED TO THE NEARBY AIRPORT WITHOUT INCIDENT.   MAINTENANCE INSPECTED THE ENGINE AND FOUND THAT NR 6 CYLINDER R	OCKER COVER HAD BEEN DAMAGED. THE COVER WAS REMOVED AND FOUND THAT THE RETAINING CLIP THAT HOLDS THE ROCKER SHAFTS IN PL	ACE FOR THE INTAKE AND EXHAUST VALVES HAD FALLEN OFF.  THE ROCKER SHAFT FOR THE INTAKE VALVE HAD FALLEN OUT ALLOWING  TH	E ROCKER TO BECOME DISLODGED THEREBY DISABLING THAT CYLINDER. THE VALVE ASSEMBLY WAS INSPECTED AND REINSTALLED WITH A RE	PLACEMENT VALVE COVER AND GASKET.  GROUND RUNS COMPLETED AND ALL CHECKS FOUND SERVICEABLE.   AS NOTED ABOVE, THE ENGINE 	1	L	7	2 	3O	3	O		A12SW   	E14EA	5	C	P33EA	 
2007061800118	20070618	00118	NM  	2007	6	18	CA070426005      	1	20070420	G	5753	RD8457049	SEAL            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT OB FLAP	MISSING         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AFTER 30 MINS INTO FLIGHT, CREW REPORT AILERON MISMATCH, AP DISCONNECTED AND AILERON STUCK.  PILOT USED FORCE TO R	ELEASE AILERONS.  REST OF FLT SYSTEM, OPS NORMAL.  THIS WAS THE FIRST FLT OF THE DAY AND THE TEMP AT FL250 WAS -45 DEG C	.  FOUND RT FLAP SEAL LOOSE, PART MISSING AND LT FLAP SEAL LOOSE. LT AND RT FLAP SEALS REPLACED. (TC NR 20070426005)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007080800157	20070808	00157	CE  	2007	8	8	CA070426007      	1	20070420	G	2910	S217840114	CONNECTOR       			CESSNA	177   	177RG       	2073709	CE  										NLG	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) AIRCRAFT PLANNING ON LANDING WHEN UNDERCARRIAGE LIGHT FAILED TO INDICATED GEAR DOWN AND LOCKED. DECLARED AN EMERGE	NCY. AFTER SEVERAL ATTEMPTS AT TRYING TO PUMP GEAR DOWN BY HAND THE PILOT GOT A GEAR DOWN AND LOCKED LIGHT. AIRCRAFT LAN	DED WITH NO EVENT TAKING PLACE. MAINTENANCE LATER FOUND THE NOSE GEAR ACTUATOR HOSE HAD SLID PARTIALLY FROM ITS SWAGED E	ND CONNECTOR AND WAS LEAKING BADLY. HOSE REPLACED. (TC NR 20070426007)			1	H	7	1 	3O				A20CE   					 
2007061800119	20070618	00119	EU  	2007	6	18	CA070426008      	1	20070419	G	3080	45150560	PROBE           			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	AOA	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING TO POSITION FOR DEPARTURE THE CREW OBSERVED AN ICE DETECTOR FAULT. THE AIRCRAFT RETURNED TO THE RAMP	 FOR TROUBLESHOOTING. MAINTENANCE REPLACED THE CAPTAINS ALPHA PROBE AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 200	70426008)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007061800120	20070618	00120	GL  	2007	6	18	CA070426009      	1	20070420	G	5521	C2TE83ND	RIB             			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			89   								(CAN) THIS ELEVATOR LEADING EDGE RIB WAS FOUND CRACKED WHILE CARRYING OUT ANNUAL INSPECTION.  IT WAS DETERMINED THAT THE	 CRACK WAS THE RESULT OF TOO SHARP OF A BEND RADIUS IN THE AREA WHERE THE PART GETS  RIVETED TO THE ELEVATOR LEADING EDG	E SKIN.  THIS DEFECT WAS COMMUNICATED AND THE TOOLING HAS BEEN REPAIRED ALLOWING FOR A MOVE UNIFORM RADIUS ON THE PART I	N QUESTION. (TC NR 20070426009)			1	H	7	1 	3R	4	T	RC	A806    	E4EA	6	C	P15EA	 
2008032000002	20080320	00002	EU  	2008	3	20	CA070427001      	1	20070416	G	5210	332A2213010006	DOOR            			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MAIN PAX	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AFTER TAKING OFF FROM AN OFFSHORE RIG AT 300 FT, 70 KNOTS, CREW HEARD A STRONG NOISE AND ONE OF THE PASSENGERS ADV	ISED THAT DOOR WAS MISSING. P/C NOTICED NO CAUTION LIGHTS. AC RETURNED TO THE RIG AND LANDED WITHOUT FURTHER INCIDENT. A	C SUBSEQUENTLY RETURNED TO CHC`S OPS MAIN BASE WITHOUT PASSENGERS AND IS PRESENTLY QUARANTINED AWAITING INVESTIGATION TE	AM.  CAPTAIN`S STATEMENT: FIRST FLIGHT OF THE DAY. BEFORE TAKEOFF DOOR CAUTION LIGHT FLICKERING. P/C CHECKED MEL AND ALL	 DOORS LOCKED. ENGINEER ON DUTY INFORMED, HE INSPECTED DOORS LOCKERS. SECOND FLIGHT. BEFORE TAKEOFF FROM (OFFSHORE RIG),	 DOORS WERE CONFIRMED LOCKED AND NO CAUTION LIGHTS. PASSING 00 FT AFTER TAKEOFF STRONG NOISE, PAX ADVISE DOOR MISSING, P	2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2007061800121	20070618	00121	EA  	2007	6	18	CA070427003      	1	20070425	G	7897	B080201500398S	CONNECTOR       			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF34*       	 	NE  					THRUST REVERSER	SHORTED         	W				K				NONE                    				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			6005 	6005 							(CAN) ON GROUND, EICAS SHOWED (PROX SYS FAULT 2).  MAINTENANCE INSPECTION FOUND PYLON CONNECTOR WITH INTERNAL SHORT, IND	ICATING FAILURE OF THRUST REV PROX SENSOR. CONNECTOR P/N B0802015-003-98SA (REF: WIRING MANUAL 71-50-01 J508) REPLACED, 	SYSTEM FUNCTION TEST NORMAL, AIRCRAFT RETURNED TO SERVICE (TC NR 20070427003)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007061800194	20070618	00194	CE  	2007	6	18	CA070427004      	1	20070423	G	2435	99121252	STARTER GEN     			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					ENGINE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			756  								(CAN) GENERATOR OUTPUT FAILURE, NO OUTPUT.  (TC NR 20070427004)						1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2007061800190	20070618	00190	SW  	2007	6	18	CA070427005      	1	20070416	G	6220	407310104103	SPRING          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON SCHEDULED INSPECTION IT WAS NOTICED THAT ONE OF THE EIGHT SPRINGS IN THE MAIN ROTOR FRAME ASSEMBLY WAS BROKEN	. (TC NR 20070427005)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2007061300142	20070613	00142	NM  	2007	6	13	CA070427006      	1	20070410	G	5754		ATTACH BRACKET  			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 7 SLAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A AND B5 INSPECTION NR 7 SLAT ATTACH BRACKET UPPER MOUNT ON FRONT SPAR CRACKED.  P/N TO BE DETERMINED FROM 	MFG ENGINEERING DRAWINGS. RDA ISSUED BY DECA ENGINEERING TO REPAIR. (TC NR 20070427006)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007061800196	20070618	00196	SO  	2007	6	18	CA070427007      	1	20070425	G	3220	16667000	LINK            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	NOSE GEAR	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING GEAR RETRACTION THE PILOTS DID NOT GET A GEAR UP AND SAFE LIGHT, UPON VISUALLY INSPECTING THE GEAR WITH THE	 MIRRORS THE NOSE GEAR WAS SEEN TO BE DANGLING AT AN APPROXIMATE 60 DEGREE ANGLE.  GEAR WAS SELECTED DOWN, DOWN AND LOCK	ED INDICATION WAS PROVIDED AND THE AIRCRAFT LANDED UNEVENTFULLY.  DURING INSPECTION OF THE GEAR SYSTEM THE NOSE GEAR DOW	N LOCK LINK ASSEMBLIES WERE FOUND TO BE BROKEN IN HALF.  THEY ARE MADE OF STEEL.  THE LINK ASSEMBLIES WERE REPLACED NEW 	AND THE GEAR SWUNG NUMEROUS TIMES SATISFACTORILY. (TC NR 20070427007)		1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2007061800197	20070618	00197	EA  	2007	6	18	CA070427008      	1	20070425	G	2710	82740220101	GUARD           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  		WORN            	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			34757	34757							(CAN) FLIGHT CREW REPORTED ROLL CONTROL INPUTS SEEMED STIFF, ESPECIALLY LT TO RT IN-FLIGHT. ON GROUND NO INDICATION OF S	TIFFNESS AND NOTHING ADVERSE WITH ROLL DISCONNECT. MAINTENANCE INSPECTION FOUND LT OB AILERON CABLE ROUTED AROUND WRONG 	SIDE OF CABLE GUARD. CABLE ROUTING WAS RECTIFIED, CABLE GUARD REPLACED, CABLE INSPECTED WITH NO SIGNS OF DETERIORATION. 	AILERON CABLES RE-TENSIONED AND INDEPENDENT INSPECTION COMPLETED. AIRCRAFT RETURNED TO SERVICE. REF: DHC-83 IPC 27-12-00	 FIG 10 ITEM 350 P/N 82740220-101 CABLE GUARD , REF: DHC-83 IPC 27-12-00 FIG. 25 ITEM 470 P/N 82700563-S001 CABLE,  REF:	 DHC SERIES 300 MAINT. TASK CARD 2710/02 PG 3 OF 6 VIEW H,  PG 6 OF 6 FIGURE 4 CABLE ROUTING. (TC NR 20070427008)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061800207	20070618	00207	EA  	2007	6	18	CA070502001      	1	20070502	G	2810	K215T6400212	FUEL TANK       			CNDAIR	CL215 	CL2156B11215	       	EA  											LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) TESTED BEFORE INSTALLATION, THE NEW TANK HAS BEEN FOUND LEAKING BY ONE OF PROBE ATTACHMENT.  THE PROBE ATTACHMENT 	NUT HAS BEEN REPLACED, RETIGHTENED AND TANK INSTALLED IN A/C.  (TC NR 20070502001)					2	H	7	2 	4T			RT	A14EA   					 
2007061800198	20070618	00198	SW  	2007	6	18	CA070502002      	1	20070426	G	6510	222044003107	HANGER ASSY     			BELL  	230   	230         	1182149	SW  										TAIL ROTOR DRIVE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) T/R HANGAR BEARING ASSY FAILURE WAS DISCOVERED AFTER THE PILOT WAS ALERTED BY AN UNUSUAL NOISE UPON ENGINE START. 	(TC NR 20070502002)					1	G	7	2 	3U			NC	H9SW    					 
2007061800206	20070618	00206	EA  	2007	6	18	CA070502003      	1	20070502	G	2810	K215T6400212	FUEL TANK       			CNDAIR	CL215 	CL2156B11215	       	EA  											LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) TESTED BEFORE INSTALLATION, THE NEW TANK HAS BEEN FOUND LEAKING BY ONE OF THE PROBE ATTACHMENT PATCH INSTALLATION.	 THE NEW TANK HAS BEEN REJECTED. (TC NR 20070502003)					2	H	7	2 	4T			RT	A14EA   					 
2007080800158	20070808	00158	CE  	2007	8	8	CA070502005      	1	20070410	G	5312	24120111	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					BS 108	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8484 								(CAN) PARTS WERE CRACKED AT ATTACH POINTS OF WHEEL WELL COVER SKIN 2412011-1 AND BULKHEADS STATION 108 AND 124 AND CRACK	 ON WHEEL WELL COVER AT RT FRONT CORNER WHERE IT ATTACHES TO BULKHEAD STATION 108.  TIEDOWN RINGS ALSO ATTACH IN THIS AR	EA.  (TC NR 20070502005)				1	H	7	1 	3O	3	O		3A17    	E286				 
2008022000010	20080220	00010	SW  	2008	2	20	CA070502006      	1	20070426	G	6320		CASE            	BELL        	427040006107	BELL  	427   	427         	1182207	SW  										TRANSMISSION	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			450  			56024					(CAN) ON INVESTIGATING AN OIL LEAKAGE, A CRACK WAS FOUND ON THE TRANSMISSION LOWER CASE (SIMILAR LOCATION AS SDR 2007021	6006) (TC NR 20070502006)					1	G	7	1 	3U				R00001RC					 
	20081104		EA  	2008	11	4	CA070502007      	2	20070501	G	7414	4371	MAGNETO         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					LEFT	MALFUNCTIONED   	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			2458 	475  							(CAN) UPON RUN-UP, THE LT MAGNETO WAS SELECTED CAUSING THE ENGINE TO STOP. THE MAGNETO WAS REPLACED, AND AFTER SATISFACT	ORY GROUND RUNNING, THE A/C WAS RELEASED FOR RETURN TO SERVICE. (TCNR 20070502007)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2008022000046	20080220	00046	SO  	2008	2	20	CA070502008      	1	20070427	G	7602	455361	CONTROL CABLE   			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	MIXTURE CONTROL	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) MIXTURE CONTROL WAS FOUND TO BE STIFF BY MAINT ON AN ENGINE START FOR TAXI TO HANGER. CABLE WAS REMOVED. THE CABLE	 ROUTING POSITIONS THE CABLE LESS THAN (6) INCHES FROM THE TURBOCHARGER. AN ASBESTOS COVER HAD PREVIOUSLY BEEN PLACED OV	ER THE CABLE AND STITCHED TOGETHER WITH LOCK WIRE TO PROTECT THE CABLE. ( NOT DONE AT OUR SHOP). ONCE THE COVER WAS REPL	ACED WE DISCOVERED THE ENTIRE OUTER CABLE SHIELD DETERIORATED AND MISSING A TWO INCH SECTION. (TC NR 20070502008)			1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920	 
2007061800122	20070618	00122	EA  	2007	6	18	CA070502009      	2	20070410	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NR 2	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NR 2 ENGINE FAILED SEVEN MINUTES PRIOR TO LANDING AT AIRPORT. NR 2 CYLINDER DROPPED DOWN INSIDE THE COWLING AND AP	PROXIMATELY 2 QUARTS OF OIL WAS LOST. THE ENGINE WAS SECURED WITHIN A FEW SECONDS AND A LANDING WAS SAFELY EXECUTED AT A	IRPORT.  THE ENGINES WERE BOTH SET AT 31 INCHES HG, 2200 RPM AND APPROXIMATELY 1500F EGT, PRIOR TO THE NR 2 ENGINE FAILU	RE. THE FAILURE OCCURRED ON THE 30 MARCH 2007. (TC NR 20070502009)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007080800159	20070808	00159	CE  	2007	8	8	CA070502010      	1	20070418	G	2710	0510105365	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	AILERONS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2392 								(CAN) DURING INSPECTION RT WING AILERON CONTROL CABLES FOUND TO BE FRAYED WITH BROKEN STRANDS AT WING STATION 100 WHERE 	CABLES TRAVEL ON TOP OF FAIRLEAD PN 0522647-10 CABLES WERE REPLACED WITH NEW UNITS FROM MFG. (TC NR 20070502010)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2007061800191	20070618	00191	NE  	2007	6	18	CA070502011      	2	20070420	G	7250		TURBINE WHEEL   			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			3238 	469  							(CAN) IN FLIGHT SHUTDOWN OF NR 1 ENGINE. POWER TURBINE WHEEL SHED BLADES. DAMAGE FOUND ON MAIN ROTOR BLADES AND TAIL ROT	OR BLADES.  LARGE AMOUNTS OF METAL ON CHIP DETECTOR. (TC NR 20070502011)					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007061800195	20070618	00195		2007	6	18	CA070502012      	1	20070424	G	3246	9546	WHEEL           								LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AXLE PLUG 9546 WHICH IS USED TO SECURE AXLE IN NOSE WHEEL SEPARATED ALLOWING AXLE BOLT TO COME HALF WAY OUT OF AXL	E WHICH THE PILOT NOTICED ON WALK AROUND. ON INSPECTION IT WAS NOTICED THAT WHEEL HALF RETAINING BOLTS/NUTS HAD LOOSENED	 CAUSING WHEEL HALVES TO SEPARATE, PUTTING ADDED FORCE ON PLUG 9546 WHICH IN TURN SHEARED PLUG CAUSING BOLT TO EXIT AXLE	 PART WAY. (TC NR 20070502012)								3	O			1E4	5	C	P6EA	 
2007080800161	20070808	00161	NM  	2007	8	8	CA070502014      	1	20070424	G	2497		FEEDER CABLE    			DORNER	DO32  	DO328300    	       	NM  	PWA   	306   	PW306B      	 	NE  					ALTERNATOR	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING TROUBLESHOOTING OF INTERMITTENT AC ALTERNATOR FOUND FEEDER WIRE CHAFED AND ARCED TO COWL STRUCTURE.  STRUCT	URE AFFECTED IS RETAINER FOR COWL SUPPORT ARM. (TC NR 20070502014)					2	H	7	2 	4T	4	F	RT	A55NM   	E35NE				 
2007061800205	20070618	00205	EU  	2007	6	18	CA070502015      	1	20070430	G	7810	1379049H401	EXHAUST PIPE    			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE	BROKEN          	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			R	B	J	PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA								P66042C			(CAN) ON CLIMB PILOTS EXPERIENCED TORQUE FLUCTUATIONS ON RT ENGINE. THEY RETURNED TO THE AIRPORT WITH NO FURTHER PROBLEM	S. ON TAXI THEY BLEW THE FIRE BOTTLES ON THE RT ENGINE.  WHEN MAINTENANCE REMOVED THE COWLS THEY DISCOVERED HEAT DAMAGE 	TO SOME WIRING. ON FURTHER INVESTIGATION THEY DISCOVERED THAT THE EXHAUST PIPE STUB HAD BROKEN AND FOLDED OVER PARTIALLY	 BLOCKING THE EXHAUST GAS FLOW. FURTHER INVESTIGATION IS REQUIRED. (TC NR 20070502015)			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2007061800201	20070618	00201	EU  	2007	6	18	CA070502016      	1	20070426	G	3240	18942	CLEVIS          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	RT BRAKE PEDAL	BROKEN          	W				D				RETURN TO BLOCK         				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) ON RUN UP THE RT BRAKE PEDAL CLEVIS FORKEND AT THE BRAZE JOINT BROKE. ON TROUBLESHOOTING THIS SNAG, IT WAS FOUND T	HAT SB 340-32-078 HAD NOT BEEN COMPLETED ON THIS A/C, THE NEW SOLID FORKEND P/N 250704 WAS INSTALLED IAW SB. (TC NR 2007	0502016)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2007061300140	20070613	00140	EA  	2007	6	13	CA070503001      	1	20070207	G	2742	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			6392 			1114					(CAN) SHORTLY AFTER DEPARTURE, RUNWAY 27L, AT APPROXIMATELY 3000 FEET, THE AC ROLLED TO 45 DEGREES, AND PITCHED UP > 18 	DEGREES. THE CREW RECOVERED THE AIRCRAFT AT AN ALTITUDE OF 4500 FEET.   POST INCIDENT INVESTIGATION FOUND NO ANOMALIES W	ITH THE AILERON CONTROL SYSTEM, AILERON TRIM SYSTEM, ELEVATOR CONTROL SYSTEM, AND THE HSTA SYSTEM. SUBSEQUENT PRE-FLIGHT	 PREPARATION DETECTED A MALFUNCTION WITHIN THE HSTA. THE HSTA WAS REPLACED.   AIR SAFETY IS IN CONTACT WITH THE TSBC WHO	 IN TURN ARE IN CONTACT WITH THE GERMAN BFU. CRJ 7901 APPEARS TO HAVE OPERATED WITHOUT FURTHER INCIDENT SINCE REPLACEMEN	T OF THE HSTA. CRJ 7901 WAS EQUIPPED WITH A 9 HSTCU DURING THE INCIDENT FLIGHT, THIS UNIT WAS NOT SUSPECTED AND WAS NOT	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007061800204	20070618	00204	NE  	2007	6	18	CA070503002      	3	20070430	G	6111	8173861	SLEEVE          			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	MR 3 BLADE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				7571 							(CAN) DURING ACTUATOR CHANGE FOUND THAT THE BLADE PIN BEARING ON THE NR 3 BLADE HAD EXCESSIVE MOVEMENT. UPON FURTHER INV	ESTIGATION, FOUND THAT THE BEARING SLEEVE WAS WORN THRU TO THE BEARING AND THAT THE BLADE PIN WAS WORN AS WELL. MFG SB 1	4SF-61-134 ADDRESSES THE PROBLEM ENCOUNTERED AND WAS NOT BEEN INCORPORATED ON THIS BLADE. (TC NR 20070503002)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061800208	20070618	00208	EA  	2007	6	18	CA070503003      	2	20070503	G	8530	LW19332S	CONNECTING ROD  			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				670  				L528761A			(CAN) IT WAS REPORTED TO MAINTENANCE THAT THE RT ENGINE HAD EXPERIENCED SOME TROUBLE.  THE ENGINE WAS SHUTDOWN (DURING F	LIGHT) AND PROP WAS FEATHERED. THE AIRCRAFT COMPLETED THE FLIGHT TO THE NEAREST AIRPORT AND LANDED WITHOUT INCIDENT.  TH	E PRELIMINARY INSPECTION INDICATES THAT THE NR 4 CYLINDER CONNECTING ROD BROKE THROUGH THE PISTON PIN HOLE.  THIS PERMIT	TED THE PISTON TO BECOME DISLODGED AND THE CYLINDER ASSEMBLY WAS SUBSEQUENTLY FORCED FREE OF THE ENGINE BREAKING ALL THE	 CYLINDER BASE HOLD DOWN STUDS. THE ENGINE WILL REQUIRE MAJOR REPAIRS. (TC NR 20070503003)		1	L	7	2 	3O	3	O		A12SW   	E14EA	5	C	P33EA	 
2007061800200	20070618	00200	WP  	2007	6	18	CA070503004      	2	20070426	G	7321	89777026	FUEL CONTROL    			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	WORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			4283 	4283 				P106684			(CAN) ENGINE WAS SHUTDOWN DUE TO ABNORMAL INDICATIONS. ENGINE REMOVED AND SENT TO OVERHAUL FACILITY, FCU AND FUEL PUMP R	EMOVED, DAMAGE FOUND TO THE FUEL CONTROL QUILL SHAFT AND THE STUB SHAFT INTERNAL SPLINES. FCU AND FUEL PUMP REPLACED.  N	OTE: FCU HAD 780.4 HOURS SINCE LAST SPLINE INSPECTION.  NOTE: FUEL PUMP P/N 897400-5 WAS REPLACED AT THIS TIME DUE TO SP	LINE CHECK OUT OF LIMITS.  (TC NR 20070503004)			1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P15EA	 
2007061800189	20070618	00189	EA  	2007	6	18	CA070503005      	2	20070413	G	8520	76786	DRIVE GEAR      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CRANKSHAFT	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			2340 					RL118861			(CAN) LT ENGINE FAILED IN CRUISE FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE REMOVED AND REPLACED. THE ACCESSORY CASE WAS 	REMOVED AND FOUND THAT THE CRANKSHAFT DRIVE GEAR HAD FAILED (TEETH STRIPPED OFF DRIVE GEAR). (TC NR 20070503005)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007061800202	20070618	00202	EA  	2007	6	18	CA070503006      	2	20070426	G	8520	C3317228	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CRANKSHAFT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L521861A			(CAN) RECEIVED ENGINE, AFTER A REPAIR FOR PREMATURE CAMSHAFT FAILURE (REF: SDR 20070319008).  AFTER INSTALLATION AND RUN	-UPS, AN OIL LEAK WAS DISCOVERED AT THE CRANKSHAFT SEAL. WHEN THE SEAL WAS REMOVED IT WAS NOTED THAT IT WAS A (SPLIT) TY	PE SEAL NOT THE ONE-PIECE AS CALLED FOR IN THE IPC.  AFTER SPEAKING WITH REPAIR STATION, THEY AGREED TO COVER THE LABOR 	AND NEW SEAL COSTS. A NEW SEAL WAS INSTALLED AND THERE HAVE BEEN NO LEAKS SINCE. WE RETURNED THE DEFECTIVE SEAL, AS THEY	 REQUESTED IT FOR QUALITY PURPOSES. (TC NR 20070503006)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007062500002	20070625	00002	NM  	2007	6	25	CA070503007      	1	20070428	G	3240	530425	LOCK            	BFGOODRICH  		DHAV  	DHC5  	DHC5A       	2803018	NM  										BRAKE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				24   		347					(CAN) DURING A ROUTINE DAILY INSPECTION, IT WAS NOTED ON ONE OF THE BRAKE UNITS WEAR INDICATOR PINS WAS NO LONGER PROTRU	DING FROM THE BRAKE. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE LOCKING CLIP FOR THE END OF THE PIN WAS MISSI	NG ALLOWING THE PIN TO SLIDE IN AND OUT OF THE UNIT. THE BRAKE UNIT HAD JUST BEEN RETURNED FROM REPAIR BY CONDOR AVIATIO	N AND INSTALLED ON THE AIRCRAFT 24.3 HOURS BEFORE. THE DEFECTIVE UNIT WAS REMOVED AND REPLACED WITH A SERVICEABLE ONE. (	TC# 20070503007)		2	H	7	2 	4T			RT	        					 
2007061800203	20070618	00203	NE  	2007	6	18	CA070503008      	2	20070429	G	8530	LW13622	VALVE STEM      			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	BENT            	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			466  								(CAN) AIRCRAFT WAS FLYING DURING A SEISMIC JOB.  ENGINE LOST POWER AND ENGINE WAS RUNNING ROUGH.  EMERGENCY LANDING TOOK	 PLACE.  MAINTENANCE INVESTIGATED AND FOUND NR 1 CYLINDER DEFECTIVE.  UPON FURTHER INVESTIGATION INTAKE VALVE STUCK OPEN	 AND CONTACTED PISTON.  CYLINDER AND PISTON WERE REPLACED AND AIRCRAFT WAS PUT BACK IN SERVICE. (TC NR 20070503008)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007061800192	20070618	00192	EU  	2007	6	18	CA070503009      	1	20070422	G	2742	9787314203	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITCH TRIM	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			7794 	5773 							(CAN) THE SECONDARY ELECTRIC MOTOR, WHICH ACTUATES THE PITCH TRIM ACTUATOR IN RESPONSE TO AUTO PILOT COMMANDS WAS NOT OP	ERATIVE. THIS RENDERED THE AUTOPILOT SYSTEM U/S. THE ACTUATOR WAS REPLACED AND THE SYSTEM WAS CHECKED AIRWORTHY. THE O/H	 INTERVAL ON THESE ACTUATORS IS 6000 HRS. OR 5 YEARS INSTALLED TIME. (TC NR 20070503009)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007061800193	20070618	00193	SW  	2007	6	18	CA070503010      	1	20070423	G	7603	C8102413	CONTROL CABLE   			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	POWER LEVER	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) CONTROL CABLE FAILED WHERE IT MAKES A BEND COMING OUT OF THE CENTER PEDESTAL.  COMMON FAILURE POINT.  REPLACED WIT	H NEW PART, REPLACED OTHER SIDE AS A PRECAUTION AS WELL. (TC NR 20070503010)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2007061900127	20070619	00127	NM  	2007	6	19	CA070503011      	1	20070428	G	2910	3811374102	CABLE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	INDICATOR	SEPARATED       	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				127  		0193					(CAN) THE ORIGINAL RESERVOIR WAS REPLACED DUE TO FAULTY DIAPHRAGM INTERNALLY.  NEW O/H UNIT WAS INSTALLED. APPROXIMATELY	 127 HOURS LATER AS THE AIRCRAFT WAS PREPARING FOR DEPARTURE THE HYD. LOW PRESS. LIGHTS ILLUMINATED. THE AIRCRAFT RETURN	ED TO THE DEPARTURE RAMP AND SHUTDOWN. DURING THE INVESTIGATION OF THE FAULT THE HYD LEVEL WAS CHECKED USING THE GAUGES 	WHICH BOTH SHOWED FULL. THE PUMP WAS REMOVED TO SEE IF THE SHAFT HAD SHEARED BUT IT DID NOT. UPON FURTHER TROUBLESHOOTIN	G IT WAS DISCOVERED THAT THE HYDRAULIC SYSTEM WAS EMPTY. IT WAS THEN NOTICED UPON CLOSER INVESTIGATION OF THE INDICATOR 	CABLE ASSY. THAT THERE WAS A KINK IN THE CABLE NEXT TO THE NUT WHICH SECURES IT TO THE TOP OF RESERVOIR PREVENTING FREE 	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061900128	20070619	00128	NM  	2007	6	19	CA070504001      	1	20070501	G	5400	312N570138	LINE            			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  						LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FORWARD PYLON PRESSURE LINE FOUND CHAFED THROUGH CAUSING LEAK.  DAMAGE CAUSED BY A DEFECTIVE HOSE CLAMP. (TC NR 20	070504001)					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2008012900014	20080129	00014	SW  	2008	1	29	CA070504002      	1	20070503	G	6220	471401241	TUBE            	BELL        		BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1D    	41516	EA  					STABILIZER BAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14126	1108 		54C					(CAN) ON NORMAL WALK AROUND PILOT NOTICED STABILIZER BAR TUBE CRACKED AT SLEEVE AT IB END OF TUBE. STAB BAR ASSEMBLY WAS	 REPLACED AND MACHINE RETURNED TO SERVICE. AD 74-08-02 COVERS THIS ISSUE ON SOME OF THE LATER MODEL STAB BARS BUT NOT TH	E EARLIER MODELS OF STAB BARS. ALTHOUGH WE CHECK THIS AS PART OF OUR NORMAL PREFLIGHT CHECK AND THIS IS HOW IT WAS FOUND	. (TC NR 20070504002)			1	G	7	1 	3O	3	O		H1      	E279				 
2008031900136	20080319	00136	EA  	2008	3	19	CA070504003      	2	20070502	G	7250	3024711	TURBINE WHEEL   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14878					PCE85202			(CAN) DURING A HOT SECTION INSPECTION, A CRACK WAS DISCOVERED ON THE CT HUB FROM ONE UNUSED BALANCE HOLE, AROUND THE FLA	NGE AND BACK TO THE SAME BALANCE HOLE.THE CRACK WAS ADJACENT TO (1) OF THE (3) PROTRUDING LOCK LUGS. (TC NR 20070504003)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007061900129	20070619	00129	NM  	2007	6	19	CA070504004      	1	20070430	G	5330		SKIN            			BOEING	737   	7372L9      	1384497	NM  	PWA   	JT8   	JT8D17      	52049	NE  					BS 727	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WASHING PROCEDURE MAINTENANCE DETECTED A SKIN CRACK AT BS727, WL215, APPROXIMATELY 1.5 INCHES LONG. THIS IS	 KNOWN AREA ADDRESSED BY SB 737-53-1065. THE AREA WAS REPAIRED IAW THE MANUFACTURERS SRM AND RETURNED TO SERVICE (TC NR 	20070504004)				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007061900130	20070619	00130	SO  	2007	6	19	CA070504006      	1	20070501	G	5343	36058711	FITTING         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	TRUNNION SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, A CRACKED LT NLG TRUNNION SUPPORT WAS DETECTED AND THE AIRCRAFT IS CURRENTLY UNDERGOING REPLACE	MENT OF THE FITTING.  (TC NR 20070504006)					2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007080800162	20070808	00162	CE  	2007	8	8	CA070504007      	1	20070507	G	3245	7008006	TUBE            			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	TIRE	LEAKING         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			185  	185  							(CAN) AIRCRAFT LANDED, DURING TAXI RT MAIN WHEEL WENT FLAT AIRCRAFT WAS REMOVED FROM RUNWAY WHEEL ASSY REMOVED, TUBE FOU	ND TO HAVE A PIN HOLE, TUBE REPLACED, AIRCRAFT RETURNED TO SERVICE (TC NR 20070504007)					1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P25EA	 
2008013100018	20080131	00018	CE  	2008	1	31	CA070504008      	1	20070503	G	2822	1013640867	PUMP            	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUEL TRANSFER	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						PC112					(CAN) RT FUEL PUMP RUNNING EVEN AFTER MASTER SWITCH OFF.  (TC NR 20070504008)						1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007061900131	20070619	00131		2007	6	19	CA070504009      	4	20070503	G	2210		COMPUTER        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FLT DIRECTOR	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT DIRECTOR CB TRIPPED AND WILL NOT RESET. (TC NR 20070504009)						1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007061900132	20070619	00132	NM  	2007	6	19	CA070504010      	1	20070502	G	3234	MS253831	SWITCH          			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG HANDLE	INTERMITTENT    	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH, THE FLIGHT CREW SELECTED LANDING GEAR DOWN. THE LAND GEAR INDICATORS ILLUMINATED 3 GREEN AND 3 	RED. THIS INDICATED A DISAGREEMENT BETWEEN LANDING GEAR HANDLE POSITION AND LANDING GEAR POSITION. THE FLIGHT CREW SELEC	TED GEAR UP AND ABORTED THE LANDING. ON THE DOWNWIND LEG THE FLIGHT CREW SELECTED LANDING GEAR DOWN AND ALL ILLUMINATION	 WAS NORMAL (3 GREEN AND NO RED ILLUMINATION). THE FLIGHT CREW LANDED UNEVENTFUL.  MAINTENANCE INSERTED THE LANDING GEAR	 PINS AND SELECTED GEAR UP AND DOWN NUMEROUS TIMES AND WAS NOT ABLE TO DUPLICATE THE PROBLEM. THE AIRCRAFT WAS RELEASED 	AND CONTINUES TO FLY WITHOUT REOCCURRENCE OF THE PROBLEM. OPERATOR HAS ORDERED AN NEW LANDING GEAR HANDLE SWITCH AND WIL	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2007062200051	20070622	00051	EA  	2007	6	22	CA070505001      	1	20070501	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE CAPTAIN`S SIDE WINDSCREEN OUTER PANE CRACKED. THE FLIGHT WAS AT 34000FT, WHEN THE INCIDENT OCCURRED, THEN THEY	 DESCENDED AND DAWNED THEIR OXYGEN MASKS AS A PRECAUTION. THERE WAS NO PRESSURE LOSS AND NO EMERGENCY DECLARED. MAINTENA	NCE INSPECTED THE AIRCRAFT AFTER LANDING AND REPLACED THE CRACKED WINDOW. (TC NR 20070505001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007061900133	20070619	00133	SW  	2007	6	19	CA070506001      	1	20070423	G	6510	204010765001	NUT             			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ON APRIL 23, 2007 DURING A TEST FLIGHT FOR MAINTENANCE THAT WAS PERFORMED, THE PILOT EXPERIENCED AN UNCONTROLLED Y	AW TO THE RIGHT WHILE IN A 4 FOOT HOVER.  THE HELICOPTER WAS IMMEDIATELY SET DOWN ON THE TARMAC.  THERE APPEARED TO BE A	 STEP WORN IN THE INTERNAL WORM GEAR SPLINE OF NUT ASSEMBLY P/N 204-010-765-001 THAT MAY HAVE AFFECTED THE RIGGING PROCE	DURE THAT WAS ACCOMPLISHED THE NIGHT BEFORE.  NO DAMAGE TO HELICOPTER, CARS 625 APPENDIX G WAS PERFORMED AT THE SCENE WI	TH NO REPORTED DEFECT.  ENTIRE QUILL ASSEMBLY WAS REPLACED; AIRCRAFT RECEIVED FURTHER INSPECTION AND RE-RIGGED TAIL ROTO	R ASSEMBLY AND TEST FLOWN WITH NO DEFECT.   TSB WAS NOTIFIED AND HAVE NOT FINISHED THEIR INVESTIGATION.  PRODUCT SUPPORT	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007061900134	20070619	00134	EA  	2007	6	19	CA070506002      	1	20070505	G	7110	22850020113	NOSE COWL       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED MAINTENANCE CHECK, AFTER FAN COWL RT REMOVAL, STRUCTURAL DAMAGE WAS OBSERVED ON THE INLET COWL 	BY THE CAPPED 14TH STAGE BLEED AIR DUCT.  DAMAGE WAS OBSERVED ON THE REMOVED FAN COWL, SAME AREA, AS WELL. MAINTENANCE P	ROCEED TO REPLACE THE FAN COWL AND THE INLET COWL. AIRFRAME HOURS=26110:41. CYCLES= 21307. (TC NR 20070506002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007061900135	20070619	00135	NM  	2007	6	19	CA070507005      	1	20070507	G	2760	82742339001	PULLEY          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	SPOILER CABLE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			8935 								(CAN) AN OPERATOR HAS REPORTED THE FOLLOWING FINDINGS DURING THE C2 INSPECTION BEING PERFORMED ON AN AIRCRAFT. DURING IN	SPECTION OF THE SPOILER CABLE DISCONNECT SENSING SYSTEM ASSY, THE FAIRLEAD ROLLER AND SPRING ATTACHMENT HAVE BEEN FOUND 	INSTALLED INCORRECTLY. THE OPERATOR STATE THAT THEY HAD NO REASON TO BELIEVE THAT THIS COULD HAVE BEEN CARRIED OUT IN SE	RVICE, AND THE ERROR WOULD HAVE OCCURRED DURING AIRCRAFT PRODUCTION.  THE OPERATOR IS CURRENTLY CONDUCTING A FLEET-WIDE 	INSPECTION AND WILL ADVISE US ON THEIR FINDINGS.  (TC NR 20070507005)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007061900136	20070619	00136	CE  	2007	6	19	CA070507007      	1	20070504	G	8011	642085A4	ADAPTER         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	NR 1 STARTER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				10   							(CAN) UNABLE TO ROTATE ENGINE DURING WALKAROUND INSPECTION PRIOR TO ENGINE START. FAULT ISOLATED TO STARTER ADAPTER ASSY	. STARTER ADAPTER FAILED ONLY 9.6 HRS IN SERVICE AFTER OVERHAUL. OVERHAUL FACILITY CONTACTED. UNIT TO BE SHIPPED TO FACI	LITY FOR TEARDOWN INSPECTION.  STARTER ADAPTER REPLACED. (TC NR 20070507007)				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2007061900137	20070619	00137	SW  	2007	6	19	CA070507008      	1	20070506	G	7120	276211495	TRUSS           			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE 6 INSPECTION, A GAPING CRACK WAS FOUND ON THE RT ENGINE TRUSS MOUNT AT THE UPPER IB WELD JOINT OF T	HE FIREWALL ATTACH FITTING. (TC NR 20070507008)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007061900138	20070619	00138	CE  	2007	6	19	CA070507009      	1	20070503	G	7931	3020958	RELIEF VALVE    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE OIL	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			7508 	125  				PCE19412			(CAN) IN CRUISE FLIGHT, OIL PRESSURE BEGAN TO FLUCTUATE FROM BOTTOM TO MIDDLE OF GREEN RANGE, 80 TO 90 PSI.  FAULT CONFI	RMED ON GROUND RUN, NOT RELATED TO INDICATION. CONSULTATION WITH ENGINE OVERHAULER, OIL PRV VALVE TO BE CHECKED. PARTS A	T TOOLS DISPATCHED, THIS REPORT OPEN. (TC NR 20070507009)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081104		EA  	2008	11	4	CA070507010      	1	20070502	G	3246	50105844	WHEEL           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14976								(CAN) DURING ROUTINE NDT HFEC INSP ON RJ MAIN WHEEL, ACCORDING TO ABSC NDT MANUAL PART 1, 32-42-03, CRACKS WERE FOUND IN	 THE LOCKING RING GROOVE. THE CRACKS HAVE A DEPTH OF .040 INCH, .020 INCH AND .010.INCH.  COMPONENT COULD BE SENT FOR MA	CHINING, BUT THE DEFECT DEPTH IS ALREADY GREATER THAN THE MACHINING LIMITS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062200001	20070622	00001	EU  	2007	6	22	CA070507011      	1	20070504	G	3297		WIRE HARNESS    			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	LT MLG WW	DAMAGED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DEPARTING THE LANDING GEAR SELECT LEVER WOULD NOT MOVE TO THE GEAR UP POSITION. THE AIRCRAFT RETURNED TO POINT OF 	DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE DETERMINED THE SOURCE OF THE PROBLEM WAS IN THE LT GEAR HARNES	S WHEELWELL CONNECTOR. THE WIRING WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070507011)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007062200002	20070622	00002	EU  	2007	6	22	CA070507012      	1	20070503	G	3610		SHUTOFF VALVE   			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	BLEED AIR SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DEPARTING THE CREW OBSERVED THAT THE ARCRAFT WAS FAILING TO PRESSURIZE NORMALLY. THE AIRCRAFT RETURNED TO POINT OF	 DEPARTURE AND LANDED WITHOUT FURTHER DIFFICULTY. MAINTENANCE REPLACED THE NR 1 BLEED AIR SHUTOFF VALVE AND THE AIRCRAFT	 WAS RETURNED TO SERVICE. (TC NR 20070507012)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007061900076	20070619	00076	EA  	2007	6	19	CA070507013      	2	20070412	G	7414		ROTOR           	BENDIX      	S4LN20      	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175*      	GL  	MAGNETO	FAILED          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				1995 							(CAN) PILOT OF AC ON FLOATS DETECTED A DEAD MAGNETO ON HIS PRE-TAKEOFF INSPECTION, AND RETURNED TO THE DOCK. (TC NR 2007	0507013)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
	20081104		CE  	2008	11	4	CA070508001      	1	20070507	G	8011	MHB4016R	STARTER         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA				440  							(CAN) PILOT DID RUN-UP, ALL ENGINE INDICATIONS WERE NORMAL SO HE COMMENCED HIS TAKE-OFF. JUST AFTER HE STARTED TO CLIMB 	HE NOTICED THAT THE ACFT DID NOT WANT TO CLIMB AS IT SHOULD. ALL ENGINE INSTRUMENTS WERE WHERE THEY WERE SUPPOSED TO BE.	 HE ABORTED HIS TAKE-OFF WITHOUT INCIDENT. ACFT WAS RUN UP BY MAINT, ALL ENGINE INDICATIONS WERE CORRECT. COWLINGS WERE 	REMOVED AND ENGINE WAS INSPECTED, NOTHING WAS NOTED AS BEING WRONG. COMPRESSION CHECK WAS COMPLETED ON ENGINE AND WHILE 	DOING THE TEST. THE STARTER BENDIX ENGAGED BY ITS SELF (NO POWER WAS ON). TALKED TO ENGINE SHOP AND CONCLUDED THAT THE S	TARTER MUST HAVE ENGAGED ITS SELF ON TAKE-OFF AND THIS CAUSED LOSS OF POWER. SERVICABLE STARTER INSTALLED AND ACFT WAS F	1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007061900078	20070619	00078	SW  	2007	6	19	CA070508002      	1	20070507	G	7120	206064106001	LEG ASSY        	BELL        	206064106   	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE MOUNT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11747								(CAN) ON STARTING A 200HR SCHEDULED INSPECTON FOUND LT ENGINE MOUNT LEG BROKEN IN (2) PIECES AND UPON REMOVAL FOUND SEVE	RE INTERNAL CORROSION THAT CAUSED THE WALL THICKNESS TO DEGRADE TO THE POINT OF COLLAPSE AND FAILURE. (TC NR 20070508002	)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007061900079	20070619	00079	WP  	2007	6	19	CA070508003      	1	20070508	G	6220	369X10045	PIN             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1333 								(CAN) DURING AN INSPECTION THE ENGINEER NOTICED THE THE M/R BLADE FOLDING PIN LOOKED BENT. UPON TAKING THE UNIT APART HE	 NOTICED THAT THE THREADS OF THE PIN WERE NOT ON THE PIN STRAIGHT, KIND OF LOPSIDED. (TC NR 20070508003)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007080800163	20070808	00163	CE  	2007	8	8	CA070508004      	1	20070411	G	2750	S19061	CONTROL SWITCH  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	TE FLAPS	FAULTY          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) DURING CIRCUITS, PILOTS SELECTED FLAPS UP AND THEY REMAINED IN THE FULL DOWN POSITION. FOUND UP CONTROL SWITCH AT 	FLAP SELECTOR IN COCKPIT FAULTY, REPLACED SWITCH, OPS CHECKED OK WITH NO FURTHER OCCURANCES. (TC NR 20070508004)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007061900082	20070619	00082	SO  	2007	6	19	CA070508005      	1	20070504	G	2913	268028	HOUSING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD PUMP	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) 2ND MAINTENANCE GROUND RUN WAS COMPLETED ON AIRCRAFT AND ENGINES SHUTDOWN. HAD LUNCH AND RETURNED TO A/C AND OBSER	VED POOL OF HYDRAULIC FLUID BENEATH THE RT ENGINE. POST INSPECTION OF HYD PUMP REVEALED A CRACKED HOUSING.  REPLACED THE	 HYDRAULIC PUMP.   (TC NR 20070508005)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007061900083	20070619	00083	NM  	2007	6	19	CA070509001      	1	20070507	G	5610	80260008	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			69   								(CAN) IN CRUISE FLIGHT AT 25,000, THE FO`S WINDSHIELD CRACKED. REMOVED AND REPLACED FO`S WINDSHIELD I/A/W Q 400 TASK 56-	10-01-000-801 AND TASK 56-10-01-400-801, REMOVED AND REPLACED FO`S WINDSHIELD ANTI-ICE CONTROLLER I/A/W Q 400 TASK 30-41	-01-00-801 AND TASK 30-41-01-400-801 OP`S TEST GOOD.  (TC NR 20070509001)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022000047	20080220	00047	CE  	2008	2	20	CA070509002      	1	20070509	G	2133	10138001313	CONTROL VALVE   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN PRESSURE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WORK WAS DONE TO THE AC THAT OPENED THE PRESSURE VESSEL. WHEN THIS WORK WAS STARTED THE AC WOULD HOLD MAX DIFF. TH	E WORK DONE LED TO A PRESSURIZATION PROBLEM, WHICH, WHILE TROUBLESHOOTING, LED TO THE DISCOVERY OF FLOW CONTROL VALVE TH	AT WAS WORKING INCORRECTLY. THE CABIN LEAK CAUSED BY THE WORK DONE WAS CORRECTED AND AN O/H FLOW PACK INSTALLED. THE AC 	STILL WOULD NOT HOLD MAX  DIFF, MORE CABIN LEAKS WERE DISCOVERED AND REPAIRED. OUTFLOW AND SAFETY VALVES WERE CHANGED. P	ROBLEM STILL REMAINED. A SERVICEABLE CONTROL VALVE FROM AN IN SERVICE AC WAS INSTALLED FOR TROUBLESHOOTING, AND THE AIRC	RAFT WOULD PRESSURIZE TO MAX  DIFF.  A SECOND O/H FLOW CONTROL VALVE WAS INSTALLED ON THE LT SIDE AS WELL AS AN O/H UNIT	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007080800164	20070808	00164	EU  	2007	8	8	CA070509003      	1	20070504	G	2841	360930001	SIGNAL COND UNIT			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					FUEL INDICATOR	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA				7    							(CAN) IN FLIGHT, ON THE WAY BACK TO BASE THE CREW NOTICED THE RT FUEL GAUGE WAS INTERMITTENT AND NOT WORKING MOST OF THE	 TIME.  THE DEFECTIVE PART WAS JUST REPLACED 7 HOURS PRIOR WITH THE SAME ISSUE.  ANOTHER SIGNAL CONDITIONER HAS BEEN INS	TALLED AND CALIBRATED.  THERE HAS BEEN NO FAULTS SINCE THE REPLACEMENT. (TC NR 20070509003)				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2007062200003	20070622	00003	EA  	2007	6	22	CA070509004      	1	20070503	G	7110	2285008114	COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 ENGINE	SEPARATED       	W				K				NONE                    				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		DE	DESCENT        	1			CA			5855 								(CAN) ON DESCENT, THROUGH FL280, CREW FELT SLIGHT VIBRATION TO THE AIRCRAFT.  FIRST OFFICER (FO) FELT A SLIGHT SHUDDER I	N THE CABIN.   ON ARRIVAL, IT WAS FOUND NR 1 LOWER ENGINE COWL HAD SEPARATED FROM THE AIRCRAFT.  UPON MAINTENANCE INITIA	L INSPECTION, IT WAS NOTED THAT 75 PERCENT OF THE CAMLOC FASTENERS THAT HOLD THE COWL WERE STILL INSTALLED IN THE COWL R	ETAINERS. THE COWL SEPARATION CAUSED DAMAGE TO THE UPPER ACCESS NOSE COWL, NOSE COWL, LOWER TORQUE BOX, LOWER OB T/R CAS	CADE, AND SOME T/R PDU LINES.  (2) RETAINERS WERE REPLACED, THE LOWER CASCADE VANE WAS REPLACED, P2 SENSE LINE WAS REPLA	CED AND THE UPPER AND LOWER COWLS WERE REPLACED.   THE A/C WAS THEN FERRIED FOR FULL INSPECTION AND REPAIR.  AFTER FURTH	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007061900085	20070619	00085	NM  	2007	6	19	CA070510001      	1	20070506	G	2920	DSC1896	CHECK VALVE     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 HYD SYS	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											(CAN) AN OPERATOR EXPERIENCED A LOSS OF NR 2 HYD FLUID SYSTEM DUE TO A FRACTURED CHECK VALVE WHEN THE LANDING GEAR WAS S	ELECTED DOWN DURING APPROACH. THE CAUSE OF THE EVENT IS A CIRCUMFERENTIAL CRACK AROUND NR 2 HYD SYSTEM MANIFOLD CHECK VA	LVE. (TC NR 20070510001)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000038	20070820	00038	CE  	2007	8	20	CA070510002      	1	20070117	G	5512		SKIN            			CESSNA	441   	441         	2076020	CE  										STABILATOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9440 								(CAN) FOUND DELAMINATION (OF 8 INCH X 16 INCH) ON TOP OF LT SIDE IB HORIZONTAL STABILIZATOR.  DELAMINATION FOUND WHEN DO	ING PHASE 2 AND 3 INSPECTION.  HORIZONTAL STABILIZATOR REPLACED, NO REPAIR IS ALLOWED ON HORIZONTAL STABILIZATOR IAW SRM	.  (TC NR 20070510002)				1	L	7	2 	3T			RT	A28CE   					 
2008022000048	20080220	00048	CE  	2008	2	20	CA070510003      	1	20070428	G	3260		SQUAT SWITCH    			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RT MLG	FAILED          	W				O				OTHER                   				G			MULTIPLE FAILURE          			DE	DESCENT        	1			CA											(CAN) OUR 1900D WAS ON APPROACH, PILOT SELECTED THE LANDING GEAR DOWN. NOTHING HAPPENED, AC RETURNED TO ITS MAIN BASE. 	WHEN MAINT RECEIVED THE AC THE FAULT COULDNT BE DUPLICATED. DURING TROUBLESHOOTING ON THE GROUND THE MAINT WAS ABLE TO 	FIND A CONSTANT FAULT ON THE GROUND, IT WAS FOUND THAT THERE WAS A CONSTANT 28 VOLTS APPLIED TO THE (UP) SOLENOID OF THE	 HYDR POWERPACK, PREVENTING THE (DOWN) SOLENOID FROM MOVING THE SELECTOR VALVE TO THE DOWN POSITION WHEN THE LANDING GEA	R HANDLE IS PLACED IN THE (DOWN) SELECTION. THE VOLTAGE SOURCE ORIGINATED FROM THE PROP GOVERNOR TEST CIRCUIT THROUGH TH	E RT MLG SQUAT SWITCH. THE SQUAT SWITCH WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070510003)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008031900137	20080319	00137	SO  	2008	3	19	CA070510004      	2	20070420	G	8530	TISN73OCA221	CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 2	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				103  				150045H			(CAN) WHEN DOING 100 HRS INSP, FOUND DAMAGE ON COVER VALVE ROCKER CYLINDER NR 4, COVER (PN : 631834) REMOVED AND FOUND R	ETAINER ROCKER SHAFT (PN: 646032) BROKEN. NEW CYLINDER WAS INSTALLED IN POSITION NR 4. ALSO FOUND CYLINDER NR 2 WITH LOW	 COMPRESSION (50 PSID), THE CYLINDER WAS REPLACED BY NEW ONE. (TC NR 20070510004)				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007061900086	20070619	00086	WP  	2007	6	19	CA070510005      	2	20070507	G	7250		TURBINE BLADES  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			607  					P116662C			(CAN) DURING POST/PREFLIGHT INSPECTION, MAINTENANCE PERSONNEL NOTICED NICKS ON 2 OF THE 3RD STAGE TURBINE BLADES. NO FOD	 DAMAGE WAS NOTICED ON THE COMPRESSOR END OF THE ENGINE, SUSPECT FIRST STAGE BLADE RETAINER COMING LOOSE FROM TURBINE DI	SC AS ON SDR NR 20061110007 AND SDR NR 20060618001.   WILL NOTIFY WHEN HAVE CONFIRMATION.  ENGINE HAS BEEN REMOVED AND S	ENT TO AN HEAVY MAINTENANCE FACILITY FOR INVESTIGATION AND REPAIR. A RENTAL ENGINE HAS BEEN INSTALLED AND THE AIRCRAFT R	ETURNED TO SERVICE. (TC NR 20070510005)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007061900087	20070619	00087	EU  	2007	6	19	CA070510006      	1	20070510	G	6520	350A33100021	GEAR            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					T/R GEARBOX	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA			691  	691  		MA1110					(CAN) GEAR SET, PINION GEAR AND BEVEL GEAR WEAR AND PRODUCED METAL.  GEAR SET SCRAPPED DUE TO SPALLING. GEAR SET INSTALL	ED AT LAST OVERHAUL OF THE GEARBOX. TGB TSN 4632.8 / TSO 691.2 GEAR SET TSN 691.2 (TC NR 20070510006)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007061900088	20070619	00088	NM  	2007	6	19	CA070510007      	1	20070504	G	3233	85311176009	ACTUATOR        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NLG	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE NOSE LANDING GEAR WOULD NOT EXTEND TO THE DOWN AND LOCKED POSITION. CREW DID A FLY-BY PASS THE AT	C CONTROL TOWER, WHO CONFIRMED THAT THE GEAR WAS EXTENDED, BUT DID NOT APPEAR TO BE LOCKED.  GEAR WAS CYCLED AND ALL (3)	 GEARS WERE CONFIRMED DOWN AND LOCKED. AIRCRAFT THEN LANDED WITHOUT FURTHER INCIDENT. AIRCRAFT WAS THEN FERRIED WITH GEA	R PINNED DOWN TO A MAINTENANCE BASE FOR FURTHER INSPECTION AND REPAIR. THE FOLLOWING DAMAGE WAS FOUND. THE NLG UPLOCK AC	TUATOR FITTING ASSY P/N 85311176-009 WAS FOUND CRACKED AT THE ACTUATOR ATTACH POINT. DISCOLORATION OF PART OF THE CRACK 	INDICATES PROPAGATION OCCURRED OVER A PERIOD OF TIME. RECOMMEND A MORE FOCUSED SPECIFIC VISUAL OR NDT INSPECTION OF THIS	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081104		WP  	2008	11	4	CA070511001      	1	20070508	G	8010	C0531	SWITCH          	ROBSIN      	C0512       	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH ACTUATOR	DEFECTIVE       	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA			487  								(CAN) ACFT SHUTDOWN AT LEASE SITE. PILOT ATTEMPTED TO START THE ACFT TO CARRY OUT DAY AND ACFT FAILED TO START. FURTHER 	INVESTIGATION CONDUCTED BY AN AME FOUND ENGAGING SWITCH HAD FAILED. THE ACTUATOR ASSY WAS VERY DUSTY AND DIRTY FROM BELT	 DEBRIS. THE ACFT WAS FERRIED BACK TO A MAINT BASE AND THERE CLUTCH ASSY WAS REPLACED AND ACFT RETURNED TO THE FLIGHT LI	NE. (TC NR 20070511001)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007080800165	20070808	00165	CE  	2007	8	8	CA070511002      	1	20070510	G	3210	504501025	TORQUE TUBE     			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C*     	GL  	MLG	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF PILOT RETACTED GEAR ALL 3 GREEN LIGHTS WENT OUT AND UNLOCKED LIGHT WAS OUT.  RADIO CALL FROM TOWER 	INFORMED PILOT THAT LT MAIN GEAR WAS NOT RETRACTED.  PILOT PUT GEAR DOWN AND GOT ALL 3 GREEN LIGHTS. SHUT DOWN LT ENGINE	 IN CASE GEAR COLLAPSED ON LANDING AND MADE UNEVENTFUL LANDING. AIRCRAFT INSPECTED AND IT WAS NOTED THAT THE LT MAIN RET	RACT TORQUE TUBE WAS BROKEN. NEW PART ON ORDER. (TC NR 20070511002)			1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
2007061800123	20070618	00123	EA  	2007	6	18	CA070511003      	2	20070410	G	8520		BUSHING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	WORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				1208 				L739061A			(CAN) DURING CRUISE PORTION OF THE FLIGHT, THE PILOT NOTICED A VIBRATION FOLLOWED BY A NOISE AND LOSS OF OIL. THE PILOT 	SHUTDOWN THE ENGINE AND DIVERTED TO A NEARBY AIRPORT AND LANDED SAFELY. THE ENGINE WAS REMOVED AND SENT TO AN ENGINE SHO	P FOR A TEARDOWN.   IT WAS DETERMINED THAT THE COUNTERWEIGHT BUSHING WAS WORN THUS CAUSING EXCESSIVE PLAY. THIS EXCESSIV	E PLAY CAUSED THE COUNTERWEIGHT CHEEK TO BREAK AND THE COUNTERWEIGHT COMING LOOSE INSIDE THE ENGINE WHICH CAUSED SUBSTAN	TIAL DAMAGE.  THE POSSIBLE REASON FOR THE FAILURE COULD BE DUE TO ENGINE OVERSPEED AT SOMETIME OR ANOTHER. (TC NR 200705	11003)	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007061800124	20070618	00124	EU  	2007	6	18	CA070511004      	1	20070405	G	3230	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  										MLG	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON A RETURN FLIGHT, GEAR DOWN WAS  SELECTED BY PILOT. AFTER GEAR DOWN AND LOCKED, THE HYDRAULIC PUMP REMAINED OPER	ATING. PILOT LANDED AIRCRAFT AND MAINTENANCE WAS NOTIFIED.  DURING TROUBLESHOOTING MAINTENANCE DISCOVERED WHEN POWER APP	LIED TO AIRCRAFT, THE HYDRAULIC PUMP REMAINED OPERATIONAL. PULLING THE HYDRAULIC CONTROL 5 AMP CIRCUIT BREAKER HAD NO EF	FECT. THIS LED MAINTENANCE TO THE K601 RELAY WHERE IT WAS FOUND THAT THE CONTACTS WERE STUCK. CONSEQUENTLY THE ONLY WAY 	TO SHUT THE PUMP OFF WAS WITH THE BATTERY MASTER SWITCH. AFTER REPLACEMENT OF THE RELAY, SYSTEM OPERATED NORMALLY. (TC N	R 20070511004)	1	L	7	1 	3T			RT	A78EU   					 
2007062000003	20070620	00003	GL  	2007	6	20	CA070511005      	2	20070502	G	7323	23007505	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				1054 							(CAN) GOVERNOR DROOPED TO 95 PERCENT WOULD NOT RETURN TO 100 PERCENT. RETURNED TO BASE, TO CHANGE AIRCRAFT.  DRIVE FROM 	GOVERNOR WAS BINDING INTERMITTENTLY. WHEN THE GOVERNOR WAS MOVED IT SOUNDED LIKE THERE WAS SOME PARTS LOOSE INTERNALLY. 	GOVERNOR REPLACED, PROBLEM RECTIFIED. (TC NR 20070511005)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007062000004	20070620	00004	SW  	2007	6	20	CA070511006      	1	20070430	G	6410	406016100119	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1596 								(CAN) TAIL ROTOR BLADE WAS FOUND CRACKED AT THE TIP BLOCK. (TC NR 20070511006)						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2007062000005	20070620	00005	SW  	2007	6	20	CA070511007      	1	20070430	G	6220	407310104105	SPRING          	BELL        	407010150105	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FRAHM ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 2 SPRINGS WERE FOUND BROKEN. (TC NR 20070511007)						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2007062000006	20070620	00006	SO  	2007	6	20	CA070511008      	2	20070502	G	8520		CRANKCASE       	CONT        	TSIO520AE3B 	CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	ENGINE	CRACKED         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA				1941 		246135					(CAN) SUDDEN DROP OF OIL PRESSURE DURING FLIGHT TO THE BOTTOM OF THE GREEN ON OIL PRESSURE GAUGE. CONTINUED FLIGHT WITH 	SAFE LANDING. CRACK NOT FOUND BY NDT.  BOTTOM END REBEARINGED, BUT ENGINE OIL PRESSURE WOULD DROP ONCE WARMED UP (POST R	EPAIR). FURTHER NDT BY RTD QUALITY SERVICES FOUND POSITIVE CRACK INDICATION AT ROOF OF OIL PICKUP PASSAGE WHERE THE OIL 	PICKUP TUBE CONNECTS TO THE SOCKET MACHINED INTO THE CRANKCASE.  NDT TECHNICIAN MENTIONED A CASTING FLAW SEEMED TO BE TH	E CAUSE.  RTD MDT REPORT SUBMITTED AS SUPPORTING DOCUMENTATION TO THIS SDR. (TC NR 20070511008)		1	L	7	2 	3O	3	O		A34CE   	E8CE	5	C	P57GL	 
2007062000007	20070620	00007	NM  	2007	6	20	CA070511009      	1	20070511	G	3246	2601483	TIE BOLT        	MESSIER     	C20509000   	BOEING	767   	767328      	1385290	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					MLG WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						04207					(CAN) DURING ROUTINE WALKAROUND CHECK AFTER LANDING, A TIE BOLT FOR NR 2 MLG WHEEL WAS FOUND BROKEN.  BROKEN PARTS FOUND	 JAMMED IN THE BRAKE ASSY CAUSING DAMAGES TO BOTH WHEEL ASSY AND BRAKE ASSY. FURTHER INVESTIGATION ON GOING AS TO THE CA	USE OF BOLT FAILURE. (TC NR 20070511009)				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
	20081104		NE  	2008	11	4	CA070511010      	2	20070510	G	7414	SB9RU3	GEAR            	BOSCH       		DHAV  	DHC1  	DHC1        	2801702	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	MAGNETO	STRIPPED        	W				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA											(CAN) ON RUNUP BEFORE FLIGHT MAG CHECK CARRIED OUT. ENGINE WOULD NOT RUN WHEN SELECTED TO RT MAG. REMOVED RT MAG, FOUND 	50 PERCENT OF TEETH ON MAIN TIMING GEAR TO BE STRIPPED OFF. RT MAG REPLACED WITH SERVICEABLE MAG. (TC NR 20070511010)					1	L	7	1 	3O	3	R		EXPA1L71	5E1	5	C	P28EA	 
2007062000008	20070620	00008	EA  	2007	6	20	CA070511011      	1	20070502	G	5210	601R317621	HANDLE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5941 	5941 							(CAN) DURING ROUTINE MAIN CABIN DOOR INSPECTION FOUND MAIN CABIN PHASE IV DOOR HANDLE WITH (2) CRACKS. DOOR HANDLE REPLA	CED.  AIRCRAFT RETURNED TO SERVICE (TC NR 20070511011)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000009	20070620	00009	NM  	2007	6	20	CA070512001      	1	20070510	G	5610	NP15790213	WINDOW          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON ARRIVAL AT THE GATE THE PILOT SET THE PARK BRAKE AND AND THE PILOT`S SIDE WINDOW OUTER LAYER SHATTERED.  THE 	WINDOW WAS REPLACED BY MAINTENANCE AND FUNCTION CHECKED SERVICEABLE.  (TC NR 20070512001)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007062000010	20070620	00010	SO  	2007	6	20	CA070514001      	1	20070511	G	2550		UNKNOWN         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	CARGO BAY	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			38990								(CAN) AT FL220 APPROXIMATELY 20 MINUTES FROM DESTINATION THE AIRCRAFT EXPERIENCED A LOSS OF PRESSURIZATION. THE CREW DES	CENDED TO 10,000 AND THE AIRCRAFT CONTINUED AND LANDED WITHOUT FURTHER PROBLEM. INVESTIGATION DETERMINED THE SOURCE OF T	HE PRESSURIZATION TO BE A CRACK MIDWAY IN THE RT EDGE OF THE UPPER CARGO. (TC NR 20070514001)				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007071100288	20070711	00288	CE  	2007	7	11	CA070514002      	1	20070509	G	6120	A1464	LINK            	HARTZL      	C23035L     	MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	PISTON UNIT	TIGHT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			291  	291  		M7489					(CAN) AT THE AIRCRAFT 100 HOUR INSPECTION AND DURING THE REMOVAL OF THE PROP PITCH LINKS, IT WAS FOUND THAT THE PIVOT PI	N WAS DIFFICULT TO REMOVE.   AFTER REMOVAL, THE PISTON UNIT (THAT WAS REPLACED RECENTLY) WAS FOUND TO HAVE PAINT INSIDE 	THE PIVOT PIN HOLE CAUSING THE TIGHT FIT.  PAINT WAS REMOVED PIVOT PIN REPLACED AND CHECKED SERVICEABLE. (TC NR 20070514	002)			1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2007061800125	20070618	00125	NE  	2007	6	18	CA070514003      	2	20070301	G	7261		SEAL            			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE OIL SYS	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE IN CLIMB AND DURING CRUISE THE LOW OIL PRESSURE WARNING ACTIVATED. THE E	NGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A LEAKING ACCESSORY GEARBOX LIP SEAL. (TC NR 20070514003)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007062000011	20070620	00011	NE  	2007	6	20	CA070514004      	2	20070502	G	7210		COVER           			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					RGB	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED ON APPROACH AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPE	CTION REVEALED LEAKING AT THE REDUCTION GEARBOX ACCESSORY COVER RELATED TO COATING LOSS. (TC NR 20070514004)					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007061800126	20070618	00126	CE  	2007	6	18	CA070514005      	1	20070228	G	2120		UNKNOWN         			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  					CABIN	SMOKE           	W				G	A			O2 MASK DEPLOYED        	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA								77216			(CAN) SMOKE WAS OBSERVED IN THE CABIN AIR FOLLOWING TAKE-OFF.  OXYGEN MASKS WERE DEPLOYED AND AN EMERGENCY DECLARED.   T	HE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (	TC NR 20070514005)				1	L	7	2 	4F	4	F		A22CE   	E25EA				 
2007062200004	20070622	00004	EA  	2007	6	22	CA070514006      	2	20070303	G	7320	304867607	FMU             			AGUSTA	AB139 	AB139       	0260110	SW  	PWA   	PT6   	PT6*        	52043	EA  						UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) ENGINE POWER REDUCED UNCOMMANDED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE FUEL MANAGEMENT MODULE (FMM	) WAS SUBSEQUENTLY REPLACED. (TC NR 20070514006)					2	G	7	2 	4U	3	T		R00002RD	E2NE				 
2007061800127	20070618	00127	NE  	2007	6	18	CA070514007      	2	20070306	G	7532		BLEED VALVE     			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) TAKEOFF WAS ABORTED DUE TO HIGH TURBINE TEMPERATURE INDICATION.  THE INTERCOMPRESSOR BLEED VALVE WAS SUBSEQUENTLY 	REPLACED. (TC NR 20070514007)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007061800128	20070618	00128	NE  	2007	6	18	CA070514008      	2	20070307	G	7322	32448716	FUEL CONTROL    			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) TAKEOFF WAS ABORTED DUE TO HIGH TURBINE TEMPERATURE INDICATIONS.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.	 (TC NR 20070514008)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007062000012	20070620	00012	CE  	2007	6	20	CA070514009      	1	20070426	G	8011		GEAR            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					STARTER	IMPROPER PART   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				400  				L601976			(CAN) THE GEARS ON THE STARTER DID NOT MESH WITH THE RING GEAR FROM THE ENGINE CAUSING THE TEETH TO RIDE UP AND HIT THE 	TOP OF THE OPPOSITE GEAR. THIS CAUSED THE ENGINE AND STARTER TO LOCK UP. (TC NR 20070514009)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007061800129	20070618	00129	NE  	2007	6	18	CA070514010      	2	20070223	G	7200		ENGINE          			RAYTHN	36    	G36         	7150061	CE  	PWA   	PT6   	PT6A68      	 	NE  						MAKING METAL    	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								RA0363			(CAN) ON A TRAINING MISSION, THE ENGINE EXPERIENCED A LOSS OF THRUST (DURING TRAFFIC PATTERN STALLS) ACCOMPANIED BY A NO	ISE AND A CHIP DETECTOR INDICATION.  THE PILOT DECLARED AN EMERGENCY AND ABORTED THE MISSION.   SUBSEQUENT INSPECTION RE	VEALED METAL PARTICLES IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC 	NR 20070514010)			1	L	7	1 	3O	4	T	RT	3A15    	E26NE				 
2007061800130	20070618	00130	NE  	2007	6	18	CA070514011      	2	20070308	G	7313	ST3367009	PACKING         			AEROSP	ATR72 	ATR72202    	8680940	EU  	PWA   	PW120 	PW124B      	 	NE  					FUEL NOZZLES	LEAKING         	W				E				ENGINE SHUTDOWN         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CLIMB AND WAS SHUTDOWN IN  FLIGHT.  SUBSEQUENT INSPECTION	 REVEALED A FUEL LEAK RESULTING FROM DAMAGED FUEL NOZZLE PACKINGS. (TC NR 20070514011)					2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2007061800131	20070618	00131	EA  	2007	6	18	CA070514012      	2	20070305	G	7532		DIAPHRAGM       			SZD   	48    	SZD48       	8821648	EU  	PWA   	PT6   	PT6A65B     	52043	EA  					BLEED VALVE	PUNCTURED       	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CLIMB.  SUBSEQUENT INSPECTION REVEALED PUNCTURED COMPRESS	OR BLEED VALVE DIAPHRAGM. (TC NR 20070514012)					1	K	0	0 	  	4	T		EXP1K00 	E4EA				 
2007061800132	20070618	00132	CE  	2007	6	18	CA070514013      	1	20070309	G	7931		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						LOW PRESSURE    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								DB0676			(CAN) THE ENGINE EXPERIENCED AN LOSS OF OIL PRESSURE DURING CRUISE AND WAS REMOVED FROM SERVICE FOR FURTHER INVESTIGATIO	N.  MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514013)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007061800133	20070618	00133	EA  	2007	6	18	CA070514014      	2	20070312	G	7314		SPLINE          			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL PUMP	WORN            	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE SUFFERED AN IN-FLIGHT SHUTDOWN DUE TO FUEL STARVATION AS A RESULT OF WORN FUEL PUMP DRIVE SHAFT SPLINES	. (TC NR 20070514014)					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2007061800134	20070618	00134	EU  	2007	6	18	CA070514015      	1	20070303	G	6123		AUTOFEATHER SYS 			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA						MM1347					(CAN) ON APPROACH, THE ENGINE EXPERIENCED UNCOMMANDED TORQUE REDUCTIONS ACCOMPANIED BY FEATHERING OF THE PROPELLER.  THE	 ENGINE WAS SHUTDOWN IN FLIGHT.  THE ENGINE AUTO-FEATHER UNIT WAS SUBSEQUENTLY REPLACED. (TC NR 20070514015)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007061800135	20070618	00135	NE  	2007	6	18	CA070514016      	2	20070314	G	7321	8197354	FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			2599 								(CAN) DURING DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT, ACCOMPANIED BY A FUEL BOOST PRESSURE WARNIN	G INDICTATION.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FAULTY MECHANICAL FUEL CONTROL UNIT	. (TC NR 20070514016)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007061800136	20070618	00136	EA  	2007	6	18	CA070514017      	2	20070316	G	7230		STATOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					COMPRESSOR	DAMAGED         	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) THE ENGINE EXPERIENCED COMPRESSOR STALLS ON TAKEOFF ROLL AND THE TAKEOFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEA	LED A DAMAGED SECOND STAGE COMPRESSOR STATOR.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.	 (TC NR 20070514017)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007061800137	20070618	00137	NE  	2007	6	18	CA070514018      	2	20070309	G	7210		GEARBOX         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	MAKING METAL    	W				O				OTHER                   				J		R	WARNING INDICATION        		PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			CA								PC0634			(CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY A NOISE AND SMOKE IN THE CABIN 	AIR.   SUBSEQUENT INSPECTION REVEALED OIL AT THE ENGINE INLET AND METALLIC DEBRIS ON THE REDUCTION GEARBOX CHIP DETECTOR	.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514018)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007061800138	20070618	00138	EU  	2007	6	18	CA070514019      	1	20070319	G	7931		ENGINE          			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  						LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA								UC0035			(CAN) ENGINE OIL PRESSURE WAS SEEN TO INCREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AN	D ADVISE OF ROOT CAUE ONCE ESTABLISHED. (TC NR 20070514019)					1	G	7	2 	3U	3	T		H7EU    	E2NE				 
2007061800139	20070618	00139	NE  	2007	6	18	CA070514020      	2	20070202	G	7200		BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					NR 2	DAMAGED         	W				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE EXHIBITED FLAMES FROM THE EXHAUST IN FLIGHT.   SUBSEQUENT INSPECTION REVEALED A DAMAGED (NR 2) BEARING.	  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514020)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007061800140	20070618	00140	CE  	2007	6	18	CA070514021      	1	20070318	G	7931		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  						LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								DD0343			(CAN) THE ENGINE EXPERIENCED AN INCREASE IN OIL PRESSURE AND TEMPERATURE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTI	ON REVEALED METALLIC DEBRIS IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABL	ISHED. (TC NR 20070514021)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007061800141	20070618	00141	EA  	2007	6	18	CA070514022      	2	20070222	G	7310		TUBE            			AYRES 	S2    	S2RHGT65    	0970110	SO  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	FRACTURED       	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN) DURING SPRAYING OPERATIONS, THE ENGINE LOST POWER RESULTING IN A FORCED LANDING. SUBSEQUENT INSPECTION REVEALED A 	FRACTURED FUEL CONTROL P3 DELIVERY LINE. (TC NR 20070514022)					1	L	7	1 	3T	4	T	NC	        	E4EA				 
2007061800142	20070618	00142	NE  	2007	6	18	CA070514023      	2	20070320	G	7310	ST3367009	PACKING         			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL MANIFOLD	LEAKING         	W				E				ENGINE SHUTDOWN         				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) THE ENGINE EXHIBITED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION R	EVEALED LEAKING FUEL MANIFOLD PACKINGS. (TC NR 20070514023)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007062200005	20070622	00005	SO  	2007	6	22	CA070514024      	2	20070514	G	8530	637781	EXHAUST VALVE   	CONT        	639056      	CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA				847  							(CAN) EXHAUST VALVE HEAD SEPARATED, STRIKING THE INTAKE VALVE AND CAUSING THE INTAKE VALVE TO FAIL. THE HEAD OF THE EXHA	UST VALVE LODGED INTO THE EXHAUST PORT. THE INTAKE VALVE HAD (2) PIECES SEPARATE AND ONE LODGED ITSELF INTO THE TOP OF T	HE NR 1 CYLINDER HEAD, THE OTHER PORTION MIGRATED TO AN ADJACENT CYLINDER. ALL CYLINDERS WILL BE REMOVED AS COMPRESSION 	IS LOW ON ALL. (TC NR 20070514024)			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007061800143	20070618	00143	NE  	2007	6	18	CA070514026      	2	20070227	G	7310	ST3367009	PACKING         			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					FUEL MANIFOLD	LEAKING         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE ENGINE FLAMED OUT ON APPROACH.  SUBSEQUENT INSPECTION REVEALED LEAKING FUEL NOZZLE MANIFOLD PACKINGS. (TC NR 2	0070514026)					2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2007062200006	20070622	00006	NE  	2007	6	22	CA070514027      	2	20070416	G	7532	0301037140	BLEED VALVE     	TMECA       	ARRIEL1D1   	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	BROKEN          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						9219					(CAN) PIPE FAILED/BROKEN AROUND COMPLETE CIRCUMFERENCE OF FLARE.  FOUND WHEN BLEED VALVE WOULD NOT PASS TEST FOR CORRECT	 OPERATION. (TC NR 20070514027)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007061800144	20070618	00144	NE  	2007	6	18	CA070514028      	2	20070322	G	7250		TURBINE BLADES  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA								PC0463			(CAN) ON ENGINE SHUTDOWN FLAMES WERE SEEN EXITING THE EXHAUST.  SUBSEQUENT INSPECTION REVEALED DAMAGED COMPRESSOR TURBIN	E BLADES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514028)					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007062200007	20070622	00007	EU  	2007	6	22	CA070514029      	1	20070422	G	5330		SKIN            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND CRACK IN SKIN OF MAIN TRANSMISSION DECK DURING SCHEDULED 500 HOUR INSPECTION. DECK REPAIRED IAW MFG REPAIR I	NSTRUCTIONS FOR CRACKS DISCOVERED IN THIS AREA. (TC NR 20070514029)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007061800145	20070618	00145	NE  	2007	6	18	CA070514030      	2	20070322	G	7310	33026779	LINE            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					FUEL CONTROL	FRACTURED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) A FUEL LEAK WAS NOTED DURING GROUND OPERATIONS.  SUBSEQUENT INSPECTION REVEALED A FRACTURE FUEL LINE AT THE FUEL C	ONTROL. (TC NR 20070514030)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061900089	20070619	00089	NM  	2007	6	19	CA070514031      	1	20070512	G	2420		TRANSFORMER     		736664A     	BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					IDG	OPEN            	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			42599			D0161					(CAN) DURING CRUISE, THE LT AC BUS FAILED WITH THE LOSS OF ASSOCIATED SYSTEMS.  THE CONCERN WAS BEING ABLE TO START THE 	APU.  FLIGHT DECLARED A PAN-PAN WITH ATC AND BEGAN DIVERSION.  AT FL 350, 2 APU START ATTEMPTS, BUT START WAS ACHIEVED O	NLY AT FL150.  IAW CHECKLIST, LT BUS TIE SWITCH WAS RESET, AND LT BUS RESTORED.  HOWEVER, APU GEN AND GEN FAILED LIGHTS 	WERE ON.  ACFT LANDED APPROX 3 TONS OVERWEIGHT.  MTC CARRIED OUT WIRING CHECKS IAW FIM 24-20-00-101, AND FOUND THE LT ID	G CURRENT TRANSFORMER OPEN.  THEY REPLACED THE LT IDG AND LT GCU IAW AMM 24-11-01-401 AND 24-22-02.  NOTE:  GCU WAS CHAN	GED ALONG WITH THE IDG.  THE REMOVED GCU INFO IS:  P/N 734284D, S/N 1696, 73326 HOURS TOTAL TIME (TC NR 20070514031)	2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2007061800146	20070618	00146	NE  	2007	6	18	CA070514032      	2	20070323	G	7250		TURBINE BLADES  			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				R	A		PARTIAL RPM/PWR LOSS      	FLAME/FIRE                		CL	CLIMB          	1			CA								127007			(CAN) THE ENGINE EXPEREINCED AN UNCOMMANDED POWER REDUCTION IN CLIMB, ACCOMPANIED BY NOISE AND FLAMES EXITING THE EXHAUS	T.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED FRACTURED HIGH POWER TURBINE BLADES.  MFG WILL I	NVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514032)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007061900090	20070619	00090	SO  	2007	6	19	CA070514033      	1	20070429	G	2410	LW18129	BELT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ALTERNATOR	LOOSE           	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			25   								(CAN) PILOT NOTICED ALTERNATOR INOPERATIVE LIGHTS ILLUMINATE A FEW TIMES THEN STAYED ON, SO HE ELECTED TO LAND AT NEARES	T AIRPORT. MAINTENANCE FOUND BOTH ALTERNATOR BELTS LOOSE, CAUSE WAS DETERMINED TO BE BELT STRETCH AND WEAR-IN DUE TO BOT	H BELTS BEING REPLACED 25 HOURS PREVIOUSLY. (TC NR 20070514033)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007061800147	20070618	00147	NE  	2007	6	18	CA070514034      	2	20070326	G	7321	32448094	FCU             			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, ENGINE POWER INCREASED UNCOMMANDED, RESULTING IN A TORQUE EXCEEDANCE.  THE ENGINE WAS SHUTDOWN IN FL	IGHT.  SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20070514034)					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2007061800148	20070618	00148	EA  	2007	6	18	CA070514035      	2	20070326	G	7310	3011849	LINE            			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  					FCU	FRACTURED       	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) A FUEL LEAK WAS DISCOVERED DURING GROUND HANDLING OPERATIONS. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL TUBE	. (TC NR 20070514035)					1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2007061800149	20070618	00149	NE  	2007	6	18	CA070514036      	2	20070328	G	7200		ENGINE          			GULSTM	200   	200         	4500308	NM  	PWC   	PW306 	PW306A      	52165	NE  						NOISY           	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								CC0071			(CAN) IN CRUISE THE ENGINE EMITTED A NOISE ACCOMPANIED BY VIBRATION, A FADEC FAULT INDICATION AND FIRE WARNING INDICATIO	N.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR	 20070514036)				2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2007061900091	20070619	00091	NE  	2007	6	19	CA070514037      	2	20070321	G	7200		ENGINE          								PWA   	PT6   	PT6A65AR    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  		NOISY           	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA								97047			(CAN) THE ENGINE EMITTED A NOISE ON TAKEOFF ROLL ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  TAKEOFF WAS ABORTED.	  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514037)										4	T			E4EA	6	C	P44GL	 
2007061800150	20070618	00150	EA  	2007	6	18	CA070514038      	2	20070328	G	7261		PACKING         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					OIL PUMP	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE OIL PRESSURE FLUCTURATED DURING FLIGHT AND OIL WAS SEEN EXITING THE ENGINE COWLINGS.  SUBSEQUENT INSPECTION	 REVEALED A DAMAGED OIL PUMP O-RING PACKING. (TC NR 20070514038)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007061800151	20070618	00151	NE  	2007	6	18	CA070514039      	2	20070330	G	7313	ST3367009	PACKING         			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL MANIFOLD	LEAKING         	W				O				OTHER                   				K	X	J	FLUID LOSS                	ENGINE FLAMEOUT           	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) THE ENGINE FLAMED OUT ON APPROACH.  SUBSEQUENT INSPECTION REVEALED DAMAGED FUEL NOZZLE MANIFOLD O-RING PACKINGS. (	TC NR 20070514039)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007061800152	20070618	00152	NE  	2007	6	18	CA070514040      	2	20070331	G	7230		FAN BLADE       			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE AND HIGH VIBRATIONS AND SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED A	 FRACTURED LOW PRESSURE COMPRESSOR FAN BLADE, DAMAGE TO THE ENGINE NACELLE INLET, MISSING ENGINES COWLS AND ASSOCIATED A	IRFRAME IMPACT DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514040)				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007061800153	20070618	00153	NE  	2007	6	18	CA070514041      	2	20070327	G	7321		DRIVE SHAFT     		9682011739  	PILATS	PC7   	PC7         	7090401	EU  	PWA   	PT6   	PT6A25      	52043	NE  					FCU	SHEARED         	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			4352 			98034					(CAN) THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT AND SUBSEQUENTLY ACCELERATED UNCOMMANDED.  THE ENGINE WAS SH	UTDOWN ON APPROACH.  SUBSEQUENT INSPECTION REVEALED A SHEARED FUEL CONTROL UNIT DRIVE SHAFT. (TC NR 20070514041)					1	L	7	1 	3T	3	T	RT	A50EU   	E4EA				 
2007061800154	20070618	00154	NE  	2007	6	18	CA070514042      	2	20070403	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								114033			(CAN) ENGINE TORQUE FLUCTUATED IN FLIGHT ACCOMPANIED BY HIGH INTER-TURBINE TEMPERATURE AND LOW OIL PRESSURE.  THE ENGINE	 WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION FOUND THE POWER SECTION SEIZED AND THE EXHAUST DUCTS DENTED.  MFG WILL M	ONITOR THE INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514042)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007061800155	20070618	00155	NE  	2007	6	18	CA070514043      	2	20070404	G	7313	ST3367009	PACKING         			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL NOZZLE	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING BOARDING, FUEL WAS DISCOVERED LEAKING FROM THE ENGINE.  SUBSEQUENT INSPECTION REVEALED DAMAGED FUEL NOZZLE 	TRANSFER TUBE PACKINGS. (TC NR 20070514043)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007061800156	20070618	00156	NE  	2007	6	18	CA070514044      	2	20070403	G	7320	31B474707	FADEC           			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION DURING DESCENT AND WOULD NOT RESPOND TO THROTTLE INPUT.  THE	 ENGINE WAS SHUTDOWN IN FLIGHT.  THE ELECTRONIC ENGINE CONTROL (FADEC) WAS SUBSEQUENTLY REPLACED. (TC NR 20070514044)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007061800157	20070618	00157	NE  	2007	6	18	CA070514045      	2	20070409	G	7250		TURBINE BLADES  			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF THE ENGINE EXHIBITED TORQUE FLUCTUATIONS AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  S	UBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. (TC NR 20070514045)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007061900093	20070619	00093	NE  	2007	6	19	CA070514046      	2	20070411	G	7230		ROTOR           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	SEIZED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								AW0015			(CAN) DURING CLIMB THE ENGINE EXHIBITED VIBRATION AND SHUTDOWN, UNCOMMANDED.  SUBSEQUENT INSPECTION REVEALED HIGH PRESSU	RE ROTOR SEIZURE AND METAL CONTAMINATION IN THE TURBO MACHINE OIL SYSTEM.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF 	ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514046)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007061900094	20070619	00094	NE  	2007	6	19	CA070514047      	2	20070411	G	7250		TURBINE BLADES  			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					TURBINE SECTION	FRACTURED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ENGINE EMITTED A NOISE AND ENGINE PARAMETERS WERE SEEN TO FLUCTUATE.  THE ENGINE WAS SHUTDOWN IN	 FLIGHT.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. (TC NR 20070514047)					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2007061900095	20070619	00095	NE  	2007	6	19	CA070514048      	2	20070413	G	7313	ST3367009	PACKING         			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  					FUEL NOZZLE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING STARTING, FUEL WAS FOUND LEAKING FROM THE ENGINE. SUBSEQUENT INSPECTION REVEALED DAMAGED FUEL NOZZLE TRANSF	ER TUBE O-RING PACKINGS. (TC NR 20070514048)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007062200052	20070622	00052		2007	6	22	CA070514049      	4	20070507	G	6122	6506715	GOVERNOR        								ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	RT PROPELLER	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) WHILE ON CLIMB OUT, AFTER THE CREW MADE A ROUTINE SELECTION OF PROP SYNC, THE RT PROP/ ENGINE BEGAN TO CYCLE UNCON	TROLLABLY. THE CREW SHUT IT DOWN AND RETURNED TO STATION. MAINTENANCE REPLACED THE RT PROP GOVERNOR AND THE A/C RETURNED	 TO SERVICE.  (TC NR 20070514049)									4	T			E282	6	C	P898	 
2007062200053	20070622	00053	NE  	2007	6	22	CA070514050      	2	20070418	G	7200	PT6A11AG	ENGINE          			FLTCHR	24    	FU24AIRPTS  	3530202	WP  	PWA   	PT6   	PT6A11AG    	52043	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) ENGINE POWER INCREASED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVI	SE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514050)					1	L	7	1 	3O	3	T		4A12    	E4EA				 
2007062200054	20070622	00054	NE  	2007	6	22	CA070514051      	2	20070418	G	7200	PT6A67A	ENGINE          			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  						FLAMED OUT      	W				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA								RD0014			(CAN) THE ENGINE FLAMED OUT IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR	 20070514051)					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2007062200055	20070622	00055	EA  	2007	6	22	CA070514052      	2	20070413	G	7200	PT6A28	ENGINE          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  						SURGES          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								51225			(CAN) THE ENGINE SURGED DURING CLIMB ACCOMPANIED BY AN INCREASE IN INTERTURBINE TEMPERATURE.  MFG WILL INVESTIGATE THE E	VENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514052)					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2007062200056	20070622	00056	NE  	2007	6	22	CA070514053      	2	20070418	G	7250		TURBINE BLADES  			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	FRACTURED       	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) ON ADVANCING POWER FOR TAKEOFF, THE ENGINE EMITTED A NOISE AND LOST POWER.  SUBSEQUENT INSPECTION REVEALED FRACTUR	ED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514053)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007062200057	20070622	00057		2007	6	22	CA070514054      	1	20070420	G	6123		AUTOFEATHER SYS 								PWA   	PW120 	PW123       	 	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) DURING WATER SCOOPING, THE ENGINE PROPELLER AUTO-FEATHERED.  THE ENGINE TORQUE SENSOR AND ELECTRICAL HARNESS WERE 	SUBSEQUENTLY REMOVED FOR INVESTIGATION. MFG WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514054)										4	T			E20NE				 
2007062200058	20070622	00058	NE  	2007	6	22	CA070514055      	2	20070422	G	7200	PW120	ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120       	 	NE  						FLAMED OUT      	W				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA											(CAN) THE ENGINE FLAMED OUT IN CRUISE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR	 20070514055)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007061900097	20070619	00097	NE  	2007	6	19	CA070514056      	2	20070420	G	7200	PW121	ENGINE          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								121328			(CAN) THE ENGINE FLAMED OUT IN CRUISE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR	 20070514056)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007061800158	20070618	00158	NE  	2007	6	18	CA070514057      	2	20070113	G	7230		BLADE           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT ENGINE OIL PRESSURE REDUCED ACCOMPANIED BY AN INCREASE IN INTER-TURBINE TEMPERATURE.  ENGINE POWER 	WAS REDUCED AND A LANDING ACCOMPLISHED AT LOW POWER.  SUBSEQUENT INSPECTION REVEALED COMPRESSOR TURBINE BLADE DAMAGE.  M	FG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514057)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007061800159	20070618	00159	EA  	2007	6	18	CA070514058      	2	20070227	G	7230		COMPRESSOR      			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	DAMAGED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								56418			(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A REDUCTION IN ALL PARAMERTERS TO ZERO.  SUBSEQUENT I	NSPECTION REVEALED COMPRESSOR AND POWER TURBINE DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ES	TABLISHED. (TC NR 20070514058)				1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
2007061900098	20070619	00098	NE  	2007	6	19	CA070514059      	2	20070423	G	7313		PACKING         			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					FUEL NOZZLE	DAMAGED         	W				O				OTHER                   				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING CRUISE ENGINE POWER REDUCED UNCOMMANDED AND THE ENGINE SUBSEQUENTLY FLAMED OUT.  INSPECTION REVEALED A DAMA	GED FUEL NOZZLE TRANSFER TUBE O-RING PACKING. (TC NR 20070514059)					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007061900099	20070619	00099	NE  	2007	6	19	CA070514061      	2	20070423	G	7250		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AT TOP OF CLIMB, ENGINE TORQUE REDUCED UNCOMMANDED ACCOMPANIED BY A POWER TURBINE OVER-SPEED CONDITION.  THE ENGIN	E WAS SHUTDOWN IN FLIGHT. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 	20070514061)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007061900101	20070619	00101	NE  	2007	6	19	CA070514062      	2	20070426	G	7250		TURBINE BLADES  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								TB0071			(CAN) THE ENGINE CHIP DETECTOR WARNING ACTIVATED IN FLIGHT AND THE ENGINE SHUTDOWN UNCOMMANDED.  SUBSEQUENT INSPECTION R	EVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED (TC NR 	20070514062)				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007080900035	20070809	00035	CE  	2007	8	9	CA070515001      	1	20070514	G	2822	MS2774317	RELAY           		2C68        	CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL PUMP	INOPERATIVE     	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) A/C ABORTED TAKEOFF AUX PUMP LIGHT ON AT HIGH POWER.  RELAY REPLACED, A/C GROUND RUN AT HIGH POWER NO FAULT FOUND 	(TC NR 20070515001)					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2007061900102	20070619	00102	EA  	2007	6	19	CA070515002      	1	20070514	G	3250	711619	COLLAR          	DHAV        	7110029     	DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						226					(CAN) DURING MAINTENACE TO REPAIR THE NOSE GEAR ASSEMBLY IT WAS NOTED THAT THE STEERING COLLAR WAS CRACKED. THE NOSE GEA	R WAS THEN FULLY DISASSEMBLED TO REMOVE THE CRACKED STEERING COLLAR. THE NLG WAS THEN VISUALLY INSPECTED AND SOME OF THE	 ITEMS SENT FOR NDT. STEERING COLLAR CRACK CONFIRMED BY NDT. STEERING LIMITS OF ACTUATOR CHECKED FOR CORRECT TRAVEL AND 	VERIFIED WITHIN LIMITS. THIS COLLAR HAS BEEN IN SERVICE FOR SOME TIME.   (TC NR 20070515002)			1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007061900103	20070619	00103	NM  	2007	6	19	CA070515003      	1	20070507	G	2910	65178444441	TUBE            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	CHAFED          	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) IB, HYDRAULIC A SYS PRESSURE WAS NORMAL ON APPROACH AND QUANTITY REPORTED APPROXIMATELY ZERO. UPON SELECTION OF FL	APS, QUANTITY READ ZERO AND LOW PRESSURE LIGHTS ILLUMINATED. FLIGHT CREW DECLARED AN EMERGENCY AND THE HYDRAULIC FAILURE	 CHECKLIST WAS CARRIED OUT AFTER MISSED APPROACH PROCEDURE. THE AIRCRAFT LANDED NORMALLY WITH NO FURTHER INCIDENT.  A HY	D LEAK WAS FOUND INSIDE THE AFT AIRSTAIR AREA ON THE LT SIDE. THE HYDRAULIC A SYSTEM PRESSURE LINE FROM THE NR 1 ENGINE 	TO THE HYDRAULIC A SYSTEM MODULE WAS FOUND CHAFED WHERE THE LINE COMES INTO THE AFT AIRSTAIR AREA FROM THE NR 1 ENGINE P	YLON. THE CHAFED LINE WAS CAUSED BY EXCESSIVE PLAY OF THE HYDRAULIC TUBING FIRE SEAL BETWEEN THE PYLON AND THE AFT AIRST	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007061900111	20070619	00111	EA  	2007	6	19	CA070515004      	2	20070502	G	8530	A4871	RETAINER        			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 25 HOUR INSPECTION, FOUND (NR 2), (A) CYLINDERS IB LOWER BAFFLE RETAINER HEAD BROKEN AND ITS SPRING MISSING	, THUS AFT BAFFLE IN CONTACT WITH NR 2 CYLINDER OIL RETURN LINE CAUSED DEEP WEAR ON OIL LINE. NO LEAK FOUND AT THAT TIME	. RETAINER, SPRING AND OIL RETURN LINE REPLACED. (TC NR 20070515004)				1	G	7	1 	3O	3	O		H10WE   	E274				 
2007061900112	20070619	00112	GL  	2007	6	19	CA070515005      	3	20070503	G	6114	D2A34C580	HUB             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3545 	1052 							(CAN) EDDY CURRENT DETECTED INDICATION BEYOND ALLOWABLE LIMITS ON HUB SOCKET NR 1, 2 TO 3 THREADS DOWN. (TC NR 200705150	05)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007061900113	20070619	00113	SW  	2007	6	19	CA070515006      	1	20070501	G	2434	LW10382	BRACKET         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ALTERNATOR	BROKEN          	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								L3515336A			(CAN) ALTERNATOR BRACKET BROKEN.  REPLACED BRACKET WITH NEW PART PN LW10382. (TC NR 20070515006)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2007061900114	20070619	00114	EA  	2007	6	19	CA070515007      	2	20070513	G	7261		OIL SYSTEM      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			26205	4436 				PCE41553			(CAN) DURING CRUISE FLIGHT, THE FLIGHT CREW NOTICED A MOMENTARY FLUCTUATION AND THEN DECREASING OIL PRESSURE, THEN EVERY	THING RETURNED TO NORMAL.   MOMENTS LATER, THE ENGINE FAILED AND THE CREW CARRIED OUT THE SHUTDOWN. THE AIRCRAFT LANDED 	WITHOUT INCIDENT, ONCE ON THE GROUND, THE FLIGHT CREW ATTEMPTED TO TURN THE PROPELLER AND FOUND IT WAS SEIZED. MAINTENAN	CE ARRIVED AND CONFIRMED A CATASTROPHIC FAILURE OF THE POWER SECTION GEAR BOX. (TC NR 20070515007)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081104			2008	11	4	CA070515008      	4	20070515	G	6122	8210410	GOVERNOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	OUT OF RIG      	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA				6508 							(CAN) ON NUMEROUS LANDINGS THE AC YAWED HARD TO THE LT. AFTER RIGGING THE SNAG WOULD GO AWAY FOR NUMEROUS LANDINGS THEN 	YAW AGAIN TO THE LT. MAINT REPLACED THE LT PROP GOVERNOR AND RETURNED THE ACFT TO SERVICE. TO DATE THE SNAG HAS NOT RE-O	CCURED. (TC NR 20070515008)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008022000049	20080220	00049	SW  	2008	2	20	CA070516001      	1	20070515	G	5310	712551	TUBE            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235K2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	FUSELAGE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3787 								(CAN) WHILE PREFLIGHTING THE AC, THE PILOT NOTED WRINKLED FABRIC AT THE LOWER AFT END OF THE FUSELAGE. OPENING THE FABRI	C REVEALED THAT THE VERTICAL TUBE THAT FORMS THE FIN SPAR AND IS THE ATTACH POINT FOR THE RUDDER HINGES AND TAILWHEEL SP	RING AFT ATTACH WAS BROKEN THROUGH ABOUT AN INCH AND A HALF UP FROM ITS LOWER END, JUST ABOVE THE WELDED SKID ATTACHMENT	.    THERE IS NO EVIDENCE THAT THIS WAS CAUSED BY ANY FLIGHT LOADS OR HARD LANDINGS.  SUSPECT THAT TAILWHEEL SHIMMY FLEX	ED THE SKID PLATE ATTACHMENT IN A TORSIONAL MANNER AND CAUSED A FATIGUING OF THE TUBE AT THIS POINT, EVENTUALLY RESULTIN	G IN ITS FAILURE. (TC NR 20070516001)	1	H	7	1 	3O	3	O		A759    	E223	5	N	P9045	 
2007080900036	20070809	00036	CE  	2007	8	9	CA070516002      	1	20070507	G	7810	2654008205	EXHAUST DUCT    			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			837  								(CAN) SECONDARY EXHAUST DUCT CRACKED ALONG THE SEAM ON THE OUTER SIDE FROM ABOUT .2500 THE LENGTH DOWN TO .7500 THE LENG	TH, CAUSING SEVERAL SMALLER CRACKS TO FORM ALONG INITIAL CRACK 90 DEGREES FROM THE ORIGINAL BOTH ON THE UPPER AND LOWER 	SIDES.  OTHER OPERATORS REPORTED THAT IT IS NOT UNCOMMON TO HAVE SOME CRACKING.  (TC NR 20070516002)				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2007062200076	20070622	00076	EU  	2007	6	22	CA070516003      	1	20070514	G	6123		SOLENOID        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FEATHERING SYS	STUCK           	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA				570  							(CAN) PILOT INITIATED START FOLLOWING TURNAROUND AND NOTICED PROP RPM FOLLOWING START WAS ONLY AT 500 RPM AND NOT AT THE	 NORMAL, ABOVE 1000 RPM AT ENGINE IDLE. ALSO HAD EIS FLASHING AMBER AND RED ON EIS AS PROP WAS OPERATING BELOW 950 RPM. 	PROP WAS NOT COMING OUT OF FEATHER POSITION. PILOT SHUTDOWN ENGINE. INVESTIGATION REVEALED A STUCK OPEN PROP FEATHERING 	SOLENOID WHICH DID NOT ALLOW UNFEATHERING OF PROP. ONCE SOLENOID COOLED DOWN SOLENOID FUNCTIONED NORMALLY. REPLACED OVER	SPEED GOVERNOR WITH REPAIRED AND TESTED UNIT. (TC# 20070516003)		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008022000050	20080220	00050	SO  	2008	2	20	CA070516004      	1	20070505	G	2810		BLADDER         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL TANK	INCORRECT       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			7400 								(CAN) AC IN FOR MAINTENANCE AND FUEL DRAINED FROM AC. DID NOT GET ANY FUEL FROM THIS QUICK DRAIN SO ADDED FUEL TO TANK A	ND OBSERVED A FUEL LEAK AROUND THE COVER PLATE IN BOTTOM OF WING UNDER THE TANK AND LOCATION OF QUICK-DRAIN. MAINT REMOV	ED COVER AND FOUND THE QUICK DRAIN NOT CONNECTED TO FUEL BLADDER. FOUND THAT SOMEONE HAD THREADED A BOLT INTO THE BLADDE	R AND HAD REDUCED THE LENGTH OF CONNECTOR TO THE QUICK DRAIN SO THE COVER PLATE WOULD FIT BACK IN PLACE. NO SNAG ON AIRC	RAFT ADDRESSING THIS AND NO WAY FUEL COULD HAVE BEEN SUMPED FROM THIS TANK. FUEL BLADDER TANK WAS REMOVED AND SERVICEABL	E BLADDER INSTALLED. (TC NR 20070516004)	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007061900115	20070619	00115	CE  	2007	6	19	CA070517001      	1	20070515	G	7920	77853	ADAPTER         			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L1859236A			(CAN) DURING GROUND RUN AFTER OVERHAUL, AN OIL LEAK WAS NOTICED ORIGINATING FROM THE LOWER RT ATTACH POINT OF THE OIL FI	LTER ADAPTER.  UPON CLOSE VISUAL INSPECTION A CRACK WAS FOUND IN THE RADIUS OF THE LOWER RT FLANGE.  UNIT WAS REPLACED A	ND LEAK CHECKED. (TC NR 20070517001)				1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2007062200077	20070622	00077	EA  	2007	6	22	CA070517002      	2	20070418	G	7200	O320D2J	ENGINE          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  		FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				2280 				L1088539A			(CAN) INTERMITTENT VIBRATION AFTER UNUSUAL FLIGHT ATTITUDES DURING TRAINING. (TC NR 20070517002)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007062200078	20070622	00078	SW  	2007	6	22	CA070517007      	1	20070508	G	5730	9000351	WINGLET         			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	WING	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) IT WAS FOUND THAT THE SHEET METAL SCREWS HOLDING THE TIP ON THE WING HAD ALL COME LOOSE. THE WING TIP THEN VIBRATE	D FOR A PERIOD OF TIME ,ELONGATING THE SCREW HOLES IN THE WING UNTIL ALL OF THE SCREWS FELL OUT AND THE WING TIP DEPARTE	D THE WING IN FLIGHT. THE PILOT DID NOT NOTICE ANYTHING ABNORMAL AND ONLY NOTICED IT WAS MISSING ON WALK AROUND. (TC NR 	20070517007)			1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P25EA	 
2007061900116	20070619	00116	EU  	2007	6	19	CA070518001      	1	20070514	G	7603	355A57217007	LEVER           			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	25OC  	250C20R     	 	GL  					RT THROTTLE	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			4995 								(CAN) PART BROKE IN (2) PIECES JUST ABOVE ATTACHMENT POINT DURING ENGINE PRE-START CHECK PROCEDURES. (TC NR 20070518001)						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
2007061900117	20070619	00117	NE  	2007	6	19	CA070518002      	2	20070516	G	8530	LW13622	INTAKE VALVE    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	FRACTURED       	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			567  								(CAN) PILOT LANDED TO CONDUCT TASK AT WELL SITE.  DURING ATTEMPTED START UP, THE AIRCRAFT WOULD NOT START. AFTER A SHORT	 TIME, THE PILOT ATTEMPTED AGAIN AND THE AIRCRAFT STARTED.   IT RAN VERY ROUGH AND EXCESSIVE VIBRATIONS. PILOT TOOK THE 	ENGINE POWER UP TO CHECK IF THE ISSUE WAS MAGNETO`S. HE THEN SHUT IT DOWN.   MAINTENANCE CONDUCTED FURTHER INVESTIGATION	S AND FOUND CYLINDER NR 3 INTAKE VALVE HAD SNAPPED OR FRACTURED IN 3 PIECES. PORTION OF THE VALVE WAS FOUND IN THE INTAK	E INDUCTION BOX.  WILL NOTIFY WHEN FURTHER DETAILS ARE AVAILABLE. (TC NR 20070518002)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081104			2008	11	4	CA070518003      	2	20070515	G	7322	206061716003	LEVER           																	FCU	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSP, ENGINEER ATTEMPTED TO REPLACE FCU LEVER ON FCU NOT YET INSTALLED ON ACFT. INSTALLING BOLT P/N AN173-5	 COULD NOT BE INSERTED THROUGH HOLE BORE OF LEVER. BORE FOUND UNDERSIZE AND REMOVED FROM SERVICE. (TC NR 20070518003)																		 
2007061800162	20070618	00162	NE  	2007	6	18	CA070518004      	2	20070325	G	8520	48564	CASE            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								JP207649			(CAN) ENGINE WAS OVERHAULED OCT 02,2005, ENGINE WAS REMOVED FROM STEEL SHIPPING CONTAINER FOR INSTALLATION MARCH 25, 200	7. CRACKS WERE FOUND ON THE REAR CASE AT THE IB HOLES FOR MAGNETO MOUNTING. THE ENGINE WAS SENT TO APPROVED AMO AND REPA	IRED. FOLLOWING REPAIR ENGINE WAS INSTALLED IN AIRCRAFT . GROUND RUN FOR 30 SECONDS AND ENGINE SHUTDOWN DUE TO OIL LEAK 	FROM REAR CASE.  VISUAL INSPECTION DISCOVERED THAT THE REAR CASE HAD (3) DISTINCT PIN HOLES THROUGH THE CASE IN THE AREA	 OF THE OIL SCREEN HOUSING. THE HOLES LOOKED LIKE CAUSED BY CORROSION. THE ENGINE WAS REMOVED AND IS TO BE SENT TO APPRO	VED AMO FOR FURTHER REPAIR OR REPLACEMENT OF REAR CASE/BLOWER ASSY.  (TC NR 20070518004)	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P736	 
2007061900118	20070619	00118	NM  	2007	6	19	CA070518005      	1	20070516	G	7500	69474753	DUCT            			BOEING	727   	727260      	138408K	NM  	PWA   	JT8   	JT8D17      	52049	NE  					BLEED AIR	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING THE DAILY INSPECTION, MAINTENANCE PERSONNEL HEARD A LOUD BANG, WHICH WAS FOLLOWED BY A DROP IN AP	U DUCT PRESSURE TO 0 PSI. UPON INSPECTION, 2 BLEED AIR DUCTS WERE FOUND RUPTURED, FORWARD OF THE APU LOAD CONTROL VALVE 	THAT CONNECT TO THE BLEED AIR BY-PASS VALVE. NO ADDITIONAL DAMAGE PROBLEMS WERE NOTED.  NOTE: INFORMATION LISTED ABOVE I	N AREA 9, BLOCK(B) PN.  THE PN LISTED ARE FOR THE TWO DUCT ASSEMBLIES THAT WERE FOUND DAMAGED.  DUCT P/N 69-47475-3 AND 	69-47474-3  (TC NR 20070518005)		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007062000013	20070620	00013	EA  	2007	6	20	CA070518006      	1	20070516	G	3260	864808	PSEU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LANDING GEAR	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			2864 								(CAN) IN CRUISE FLIGHT CREW RECEIVED PROX SYS CHAN FAULT CAUTION MESSAGE AS WELL AS (3) RED GEAR INDICATIONS, IAW AFM HA	D TO PERFORM ALTERNATE EXTENSION, FLIGHT LANDED WITHOUT INCIDENT.  AFTER MAINTENANCE TROUBLESHOOTING THE MDC IS POINTED 	TOWARDS THE PSEU ITSELF.  THE PSEU WAS REPLACED AND FUNCTION TESTS WERE CARRIED OUT AND GEAR SWINGS AND THE AIRCRAFT WAS	 RETURNED TO SERVICE.  PRESENT AC HRS:24426:01 AND CYCLES: 20077 (TC NR 20070518006)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000014	20070620	00014	SW  	2007	6	20	CA070518007      	1	20070517	G	6510	MS150011	GREASE FITTING  		407040303135	BELL  	407   	407         	1182206	SW  										HANGAR BRGS	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			200  								(CAN) WHILE THE SHAFT WAS REMOVED THE MECHANIC WENT TO WIPE THE HANGER BEARING GREASE FITTING AND THE FITTING CAME OFF I	N HIS HAND.  ALL OTHER HANGER BEARING GREASE FITTINGS WERE THEN CHECKED AND 4 OUT OF THE 6 WERE FOUND TO BE VERY LOOSE. 	THE ONES WE FOUND LOOSE WERE AS FOLLOWS: BOTH FWD AND AFT OIL COOLER BLOWER HANGER BEARINGS AND THE 4TH AND 6TH HANGER B	EARINGS. (TC NR 20070518007)			1	G	7	1 	3U			O	H2SW    					 
2007062000015	20070620	00015	SW  	2007	6	20	CA070518008      	1	20070517	G	2810	457370	FUEL CAP        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT WING	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, THE CREW NOTICED THAT FUEL WAS LEAKING FROM THE LT WING FUEL CAP. THE CREW RETURNED TO BASE	 WITHOUT INCIDENT.  THE AIRCRAFT WAS INSPECTED AND IT WAS DISCOVERED THAT THE FUEL CAP WAS DEFECTIVE.  THE LARGE PLASTIC	 NUT AT THE BASE OF THE CAP ASSEMBLY IS HELD AT THE CORRECT TORQUE WITH THE USE OF A PIN THAT PASSES THROUGH THE NUT INT	O THE BASES OF THE ASSEMBLY.  THIS PIN WAS MISSING, WHICH ALLOWED THE NUT TO TURN WHEN THE FUEL CAP WAS OPENED AND CLOSE	D.  THE TORQUE ON THIS NUT SETS THE PROPER SEATING OF THE FUEL CAP.  BECAUSE THE NUT BACKED OFF, THE FUEL CAP BECAME LOS	E AND ALLOWED FUEL TO LEAK PAST THE FUEL CAP. THE FUEL CAP WAS REPLACED WITH AN IMPROVED CAP THAT IS DESIGNED TO PREVENT	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007062000016	20070620	00016	NM  	2007	6	20	CA070518009      	1	20070516	G	2915	9752753	RELIEF VALVE    			BOMBDR	CL600 	CL6002D15   	       	NM  	GE    	CF34  	CF34*       	 	NE  					HYDRAULIC SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3105 	1230 							(CAN) ON PUSHBACK FROM GATE CREW RECEIVED NOSE STEERING INOP MESSAGE. AIRCRAFT STEERING MEL`D. AFTER TAKEOFF GEAR FAILED	 TO RETRACT. AIRCRAFT RETURNED TO ORIGINATING AIRPORT FOR NORMAL LANDING. MAINTENANCE TROUBLESHOOTING REPLACED HYD BALAN	CE RELIEF VALVE, NR 3 HYD SYSTEM BLED, GEAR SWINGS COMPLETED, AIRCRAFT RETURNED TO SERVICE. (NOTE: PART AT LAST REPAIR H	AD BEEN RETURNED TO VENDOR AS CAUSING NOSE STEERING INOP (1875HR/853CY TSN)  (TC NR 20070518009)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000017	20070620	00017	EA  	2007	6	20	CA070520001      	1	20070520	G	3230		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						COLLAPSED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON ARRIVAL CREW HAD A SUSPECTED HARD LANDING, STAB TRIM AURAL WARNING CLACKER SOUNDED AND BOTH MAIN GEAR COLLAPS	ED. THERE WAS MAJOR STRUCTURAL DAMAGE AND PRELIMINARY REVIEW OF PICTURES SHOWS EXCESSIVE ENGINE BLADE DAMAGE DUE TO DEBI	S INGESTION, FURTHER UPDATE TO FOLLOW.  TSB HAS PULLED THE FDR AND CVR.  PRESENTLY INVESTIGATION IS UNDERWAY AND WILL UP	DATE FURTHER WHEN COMPLETE.  (TC NR 20070520001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000018	20070620	00018	EA  	2007	6	20	CA070521001      	1	20070520	G	3230		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						COLLAPSED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON ARRIVAL, CREW HAD A SUSPECTED HARD LANDING. STAB TRIM AURAL WARNING CLACKER SOUNDED AND BOTH MAIN GEAR COLLAP	SED. THERE WAS MAJOR STRUCTURAL DAMAGE AND A PRELIMINARY REVIEW OF THE PICTURES SHOWS EXCESSIVE ENGINE BLADE DAMAGE DUE 	TO DEBRIS INGESTION. THE FDR AND CVR HAVE BEEN PULLED BY TSB AND AN INVESTIGATION IS UNDERWAY. NO PICTURES AVAILABLE TO 	THE FSR AS OF YET. (TC NR 20070521001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000019	20070620	00019	EA  	2007	6	20	CA070521002      	1	20070514	G	2740	70609	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZ STAB	MALFUNCTIONED   	W				B	H	A		EMER. DESCENT           	DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         		F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THERE WAS A STAB TRIM RUNAWAY EVENT THAT OCCURRED. AN EMERGENCY WAS DECLARED AND A RETURN TO BASE. FURTHER AC DAMA	GE AFTER SUCCESSFUL LANDING. BASED ON THE ATTACHED CREW REPORT, IT WAS A STAB TRIM RUNAWAY NOSE DOWN EVENT.  PLEASE NOTE	 THAT A DFDR DOWNLOAD WAS CARRIED OUT ON THIS AC AND A COPY OF THIS DOWNLOAD WILL BE SENT TO THE APPROPRIATE PEOPLE WITH	IN MFG AS SOON AS IT BECOMES AVAILABLE TO ME.  THE NTSB ADVISED THAT THE FAA HAS REPORTED THIS AIRCRAFT DECLARED AN EMER	GENCY DUE TO A STABILIZER TRIM PROBLEM.  THE AIRCRAFT WAS ON A SCHEDULED FLIGHT WHEN THE STAB TRIM RUNAWAY FAULT OCCURRE	D.  THE NTSB ALSO REPORTED THAT THE CREW FOLLOWED THE QRH PROCEDURES AND AIRCRAFT REACHED A NOSE-DOWN ATTITUDE BY THE TI	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000020	20070620	00020	EU  	2007	6	20	CA070522001      	1	20070518	G	7110	V40GT3911AA	SPRING          		10562648    	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE COWLING	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) COMING OUT OF A MAJOR INSPECTION WHERE THE EJECTION SPRING ON ALL THE COWLS (P/N 105-62648, 105-62664, 105-62643 A	ND 105-62663) WERE REPLACED, SEVERAL EJECTION SPRING P/N V40GT39-1-1AA WERE BREAKING IN TWO PIECES.  THIS PROBLEM HAPPEN	ED STATICALLY AND IN FLIGHT.  THESE EJECTION SPRINGS WERE ORDERED NEW FROM MFG AND RECEIVED ON DEC 22/06. BATCH NR S2006	02192. (TC NR 20070522001)			1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2007062000021	20070620	00021	WP  	2007	6	20	CA070522002      	1	20070519	G	3213	369H60022	STRUT           	HUGHES      	369H600132  	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ANNUAL INSPECTION OF THE AIRCRAFT IT WAS NOTICED THAT THE LANDING GEAR HAD SOME PLAY IN IT.  UPON FURTHE	R INSPECTION THE ENGINEER FOUND THAT THE BRACE TO STRUT BOLT HAD SOME SLOP IN IT.  THE ENGINEER REMOVED THE BRACE BOLT A	ND FOUND 3 CRACKS EMMITTING FROM THE BLACE BOLT HOLE ON THE AFT RT LANDING GEAR STRUT.  ONE CRACK ON THE TOP OF THE STRU	T AND 2 CRACKS ON THE BOTTOM OF THE STRUT. (TC NR 20070522002)			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007062000022	20070620	00022	SO  	2007	6	20	CA070522003      	2	20070507	G	8520	653058	CAMSHAFT        	CONT        	IO520       	CESSNA	180   	180K        	2072624	CE  	CONT  	O520  	O520*       	 	SO  	MCAULY	D3A34	D3A34C403   	GL  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1087 			821995R					(CAN) IN REMOVING NR 1 CYLINDER TO BE CHANGED OUT THE LIFTERS WERE REMOVED TO BE BLEED DOWN, LIFTERS WERE SPAWLED. THE A	ME INSPECTED THE CAM AND THE EXHAUST LOBE WAS ALSO SPALLED. THE ENGINE WAS REMOVED AND PREPARED FOR SHIPMENT TO A REPAIR	 SHOP. UNDER FURTHER INVESTIGATION WE FOUND OTHER LOBES AND LIFTERS WITH SPALLING.  OUR HYPOTHESIS IS LACK OF ENGINE USE	 CAUSING INTERNAL CORROSION/RUST WICH LEAD TO FAILURE   (TC NRIN 20070522003)			1	H	7	1 	3O	3	O		5A6     	E5CE	5	C	P47GL	 
2008022000051	20080220	00051	SW  	2008	2	20	CA070522004      	1	20070522	G	6220	407310101101	BEARING         	BELL        	407010100   	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1493 			LK37					(CAN) COMPLETE FAILURE/SEPARATION OF SHEAR BEARING ELASTOMERIC LAMINATIONS (4 OF 4). FOUND AT INSPECTION. SHEAR BEARING 	P/N 407-310-100-115. S/N 8345, 8325, 8109, 8113. (TC NR 20070522004)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2007062000023	20070620	00023	EA  	2007	6	20	CA070522005      	2	20070521	G	7250		TURBINE WHEEL   	PWC         	PT6A65B     	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	UNKNOWN         	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA				4137 							(CAN) ECTM TREND INDICATED ENGINE ITT WAS INCREASING WITH TIME. ENGINE SPLIT. CT WHEEL NOTED AS CONTACTING THE GUIDE VAN	E ASSY. ENGINE TO BE SENT TO MFG TO INVESTIGATE. (TC NR 20070522005)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008022000052	20080220	00052	CE  	2008	2	20	CA070522006      	1	20070520	G	2731	10552002221	CONTROL CABLE   			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	ELEVATOR TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT WAS IN THE HANGER FOR INSPECTION. AN INSPECTION WAS BEING STARTED IN THE AFT TAIL AREA. THE AME APPRENTIC	E NOTICED THE ELEVATOR TRIM CABLE SEVERELY FRAYED WHERE IT WRAPPED AROUND THE TRIM SERVO. THE CABLE WAS REMOVED AND REPL	ACED WITH A NEW PART (TC NR 20070522006)				1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2008022000053	20080220	00053	CE  	2008	2	20	CA070523001      	1	20070522	G	7920	3391000015	LINE            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  	MCAULY	3A32C	3A32C406    	GL  	OIL SYSTEM	FRACTURED       	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			8334 								(CAN) OIL PRESSURE LINE FRACTURED AT FIREWALL CAUSING AN OIL LEAK ON THE INSIDE OF THE FIREWALL.   LINE APPEARS TO BE HA	RD FROM AGE.  AIRCRAFT LANDED WITHOUT ANY FURTHER PROBLEMS. (TC NR 20070523001)					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
2008022000054	20080220	00054	CE  	2008	2	20	CA070523002      	1	20070518	G	2120	EM6303	BLOWER          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	CABIN	SEIZED          	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WHILE ENROUTE, THE AC CABIN AND COCKPIT FILLED UP WITH SMOKE FROM WHAT SMELLED ELECTRICAL IN NATURE. OXYGEN WAS US	ED AND THE AC FINISHED ITS TRIP AND LANDED (DESTINATION WAS CLOSER THAN TO TURN AROUND). MAINT WAS CALLED AND AN AC WAS 	DISPATCHED TO CONTINUE THE DAY. SYSTEMS WERE CHECKED, NO FAULTS WERE FOUND. THE AC WAS RETURNED TO BASE WITH NO PASSENGE	RS ON BOARD. UPON FURTHER INSP AT THE BASE, IT WAS FOUND THAT ONE OF THE CABIN VENT BLOWERS WAS SEIZED AND THE (2) SPEED	 ADJUSTING RESISTORS INSTALLED ON THE BLOWER WERE WARPED AND MELTED FROM HEAT. THE VENT BLOWER WAS REPLACED AND THE AC W	AS RETURNED TO SERVICE. (TC NR 20070523002)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007062000024	20070620	00024	EA  	2007	6	20	CA070523003      	1	20070523	G	2810		UNKNOWN         		21564075    	CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	FUEL SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1850 			546					(CAN) LEAK AT (3) LOWER CORNERS NEAR INTERCONNECTS.  DROPS 9180 (TC NR 20070523003)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008031900139	20080319	00139	NM  	2008	3	19	CA070523004      	1	20070410	G	4930	69254518	SHUTOFF VALVE   			AMD   	FALC50	FALCON2000  	2730170	NM  	PWC   	PW308 	PW308C      	52182	NE  					APU	OPEN            	W				O				OTHER                   				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			118  	118  		P439					(CAN) WHILE PREPARING FOR A DEPARTURE. APU FAILED TO START. APU NEVER ACCEL`D PAST 13 PERCENT ON FIRST ATTEMPT AND LARGE	 AMOUNT OF FUEL VAPOR EMITTED FROM EXHAUST. NEAR THE END OF START ATTEMPT, BRIEF FLAME AND SMOKE EVIDENT AT EXHAUST PIPE	 EXIT. AFTER ALLOWING TIME FOR TRAPPED FUEL TO DRAIN, 2ND START ATTEMPTED. THIS TIME NO ACCEL PAST APPROX 10 PERCENT AND	 FIRE AND SMOKE EMITTING FROM TAILPIPE AND TAILCONE UPPER AIRSCOOPS. FIRE SELF EXTINGUISHED PRIOR TO DISCHARGE OF FIRE B	OTTLES.  INITIAL INDICATIONS FALSELY LED US TO TROUBLESHOOT POSSIBLE A/C ELECTRICAL PROBLEM DUE TO ABNORMALLY HIGH START	 AMPERAGES AND VOLTAGE INDICATIONS. BOTH AIRFRAME AND APU MFG TECH REPS INVOLVED IN THE (4) DAY TROUBLESHOOTING PROCESS.	2	L	7	2 	4F	4	F	RT	A50NM   	E00065EN				 
2007062000025	20070620	00025	EA  	2007	6	20	CA070523005      	1	20070523	G	2810	215640022	FLUID           		215640022   	CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	FULE SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1849 			540					(CAN) LEAK AT LOWER CORNERS NEAR INTERCONNECTS.    (TC NR 20070523005)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
	20081104		CE  	2008	11	4	CA070523006      	1	20070430	G	3246	08A01156027	GUSSET          			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FLOAT ASSY	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			15   								(CAN) AS THE RESULT OF BUMPING A DOCK, THE FWD BULKHEAD HAD TO BE REPLACED ON THE LT FLOAT ASSY ON THE ACFT.  AFTER GAIN	ING ACCESS, IT WAS FOUND THAT THE AREA WHICH IS NOT NORMALLY ACCESSED HAD SEVERAL PARTS RIVETED AS PART OF THE STRUCTURE	 HAD NO PROPER EDGE DISTANCE ON THE RIVETS. FURTHER INVESTIGATION FOUND THE OTBD GUSSET WAS PAINTED OVER WITH PRC HIDING	 THE FACT THAT THE HOLES WERE DRILLED ONLY HALF ON THE GUSSET.  QC HAS BEEN ADVISED OF THE PROBLEM AND SUPPLIED REPLACEM	ENT PARTS, AND IS IN REVIEW OF QUALITY INSP PROCEDURES TO VERIFY WHY THIS HAPPEND SO IT WILL NOT HAPPEN AGAIN.  ADVISED 	OF A POSSIBLE ENGINEERING CHANGE ON THE PART TO INCREASE IT`S SIZE SLIGHTLY TO GET THE REQUIRED EDGE DISTANCE. THERE WER	1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2008012900017	20080129	00017	WP  	2008	1	29	CA070523007      	1	20070521	G	6210		PIN             	HUGHES      		HUGHES	369   	369A        	4470503	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3885 			0098848293					(CAN) PIN FOUND BROKEN AT FIRST THREAD / SHANK. NUT WAS CAPTURED IN THE HANDLE CLIP.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007062200079	20070622	00079	GL  	2007	6	22	CA070523008      	1	20070504	G	2720	C2CF1777A	ARM             			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 FOUND IN WELD RADIUS ON OB SIDE OF CABLE ATTACH ARM. (TC NR 20070523008)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007062000026	20070620	00026	NE  	2007	6	20	CA070524001      	2	20070517	G	7314		PUMP            		TA7         	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			DE	DESCENT        	1			CA				1743 		662AL3381					(CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPERATIONS, UPON DESCENT WITH AN EXTERNAL LOAD: THE MASTER CAUTION WARNING I	NDICATION WAS ILLUMINATED. THE LOAD WAS SET AND RELEASED.  THE CAUTION PANEL OBSERVED TO REVEAL THAT THE ENGINE DRIVEN F	UEL PUMP WARNING LIGHT WAS ON. THE P/C IMMEDIATELY ABORTED ANY FURTHER OPERATIONS AND RETURNED TO THE SERVICE LANDING WH	ICH WAS APPROXIMATELY ONE KILOMETER AWAY AND THE NEAREST SUITABLE LANDING SIGHT. A NORMAL LANDING AND ENGINE SHUTDOWN WA	S CARRIED OUT. TROUBLESHOOTING BY THE AME AT SERVICE FOUND THAT IT WAS A POSITIVE INDICATION THAT ONE OF THE TWO PUMP EL	EMENTS HAD FAILED TO DELIVER FUEL PRESSURE.  AD 2006-11-16, 1250 HOUR MAIN AND SECONDARY DRIVE SHAFT AND PUMP GEAR SPLIN	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007062000027	20070620	00027	EU  	2007	6	20	CA070524002      	1	20070522	G	2424	243211	GCU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 1	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA				157  							(CAN) DURING DEPARTURE THE NR 1 AC WILD SYSTEM WENT OFF LINE. WHEN THE CREW ATTEMPTED A RESET THE (BLUE) HYDRAULIC SYSTE	M WENT OFF LINE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND CARRIED OUT A NORMAL LANDING. MAINTENANCE REPLACED THE 	NR 1 AC WILD GCU. AFTER WHICH THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070524002)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007062000028	20070620	00028	EA  	2007	6	20	CA070524003      	1	20070524	G	3246	C3UF1085	STRUT           	DHAV        	557170      	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION A (4 TO 5) CRACK WAS FOUND. THE CRACK PROPAGATED COMPLETELY THROUGH THE BOTTOM CENTER OF 	THE STRUT LEG BETWEEN THE LOWER ATTACH POINTS. THE STRUT LEG WAS REMOVED AND REPLACED. PICTURES ON FILE AT REPAIR STATIO	N. (TC NR 20070524003)				1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
2007062000029	20070620	00029	EA  	2007	6	20	CA070524004      	1	20070523	G	3240	10100199	SENSOR          			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF34*       	 	NE  					NR 1 BRAKE	CORRODED        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA			5781 	5781 							(CAN) DURING CRUISE CREW RECEIVED BRAKE OVERHEAT WARNING , LT OUTER BTMS SHOWING INCREASING BRAKE TEMP UP TO 20 UNITS, T	HEN STARTED TO DECREASE. AIRCRAFT DESCENDED TO LOWER ALTITUDE AND SPEED SLOWED. BRAKE TEMP STARTED TO RISE TO 18 UNITS. 	GEAR EXTENDED, BRAKE TEMPS RETURNED TO NORMAL GREEN INDICATION. RETURNED TO ORIGINATING AIRPORT, NORMAL LANDING. MAINTEN	ANCE FOUND NR 1 BRAKE TEMP SENSOR HAD CORRODED PINS. BRAKE TEMP SENSOR REPLACED. AIRCRAFT RETURNED TO SERVICE. (NOTE: PA	RT IS AN EXPENDABLE AND SYSTEM DOES NOT TRACK COMPONENT TIME. TIMES PROVIDED ARE AIRCRAFT TOTAL TIME.) (TC NR 2007052400	4)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000030	20070620	00030		2007	6	20	CA070524005      	1	20070519	G	2710	82740162001	LINK ASSY       								PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT AILERON	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			795  								(CAN) WHEN DOING WP8 INSPECTION TASK 000-057-640-500 GVI OF THE (RT) AILERON ASSY. MAINTENANCE FOUND LINK ASSY P/N 82740	162-001 FROM THE RT AILERON LVDT BROKEN. (TC NR 20070524005)										4	T			E00062EN	6	C	P17BO	 
2007062200080	20070622	00080	NE  	2007	6	22	CA070524006      	2	20070517	G	7200	CT581402	ENGINE          			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					NR 1	FAILED          	W				B				EMER. DESCENT           				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA			22313	102  				295130C			(CAN) REPORT NR 07-02204 (ON MAY 11, 2007) THE AC UNDERWENT AN ENGINE CHANGE ON NR 1 ENGINE AND REQUIRED A MAINTENANCE T	EST FLIGHT. AFTER (2) GROUND RUNS INCLUDING LEAK CHECKS, DEPARTED TO THE TRAINING AREA TO PERFORM REQUIRED ENGINE TOPPIN	G CHECK.  VERIFIED WEATHER CONDITIONS AT 2000 FT, PA AND DESCENDED TO 1000 FT PA TO BEGIN CHECK. WITH NR 2 ENGINE SSL PU	LLED BACK TO 94 PERCENT NF AND NR 1 ENGINE AT FULL THROTTLE WE NOTED ENGINE VALUES CLIMBING THROUGH 2000 PA. LEVELED AIR	CRAFT OFF TO CHECK EMERGENCY FUEL LEVER RIGGING AND THE CO-PILOT INCREASED EMERGENCY FUEL LEVER TO MAXIMUM AFTER DECREAS	ING  NR1 ENGINE SSL TO ABOVE GOVERNING RANGE. TOPPING VALUES WERE ON TARGET FOR NR 1 ENGINE AND THE CO-PILOT SLIGHTLY RE	2	G	7	2 	4U	4	U		1H15    	1E3				 
2007062000031	20070620	00031	EA  	2007	6	20	CA070524007      	1	20070520	G	2752	735619C	COUPLING        			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	T/E FLAP	TORN            	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) CREW REPORTED (FLAP DRIVE) CAUTION LIGHT ILLUMINATED DURING FLAP EXTENSION , FLAPS CONTINUED TO MOVE. NORMAL LANDI	NG. MAINTENANCE INSPECTION FOUND FLAP SECONDARY CENTER DRIVE COUPLING TORN FROM MOUNTING BRACKET AND LYING IN RT ARMPIT.	 FLAP SECONDARY CENTER DRIVE SECTION (CORE AND HOUSING) REPLACED, FLAP SECONDARY DRIVE CENTER COUPLING REPLACED. MOUNTIN	G BRACKET REPLACED. FLAP SECONDARY DRIVES CLEANED AND LUBRICATED. AIRCRAFT RETURNED TO SERVICE.  NOTE: FLAP SECONDARY DR	IVE INSPECTION AND LUBRICATION TASKS (1500HR INTERVAL) LAST COMPLETED 791HR / 949CY PREVIOUS. (TC NR 20070524007)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081104		WP  	2008	11	4	CA070524008      	1	20070523	G	6310	V31001	SWITCH          	ROBSIN      	C0511       	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CLUTCH ACTUATOR	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			349  								(CAN) DURING AN INSP, CLUTCH ACTUATOR FAILED TEST AND CLUTCH WOULD NOT ENGAGE DUE TO MICROSWITCH FAILURE. CLUTCH REPLACE	D AND CHECKED SERVICEABLE. (TC NR 20070524008)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2007062000032	20070620	00032	EA  	2007	6	20	CA070525001      	1	20070525	G	3233	2158500116	ACTUATOR        		2158500116  	CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	LANDING GEAR	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						H213					(CAN) THE NEWLY OVERHAULED ACTUATOR FAIL THE FUNCTIONAL CHECK AFTER INSTALLATION, IT DOESNT STAY LOCKED WITH HYDRAULIC 	PRESSURE REMOVED.  (TC NR 20070525001)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007062000033	20070620	00033	NE  	2007	6	20	CA070525002      	2	20070511	G	7210	MS949034	BOLT            	PWC         	311276701   	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			946  	946  		83D248					(CAN) ENGINE WAS REMOVED AFTER THE PILOT REPORTED THAT A LOUD BANG AND SHUDDER WAS EXPERIENCED BY THE AIRCRAFT DURING CL	IMB IN AUTOPILOT NEAR TAKEOFF POWER APPROXIMATELY 5 MINUTES AFTER TAKEOFF AT 6000 FT.  THE REDUCTION GEARBOX CHIP DETECT	OR WAS ILLUMINATED AND THE AIRCRAFT RETURNED BACK TO BASE AT LOW POWER WITH NO OTHER ABNORMALITIES OBSERVED.  ALL GROUND	 OPERATIONS WERE NORMAL.  THE DATE OF THE INCIDENT WAS MAY 11, 2007.  DURING INVESTIGATION DISMANTLE OF THE POWER SECTIO	N AND FIRST-STAGE REDUCTION CARRIER ASSEMBLY, OF (6) MACHINE HEX BOLTS (IPC P/N 3038338, CH. 72-11-00, FIGURE 4, ITEM 20	0, P/N MS9490-34) WAS FOUND WITHOUT THE BOLT HEAD ATTACHED.  NOTE THAT THE CARRIER HEX BOLTS SECURE THE FIRST-STAGE CARR	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2007062200081	20070622	00081	EU  	2007	6	22	CA070525003      	1	20070524	G	3230	A1029E	BOLT            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NLG RETRACTION JACK MOUNT UPPER IB MOUNTING BOLT SHEARED. DISCOVERED DURING SCHEDULED NLG RETRACTION, JACK ATTACH 	BOLT INTEGRITY INSPECTION. ALL MOUNTING BOLTS REPLACED WITH NEW. (TC NR 20070525003)					2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	3PNE	 
2007062200082	20070622	00082	NE  	2007	6	22	CA070528001      	2	20070521	G	7250		TURBINE         	CFMINT      	71200011    	AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA						733107					(CAN) WAITING FOR SHOP TEAR DOWN, SUSPECTED FAILURE CAUSES BUT NOT CONFRIMED ARE NR 4 BEARING OR HPT BLADE.  ENG TT 2646	2, CYC 12034, TSI 13977, CSI 6250. (TC NR 20070528001)					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007080900038	20070809	00038	EU  	2007	8	9	CA070528002      	1	20070511	G	3230	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3047 								(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN. THE NOSE LANDING GEAR IN TRANSIT LIGHT WAS SLOW TO EXTINGUISH.  UP	ON MAINTENANCE TROUBLESHOOTING THE HYDRAULIC PUMP WAS FOUND TO BE INTERMIITTENTLY CUTTING OUT.  THE LANDING GEAR RELAY W	AS REPLACED AND NO FURTHER ADNORMALITIES WERE REPORTED. (TC NR 20070528002)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007062200083	20070622	00083	GL  	2007	6	22	CA070528003      	3	20070319	G	6114	4716	HUB             	MCAULY      	D2A34C58    	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			3399 	647  		740488					(CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, FOUND HUB THREADS CRACKED, FOUND ONE BLADE THREAD CRACK	ED, FOUND ONE BLADE RETENTION NUT CRACKED.  FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR INITIAL INSPECTION AND MODIFIC	ATION WHICH HAD BEEN ACCOMPLISHED (TC NR 20070528003)				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007061800163	20070618	00163	NM  	2007	6	18	CA070528004      	1	20070307	G	3244		TIRE            			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A3    	 	NE  					NLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH AT 5000 FT CREW HEARD LOUD BANG, AIRCRAFT LANDED WITHOUT INCIDENT, FLIGHT CREW SUSPECTED A BIRD STRIKE	. AT ARRIVAL GATE MAINTENANCE FOUND LT NOSE WHEEL TIRE DEFLATED AND OFF THE RIM. BOTH NOSE WHEEL ASSEMBLIES REPLACED, SH	OP FOUND THAT THE LT NOSE WHEEL ASSEMBLY OVER INFLATION VALVE HAD BLOWN. NO EVIDENCE OF A BIRD STRIKE WAS FOUND. (TC NR 	20070528004)			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007062200084	20070622	00084	GL  	2007	6	22	CA070528005      	3	20070319	G	6114	4716	HUB             	MCAULY      	D2A34C58    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1563 		690816					(CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, AT THAT TIME THE PROPELLER HAD BEEN INSPECTED IAW AIRWO	RTHINESS MANUAL PART VI APPENDIX C (4).  THE LAST OVERHAUL COMPLETED WAS JUNE 1987.  THE PROPELLER HAD EXCEEDED THE MFG 	HARD TIME OF 1,500 HOURS BETWEEN OVERHAULS. FOUND HUB THREADS CRACKED.  FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR IN	ITIAL INSPECTION AND MODIFICATION WHICH HAD BEEN ACCOMPLISHED.   (TC NR 20070528005)			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007062200085	20070622	00085	GL  	2007	6	22	CA070528006      	3	20070301	G	6111	S90AT4	BLADE           	MCAULY      	D2A34C58    	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			890  	890  		736835					(CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, AT THAT TIME THE PROPELLER HAD BEEN INSPECTED PER AIRWO	RTHINESS MANUAL PART VI APPENDIX C (4).  THE LAST OVERHAUL COMPLETED WAS OCTOBER 1991. FOUND BOTH BLADE THREADS CRACKED.	  FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR INITIAL INSPECTION AND MODIFICATION WHICH HAD BEEN ACCOMPLISHED. (TC NR 	20070528006)			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007062200120	20070622	00120	EA  	2007	6	22	CA070528007      	1	20070526	G	3234	750006000	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NLG WW	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGHT 13000 FT AT 290 KIAS, THE NLG DOOR WARNING/UNSAFE MESSAGE WAS DISPLAYED AND CREW COULD HEAR A CL	UNKING NOISE FROM THE NLG AREA.  ELECTED TO RETURN. MLG EXTENDED NORMALLY WITH (3) GREEN LIGHTS AND NO CAUTION/ADVISORY 	MESSAGES DISPLAYED.  AIRCRAFT LANDED AND TAXIED TO THE GATE WITHOUT FURTHER PROBLEM. TROUBLESHOOTING WAS IN PROGRESS AND	 FOUND THE LANDING GEAR SELECTOR VALVE WAS UNSERVICEABLE. PART WAS REPLACED, FUNCTION CHECK FOUND NO FURTHER DEFECT. AIR	CRAFT RETURNED FOR SERVICE (TC NR 20070528007)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062200121	20070622	00121	EU  	2007	6	22	CA070528008      	1	20070413	G	7933	RP22100	SENSOR          	CFMINT      	CFM565C4    	AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					OIL SYSTEM	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			AP	APPROACH       	1			CA			27909	15670		741603		741603			(CAN) NR 2 ENGINE OIL TEMPERATURE HIGH, 30 MILES FROM AIRPORT, ENGINE SHUTDOWN IAW QRH PROCEDURES, AIRCRAFT LANDED WITHO	UT INCIDENT. ENGINE OIL TEMP SENSOR AND FUEL RETURN VALVE REPLACED, NO SUBSEQUENT FAULTS AFTER PARTS CHANGED. (TC NR 200	70528008)				2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2008013100034	20080131	00034	EA  	2008	1	31	CA070528009      	2	20070527	G	7310	3032791	LINE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LT ENG FUEL	CHAFED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) FUEL FLOW TRANSMITTER LINE P/N 3032791 FOUND CHAFED. NEW PART ON ORDER. (TC NR 20070528009)						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007062200122	20070622	00122	NM  	2007	6	22	CA070528010      	1	20070526	G	2530		UNKNOWN         			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					GALLEY	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) A FLIGHT ATTENDANT RECEIVED AN ELECTRIC SHOCK FROM THE WATER DISPENSER IN THE REAR GALLEY.  COFFEE MAKERS REMOVED,	 GALLEY WIRING INSPECTED AND CONTINUITY CHECK CARRIED OUT (L-4355954).  MORE IT TROUBLESHOOTING STEPS HAVE BEEN PROVIDED	 BUT NOT COMPLETED YET.  (TC NR 20070528010)				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2008013100035	20080131	00035	CE  	2008	1	31	CA070528011      	1	20070528	G	5610	PPG10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CO-PILOTS WINDSCREEN CRACKED UNDER PRESSURIZED CONDITION. AIRCRAFT RETURNED TO BASE FOR WINSHEILD REPLACEMENT. UNA	BLE TO INDICATE CORRECT MFG.  (NOT IN LIST)  (TC NR 20070528011)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008031900140	20080319	00140	CE  	2008	3	19	CA070528012      	1	20070524	G	2435	300SGC12902	STARTER GEN     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RIGHT	UNSERVICEABLE   	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA				771  				DC0074			(CAN) RT ENGINE GENERATOR FAILED WHICH ILLUMINATED THE GENERATOR FAIL LIGHT. AC RETURNED TO BASE. (TC NR 20070528012)						2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007080900039	20070809	00039	EU  	2007	8	9	CA070528013      	1	20070522	G	3251	1855A000003	MODULE          			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E6    	30015	NE  					NLG STEERING	MALFUNCTIONED   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			2829 								(CAN) STEERING FAIL MESSAGE ON FINAL APPROACH, FLIGHT DID 2 MISSED APPROACHES FOR GEAR RECYCLING, LANDED ON THIRD CYCLIN	G OF GEAR. FLIGHT HISTORY DATA BASE DOWNLOADED, MFG REP FOUND STEERING CONTROL MODULE AT FAULT. ACFT THR 3643, TCY 1663 	(TC NR 20070528013)				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008031900141	20080319	00141	EU  	2008	3	19	CA070528014      	1	20070527	G	7120	7254120511	MOUNT           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R389	R3894123F25 	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AFT ENGINE MOUNT BRACKET WAS DISCOVERED TO BE CRACKED DURING A SCHEDULED ENGINE CHANGE. THE AFFECTED BRACKET W	AS REPLACED WITH A SERVICEABLE UNIT. NO FURTHER ACTION NOTED. (TC NR 20070528014)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P30NE	 
2007062200123	20070622	00123	WP  	2007	6	22	CA070529001      	2	20070529	G	7250	30606901	TURBINE BLADES  	GARRTT      	TFE73120R1B 	LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RT ENGINE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2232 	2232 		P111221C					(CAN) DURING A DAILY INSPECTION, IT WAS NOTICED BY THE TECHNICIAN THAT A PIECE OF A BLADE FROM THE RT ENGINE TURBINE WAS	 MISSING. NO DIFFICULTIES HAD BEEN REPORTED BY THE FLIGHT CREW AND NO OTHER DAMAGE HAS BEEN NOTED ON THE ENGINE. THE ENG	INE WILL BE REMOVED AND SENT FOR REPAIR TO AN OUTSIDE ENGINE SHOP. (TC NR 20070529001)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008020400157	20080204	00157	EU  	2008	2	4	CA070529002      	1	20070528	G	6220	704A3363320851	SPHERICAL STOP  	SNIAS       	AS350B2     	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					M/R HEAD	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13   			2785					(CAN) ALL SPHERICAL STOPS WHERE REPLACED DURING A 500 HRS INSPECTION. PILOT REPORTED UNCONTROLLED STICK MOVEMENT DURING 	HYDRAULIC OFF TEST. WITH HYDRAULIC ON, NO PROBLEM WAS REPORTED. DURING TROBLESHOOTING THIS PROBLEM IT WAS FOUND THAT ONE	 OF THE SPHERICAL STOP BEARINGS PREVIOUSLY INSTALLED HAD A MFG DESIGN PROBLEM.  THE PRESET ANGLE ATTACH BOLT WHICH ATTAC	H TO THE STARFLEX WAS FOUND NOT IAW SPEC  WHICH INDUCED AN UNCONTROLLED STICK MOUVEMENT DURING HYDRAULIC OFF TEST. THIS 	PART WAS RETURNED TO MFG FOR EXCHANGE UNDER WARRANTY (TC NR 20070529002)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007062200124	20070622	00124	NE  	2007	6	22	CA070529003      	2	20070527	G	8500		ENGINE          			DOUG  	DC4   	C54EDC      	3021528	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  		MAKING METAL    	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ENGINE REMOVED DUE TO METAL IN OIL SCREEN, TBO 750 HOURS.  ENGINE BEING SENT OUT FOR OVERHAUL. (TC NR 20070529003)						2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
2007080900040	20070809	00040	NM  	2007	8	9	CA070529004      	1	20070507	G	3010	29S7D524007	BOOT            			DORNER	DO32  	DO328100    	2996000	NM  										DE-ICE SYSTEM	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			55   								(CAN) PILOTS REPORTED LT HORIZONTAL STAB DE-ICE BOOT APPEARS LOOSE. MAINTENANCE INSPECTED THE BOOT AND FOUND THE DE-ICER	 BOOT HAD COME LOOSE FROM THE AIRCRAFT AT THE AFT EDGES. THE ADHESIVE (3M 1300L) DID NOT SECURE THE DEICER BOOT TO STAB.	  THE DEICER BOOT WAS RECENTLY REPLACED UNDER WORK ORDER 15249. TIME ON PART 54.6 HOURS AND 73 LANDINGS. DEICER BOOT REP	LACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070529004)			2	H	7	2 	4T			RT	A45NM   					 
2007080900041	20070809	00041	CE  	2007	8	9	CA070529005      	1	20070511	G	5531	07310292	SPAR            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4534 								(CAN) DURING AN ANNUAL/100 HOUR INSPECTION FIN AFT SPAR WAS FOUND CRACKED. MFG SINGLE ENGINE CUSTOMER CARE SERVICE INFOR	MTION LETTER SE 80-85 ADDRESSES THIS PROBLEM. SERVICE KIT SK 185-25A INSTALLED THIS DATE. (TC NR 20070529005)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2007062200125	20070622	00125	SO  	2007	6	22	CA070529006      	2	20070507	G	8520	646778	CONNECTING ROD  	CONT        	IO520D      	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	DESTROYED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						174942R					(CAN) DURING FLIGHT, THE ENGINE BEGAN TO RUN ROUGH. THE AIRCRAFT MADE AN UNSHEDULED LANDING FOR INSPECTION. THE CRANKCAS	E WAS FOUND CRACKED AT THE NR 2 CYLINDER.  THE ENGINE WAS REMOVED FROM THE AIRCRAFT. (TC NR 20070529006)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2007080900042	20070809	00042	CE  	2007	8	9	CA070529007      	1	20070529	G	2701	4527102070001	WASHER          			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					CONTROL COLLUMN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2158 								(CAN) DURING A SCHEDULE INSPECTION THE PILOT CONTROL WHEEL WAS FOUND TO HAVE MORE FREE PLAY THAN THE CO-PILOT. UPON FURT	HER INVESTIGATION IT WAS FOUND THAT THE TAB WASHER P/N 4527102070-001 WHICH IS SECURING THE NUT P/N NAS1423-20. HAD ONLY	 ONE TAB BENT, TO ADD TO THE PROBLEM THE TAB WAS IMPROPERLY BENT. AFTER A WHILE THE TAB PERMITTED THE NUT TO BACK OFF ON	E FLAT GIVING THE FREE PLAY TO THE CONTROL WHEEL. IT WAS FOUND IN THE MM, CHAPTER 27-10-01 PAGE 202 SECTION B) 9.   BEND	 THE WASHER TABS TO THE NUT FLATS. ONLY ONE TAB WAS BENT, PERMITTING THE NUT TO BACK OFF, THE CO-PILOT CONTROL WHEEL WAS	 INSPECTED FOR PROPER INSTALLATION AND FOUND TO BE DONE CORRECTLY. THE TAB WASHER WILL BE REPLACED PRIOR TO RETURNING TH	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008022000055	20080220	00055	EU  	2008	2	20	CA070529008      	1	20070528	G	2932	MA12401	PRESSURE SWITCH 			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					HYDRAULIC SYSTEM	DEFECTIVE       	W				D				RETURN TO BLOCK         				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) SWITCH REMAINED OPEN AND WOULD NOT ACTIVATE THE HYDRAULIC PRESSURE WARNING HORN. (TC NR 20070529008)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007080900043	20070809	00043		2007	8	9	CA070530001      	4	20070529	G	3422	25863333	GYRO            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					DIRECTIONAL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE COMPLETION OF AN UNASSOCIATED SB IT WAS NOTICED THAT THE C-12 GYRO HAD FREED ITSELF OF ITS MOUNTING. UN	TIL NOW NO COMPARATOR ANNUNCIATIONS OR COMPASS RELATED SNAGS HAD BEEN REPORTED OR DETECTED. (TC NR 20070530001)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081104			2008	11	4	CA070530002      	4	20070530	G	2562	CIR112	ELT             			BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	CABIN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN TESTING ELT FOR THE REQUIREMENT OF CAR 571 APPENDIX G FOUND G SWITCH WOULD NOT ACTIVATE. (TC NR 20070530002)						1	L	7	2 	3T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007061800166	20070618	00166	EA  	2007	6	18	CA070530003      	2	20070320	G	8520		CRANKSHAFT      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			CA											(CAN) ON THE WAY BACK TO THE AIRPORT THE ENGINE DEVELOPED ABNORMAL VIBRATIONS AND THE PILOT DECIDED TO CLIMB TO 2,400 FT	, THEN THE ENGINE SUDDENLY STOPPED. THE PILOT DECIDED TO FORCE LAND ON THE AUTO ROUTE IN A WESTERLY DIRECTION. AFTER INS	PECTION, IT WAS DETERMINED THAT THERE WAS NO LOSS OF OIL AND THAT THE PROP WAS UNABLE TO TURN. THE ENGINE CRANKSHAFT WAS	 THE CAUSE OF FAILURE. (TC NR 20070530003)			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007062200126	20070622	00126	NE  	2007	6	22	CA070530004      	2	20070528	G	7261	36022375	SEAL            	PWA         	PW121       	AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  					NR 1 ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						PCE120714		PCE120714			(CAN) WHILE CONDUCTING AN ACCEPTANCE CHECK FLIGHT, THE CREW OBSERVED A LOW OIL PRESSURE CONDITION ON THE NR 1 ENGINE. TH	E CREW CONDUCTED A PRECAUTIONARY SHUTDOWN OF THE ENGINE AND RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PR	OBLEM.   MAINTENANCE DETERMINED THE NR 1 STARTER GENERATOR DRIVE SEAL WAS LEAKING. THE SEAL WAS REPLACED AND THE AIRCRAF	T RETURNED TO SERVICE AFTER SATISFACTORY GROUND RUN. (TC NR 20070530004)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007081000094	20070810	00094	CE  	2007	8	10	CA070530005      	1	20070520	G	3010	SMR517515	BOOT            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	DE-ICE SYSTEM	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			252  								(CAN) DE-ICE BOOT, FOUND WORN RUBBER THAT WAS MELTED FROM EXHAUST GASES. MINOR BLISTERING FOUND ON TOP RT OF BOOT. (TC N	R 20070530005)					1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2007062200127	20070622	00127	NM  	2007	6	22	CA070530006      	1	20070530	G	2134		WARNING SYSTEM  			BOEING	727   	727225      	1384077	NM  										CABIN PRESSURE	ACTIVATED       	W				J	A			DUMP FUEL               	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, WHEN AT 13,000 FEET ALT WARNING HORN SOUNDED AND COULD NOT BE SILENCED WITH THE HORN CUTOUT. CREW	 TRIED SWITCHING TO STBY WITH NO RESULTS. HORN CONTINUED ON APPROACH. AT TIME OF INITIAL HORN, CABIN PRESSURE WAS 5000 F	T AND 5PSI DIF. THE AIRCRAFT DUMPED FUEL FOR THE LANDING AND LANDED SUCCESSFULLY AND RETURNED TO THE RAMP. THE MAINTENAN	CE PERSON CARRIED OUT MM SYSTEM TESTS WITH NO FAULTS. AIRCRAFT WAS GROUND PRESSURIZED AND AGAIN NO FAULTS. THE CREW ATTE	MPTED A SECOND DEPARTURE AND HAD THE WARNING COME ON AT 9000 FT. AIRCRAFT RETURNED TO DEPARTURE POINT AND IS AOG WHILE T	ROUBLESHOOTING IS IN PROGRESS. OPERATOR WILL ADVISE SDR REPORTING OF RECTIFICATION WHEN IT IS ESTABLISHED. (TC NR 200705	2	L	7	3 	4F				A3WE    					 
	20081104			2008	11	4	CA070530007      	4	20070530	G	2562	AK450	ELT             			AMTR  	F1156 	F1156C      	5910310	GL  	LYC   	O540  	IO540*      	41532	EA  						MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN TESTING ELT FOR THE REQUIREMENT OF CAR 571 APPENDIX G FOUND LITTLE OR NO AUDIO MODULATION. UNIT WAS TRANSMITT	ING RF CARRIER ONLY. (TC NR 20070530007)					1	H	7	1 	3O	3	O	NC	EXPA1H71	1E4				 
2007062000034	20070620	00034	EA  	2007	6	20	CA070531001      	1	20070527	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA			9395 								(CAN) CREW NOTED THAT LT W/S CRACKED IN CRUISE FLT (40,000FT) AND DIVERTED FOR MTX NO OTHER PROBLEMS NOTED.  C/A REMOVED	 AND REPLACED LT WINDSHIELD IAW MM 56-11-01. REF LGPG 2330059 ITEM 1, 2, AND 3 FOR OK TO INSTALL, FUNCTIONAL CHECK AND O	PS CHECK.  END (TC NR 20070531001)				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007062000035	20070620	00035	NE  	2007	6	20	CA070531002      	2	20070524	G	7200	CF343A1	ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	VIBRATION       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	D	F	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	FLT CONT AFFECTED         	CR	CRUISE         	1			CA			5800 								(CAN) AIRCRAFT (FLT 4344) WAS ENROUTE WHEN CREW EXPERIENCED AN UNCONTROLLABLE VIBRATION FROM THE RT ENGINE. THE ENGINE W	AS SHUTDOWN IN FLIGHT. THE AIRCRAFT WAS DIVERTED AND LANDED AT TRI.   IT WAS REPORTED BY THE CREW (TO MAINT CONTROL) THA	T THE RT THROTTLE WAS BINDING NEAR FLIGHT IDLE BUT THEY WERE ABLE TO PERFORM A SHUTDOWN.  IN ADDITION, IT WAS REPORTED T	HAT PARTS OF THE COWL/NACELLE HAVE DEPARTED THE AIRCRAFT. (TC NR 20070531002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062000036	20070620	00036	NM  	2007	6	20	CA070531003      	1	20070530	G	3411		PITOT SYSTEM    			BOEING	727   	727260      	138408K	NM  	PWA   	JT8   	JT8D17      	52049	NE  					PITOT/STATIC SYS	OBSTRUCTED      	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) THE AIRCRAFT BEGAN THE TAKEOFF ROLL WHEN THE FLIGHT CREW NOTICED A LAG IN THE FIRST OFFICERS AIR SPEED INDICATION.	 THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE WITH NO ADDITIONAL PROBLEMS. UPON INSPECTION OF THE FIRST	 OFFICERS PITOT INSTALLATION AN OBSTRUCTION WAS FOUND (BUG/INSECT) AND WAS REMOVED. THE PITOT STATIC SYSTEM WAS TESTED I	AW THE AIRPLANE MM WITH NO FURTHER FAULTS. THE AIRCRAFT WAS RETURNED TO SERVICE.  (TC NR 20070531003)			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007062200128	20070622	00128	EU  	2007	6	22	CA070531004      	1	20070530	G	2120		UNKNOWN         			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211*      	54555	NE  					CABIN	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, A PAPER BURNING SMELL AT SEAT 26DE WAS REPORTED TO THE CABIN CREW. THE AUDIO SYSTEM WAS SHUTOFF IAW	 PRECAUTION AND SMELL DISAPPEARED AFTER 20 MINUTES. THE AUDIO SYSTEM WAS TESTED ON ARRIVAL AND THE AREA INSPECTED FOR BU	RNING MARKS. AUDIO SYSTEM AND AREA WAS FOUND NORMAL WITH NO DEFECT. AIRCRAFT WAS RETURN TO SERVICE WITH NO REPEAT.   (TC	 NR 20070531004)			2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
2007062200129	20070622	00129	NE  	2007	6	22	CA070531005      	2	20070425	G	7313	3186100	VALVE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			CA											(CAN) ASSEMBLY IS ON CONDITION.  AFTER CARRYING OUT A 100 HR AND 300 HR INSPECTION A FUNCTIONAL CHECK WITH THE INJECTOR 	ELECTRO VALVE (IEV) WAS ACCOMPLISHED. FOLLOWING A RUN-UP TO 100 PERCENT, THE ENGINE RPM WAS REDUCED AND STABILIZED AT JU	ST OVER FLIGHT IDLE FOR 30 SECONDS IAW COOL DOWN REQUIREMENTS. DEPRESSION OF THE STARTER BUTTON AT THIS POINT SHOULD NOT	 HAVE CAUSED ANY PROBLEM BUT IN THIS FUNCTIONAL CHECK A FLAME OUT OCCURRED. FOLLOWING THE FLAME OUT A BENCH TEST WAS CAR	RIED OUT AND IT WAS DETERMINED THAT IT`S OPERATION AT A PRE DETERMINED P2 PRESSURE WAS INTERMITTENT. SENT UNIT TO MFG FO	R REPAIR OR OVERHAUL AND THE UNIT WAS SCRAPPED. (TC NR 20070531005)	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022000319	20080220	00319	WP  	2008	2	20	CA070531006      	1	20070529	G	6310	C0183	CLUTCH          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TRANSMISSION	SEIZED          	W				D				RETURN TO BLOCK         				O			OTHER                     			AP	APPROACH       	1			CA			948  	948  							(CAN) LOUD BANG DURING POWER CHANGE ON APPROACH.  INSPECTED AC AND FOUND CLUTCH ASSY ROUGH.  TURNED IT A FEW TIMES BY HA	ND AND SEIZED. NEW CLUTCH ASSY INSTALLED, DEFECT RECTIFIED. CLUTCH BEING SENT TO OUR IN HOUSE COMPONENT SHOP FOR INVESTI	GATION.  WILL FWD THE PICTURES AND INFORMATION WHEN RECEIVED FROM THE COMPONENT SHOP. PICTURES ATTACHED AND CLUTCH ASSY 	BEING SENT TO MFG FOR WARRANTY AND INVESTIGATION. (TC NR 20070531006)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007062200130	20070622	00130	NE  	2007	6	22	CA070531007      	2	20070425	G	7313	3186100	VALVE           			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	60048	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			CA											(CAN) ASSEMBLY ON CONDITION. THIS UNIT WAS REMOVED SERVICEABLE FOR ANOTHER AIRCRAFT. A FUNCTIONAL CHECK WAS CARRIED OUT.	 FOLLOWING A RUN UP TO 100 PERCENT THE ENGINE RPM WAS REDUCED AND STABILIZED AT JUST OVER FLIGHT IDLE FOR 30 SECONDS IAW	 COOL DOWN REQUIREMENTS.  DEPRESSION OF THE STARTER BUTTON AT THIS POINT SHOULD NOT HAVE CAUSED ANY PROBLEM BUT IN THIS 	FUNCTIONAL CHECK A FLAME OUT OCCURED. A BENCH WAS CARRIED OUT WITH CONSISTENT FAILURES OCCURRED AT PRESCRIBED P2 PRESSUR	E. (TC NR 20070531007)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007062200131	20070622	00131	SO  	2007	6	22	CA070601001      	1	20070528	G	5330		SKIN            			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PRE-FLIGHT CHECK PRIOR TO DEPARTING, CRACKING WAS OBSERVED IN THE AFT FUSELAGE SKIN IN THE AREA OF STATION 	946. THE AIRCRAFT HAS BEEN FERRIED FOR REPAIR. (TC NR 20070601001)					2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007071100287	20070711	00287	EA  	2007	7	11	CA070601002      	1	20070531	G	2420	820465	ADG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						DEPLOYED        	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			6118 	6118 							(CAN) ADG DEPLOYED AS THE LANDING GEAR WAS SELECTED UP.  THE FLIGHT RETURNED WITHOUT INCIDENT.  MAINTENANCE TROUBLESHOOT	ING WAS CARRIED OUT AND THE ADG AUTO DEPLOY CONTROLLER WAS REPLACED AND TESTED SERVICEABLE. THE ADG WAS INSPECTED VISUAL	LY IAW MFG AND IS TO HAVE FLUORESCENT PENETRANT CARRIED OUT WITHIN 3 CALENDAR DAYS.  (TC NR 20070601002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000320	20080220	00320	SW  	2008	2	20	CA070601003      	1	20070528	G	2810	2060636321	FUEL CELL       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  						LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) FUEL SMELL NOTED. INSPECTION FOUND SMALL FUEL LEAK. FUEL CELL REMOVED SENT OUT FOR REPAIR, REINSTALLED. (TC NR 200	70601003)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007071100286	20070711	00286	EA  	2007	7	11	CA070601004      	1	20070529	G	2797		WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	BURNED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) FLAP FAIL MESSAGE COME ON DURING CRUISE AT ALT FL330 WITH NO FLAP SELECTION MADE.  AIRCRAFT RETURN TO  ORIGINATING	 STATION, MAINTENANCE REPLACED THE BPSU AND FECU BUT NO FIX. FURTHER INVESTIGATION REVEALED SOME BURNED WIRES AT LT BPSU	 CONNECTOR.  TEMPORARY REPAIRS CARRIED OUT AND AIRCRAFT FERRIED.  AIRCRAFT IS NOW UNDERGOING A HEAVY CHECK AND THE SNAG 	IS STILL BEING WORKED ON.  MORE SPECIFICS OF THE DEFECT RECTIFICATION TO FOLLOW. (TC NR 20070601004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007062200132	20070622	00132	SW  	2007	6	22	CA070604001      	1	20070603	G	6320	23063393	GEARBOX         	ALLSN       	250C47B     	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	SEIZED          	W				R				AUTOROTATION            				J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CA			6077 			CAE847124		CAE847124			(CAN) ENGINE CHIP ILLUMINATED, APPROX 3-4 SECONDS LATER ENGINE FAILED. (TC NR 20070604001)						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2007071100284	20070711	00284	GL  	2007	7	11	CA070604002      	2	20070518	G	7320		FADEC           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  						MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A FLIGHT ON MAY 18 AT 6755.9 TAT, THE PILOT EXPERIENCED A CONTROLLED ENGINE OVERSPEED CONDITION.  THE PILOT	 WAS NOT GIVEN AT INDICATION IAW MFG FM CRITERIA.  LATER THE PILOT REPORTED THE CONDITION TO THE AME. THE AME DOWN LOADE	D THE FADEC INFORMATION AND THE FOLLOWING WERE NOTED.  38060 NP AND 53.3 PERCENT Q.  WHICH IS ACTUALLY 80 RPM BELOW THE 	POINT WHERE THE PILOT WOULD GET A LIGHT BUT OVER THE LIMITS IN MM 72-00-00 AND 77-50-00.  THE AIRCRAFT WAS REMOVED FROM 	SERVICE AND RETURNED TO THE MAIN MAINTENANCE BASE UNDER A TC FLIGHT PERMIT.  THE ENGINE HAS BEEN REMOVED AND SENT TO MFG	 FOR INSPECTION. (TC NR 20070604002)	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2008022000321	20080220	00321	WP  	2008	2	20	CA070604003      	1	20070526	G	2435	32991	LINK            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER GEN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100HR INSPECTION FOUND CRACKED STARTER GENERATOR LINK. (TC NR 20070604003)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007071100282	20070711	00282	NE  	2007	7	11	CA070605001      	2	20070603	G	7321		FCU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2 ENGINE	INOPERATIVE     	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB AFTER DEPARTURE, THE CREW OBSERVED A SLOW DECREASE IN TORQUE ON THE NR 2 ENGINE AND WITH REDUCED FUEL	 FLOW.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM.   MAINTENANCE REPLACED THE NR 2 	FUEL CONTROL UNIT (FCU) AND RETURNED THE AIRCRAFT TO SERVICE AFTER SATISFACTORY GROUND RUN. (TC NR 20070605001)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007071100281	20070711	00281	NE  	2007	7	11	CA070605002      	2	20070512	G	7320	3035381A	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HMU-P3	CRACKED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) THE NR 2 ENGINE WAS SNAGGED AS NOT PRODUCING FULL POWER ON TAKEOFF AND IN FLIGHT. MAINTENANCE FOUND THAT THE P3 SE	NSE LINE WAS CRACKED AT THE HYDRO MECHANICAL UNIT.  UPON REMOVAL, THE LINE BROKE. THE SENSE LINE WAS REPLACED AND THE AI	RCRAFT RETURNED TO SERVICE. (TC NR 20070605002)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007071200127	20070712	00127	EA  	2007	7	12	CA070605003      	2	20070601	G	8520	LW15328	MAIN BEARING    	LYC         	O360E1A6D   	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3690 		RL38277T					(CAN) MAIN BEARING FAILED DUE TO EXCESSIVE TSO. CRANKCASE DAMAGED BEYOND REPAIR. VERY CLOSE TO HAVING A COMPLETE ENGINE 	FAILURE. (TC NR 20070605003)					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
	20081229		CE  	2008	12	29	CA070605004      	1	20070605	G	2730	05341221	BELLCRANK       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ELEVATOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8805 								(CAN) ELEVATOR UP TRAVEL FOUND TOO LOW. INVESTIGATION REVEALED UP CABLE ATTACH BOLT INSTALLED WRONG WAY. THIS RESULTED I	N CONTACT WITH VERT STAB ATTACH BRACKET (WHERE CABLE PASSES THROUGH LIGHTENING HOLE)THUS LIMITING TRAVEL BY APPROX 3 DEG	 LESS THAN REQUIREMENT. BOLT INSTALLED PROPERLY AND SYSTEM RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007081000095	20070810	00095	SO  	2007	8	10	CA070605005      	1	20070605	G	5340	4178902	ATTACH BOLT     			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG ACTUATOR	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			202  								(CAN) CONTINUOUS PROBLEM OF PREMATURE WEAR AND INDICATIONS OF STRESS ON MAIN LANDING GEAR ACTUATOR ATTACH HARDWARE.  LOW	ER FORK BOLT PN 41789-02 AND UPPER ACTUATOR ATTACH BOLT 401-195 (AN5-17A) (BOTH LIFE LIMITED BY MFG INSPECTION PROGRAM) 	SHOW SIGNS OF BENDING AND/OR WEAR VIRTUALLY EACH DETAILED GEAR INSPECTION (TYPICALLY 200 AIRCRAFT HOURS). THESE PARTS AR	E REMOVED AND CLOSELY INSPECTED EACH GEAR INSPECTION AND TYPICALLY REPLACED AT FAR LOWER INTERVALS THAN THE PUBLISHED LI	FE LIMITS. (TC NR 20070605005)		1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2007081000096	20070810	00096	SW  	2007	8	10	CA070606002      	1	20070602	G	2910	2781032261	LINE            			SWRNGN	SA227 	SA227AC     	8780603	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 LEAK IN RT WHEEL WELL.  FOUND LINE CHAFED, LINE REPLACED AND AIRCRAFT RETURNED TO SERVICE AFTER SUCCESSFUL GEA	R SWINGS CARRIED OUT. (TC NR 20070606002)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2007071200128	20070712	00128	WP  	2007	7	12	CA070606003      	2	20070605	G	7250		TURBINE BLADES  	GARRTT      	TPE33112UHR 	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			5510 	5510 		P70224					(CAN) THE AIRCRAFT WAS ON A SHORT REPOSITIONING FLIGHT.  AFTER AN UNEVENTFUL TAKEOFF AND CLIMB, THE CREW LEVELED AT 9,00	0 FT AND REDUCED POWER TO 30 PERCENT.  FIVE MINUTES LATER, THE RT ENGINE HAD A VIOLENT AND SUDDEN VIBRATION.  THE CREW S	HUTDOWN THE ENGINE IMMEDIATELY AND DECLARED AN EMERGENCY.  THE AIRCRAFT MADE AN UNEVENTFUL LANDING. MAINTENANCE INSPECTE	D THE ENGINE AND FOUND THAT THE NR 3 TURBINE WHEEL HAD (4) BLADES MISSING LARGE SECTIONS. THE OIL FEED LINE WAS SEVERED 	AND IMPACT DAMAGE WAS FOUND ON THE EXHAUST CONE AND TAIL PIPE. THE LAST MAJOR INSPECTION ON THIS ENGINE WAS A HSI/GBI AT	 3499.2 HOURS.   (TC NR 20070606003)	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081104		EA  	2008	11	4	CA070606004      	1	20070605	G	3233	HF6G	ROD END         			DHAV  	DHC3  	DHC3        	2800202	EA  	WALTER	M601  	M601E11     	 	EU  					ACTUATOR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) PILOT COULD NOT GET GEAR DOWN INDICATION, BUT COULD GET GEAR UP AND LOCKED INDICATION. WATER LANDING CARRIED OUT. 	MAINT FOUND LT NOSE GEAR WOULD NOT EXTEND. ROD END FOUND BROKEN ON NOSE GEAR ACTUATOR, REPLACED AND ACFT RETURNED TO SER	VICE. (TC NR 20070606004)				1	H	7	1 	3R	3	T		A815    	E00048EN				 
2007071200129	20070712	00129	EA  	2007	7	12	CA070606006      	2	20070601	G	8530	LW12966	CYLINDER        	LYC         	TIO540A2C   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1636 								(CAN) LT ENGINE,  NR 5 CYLINDER WAS FOUND TO HAVE LOW COMPRESSION DURING THE INSPECTION PROCESS.  EXCESSIVE AIR WAS PASS	ING THE RINGS. CYLINDER WAS FOUND TO BE GLAZED. CYLINDER WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. WILL UPDATE WITH	 CYLINDER HOURS. (TC NR 20070606006)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007081000097	20070810	00097	CE  	2007	8	10	CA070607001      	1	20070530	G	3230		BEARING         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					UPLOCK ROLLER	WORN            	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			7559 	40   							(CAN) AC WAS UNABLE TO LOWER THE RT MAIN LANDING GEAR. THE EMERGENCY EXTENSION PROCEDURE DID NOT INITIALLY RELEASE THE L	ANDING GEAR UPLOCK. SUBSEQUENT MANIPULATION OF THE SYSTEM RELEASED THE GEAR TO A DOWN AND LOCKED CONDITION AND THE AIRCR	AFT MADE A SAFE LANDING. MAINTENANCE INVESTIGATION REVEALED (2) CONDITIONS WHICH CONTRIBUTED TO THIS SITUATION. IT WAS N	OTED DURING INSPECTION OF THE SYSTEM THAT THE EMERGENCY EXTENSION CABLE WAS CONTACTING THE BRAKE ASSY IN SUCH A WAY THAT	 THE CABLE WAS BEING DEFLECTED APPROXIMATELY .2500 INCH AND COULD PREMATURELY PULL THE HOOK OFF THE ROLLER.  THE CONCERN	 IS THAT THE CABLE MAY FRAY AND BREAK PREVENTING MANUAL EXTENSION OF THE GEAR. THIS WAS NOT A FACTOR IN THIS CASE.   INV	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008031900142	20080319	00142	CE  	2008	3	19	CA070607002      	1	20070606	G	2410	359553S8	RETAINING NUT   	MOTORCRAFT  		CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ALTERNATOR SHAFT	MISSING         	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA				1    		97043226					(CAN) PILOT HAD CALLED AND REPORTED THAT THE ALTERNATOR THAT WE HAD REPLACED THE NIGHT BEFORE HAD GONE OFFLINE .7 HRS AN	D A SLIGHT ODOR OF BURNING RUBBER NOTED INTO HIS FIRST LEG OF FLIGHT. UPON LANDING INVESTIGATION HAD REVEALED THAT THE A	LTERNATOR SHAFT FAN RETAINING NUT HAD COME LOOSE AND EXITED THE AC.  FAN HAD ROTATED ON SHAFT AND DRIVE BELT HAD COME OF	F. NO DAMAGE TO ANYTHING IN ENG COMPARTMENT EXCEPT TO ALTERNATOR COMPONENTS. THIS ALTERNATOR HAD BEEN REPAIRED AND TESTE	D BY A COMPANY, WHICH I WILL NOT NAME THAT THIS HAS HAPPENED BEFORE. THE FAN HAD ALSO COME OFF THE SHAFT, POSSIBLY DUE T	O INSUFFICENT TORQUE ON RETAINING NUT OR SELF LOCKING ABILITY OF NUT WAS NOT SUFFICENT. SERVICEABLE ALTERNATOR INSTALLED	1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2007071100155	20070711	00155	EA  	2007	7	11	CA070607003      	2	20070511	G	8530	05K21108	CYLINDER        			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			1279 					L896061A			(CAN) DURING A VISUAL INSPECTION OF THE ENGINE, A CRACK WAS FOUND UNDERNEATH THE PUSHROD TUBE.  THE CRACK WAS RUNNING FR	OM THE BASE OF THE CYLINDER HEAD ALONG THE BOTTOM OF THE COOLING FINS TOWARDS THE HEAD. THE CRACK IS SIMILAR TO THAT FRO	M SDR 20070423005. (TC NR 20070607003)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007071100156	20070711	00156	EA  	2007	7	11	CA070607004      	2	20070515	G	8530	05K21108	CYLINDER        			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			1744 					RL145668A			(CAN) WHILE INSPECTING THE ENGINE, A CRACK WAS FOUND IN THE PUSHROD TUBE AREA OF THE NR 2 CYLINDER.  IT WAS AT THE BASE 	OF THE COOLING FINS AND RAN FROM THE BOTTOM OF THE CYLINDER HEAD TOWARDS THE TOP OF THE CYLINDER.  THE CRACK STARTS WHER	E THE CYLINDER HEAD IS ATTACHED TO THE BARREL.  THIS IS SIMILAR TO THE EVENTS IN SDR`S 20070607003 AND 20070423005.   (T	C NR 20070607004)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007071100158	20070711	00158	GL  	2007	7	11	CA070607005      	1	20070528	G	8011	AN33711	RELAY           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985*       	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	STARTER	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) JUST AFTER TAKEOFF, PILOT NOTICED FAINT SMOKE ODOR BUT UNSURE OF SOURCE, CONTINUED.  DURING CLIMB WHITE SMOKE CAME	 IN AROUND RUDDER PEDALS SO PILOT SHUTDOWN ELECTRICS AND PROCEEDED TO LAND AIRCRAFT.  AFTER LANDING PILOT NOTICED SMOKE 	COMING FROM THE ACCESSORY SECTION BUT IT DIMINISHED RAPIDLY AND THERE WERE NO SIGNS OF FIRE. UPON FURTHER INSPECTION BY 	MAINTENANCE STAFF, THE STARTER (PN 756-21C) SHOWED SIGNS OF OVERHEATING AND WAS REPLACED.  THE STARTER RELAY (PN AN3371-	1) WAS ALSO REPLACED.  UPON EVALUATION OF THE RELAY THE FOLLOWING WAS NOTED: CLOSE AT 5 VDC OPEN AT 0 VDC TESTED COIL RE	SISTANCE 9.1 OHMS OILY UNDER COVER, SCREWS AND GASKETS CONTACT A1 SHOWS SIGNS OF RECENT STICKING CONTACT SHOWS ARCING AR	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2007081000098	20070810	00098	CE  	2007	8	10	CA070607006      	1	20070606	G	5100	AE366372460330	HOSE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	UNKNOWN	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			1    	1    							(CAN) HOSE PN-AE366372460330 REPLACED DUE TO SHEDULED MAINTENANCE AND LEAK CHECKED SERVICEABLE, AFTER 1.4 HRS AND 4 CYCL	ES FOUND LEAKING DURING GROUND HANDLING. HOSE REPLACED AND LEAK CHECKED SERVICEABLE (TC NR 20070607006)					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2007081000099	20070810	00099	CE  	2007	8	10	CA070607008      	1	20070607	G	3230	MS2124010C40	UPLOCK ROLLER   			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CAMPAIGN NOTICE 851-32-40-040 AND 851-32-40-040R1 CARRIED OUT. ACTION WAS REQUIRED TO THE RT MAIN GEAR BEARING P/N	 MS21240-10C40. THE INSIDE BEARING MATERIAL WHEN INSPECTED WAS FOUND TO HAVE PIECES MISSING AND FURTHER INSPECTION REVEA	LED THE REMAINDER OF THE LINER WAS EASY TO REMOVE BY HAND. THERE WAS NO DAMAGE FOUND ON THE INNER SLEEVE OR ON THE BOLT.	 PRIOR TO DISASSEMBLY THE ROLLERS WERE INSPECTED IN SITU AND FOUND TO TURN WITH VERY LITTLE EFFORT REQUIRED. NEW BEARING	 WAS INSTALLED (TC NR 20070607008)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007071100159	20070711	00159	NE  	2007	7	11	CA070607009      	3	20070604	G	6111	E10950PK	BLADE           	HARTZL      		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8796 			HJ448					(CAN) DURING ROUTINE MAINTENANCE, THE LT PROPELLER BLADE NR 1 WAS FOUND CRACKED. THE CRACK RAN CHORD WISE APPROXIMATELY 	2.3750 INCH FROM THE BLADE ROOT WITH A LENGTH OF APPROXIMATELY 1 INCH. THE PROPELLER HAS BEEN REPLACED AND WILL BE SENT 	FOR REPAIR AS WELL AS A STRIP REPORT. (TC NR20070607009)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007071100161	20070711	00161	NM  	2007	7	11	CA070607010      	1	20070607	G	2910	012152130010	LINE            			BOEING	777   	777*        	UTILUSE	NM  										HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ON TRAINING FLIGHT RT HYDRAULIC QUANTITY REDUCED. HYDRAULIC LEAK FOUND IN RIGHT ENGINE PYLON AREA. HYDRAULIC SUPPL	Y PIPE FOUND LEAKING AT FLEXIBLE AREA, THIS FLEXIBLE AREA IS COVERED BY A RUBBER SHEATH.  PEN INDICATES AREA FLUID WAS L	EAKING FROM (TC NR 20070607010)				2	L	7	2 	4F			RT	T00001SE					 
2007081000100	20070810	00100	EA  	2007	8	10	CA070607011      	1	20070606	G	2750	601R930507	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) (FLAPS FAIL) MESSAGE DISPLAYED ON APPROACH.  FLAPS FAILED WHEN SELECTING FROM FLAP 20 DEGREES TO FLAPS 30 DEGREES.	  FLAPS REMAINED AT 20 DEGREES AT A SPEED OF 170 KIAS.  MAINTENANCE REPLACED FECU (FLAPS ELECTRONIC CONTROL UNIT) DUE TO	 UNABLE TO TEST AND THE LT BPSU (BRAKE POWER SENSOR UNIT) P/N 8550100-9, S/N 372. AIRFRAME HOURS: 24818:12 CYCLES: 20440	. (TC NR 20070607011)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007081000101	20070810	00101	CE  	2007	8	10	CA070607012      	1	20070517	G	2730	4527301000U1	DISCONNECT UNIT 			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2400 	2400 							(CAN) WHEN AIRCRAFT WAS DOWN FOR A 2400 HR INSPECTION, IT WAS DISCOVERED THAT THERE WAS PLAY BETWEEN THE LT AND RT ELEVA	TOR (INSPECTION IRN D2730007).  AN ELEVATOR FREE-PLAY CHECK WAS C/W AND ELEVATORS WERE FOUND TO BE OUT OF LIMITS.  ELEVA	TOR CONTROL SYSTEM T/S AND FREE PLAY FOUND IN THE AFT ELEVATOR DISCONNECT.  PART REPLACED, FREE-PLAY RE-CHECKED AND FOUN	D TO BE WITHIN LIMITS. (TC NR 20070607012)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008030600044	20080306	00044	CE  	2008	3	6	CA070608001      	1	20070606	G	5510	115620010101	STRUCTURE       			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11730								(CAN) CRACK FOUND IN STRUCTURE OF HORIZONTAL STAB. CRACK LOCATED AT TRAILING EDGE UPPER SURFACE AT CENTER OF HORIZONTAL 	STAB. CRACK LENGTH 0.600, CRACK REPAIRED IAW REPAIR DWG SUPPLIED BY MFG AND AIRCRAFT RETURNED TO SERVICE. (TC NR 2007060	8001)				1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007081000102	20070810	00102	CE  	2007	8	10	CA070608002      	1	20070524	G	2720	4555401134011	TORQUE TUBE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2400 	2400 							(CAN) DURING 2400 HR INSPECTION, SB 45-27-24/ DVI IAW 5-19-00-N2720030, CORROSION WAS FOUND INSIDE OF RUDDER TORQUE TUBE	.  TORQUE TUBE WAS TO BE REPLACED IAW SB45-27-25.  WHEN TORQUE TUBE KIT ARRIVED, IT WAS DISCOVERED THAT THE REPLACEMENT 	TORQUE TUBE WAS MANUFACTURED INCORRECTLY.  A SECOND KIT WAS ORDERED AND IT TOO WAS INCORRECT.  ORIGINAL TORQUE TUBE CORR	OSION CLEANED AND REINSTALLED. (TC NR 20070608002)			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007081000103	20070810	00103	CE  	2007	8	10	CA070608003      	1	20070524	G	5741		ATTACH FITTING  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					WING TO BODY	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2400 	2400 							(CAN) DURING 2400 HR INSPECTION, IT WAS DISCOVERED THAT A NR OF THE WING TO FUSELAGE LINKS HAD WORN PAINT OFF THE ATTACH	 FITTINGS.  ALL AFFECTED FITTINGS AND LINKS INSPECTED.  NO DAMAGE FOUND.  MFG ADVISED OF FINDINGS.  MFG FOLLOWED UP WITH	 A LETTER OF APPROVAL TO INSTALL PHENOLIC SPACERS BETWEEN ALL LINKS AND FITTINGS. (TC NR 20070608003)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007071100163	20070711	00163	CE  	2007	7	11	CA070608004      	1	20070524	G	6100		UNKNOWN         	MCAULY      	1A103       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8656 	2793 		SR774449					(CAN) PROPELLER RECEIVED FOR INSPECTION IAW AD 2003-12-05. INSPECTION FOUND CRACK INDICATIONS IN PREVIOUSLY REPAIRED ARE	AS.  PROPELLER HAS BEEN REMOVED FROM SERVICE IAW THIS AD AND ASB 221C. (TC NR 20070608004)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081104			2008	11	4	CA070608005      	4	20070608	G	2562	E01	ELT             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  		INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHEN TESTING ELT FOR THE REQUIREMENT OF CAR 571 APPENDIX G FOUND G SWITCH INOPERATIVE. UNIT BEING RETURNED TO MFG 	FOR REPAIR. (TC NR 20070608005)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007081000104	20070810	00104	EU  	2007	8	10	CA070608006      	1	20070606	G	6220	350A31190700	STARFLEX        	SNIAS       		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					MAIN ROTOR HEAD	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2139 			M1199					(CAN) WHILE WAITING FOR HIS CREW TO RETURN, THE PILOT NOTICED SOME BLACK SOOT AROUND ONE OF THE STARFLEX ARMS. FURTHER E	XAMINATION REVEALED THAT THE STAINLESS STEEL BUSHING BONDED ON THE END OF THE STARFLEX ARM HAD COME LOOSE AND WAS FLOATI	NG INSIDE THE SPHERICAL BEARING IN THE FREQUENCY ADAPTER. THE BUSHING WAS IN GOOD CONDITION THAT MORNING BEFORE THE FLIG	HT AND NO UNUSUAL NOISES OR VIBRATIONS WERE DETECTED PRIOR TO DISCOVERING THE DAMAGED STARFLEX. THE PILOT AND CREW HAD T	O BE FLOWN OUT OF THE BUSH WITH ANOTHER HELICOPTER. A NEW STARFLEX WAS INSTALLED ON SITE THE NEXT DAY WITH NO FURTHER IS	SUES. (TC NR 20070608006)	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007071100167	20070711	00167	NM  	2007	7	11	CA070608007      	1	20070604	G	2900	10607102	BYPASS VALVE    			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON ARRIVAL, THE IB FLAPS FAILED TO EXTEND WHEN LANDING, CONFIGURATION SELECTED. THE CREW ELECTED TO DIVERT. THE AI	RCRAFT COMPLETED A NORMAL LANDING. MAINTENANCE WAS UNABLE TO DUPLICATE THE PROBLEM AND INSPECTED THE SYSTEM FOR LEAKS AN	D ANOMALIES. THE FLAP POSITION INDICATOR WAS REPLACED AS PRECAUTION AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE AIRCRA	FT SUBSEQUENTLY REPOSITIONED WITHOUT FURTHER PROBLEM. HOWEVER DURING DEPARTURE THE CREW OBSERVED LOW HYDRAULIC QUANTITY 	ON THE A SYSTEM AFTER SELECTING GEAR AND FLAPS UP. THE AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE	 REPLACED A FAILED IB FLAP BYPASS VALVE.  BOTH A SYSTEM PUMPS AND THE RESPECTIVE CASE DRAIN FILTERS WERE REPLACED NO CON	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007071100169	20070711	00169	EU  	2007	7	11	CA070608008      	1	20070606	G	2730		CONTROL CABLE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAYMK65015  	 	EU  					ELEVATOR	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN)  FLIGHT CREW REPORTED DURING HEAD START CHECKS THAT THE FLIGHT CONTROL LOCK WOULD NOT LOCK THE ELEVATOR CONTROLS A	ND WAS VERY STIFF WHEN MOVING CONTROL LOCK TO FREE POSITION.  RECERTIFICATION, FOUND THE FLIGHT CONTROL LOCK CABLE FCL1 	SNAPPED AT AILERON FLIGHT CONTROL LOCK PULLEY.  CABLE REPLACED AND ADJUSTMENT COMPLETED.  OPERATIONAL TEST OF FLIGHT CON	TROL LOCK SYSTEM COMPLETED.  FOLLOW UP ACTION THE CABLE BROKE AT AN IDLER PULLEY AND APPEARED TO HAVE BEEN POSSIBLE FRAY	ED. ENTIRE ELEVATOR CONTROL LOCK CABLE RUN INSPECTED AND FOUND SERVICEABLE.  IN FOLLOW UP A SPECIAL INSPECTION WILL BE I	SSUED FOR AIRCRAFT TO INSPECT THE SAME AREA. (TC NR 20070608008)	2	L	7	2 	4F	4	F	RT	        	 				 
2007071100170	20070711	00170	NE  	2007	7	11	CA070608009      	2	20070607	G	7310	D22AA1022	VALVE           			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUEL RETURN	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA			30078	11851				731901			(CAN) DUE TO A LT ENGINE STALL MESSAGE ON ECAM, THE FLIGHT CREW SHUTDOWN THE NR 1 ENGINE AS A PRECAUTION.   MAINTENANCE 	FOUND FUEL RETURN VALVE AT FAULT DURING AN ENGINE MOTORING TEST, UNIT REPLACED IAW AMM 73-11-50. (TC NR 20070608009)					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
	20081104			2008	11	4	CA070608010      	1	20070608	G	6320	RG36343	SHAFT           																	GEARBOX PUMP	DAMAGED         	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			1556 								(CAN) S 76 MAIN GEARBOX REMOVED FOR GENERATING METAL. TSN 1556.5  THE METAL HAS BEEN SENT OUT FOR ANALYSIS TO ENSURE THA	T IT IS THE TYPE CONSISTANT WITH THE DAMAGED PARTS. WE WILL ATTACH THE REPORT WHEN RECEIVED. (TC NR 20070608010)																		 
2007081000105	20070810	00105	EU  	2007	8	10	CA070611001      	1	20070608	G	2822	9638411403	PUMP            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				697  							(CAN) WHILE PERFORMING A DEFUEL OF AIRCRAFT TO PERFORM SCHEDULED MAINTENANCE, RT WING FUEL BOOST PUMP POPPED CIRCUIT BRE	AKER AFTER 3 MINUTES OF OPERATION DEFUELING AIRCRAFT.  PUMP WAS ALLOWED TO SIT FOR 10 MINUTES AND C/B RESET AND PUMP WOU	LD AGAIN WORK FOR 3 MINUTES. THIS HAPPENED 3 TIMES UNTIL DEFUEL WAS COMPLETE.  PUMP WAS REPLACED WITH O/H UNIT.  TESTED 	SATISFACTORY (TC NR 20070611001)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007071100174	20070711	00174	NM  	2007	7	11	CA070611002      	1	20070610	G	3244	DR0231T	TIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 4	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) DURING A NORMAL AND SMOOTH TAKEOFF ROLL, CREW NOTICE A VIBRATION (120KNTS,V1=134KNTS).  AT VR ROTATED INTO SMOOTH 	CLIMB AND REQUESTED GEAR UP WITH POSITIVE CLIMB.  SHORTLY AFTERWARDS CABIN CREW CALLED TO SAY PASSENGERS REPORTED A WHEE	L CAME OFF DURING TAKEOFF.  AIRCRAFT COMPLETED AN UNEVENTFUL LANDING.  NR 4 MAINWHEEL TIRE WAS FOUND SHREDDED WITH MAINW	HEEL ASSY STILL IN PLACE. (TC NR 20070611002)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007081000106	20070810	00106	EU  	2007	8	10	CA070612001      	1	20070529	G	3233		SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	MLG ACTUATOR	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA						0623E					(CAN) CREW REPORTED THE LT MAIN LANDING GEAR DOWN AND LOCK INDICATION WAS SHOWING (IN TRANSIT) WHEN SELECTED DOWN.  THE 	SYSTEM WAS TROUBLESHOT TO THE DOWNLOCK INDICATOR SWITCH IN THE GEAR ACTUATOR.  ACTUATOR REPLACED AND AIRCRAFT RETURNED T	O SERVICE.  (TC NR 20070612001)				1	L	7	1 	3T	4	T	RT	A78EU   	E4WE	6	C	P61GL	 
2007071100175	20070711	00175	NM  	2007	7	11	CA070612002      	1	20070611	G	3232	82970014009	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG DOOR	BYPASSING       	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			44480	44480							(CAN) ON LANDING, GEAR DOWN SELECTION HEARD LOUD CLUNK, AND RT MAIN GEAR UNSAFE WARNING. CYCLED GEAR WITH SAME RESULT.  	ALTERNATE GEAR EXTENSION ACTIVATED, ALL GEAR INDICATED DOWN, NORMAL LANDING.  MAINTENANCE INSPECTION FOUND RT AFT GEAR D	OOR ACTUATOR SLOW TO OPEN DOORS DUE TO INTERNAL PRESSURE BYPASSING.  RT AFT GEAR DOOR ACTUATOR REPLACED, LEAK AND FUNCTI	ON CHECKS COMPLETED.  AIRCRAFT RETURNED TO SERVICE. (TC NR 20070612002)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007071100176	20070711	00176	NM  	2007	7	11	CA070612003      	1	20070601	G	2421		BRUSHES         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					ALTERNATOR	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			215  								(CAN) ON BACK OF ALTERNATOR, POWER-OUT STUD FOUND LOOSE AND NYLON BUSHING FOUND MELTED. WIRE TERMINAL WAS FOUND MELTED A	ND BROKEN.  PROBLEM HAS SINCE BEEN DETECTED ON TWO OTHER AIRCRAFT. (TC NR 20070612003)					1	G	7	1 	3O	3	O		H10WE   	E286				 
2007081000107	20070810	00107	SW  	2007	8	10	CA070612004      	1	20070612	G	6310	269A5512	DRIVE BELT      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAIN ROTOR	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			59   								(CAN) DRIVE BELT AXIAL SPLIT OVER 50 PERCENT OF BELT CIRCUMFERENCE; SPLIT OCCURS UNDER OUTER LAYER OF BELT.   NOTE:  PLE	ASE ADVISE IF PHYSICAL VERIFICATION IS REQUIRED AS MUST RETURN BELTS TO MFR FOR WARRANTY CONSIDERATION. (TC NR 200706120	04)				1	G	7	1 	3O	3	O	O	4H12    	E286				 
2007071200130	20070712	00130	GL  	2007	7	12	CA070612005      	2	20070610	G	7250	23034787	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			534  	534  							(CAN) FOUND METAL ON BOTH CHIP PLUGS AND THEN FOUND THAT THE 2.5 BEARING HAD STARTED TO FAIL.  REPLACED BEARING AND INNE	R RACE OF SPUR ADAPTER. NO FURTHER PROBLEMS. (TC NR 20070612005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007071200131	20070712	00131	EU  	2007	7	12	CA070613001      	2	20070612	G	7270	JR21756A	DUCT            								RROYCE	SPEY  	SPEY55515P  	54521	EU  					ENGINE BYPASS	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			14716	2950 							(CAN) ENGINE FRONT BYPASS DUCT FOUND AT INSPECTION WITH NON STANDARD REPAIR OUTSIDE OEM LIMITATION. PATCH REPAIR ON OUTS	IDE WALL 8 INCH LONG BY 2.5 INCH WIDE OUTSIDE SCOPE OF XRS3025. PART REJECTED AND REMOVED FROM ENGINE.  (TC NR 200706130	01)									4	F			E2EU				 
2007071100177	20070711	00177	EA  	2007	7	11	CA070613002      	1	20070613	G	2810	21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT WING	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			1803 								(CAN) FUEL LEAK SUSPECTED ON RT WING.  RT FUEL CELL NR 6 HAS BEEN FOUND LEAKING AFTER INVESTIGATION AND REPLACED.  DROPS	  9050 (TC NR 20070613002)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
	20081104		CE  	2008	11	4	CA070613003      	1	20070612	G	8011	MMU4001R	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  		SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				421  							(CAN) STUDENT TRIED TO START ENGINE THE STARTER WOULD NOT ENGAGE. AIRCRAFT BROUGHT INTO HANGAR AND COWLS REMOVED. AME TR	IED TO ENGAGE STARTER IN THE SHOP BUT IT WOULD NOT ENGAGE. WHEN HE CHECKED THE STARTER IT WAS VERY HOT AND THERE WAS SOM	E SMOKE COMING OUT OF IT. STARTER REMOVED AND SENT BACK FOR WARRANTY REPLACMENT.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
	20081104		GL  	2008	11	4	CA070613004      	1	20070611	G	2497	AN316010	CIRCUIT BREAKER 			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN3     	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  		FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLESHOOTING A U/S TAIL NAV LIGHT AND REPLACING A CORRODED KNIFE CONNECTOR AT THE TAILCONE, POWER WIRE TO	 THE LIGHT ASSEMBLY OVERHEATED AND MELTED, FILLING THE CABIN WITH SMOKE. PWR WAS DISCONNECTED AND SMOKE DISSIPATED. FURT	HER INVESTIGATION REVEALED THAT NAV LIGHT SOCKET HAD CORROSION BUILDUP ON THE WIRING TERMINALS THAT HAD SHORTED THE SOCK	ET TO GROUND. PWR LIRE MELTED FROM THE SOCKET BACK TO CIRCUIT BREAKER, AND FROM THERE TO MAIN BUS. INVESTIGATION WAS THE	N CENTERED ON THE CIRCUIT BREAKER WHICH HAD NOT TRIPPED. BREAKER WAS FOUND TO BE A 10 AMP BREAKER AND NOT THE 5 AMP UNIT	 LISTED IN THE ACFT MANUAL. A FUNCTION CHECK OF THE BREAKER REVEALED THAT IT WOULD NOT TRIP AT ALL.  AN APPROPRIATELY RA	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2007081000108	20070810	00108	SW  	2007	8	10	CA070614001      	1	20070608	G	6310	269A5512	DRIVE BELT      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					MAIN ROTOR	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			177  								(CAN) DRIVE BELT AXIAL SPLIT OVER 50 PERCENT OF BELT CIRCUMFERENCE; SPLIT OCCURS UNDER OUTER LAYER OF BELT. DEFECT HAS B	EEN FOUND ON (2) OTHER AIRCRAFT OF THE SAME TYPE.  NOTE:  PLEASE ADVISE IF PHYSICAL INSPECTION IS REQUIRED AS MUST RETUR	N BELTS TO MANUFACTURER FOR WARRANTY CONSIDERATION. (TC NR 20070614001)				1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2008031900143	20080319	00143	SO  	2008	3	19	CA070614002      	1	20070604	G	7810	LW15849	EXHAUST STACK   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT ENGINE	SEPARATED       	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								L258765A			(CAN) PRIOR TO DEPARTURE, ENGINE RUN-UP PILOT REPORTED THAT RT ENGINE RUNNING ROUGH. ENGINE ONLY PRODUCING 30" MP AND MA	X 2250 RPM, AT GPH FF. RT MAG DROP WAS EXCESSIVE. MAINT INVESTIGATION FOUND ENGINE RT EXHAUST SEGMENT P/N LW-15849 SEPAR	ATED FROM NR 5 EXHAUST STACK PIPE PN LW-10161 AT THE SLIP JOINT. NEW EXHAUST SEGMENTS INSTALLED AND ENGINE OPERATION CHE	CKED SERVICEABLE. NO VISIBLE HEAT DAMAGE NOTED TO AREA WIRING OR COMPONENTS. SLIGHT DISTORTION NOTED TO SOME AREA HOSE S	UPPORT WRAPPING. NOTE: THIS ENG WAS RECENTLY INSTALLED AND HAD ACCUMULATED 2.2 HRS SINCE INSTALLATION. THE ORIGINAL EXHA	UST SEGMENTS FROM THE REMOVED ENGINE WERE INSTALLED. NO DEFINITIVE CAUSE FOR THE SEPARATION HAS BEEN DETERMINED. SUSPECT	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007071100178	20070711	00178	SW  	2007	7	11	CA070614003      	1	20070613	G	2910	2781032682	LINE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) CREW NOTICED A LARGE PUDDLE OF HYDRAULIC FLUID COMING FROM THE NOSE WHEEL WELL AREA.  DETERMINED TO BE A CRACKED L	INE ON A BEND RADIUS, WHICH WAS THE SUPPLY LINE TO THE NWS SYSTEM.  THE SYSTEM WAS DISABLED AND PLACED ON AN MEL DEFERRA	L, CLEANED AND LEAK TESTED, SERVICEABLE.  AWAITING PARTS FOR REPAIR. (TC NR 20070614003)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2007071700011	20070717	00011	NM  	2007	7	17	CA070614004      	1	20070511	G	2497		CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AC POWER MONITOR	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA						552					(CAN) UPON GETTING IN A/C DISCOVERED AC POWER C/B`S POPPED UPON  EXTERNAL PLUGGED INTO A/C ASSUME POPPED WHEN GSE PLUGGE	D IN PILOT ENTERED COCKPIT AND PUSHED ALL BREAKERS IN ON WALK AROUND  EXITING A/C AND DOING WALKAROUND WENT BACK TO COCK	PIT AND DISCOVERED SMOKE REMOVED POWER FROM A/C AND CALL MAINTENANCE UPON REMOVAL OF AC POWER MONITOR DISCOVERED BURNED 	CONNECTOR ON INDICATOR AND CONNECTOR, CONNECTOR AND INDICATOR /MONITOR REPLACED WITH NO FURTHER ISSUES.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007071100179	20070711	00179	NE  	2007	7	11	CA070614005      	2	20070307	G	7250	MS955608	BOLT            			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					GAS GENERATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4400 								(CAN) DURING SCHEDULED MAINTENANCE ACTIVITIES, 3 OF THE MS9556-08 BOLTS LOCATED AT THE ENGINE GAS GENERATOR TO INTERMEDI	ATE CASE FLANGE WERE DETERMINED TO BE LOOSE. AN ADDITIONAL BOLT WAS FOUND TO BE COMPLETELY MISSING.  MFG WILL INVESTIGAT	E AND ADVISE ON ROOT CAUSE AND REMEDIAL MAINTENANCE ACTIONS. (TC NR 20070614005)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007071100279	20070711	00279	NM  	2007	7	11	CA070615001      	1	20070612	G	2435	23088008	GENERATOR       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1	INTERMITTENT    	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			2594 								(CAN) AFTER SEVERAL SECTORS WITH INTERMITTENT NR 1 DC GEN PROBLEMS, CREW REPORTED ILLUMINATION OF DC BUS CAUTION LIGHT P	LUS SEVERAL OTHER CAUTIONS: AUX INV, NR 1 DC GEN, RUD FULL PRESS, NR 2 RUD HYD, EPWS.  THE QRH WAS ACTIONED BUT THEY WER	E NOT ABLE TO RESTORE THE LOST BUSES. THE NR 1 DC GENERATOR WAS REPLACED AND THE SYSTEM TESTED NORMALLY. ON REMOVAL FROM	 THE A/C, THE DC GENERATOR WAS NOTED TO HAVE SIGNIFICANT DAMAGE WITH SEVERAL LARGE METALLIC (CHUNKS) DROPPING OUT. (TC N	R 20070615001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007081000109	20070810	00109	NM  	2007	8	10	CA070615002      	1	20070606	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAIN ROTOR	SEPARATED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			38   								(CAN) BELTS WERE REPLACED AT 2200HR OVERHAUL AND AFTER 38 HRS IN SERVICE WERE FOUND SEPARATED IN A SECTION ABOUT 2 INCHE	S LONG. (TC NR 20070615002)					1	G	7	1 	3O	3	O		H10WE   	E286				 
2007071100278	20070711	00278		2007	7	11	CA070615003      	1	20070613	G	3230	622800200	SWITCH          			BAG   					GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	FAILED          	W				O				OTHER                   				L			NO TEST                   			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, THE CREW EXPERIENCED A LANDING GEAR FAILURE AND OBSERVED THE CIRCUIT BREAKER HAD POPPED. THEY PRO	CEEDED WITH AN EMERGENCY LANDING GEAR EXTENSION AND LANDED WITHOUT INCIDENT. THE FAULT WAS TRACED TO THE LT UPLOCK MICRO	SWITCH. WHEN THE MICROSWITCH WAS ACTIVATED THE FAULT DISAPPEARED AND WAS UNABLE TO BE RE-CREATED. THE SWITCH WAS REPLACE	D. (TC NR 20070615003)								4	T			E4WE	6	C	3PNE	 
2007071100276	20070711	00276	EU  	2007	7	11	CA070615004      	1	20070613	G	3220	A1026EAND9E	BOLT            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	NLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SCHEDULE INSPECTION AD UK 024-05-87 / SB53A-JA870510R1, WE NOTICE THE 2 UPPER BOLT OF THE NLG JACK MOUNTING BRACKE	T WERE SHEARED AND THE 2 LOWER ONES WERE LOOSE.  ACCOMPLISHED PART A OF THE SB C/OUT(ALL 4 BOLTS AND NUTS REPLACED), PAR	TS INSPECTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070615004)				2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2007081000110	20070810	00110		2007	8	10	CA070615005      	4	20070613	G	2350	M1035CHKFJLJ2	AUDIO CONTROL   			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  		STICKING        	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) BUTTONS HAVE TO BE PRESSED NUMEROUS TIMES BEFORE THEY ENGAGE, REPLACED UNIT.   (TC NR 20070615005)						2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
2008031900146	20080319	00146		2008	3	19	CA070615006      	4	20070613	G	2300	M1035CHKFJLJ2	AUDIO CONTROL   			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	STICKING        	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) BUTTONS HAVE TO BE PRESSED NUMEROUS TIMES BEFORE THEY ENGAGE, REPLACED UNIT (TC NR 20070615006)						2	L	7	2 	4T	3	T	RT	A8SW    	E2WE	6	C	3PNE	 
2007071100180	20070711	00180	WP  	2007	7	11	CA070616001      	2	20070527	G	7200		ENGINE          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					LEFT	MAKING METAL    	W				A				UNSCHED LANDING         				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		CR	CRUISE         	1			CA								P107188			(CAN) DURING CRUISE, CREW NOTED ODOR IN CABIN AND VIBRATION, AND EXECUTED PRECAUTIONARY LANDING.  LT ENGINE HAD HIGH VIB	RATION ON LOW POWER GROUND RUN, ENGINE OIL FILTER WAS HEAVILY CONTAMINATED WITH BOTH FERROUS AND NON-FERROUS MATERIAL, E	NGINE WAS REMOVED FOR REPAIR, SUSPECT BEARING AND/OR CARBON SEAL FAILURE, TEARDOWN REPORT PENDING. (TC NR 20070616001)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007081000111	20070810	00111	CE  	2007	8	10	CA070618001      	1	20070617	G	3210	MS2124010C40	BEARING         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS SDR IS BEING SUBMITTED TO SATISFY THE REQUIREMENT OF AIRCRAFT SERVICES DIRECTORATE CAMPAIGN NOTICE CN-1 851-3	2-40-040R1 THE INTERNAL TEFLON MATERIAL OF THE BEARING HAD DETERIORATED CAUSING THE BEARING TO BE DIFFICULT TO ROTATE. (	TC NR 20070618001)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007071100181	20070711	00181	EA  	2007	7	11	CA070618002      	2	20070606	G	8520		CRANKSHAFT      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2746 	2746 							(CAN) ENGINE CONVERTED TO 160 HP IAW STC SE367CH.  ENGINE NOW SIMILAR TO O-320-D2A.  CRANKSHAFT INSPECTED IAW AD 98-02-0	8.  PITTED FOUND, NO CRACKS. (TC NR 20070618002)					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007081000112	20070810	00112	SW  	2007	8	10	CA070618003      	1	20070616	G	2752	20619502	ACTUATOR        			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	TE FLAP	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			616  								(CAN) DURING APPROACH FOR A SCOOPING OPERATION, THE FLAPS WOULD NOT EXTEND WITH AN AIR LOAD.  THE AIRCRAFT RETURNED TO B	ASE.  UPON INVESTIGATION BY MAINTENANCE STAFF,  FLAPS WOULD EXTEND THE FIRST 10 DEGREES WITH NO AIR LOAD AND THE ACTUATO	R MADE A GRINDING NOISE.  THE FLAP ACTUATOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC 20070618003)				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2007081000113	20070810	00113	EA  	2007	8	10	CA070618004      	1	20070613	G	2897	MS312183P	CONNECTOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					AUX TANK	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) ON PATS RT AUXILARY TANK FOUND THE PRESSURE DIFFERENTIAL SWITCH, THE SOCKET OF THE SWITCH AND THE ELECTRICAL HARNE	SS CONNECTOR HAVING BOTH PINS, THE CONNECTOR SHOULD BE A FEMALE TYPE. THE DIFFERENTIAL SWITCH IS WORKING ONLY ON GROUND 	DURING FUELING. FOUND ALSO THAT THE SYSTEM IS WORKING BECAUSE THAT THE PINS ARE CONTACTING EACH OTHER. PATS THE STC HOLD	ER ADVISED AND A SB IS ALREADY OUT (TC NR 20070618004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007081000114	20070810	00114	CE  	2007	8	10	CA070618005      	1	20070504	G	7603	509440767	POWER LEVER     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	LT ENGINE	WORN            	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) FLIGHT SNAG REPORTED - (LT ENGINE REMAINS AT HIGH IDLE AT LOW IDLE SETTINGS).  MAINTENANCE FOUND THE AIRFRAME POWE	R LEVER ARM AT THE REVERSING CAM GROUND PIN HEAD JUMPED THE SPLINE, CAUSING THE SHOULDERED PIN TO HOLD THE FCU INTERCONN	ECT ARM FROM RESETTING TO GROUND IDLE.THE ARM WAS RE-ADJUSTED AND IS ASSUMED WORN OUT INTERNALLY. AS A PRECAUTION ALL TH	ROTTLE ARMS WERE REPLACED. (TC NR 20070618005)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007071100182	20070711	00182	EA  	2007	7	11	CA070618007      	2	20070618	G	7297	311792401	WIRE HARNESS    								PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACCESSORIES SERVICES PLANT 2.  DURING BENCH CHECKING ACTIVITIES THE PART WAS EXHIBITING AN UNKNOWN CONFIGURATION. 	UNABLE TO DETERMINE THE MANUFACTURING SOURCE.  THE PART WAS REPLACED WITH GENUINE PART. THIS PART WILL BE KEPT FOR 1 MON	TH FOR EXAMINATION. (TC NR 20070618007)									4	T			E4EA				 
2007081000115	20070810	00115	EA  	2007	8	10	CA070618008      	1	20070617	G	3213	492009	AXLE            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					LT MLG	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			4513 								(CAN) REPORTED A FRACTURED LT IB MLG AXLE (NR 2) ON A/C, LT SHOCK STRUT ASSY HAS P/N 49200-9 WITH SPP0049 WITH CURRENTLY	. EFFECTED SUBASSY PISTON/AXLE HAS P/N 49263-1 WITH S/N BA0066 AND IS ORIGINALLY INSTALLED ON A/C SINCE DELIVERY. RT SHO	CK STRUT ASSY HAS P/N 49200-10 WITH S/N SPP0097 AND SUBASSY PISTON AXLE ASSY WITH P/N 49263-1 AND S/N BA0111 AND BOTH HA	VE TAC=7763 (ORIGINALLY INSTALLED SINCE DELIVERY). (TC NR 20070618008)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007081000116	20070810	00116	EA  	2007	8	10	CA070618009      	1	20070615	G	2820		O-RING          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL SYSTEM	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, ENROUTE,  THE CREW OBSERVED A RT FUEL LOW PRESS MESSAGE ON EICAS FOLLOWED BY FUEL IMBALANCE.  AT 10	00 LB FUEL DIFFERENTIAL BETWEEN TANKS, THE QRH PROCEDURE FOR FUEL IMBALANCE WAS INITIATED. AS A RESULT, THE RT ENGINE WA	S SHUTDOWN.  THE AIRCRAFT DIVERTED.  AN EMERGENCY WAS DECLARED AND GROUND EMER EQUIP WAS ON STANDBY.  THE AIRCRAFT LANDE	D WITHOUT FURTHER EVENT.  MAINT FOUND A CLAMP FOR THE FUEL FEED LINE FROM THE RT COLLECTOR TANK WAS NOT PROPERLY ATTACHE	D.  THE CLAMP HAD SHIFTED SUFFICIENT TO ALLOW A MISALIGNMENT OF THE FUEL LINES RESULTING IN THE ESCAPE OF FUEL AT THAT L	OCATION.  THE ROOT CAUSE FOR THIS IS NOT FULLY ESTABLISHED.  MAINT REPLACED THE COUPLING O-RINGS AND RECONNECTED THE WIG	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007082000039	20070820	00039	EA  	2007	8	20	CA070618010      	1	20070613	G	3213	492033	AXLE            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					MLG	SHEARED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			956  								(CAN) WHILE LOADING, THE PASSENGER AT SLC THE FLIGHT CREW FELT A CERTAIN JOLT . INVESTIGATING THE SOURCE , THE CREW FOUN	D MLG NR 4 AXLE COMPLETELY SHEARED OFF. MLG NR 4 MLG  AXLE COMPLETELY SHEARED OFF.  (TC NR 20070618010)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081104		CE  	2008	11	4	CA070619001      	1	20070617	G	2731	26616151	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELEVATOR TRIM	BINDING         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			3730 	551  							(CAN) EXCESSIVE RESISTANCE IN ELEVATOR TRIM REPORTED. RT ELEVATOR TRIM ACTUATOR FOUND TO BE BINDING AND REPLACED WITH OV	ERHAULED UNIT. ACFT HAS FLOWN WITH NO REOCCURENCE OF THE DEFECT. THE SUBJECT ACTUATOR WAS OVERHAULED AND FITTED IAW THE 	MAINT SCHEDULE IN JULY 2006. (TC NR 20070619001)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2007082000040	20070820	00040	CE  	2007	8	20	CA070619002      	1	20070618	G	5210	504300401	STEP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSP IT WAS NOTICED THAT THE STEP ON THE AIRSTAIR DOOR WAS CRACKED AT THE PIVOT STUD.  THE STEP WAS REMO	VED AND A SERVICEABLE STEP WAS INSTALLED. (TC NR 20070619002)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007082000041	20070820	00041	CE  	2007	8	20	CA070619006      	1	20070618	G	3297		WIRE            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	MLG	CUT             	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			2738 								(CAN) LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF DUE TO A FAULTY WIRE TERMINAL CONNECTION BETWEEN THE (GEAR-UP LIMIT S	WITCH) AND THE (GEAR MOTOR RELAY). (TC NR 20070619006)					1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P25EA	 
2007082000042	20070820	00042	NE  	2007	8	20	CA070619007      	2	20070611	G	7321		BOLT            			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					FCU CONNECTION	LOOSE           	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) OCCURRENCE WHERE THE ENGINE SPEED CONTROL DISENGAGED FROM THE FUEL CONTROL UNIT, RESULTING IN AN IN-FLIGHT SHUTDOW	N OF THE ENGINE. SUSPECTED CAUSE WAS A LOOSE SELF LOCKING BOLT, P/N NK4-4A, AND OR A WORN NON METALLIC LOCKING INSERT ON	 THE NK4-4A BOLT. IN ORDER TO PREVENT THIS FROM HAPPENING AGAIN, THE MAINTENANCE CREW HAVE BEEN REMINDED TO TAKE CARE WH	EN INSTALLING THE SPEED CONTROL WHEN RE-USING THE NK4-4A BOLT TO ENSURE THAT THERE IS THREAD INTERFERENCE.  MM, SA 4045-	80, SECTION 20-00, PAGE 5, PARAGRAPH 9 (REUSE OF SELF LOCKING NUTS), SUB-PARAGRAPH C. STATES THAT ALL NUTS MUST BE CHECK	ED BEFORE RE-USE. THERE MUST BE THREAD INTERFERENCE, SUCH INTERFERENCE INDICATES THAT THE SELF LOCKING FEATURE IS WORKIN	2	G	7	2 	4U	4	U		1H15    	1E3				 
2007082000043	20070820	00043		2007	8	20	CA070620002      	4	20070322	G	6122	321524	SOLENOID        	HAMSTD      	4U1827      	CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	PROP GOVERNOR	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						CSP0059					(CAN) DURING A TEST FLIGHT, THE NR 1 PROP WAS FEATHERED TO VERIFY CORRECT FUNCTION OF THE SYSTEM. THE FLIGHT CREW WAS UN	ABLE TO UNFEATHER THE PROPELLER AND RETURNED TO THE AIRPORT.  MAINTENANCE CREWS FUNCTION TESTED THE SYSTEM ON THE GROUND	 AND THE SYSTEM FUNCTIONED CORRECTLY. THE PROP FEATHERING SOLENOID WAS SUSPECT AND WAS REPLACED. AIRCRAFT WAS RETURNED T	O SERVICE. (TC NR 20070620002)			2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2007071100183	20070711	00183	NM  	2007	7	11	CA070620003      	1	20070607	G	3150		UNKNOWN         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  		UNKNOWN         	W				H				DEACTIVATE SYST/CIRCUITS				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			946  								(CAN) WHEN REFUELING AIRCRAFT GROUND CREW NOTICED THAT WHEN THE REFUEL PANEL DOOR WAS OPEN THAT THEY HAD LIGHTS ON THE P	ANEL THAT SHOULD NOT HAVE BEEN ON. (TC NR 20070620003)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007082000044	20070820	00044	EU  	2007	8	20	CA070621001      	1	20070621	G	6220		BUSHING         	UROCOP      		UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					SCISSOR LINK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			98   								(CAN) FACTORY NON- FIELD REPLACEABLE BUSHING BOND FAILED IN THE SCISSOR LINK, BROKE FREE AND WORE INTO THE SISSOR LINK. 	EXCESSIVE PLAY AND "SMOKE" WAS EVIDENT. (TC NR 20070621001)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2007082000045	20070820	00045	CE  	2007	8	20	CA070621002      	1	20070616	G	2910		MOTOR           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	HYD SYSTEM	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, PILOTS SELECTED LANDING GEAR DOWN, GEAR MOTOR CIRCUIT BREAKER POPPED AND GEAR WOULD NOT EXTEND. A	N EMERGENCY EXTENSION WAS CARRIED OUT SATISFACTORILY.  AFTER RETURN TO BASE MECHANICS FOUND THAT THE HYDRAULIC MOTOR WAS	 CONTAMINATED WITH HYDRAULIC FLUID WHICH LED TO AN ELECTRICAL SHORT.  FURTHER INSPECTION FOUND THAT THE O-RING WHICH SEP	ARATES THE RESERVOIR AND THE MOTOR WAS DETERIORATED. MECHANICS FOUND THAT SPARE POWER PACKS IN STORES HAD SIMILAR CONTAM	INATION DUE TO FAULTY O-RINGS. THESE SPARE POWER PACKS ARE LAID ON THEIR SIDES WHICH WOULD ALLOW FLUID TO PASS TO THE MO	TOR. A FLEET WIDE INSPECTION OF POWER PACKS IN SERVICE IS BEING CARRIED OUT BY THE AMO TO PREVENT FURTHER OCCURRENCES. A	1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2007082000046	20070820	00046	CE  	2007	8	20	CA070621003      	1	20070620	G	5711	1058100237	FRAME           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	RT WING	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING TAXI PILOTS FELT THE RT WING DROP SUDDENLY AND HEARD A TIRE SKIDDING SOUND. THEY IMMEDIATELY STOPPED THE AI	RCRAFT.  MECHANICS FOUND THE LANDING GEAR A-FRAME HAD BROKEN FREE FROM THE MAIN LANDING GEAR TRUNNION. THE LANDING GEAR 	DID NOT COLLAPSE BUT ROTATED OB AND CONTACTED THE WING WHEEL WELL SKIN CUTOUT, AFTER THE A-FRAME BECAME DISCONNECTED. TH	E A-FRAME THAT FAILED HAD BEEN REPLACED WITH AN IMPROVED DESIGN AS REQUIRED BY AD 97-06-10. A FLEET WIDE INSPECTION OF A	-FRAMES IN SERVICE ON COMPANY OPERATED AIRCRAFT IS BEING CONDUCTED BY THE AMO TO DETECT EVIDENCE OF CRACKS AT THE WELD B	ETWEEN THE UPPER ATTACH FITTING (SQUARE SHAPE) AND THE ROUND TUBULAR STRUCTURE. (TC NR 20070621003)	1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2007082000047	20070820	00047	SO  	2007	8	20	CA070621004      	1	20070611	G	2731	4173478	CABLE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR TRIM	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			14256								(CAN) PILOT REPORTED ELEVATOR TRIM VERY STIFF WHILE IN FLIGHT, THEN FREE AFTER SEVERAL ATTEMPTS. MAINT INVESTIGATION REV	EALED TRIM CABLE P/N 41734-78 SEPARATED AT THE TRIM SERVO P/N 1C469-6-498. CABLE WAS REPLACED AND SYSTEM RIGGED IAW MM 5	-32. CABLE INSPECTION DID NOT REVEAL ANY UNUSUAL WEAR OR FRAYING AT THE SEPARATED ENDS. CABLE WAS SHREDDED AND APPEARED 	TO BE TORN APART. FURTHER INVESTIGATION BY AVIONICS REPAIR STATION REVEALED THAT THE ELEVATOR ELECTRIC/AP TRIM SERVO CLU	TCH RELEASE MECHANISM WAS INTERMITTENT. SERVO WAS REPAIRED AND OPERATION CHECKED SERVICEABLE.  (TC NR 20070621004)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007082000048	20070820	00048	EA  	2007	8	20	CA070622002      	2	20070620	G	8550	O320H2AD	ENGINE          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LEFT	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			6383 	2085 				RL567576T			(CAN) OIL LEAKING FROM FRONT LT AREA OF ENGINE. (TC NR 20070622002)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082000049	20070820	00049	WP  	2007	8	20	CA070622003      	1	20070619	G	6310		SHAFT           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH	WORN            	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			563  								(CAN) LOUD (BANG) HEARD DURING FLIGHT. CLUTCH SUSPECTED. REMOVED TO INSPECT. CLUTCH WAS TORN DOWN IN THE COMPONENT SHOP 	AND SHAFT WAS FOUND WORN BEYOND LIMITS.  SPRAG WAS MOST LIKELY DRAGGING ON THE SHAFT. CLUTCH AND SHAFT ASSY BEING SENT B	ACK FOR WARRANTY. (TC NR 20070622003)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007082000050	20070820	00050	EU  	2007	8	20	CA070622004      	1	20070619	G	2121	9599022154	BLOWER          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RIGHT	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			6594 								(CAN) RT VENTILATION BLOWER WOULD NOT OPERATE WHEN SWITCHED ON. REPLACED WITH NEW. (TC NR 20070622004)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007082000051	20070820	00051	SW  	2007	8	20	CA070622005      	1	20070621	G	2841	EA4703587	INDICATOR       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL QTY	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL QUANTITY INDICATOR WAS REMOVED DUE TO INDICATION PROBLEMS.  WHEN REMOVED IT WAS FOUND THAT THE FLOAT WAS FULL	 OF FUEL AND ONE OF THE DECALS FROM PHP WAS GONE AND WAS IN THE FUEL SYSTEM.  DECAL WAS LOCATED AND SENDER IS BEING REPL	ACED WITH A NEW UNIT. (TC NR 20070622005)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007071100184	20070711	00184	CE  	2007	7	11	CA070622006      	1	20070619	G	2822	025323150	PUMP            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1453 							(CAN) DURING AN INSPECTION THE INLET FILTER WAS REMOVED. THE FILTER COVER (CAP) WAS FOUND CRACKED UNDER THE O-RING LOCAT	ION ALL THE WAY AROUND.  IT APPEARS TO HAVE BEEN OVER TORQUED.  IT WAS NOT LEAKING AT THIS TIME.  THE INLET FILTER ASSEM	BLY WAS REPLACED. (TC NR 20070622006)				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	5	C	P60GL	 
2007082000052	20070820	00052	EU  	2007	8	20	CA070622007      	1	20070619	G	6220	C623A2005103	SCISSOR LINK    			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					MAIN ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			98   								(CAN) (1) OF (4) BONDED BUSHINGS FAILED, RESULTING EXCESSIVE PLAY/SMOKING. BUSHING CONTINUED TO WEAR INTO SCISSOR LINK U	NTIL CAUGHT AT FIRST 100 HOUR INSPECTION (SINCE NEW). (TC NR 20070622007)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2007082000053	20070820	00053	CE  	2007	8	20	CA070622008      	1	20070612	G	2730	1016100190014	TORQUE TUBE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	ELEVATOR CONTROL	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING RIGGING CHECK, DUE TO REPLACEMENT OF THE ELEVATOR TORQUE TUBE, DISCOVERED THE ARM LOCATION WAS INCORRECT IN	 RELATION TO THE MOUNTING PLATE.  THIS RESULTED IN NOT BEING ABLE TO ACHIEVE FULL TRAVEL OF THE ELEVATOR.  THIS WAS CONF	IRMED WHEN COMPARED TO THE REMOVED TORQUE TUBE AND THE SECOND REPLACEMENT.  THE CONCLUSION IS INCORRECT ASSEMBLY AT MFG.	  (TC NR 20070622008)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007071100185	20070711	00185	EA  	2007	7	11	CA070625001      	2	20070606	G	8530	O320H2AD	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA				1400 				L518276T			(CAN) INSTRUCTOR RETURNED FROM A FLIGHT WHERE HE EXPERIENCED A ROUGH ENGINE AND LOSS OF POWER FOR A FEW MOMENTS, AFTER W	HICH THE ENGINE RAN NORMALLY AGAIN.  WHEN MAINTENANCE REMOVED THE COWLING TO CHECK OVER THE ENGINE, A LOT OF OIL WAS NOT	ICED IN THE COWL, FURTHER INSPECTION AND CLEANING FOUND A 2 INCH LONG CRACK IN THE CRANKCASE FROM CYLINDER NR 2 MOUNTING	 PAD AND FORWARD. (TC NR 20070625001)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082000054	20070820	00054	NE  	2007	8	20	CA070625004      	2	20070624	G	8560		SUPERCHARGER    			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R1340 	BWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA				1906 							(CAN) AT TOP OF CLIMB ENGINE POWER DECREASED TO 20 INCH MANIFOLD PRESSURE AND 80 BMEP.  ENGINE WAS SHUTDOWN AND AIRCRAFT	 RETURNED TO AIRPORT.  SUSPECT ENGINE SUPERCHARGER BLOWER FAILED. (TC NR 20070625004)					2	L	7	4 	4R	3	R		6A4     	ATC14	6	C	P871	 
2007082000055	20070820	00055	EU  	2007	8	20	CA070625005      	1	20070613	G	6720	21863753	PUSH-PULL ROD   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					T/R GEARBOX	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1000 								(CAN) HEAT SHRINK WHICH PROTECTS THE TAIL ROTOR PUSH PULL TUBE AS IT GOES THRU BEARING P/N 359A27-1191-20 IS CHAFING PRE	MATURLY AT THE AFT MOST BEARING LOCATION ON THE TAILBOOM.  IPC 67.20.10.00006.00 FIG. 3 (TC# NR 20070625005)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007082000056	20070820	00056	SW  	2007	8	20	CA070626001      	1	20070622	G	2820	206063607101	HOSE            			BELL  	206   	206L4       	1182110	SW  										FUEL SYSTEM	DEBONDED        	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) FUEL HOSE ASSY DEBONDED CAUSING FUEL LEAK FROM FWD TANKS. THE RUBBER BELLOW PART OF THE TUBE ASSEMBLY DEBONDED FRO	M THE ALUMINUM TUBING. THIS HOSE ASSEMBLY IS LOCATED ON THE LT SIDE FWD FUEL TANK. REFER TO HELICOPTER IPB FIGURE 28-3 I	TEM NR 57.  (TC NR 20070626001)				1	G	7	1 	3U			NC	H2SW    					 
2007082000057	20070820	00057	CE  	2007	8	20	CA070627001      	1	20070622	G	3260	1013646281	DOWNLOCK SWITCH 			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	LT MLG	UNSERVICEABLE   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) THE AIRCRAFT WAS ON A RETURN LEG, WHEN THE CREW LOWERED THE LANDING GEAR THEY NOTICE AN UNSAFE INDICATION ON THE L	T MAIN. THEY ABORTED THE LANDING AND INITIATED A (GO-AROUND) PROCEDURE. THE LANDING GEAR WAS CYCLED TWICE MORE AND ON TH	E SECOND TRY A SAFE INDICATION WAS OBSERVED. THE AIRCRAFT LANDED WITHOUT INCIDENT. THE LT MAIN LANDING GEAR DOWNLOCK SWI	TCH ASSY (P/N 101-364628-1) WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC 	NR 20070627001)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007082000058	20070820	00058	NE  	2007	8	20	CA070627002      	2	20070624	G	7261	4138T09P03	CARBON SEAL     		CF343B1     	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								872403			(CAN) ON CLIMB OUT, CREW REPORTED NR 2 OIL PRESSURE WAS LOW AND FLUCTUATING BETWEEN 30-41 PSI.  INTERMITTENTLY TRIGGERIN	G THE LOW OIL WARNING. THE AIRCRAFT WAS DIVERTED AND LANDED NORMALLY. AT LOCATION, CONTRACT MAINTENANCE ADDED (4) QUARTS	 OF OIL AND A/C WAS CHECKED SERVICEABLE.  THE A/C THEN RETURNED TO ORIGINATING BASE WHERE FURTHER TROUBLESHOOTING WAS TO	 BE CARRIED OUT.  MAINTENANCE FOUND NR 2 ENGINE IDG CARBON SEAL DAMAGED.  THE CARBON SEAL WAS REPLACED AND LEAK CHECKS A	ND RUNS CARRIED OUT AND CHECKED SERVICEABLE.  A/C HRS.:17552:25, CYCLES:13370  (TC NR 20070627002)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007082000059	20070820	00059	CE  	2007	8	20	CA070627003      	1	20070626	G	2621	3090385659	SQUIB           	PACIFICSCIEN		LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FIRE BOTTLE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2172 			39925B1					(CAN) WHILE PERFORMING ANOTHER MAINTENANCE TASK IT WAS DISCOVERED THAT THE LOWER (FWD) FIRE BOTTLE SQUIBS WERE NOT INSTA	LLED IN THE CORRECT POSITION.  BOTH FIRE BOTTLES CONTAIN A SQUIB FOR THE LT AND RT ENGINES, THE LOWER NR 1 BOTTLE IS FOR	 THE FIRST SHOT AND THE UPPER NR 2 BOTTLE IS FOR THE SECOND SHOT.  THE LT AND RT SQUIBS ON EACH BOTTLE HAVE A DIFFERENT 	PN WITH A DIFFERENT CONNECTOR PLUG RECEPTACLE IN ORDER NOT TO ACCIDENTALLY SWAP LT AND RT ENGINES EXTINGUISHING CAPABILI	TIES.  HOWEVER, SINCE THE SQUIBS WERE INSTALLED INCORRECTLY THE FIRST EXTINGUISHING SHOT WOULD HAVE BEEN DIRECTED TO THE	 WRONG ENGINE.  UPON INVESTIGATION IT WAS DISCOVERED THAT THE SQUIBS MAY HAVE BEEN INSTALLED INCORRECTLY AT THE LAST 10-	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007071100187	20070711	00187	NE  	2007	7	11	CA070628001      	3	20070625	G	6114	7826691	BOLT            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	PROPELLER HUB	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19004	8360 							(CAN) DURING REINSTALLATION OF PROPELLER ASSEMBLY AFTER NR 2 ENGINE CHANGE, ONE OF THE MOUNTING BOLTS (P/N 782669-1) SHE	ARED. A DIFFERENT PROPELLER ASSEMBLY WAS INSTALLED. AFFECTED SHEARED BOLT TO BE REMOVED AND REPLACED IAW CMM P/N 802325-	1, CH 61-13-06, HUB  REPAIR 7-5, PAGES 601-602. TIMES AND CYCLES ARE FOR HUB ASSEMBLY. (TC NR 20070628001)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000060	20070820	00060	NE  	2007	8	20	CA070628003      	2	20070516	G	7260	MS949034	BOLT            			MRCHTI	S205  	S20522R     	8120412	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					FIRST STAGE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			175  					PCE97543			(CAN) ENGINE S/N PCE 97543 WAS REMOVED SUBSEQUENT TO IN-FLIGHT SHUTDOWN AFTER THE ENGINE OIL PRESSURE DROPPED TO (0) IN 	FLIGHT.  METAL WAS FOUND IN THE OIL FILTER AND RGB DURING GROUND CHECKS PRIOR TO ENGINE REMOVAL.  DURING INVESTIGATION D	ISMANTLE OF THE POWER SECTION, (2) OF (6) FIRST-STAGE REDUCTION CARRIER ASSEMBLY MACHINE HEX BOLTS (IPC P/N 3032844, CH.	 72-11-00, FIGURE 4, ITEM 200, P/N MS9490-34) WERE FOUND WITHOUT THE BOLT HEADS ATTACHED (REFERENCE FIGURE 1).  NOTE THA	T THE CARRIER HEX BOLTS SECURE THE FIRST-STAGE CARRIER AND THE FIRST-STAGE REDUCTION SPLINED ADAPTER.  THERE ARE A QUANT	ITY OF SIX HEX BOLTS INSTALLED WITH KEYWASHERS AND ARE TORQUED 75 TO 85 IN.LB.  ENGINE OVERHAUL RECORDS INDICATED THAT Q	1	L	7	1 	3O	4	T		A9EU    	E4EA				 
2007082000061	20070820	00061	WP  	2007	8	20	CA070629001      	2	20070625	G	7210	8941241	SHAFT           								GARRTT	TPE331	TPE33110    	01514	WP  					SPLINES	WORN            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA				2321 							(CAN) AIRCRAFT EXPERIENCED A NTS EVENT DURING LANDING PHASE, WITH POWER LEVER REDUCED TO FLIGHT IDLE, AC CONFIGURED FOR 	LANDING, WITH NORMAL ATTITUDE FOR LANDING. AIRCRAFT LANDED AND TAXIED WITH NO OTHER PROBLEMS REPORTED. AIRCRAFT INSPECTE	D, FLIGHT IDLE BLADE ANGLES ADJUSTED AND RETURNED TO SERVICE.  DUE TO SOAP RESULTS AND NTS GROUND CHECK RESULTS, THE ENG	INE WAS SUBSEQUENTLY REMOVED FROM SERVICE. NTS ACTION IS POTENTIALLY DUE TO (SUSPECTED) COMBINATION OF WEAR OF THE QUILL	 SHAFT AND BALL LOCK WHICH WOULD HAVE IN EFFECT, CAUSED A REDUCTION IN THE PRELOAD OF THE NTS SYSTEM, THEREBY ALLOWING T	HE NTS TO ACTIVATE AT A LOWER THRESHOLD THAN SET CALIBRATION.  CODE (TC NR20070629001)						4	T			E4WE				 
	20081105			2008	11	5	CA070629002      	1	20070629	G	2910		PACKING         																	HYD ACTUATOR	DEFECTIVE       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHILE REPLACING O-RINGS AND BACK-UP SEALS IN SOME HYDRAULIC ACTUATORS, FOUND SOME OF NEW BACK-UP SEALS DEFECTIVE. 	THE CHAMFERED EDGE OF THE SEAL IS TO SHORT WHICH IN TURN CAUSED THE EDGE TO DAMAGE THE O-RING. IT SEEMS TO ACT AS A KNIF	E EDGE. ALL SEALS IN A BATCH WERE NOT FOUND LIKE THIS, ONLY A FEW.  THAT IS WHY SOME OF OUR ACTUATORS HAVE BEEN LEAKING 	DUE TO THE BACK-UP SEAL CUTTING THE O-RING.  WILL BE SENDING A REPORT AND PICTURES TO THE VENDOR.																 
2007082000062	20070820	00062	WP  	2007	8	20	CA070629003      	1	20070525	G	2916	D2112	RESERVOIR       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA			196  								(CAN) DURING POST INSPECTION RUN UPS, IT WAS WITNESSED THE HYDRAULIC RESERVIOR WAS VENTING HYDRAULIC FLUID OUT OF THE VE	NT. NO DETERMINING FACTOR COULD BE FOUND, SO THE RESERVIOR WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 2007062	9003)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022000322	20080220	00322	SO  	2008	2	20	CA070703001      	1	20070628	G	3211	4032700	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT MLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			19470				317405228				(CAN) DURING A SCHEDULED LAYOVER, ON POST FLIGHT WALK AROUND THE PILOTS NOTICED THAT THE LT GEAR STRUT WAS DEFLATED. EXA	MINATION BY MAINT SHOWED THAT THE TRUNNION HAD CRACKED ALONG THE WELD THAT HOLDS THE (2) HALVES OF THE TRUNNION TOGETHER	. IT HAD CRACKED UP PAST THE ORINGS INTO THE SEALED AREA OF THE STRUT.  IT IS UNKNOWN IF THIS STRUT IS THE ORIGINAL AIRC	RAFT ONE. (TC NR 20070703001)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081104		EA  	2008	11	4	CA070703002      	2	20070509	G	7414	M3548	ROTOR SHAFT     	SLICK       	4370        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	SHEARED         	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			1272 								(CAN) A STUDENT PILOT NOTICED THAT THE ENGINE WOULD NOT RUN WHEN THE RT MAGNETO WAS SELECTED. MAINT WAS CALLED AND THE R	T MAGNETO WAS REMOVED FROM THE ENGINE AND DISSASSEMBLED. THE ROTOR WAS FOUND SHEARED AT THE CAM ROTOR SLOT. (TC NR  2007	0703002)				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2008013100071	20080131	00071	SW  	2008	1	31	CA070703003      	1	20070701	G	2822	1C27	CARTRIDGE       	AIRBORNE    		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					BOOST PUMP	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CAUTION LIGHT ILLUMINATED DURING FLIGHT INDICATING A BOOST PUMP FAILURE. FUEL SYSTEM INSPECTED FWD BOOST FOUND TO 	BE NOT OPERATING. CARTRIDGE CHANGED OUT WITH AN OVERHAULED UNIT.FUEL SYSTEM SERVICABLE. (TC NR 20070703003)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007082000063	20070820	00063	SO  	2007	8	20	CA070703004      	2	20070613	G	8530	AEC631397	CYLINDER        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NR 2	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			484  	454  				547388			(CAN) CYLINDER CRACKED FROM FUEL INJECTOR TO SPARK PLUG HOLE, CRACK FOUND DURING 100 HR INSPECTION (TC NR 20070703004)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2007082000064	20070820	00064	SO  	2007	8	20	CA070703005      	2	20070608	G	7414	662	MAGNETO         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				300  							(CAN) SHEARED MOUNTING FLANGE HOUSING. (TC NR 20070703005)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2007082000065	20070820	00065	NM  	2007	8	20	CA070703006      	1	20070702	G	2612	4739551	CONTROL PANEL   			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					FIRE CONTROL	DAMAGED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			10460	10460							(CAN) ON JULY 2/07 IN PREPARATION FOR THE DAYS FLYING THE CREW REPORTED THE CARGO FIRE BELL SOUNDING.  THE FORWARD CARGO	 FIRE C/BS WERE FOUND POPPED AND SMOKE WAS COMING FROM THE FLIGHT DECK CARGO FIRE DETECTOR PANEL.  THIS RESULTED IN THE 	FWD CARGO PIT EXTINGUISHER DISCHARGING ITSELF. THE FIRE PANEL MODULE AND THE DEPLETED FIRE BOTTLE WERE REPLACED.  THE OE	M TO WHICH THE DAMAGED PANEL WAS SENT HAS BEEN REQUESTED TO INVESTIGATE, PROVIDE A DETAIL STRIP REPORT AND PHOTOS.  FURT	HER INFORMATION WILL BE SUBMITTED AT THE CONCLUSION OF THIS INVESTIGATION. (TC NR 20070703006)		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007082000066	20070820	00066		2007	8	20	CA070704001      	1	20070703	G	7810	31015827	EXHAUST DUCT    								GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON ROUTINE INSPECTION, THE MAINTENENCE CREW FOUND THE EXHAUST DUCT CRACKED. THE ENGINE WAS REMOVED AND THE EXHAU	ST DUCT WAS REPLACED WITH A OVERHAULED ONE. NO OTHER PROBLEMS WERE DETECTED AT THIS INSPECTION. (TC NR 20070704001)										4	T			E4WE				 
2007082000067	20070820	00067	EA  	2007	8	20	CA070704002      	1	20070703	G	2750	C6CF14681	ROD             			DHAV  	DHC6  	DHC6300     	2802606	EA  										TE FLAPS	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE FLAP RODS IAW S/B 6/502 AND 6/388 IT WAS NOTICED THAT THE SWAGED END OF THE FLAP ROD WAS 	NOT COMPRESSED.  UPON INSPECTION OF THE ROD IT WAS NOTED THAT THE COLLAR WAS NOT IN THE CORRECT POSITION AND HAD NOT BEE	N COMPRESSED ENOUGH.  THE SWAGED END MEASURES 0.9880OF AN INCH AND THE END IN QUESTION MEASURES 1.0055 OF AN INCH. THERE	 IS NORMALLY A BUMP IN THE SWAGED END, BUT THE END IN QUESTION DOES NOT HAVE ANY BUMP ON IT.  (TC NR 20070704002)			1	H	7	2 	3T			RT	A9EA    					 
2007082000068	20070820	00068	NM  	2007	8	20	CA070704003      	1	20070704	G	5210	85210276101	BOLT            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HANDRAIL SUPPORT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CREW REPORTED THAT MAIN CABIN DOOR WOULD STOP OPENING SOMETIMES. FLIGHT ATTENDANT HAD TO PUSH THE HANDRAIL TO GET 	THE DOOR FULLY OPEN. LINE MAINTENANCE FOUND REAR HANDRAIL SUPPORT STRUT BOLT (REF IPC 52-10-00-35-50) UNSCREWED AND CONT	ACTING WITH HANDRAIL LOWER NEWEL STRUT (REF IPC 52-10-00-40-90). THE BOLT HAS NO LOCKING FEATURE. THE BOLT WAS TIGHTENED	, SYSTEM CHECKED SERVICEABLE AND THE AIRCRAFT RELEASED INTO SERVICE (TC NR 20070704003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081104		CE  	2008	11	4	CA070704004      	1	20070703	G	2435		BRUSHES         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	STARTER GEN	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			1005 								(CAN) PILOT ATTEMPTED TO START AIRCRAFT. AIRCRAFT FAILED TO START. FURTHER INVESTIGATION REVEALED A STARTER BRUSH HAD FR	ACTURED AND SEPARATED INTO A FEW PIECES. DAMAGE TO THE COMMUNTATOR WAS FOUND. IT WAS APPROXIMATELY 240 HRS SINCE THE LAS	T BRUSH INSPECTION AND NO ISSUE WERE NOTED.  (TC NR 20070704004)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2007082000069	20070820	00069	NM  	2007	8	20	CA070704005      	1	20070627	G	5210	R2210151	DOOR FRAME      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING VISUAL INSPECTION TO COMPLY WITH AWD 2005-16-05 LT DOOR ASSY WAS FOUND CRACKED.  FUTHER INSPECTION OF THE T	ECH-TOOL DOOR AND FRAME REVEALED ADDITIONAL CRACKS. DOOR FOUND TO BE U/S AND REMOVED FROM A/C. (TC NR 20070704005)					1	G	7	1 	3O	3	O		H10WE   	E274				 
2008013100037	20080131	00037	NM  	2008	1	31	CA070704006      	1	20070627	G	5210	R2210152	FRAME           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					RT DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING VISUAL INPECTION TO COMPLY WITH AWD 2005-16-05 RT DOOR ASSY WAS FOUND CRACKED. FUTHER INPECTION OF THE TECH	-TOOL DOOR AND FRAME ASSY REVEALED ADDITIONAL CRACKS. DOOR FOUND TO BE UNSERVICEABLE AND REMOVED FROM A/C. (TC NR 200707	04006)				1	G	7	1 	3O	3	O		H10WE   	E274				 
2007082000070	20070820	00070		2007	8	20	CA070704007      	4	20070704	G	6113	05503214	BULKHEAD        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			652  								(CAN) BULKHEAD IS CRACKED AROUND SEVERAL OF THE PROP THROUGH BOLT HOLES. (TC NR 20070704007)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082000071	20070820	00071		2007	8	20	CA070704008      	4	20070517	G	6113	05503214	BULKHEAD        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			320  								(CAN) CRACKED AROUND SEVERAL OF THE PROP BOLT THROUGH HOLES. (TC NR 20070704008)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082000072	20070820	00072	NE  	2007	8	20	CA070704009      	2	20070509	G	7313	ST3367009	PACKING         			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL MANIFOLD	DEFECTIVE       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKE-OFF PASSENGERS REPORTED FLUID ESCAPING FROM THE ENGINE.  THE PILOT REDUCED ENGINE POWER AND DIV	ERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED LEAKING FUEL NOZZLE MANIFOLD PACKINGS.  MFG HAS DETERMINED 	THE PACKINGS TO BE ASSOCIATED WITH A MANUFACTURER`S QUALITY ESCAPE (REFERENCE: MFG SERVICE BULETIN SB21740) (TC NR 20070	704009)			2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007082000073	20070820	00073	EA  	2007	8	20	CA070704010      	2	20070505	G	7532		BLEED VALVE     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					COMPRESSOR	FAULTED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA			4107 								(CAN) ON APPROACH, AN ENGINE FADEC CAUTION LIGHT ILLUMINATED AND THE PILOT ELECTED TO SHUTDOWN THE ENGINE (PRECAUTIONARY	).  SUBSEQUENT INSPECTION REVEALED A FAULTY INTERCOMPRESSOR BLEED VALVE. (TC NR 20070704010)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007082000074	20070820	00074	NE  	2007	8	20	CA070704011      	2	20070514	G	7261		OIL SYSTEM      			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					ENGINE	OVERTEMP        	W				E				ENGINE SHUTDOWN         				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA								104058			(CAN) IN FLIGHT, THE ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE AND THE ENGINE WAS SHUTDOWN.  POST-FLIGHT INSPECTION RE	VEALED OIL LEAKAGE AT THE ENGINE (C) FLANGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 	(TC NR 20070704011)				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2007082000075	20070820	00075	EU  	2007	8	20	CA070704012      	1	20070511	G	2913	3022375	SEAL            			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  					HYDRAULIC PUMP	FRACTURED       	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND SUBESQUENTLY DECREASE.  OIL WAS SEEN ESCAPING FROM THE EN	GINE NACELLE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED A FRACTURED HYDRAULIC PUMP PAD OIL 	SEAL. (TC NR 20070704012)				1	L	7	2 	3T	3	T	RT	A54EU   	E4EA				 
2007082000076	20070820	00076	NE  	2007	8	20	CA070704014      	2	20070519	G	7310	ST3367009	PACKING         			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL MANIFOLD	FRACTURED       	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) FUEL WAS FOUND LEAKING FROM THE FUEL MANIFOLD DRAIN DURING TAXI.  SUBSEQUENT INSPECTION REVEALED LEAKING FUEL MANI	FOLD PACKINGS.  MFG HAS DETERMINED THE PACKINGS TO BE ASSOCIATED WITH A MANUFACTURER`S QUALITY ISSUE (REFERENCE MFG SB21	740). (TC NR 20070704014)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007082000077	20070820	00077	NE  	2007	8	20	CA070704015      	2	20070511	G	7261		ENGINE          								PWA   	PT6   	PT6A65AR    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  		SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	R		SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA								97048			(CAN) IN CRUISE, SMOKE WAS OBSERVED IN THE CABIN AND ENGINE POWER REDUCED UNCOMMANDED.  THE ENGINE WAS SHUTDOWN IN FLIGH	T AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED SEIZURE OF THE ENGINE AND OIL LEAKAGE	.  MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070704015)									4	T			E4EA	6	C	P44GL	 
2007082000078	20070820	00078	EA  	2007	8	20	CA070704016      	2	20070513	G	7210		GEARBOX         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	DISTRESSED      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								41553			(CAN) PRIOR TO START OF DESCENT, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE. DURING THE DESCENT THE ENGINE FLAMED OUT.  S	UBSEQUENT INSPECTION REVEALED REDUCTION GEARBOX DISTRESS.  MFG WILL INVESTIGATE THE EVENT AND ADVICE OF ROOT CAUSE ONCE 	ESTABLISHED. (TC NR 20070704016)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007082000079	20070820	00079	NE  	2007	8	20	CA070704017      	2	20070523	G	7200		ENGINE          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  						OVERTEMP        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A	J		FLAME/FIRE                	WARNING INDICATION        		CR	CRUISE         	1			CA								PJ0243			(CAN) IN CRUISE, THE ENGINE INTER-TURBINE TEMPERATURE WAS SEEN TO INCREASE AND FLAMES AND SPARKS WERE SEEN EXITING THE E	XHAUST.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISH	ED. (TC NR 20070704017)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081104			2008	11	4	CA070704018      	1	20070702	G	3240	95214071	LINER           	LORAL       	95409761    															BRAKE ASSY	SEPARATED       	W				D				RETURN TO BLOCK         				O			OTHER                     			LD	LANDING        	1			CA				2    							(CAN) DURING THE ROLLOUT AFTER LANDING, THE FLIGHT CREW NOTICED THE LT BRAKE PEDAL TRAVEL WAS MORE THAN NORMAL. UPON INS	P IT WAS NOTED THAT THE FIXED LININGS P/N 9521407-1 (2 OF THE 3) HAD SEPARATED FROM THE BRAKE ASSY. THE LININGS WERE LAT	ER LOCATED ON THE RUNWAY THAT THE ACFT HAD LANDED ON. THERE WAS NO VISIBLE EVIDENCE AS TO WHY THE LININGS SEPARATED. ONE	 THEORY IS THAT A FOREIGN OBJECT SUCH AS A ROCK WAS THROWN INTO THE BRAKE ASSY AT THE TIME OF LANDING. THE ACFT WAS INSP	ECTED, THE BRAKE ASSY WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. (TC NR 20070704018)															 
2007082000080	20070820	00080		2007	8	20	CA070705001      	2	20070528	G	7320		FADEC           			CESSNA	680   	680CE       	2076811	CE  											MALFUNCTIONED   	W				O				OTHER                   				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		LD	LANDING        	1			CA											(CAN) THE ENGINES FAILED TO RESPOND TO THROTTLE INPUT FOLLOWING TOUCHDOWN. PRELIMINARY INVESTIGATION REVEALED THE ISSUE 	RELATED TO THE FADEC`S RESPONSE TO ARMING THE THRUST REVERSERS ON APPROACH (NOT AN AFM PROCEDURE), COUPLED WITH A BOUNCE	 FOLLOWING INITIAL TOUCHDOWN.  P&WC WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20070705001)				2	L	7	2 	4F			RC	T00012WI					 
2007082000081	20070820	00081	CE  	2007	8	20	CA070705002      	1	20070530	G	2435		SEAL            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					STARTER GEN	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE OIL PRESSURE WAS SEEN TO REDUCE AND FLUCTUATE IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT 	INSPECTION REVEALED A FAULTY LIP SEAL (RECENTLY REPLACED) ON THE STARTER GENERATOR DRIVE SHAFT. (TC NR 20070705002)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007082000082	20070820	00082	EU  	2007	8	20	CA070705003      	1	20070528	G	2435	3022383	SEAL            			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	STARTER GEN	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ON A MAINTENANCE FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUB	SEQUENT INSPECTION REVEALED A LEAKING STARTER GENERATOR GARLOCK LIP SEAL. (TC NR 20070705003)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007082000083	20070820	00083	NE  	2007	8	20	CA070705004      	2	20070519	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA								PC0810			(CAN) IN CRUISE FLIGHT, THE ENGINE EMITTED A LOUD NOISE AND LOST POWER, RESULTING IN A FORCED LANDING.  MFG WILL MONITOR	 INVESTIGATION OF THE INCIDENT AND REPORT ROOT CAUSE ONCE DETERMINED. (TC NR 20070705004)					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007082000084	20070820	00084	NE  	2007	8	20	CA070705005      	2	20070303	G	7321	3244768	FCU             			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT642A      		NE  					ENGINE	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN FLIGHT THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION RESULTING IN AN OVER-TORQUE CONDITION.  SUBSEQUENT IN	SPECTION REVEALED A FAULTY FCU.  (TC NR 20070705005)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2007082000085	20070820	00085	EA  	2007	8	20	CA070705006      	1	20070618	G	5330	215300174	SKIN            			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	BS 584.5	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1308 								(CAN) A 3 INCH CRACK WAS DISCOVERED IN THE SKIN.  CAUSE AT HIS TIME IS UNKKOWN AIND IS UNDER FURTHER INVESTIGATRION (TC 	NR 20070705006)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007082000086	20070820	00086	EA  	2007	8	20	CA070705007      	1	20070618	G	5330	215300174	SKIN            			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	BS 584.5	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1308 								(CAN) A (5) INCH CRACK WAS DISCOVERED IN THE SKIN AT APPROX F/S 584.50 AND W/L100. CAUSE AT THE TIME IS NOT KNOWN AND IS	 UNDER FURTHER INVESTIGATION. (TC NR 20070705007)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
	20081104			2008	11	4	CA070705008      	2	20070705	G	7414	10160858	HOUSING         																	MAGNETO	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			499  								(CAN) MAG SENT IN FOR 500 HR INSP. FOUND MOUNTING EAR CRACKED WHERE HOLD-DOWN NUT AND WASHER CONTACT EAR. THIS IS A NEW 	STYLE OF CASTING FROM MFG WITH THE NAME "EMPIRE" CAST INTO THE INTERIOR OF THE HSG AND JUST THE LETTERS "TCM" CAST ON TH	E OUSIDE OF THE HSG. THE OLD STYLE OF HSG HAD EITHER "TCM" OR "BENDIX" AND THE MAGNETO INFORMATION BLOCK CAST INTO THE O	UTSIDE OF THE HSG. THE OLD STYLE OF HSG WOULD CRACK IF OVERTORQUED OR IF THE WRONG GASKET WAS USED IN APPROXIMATELY 1 OU	T OF 30 MAGS RECEIVED FOR INSP. IN THIS CASE 4 OF 6 MAGS WITH THE NEW CASTING HAVE CRACKS IN THIS LOCATION. SEPERATE SDR	`S WILL BE FILED FOR EACH MAGNETO. (TC NR 20070705008)														 
	20081105			2008	11	5	CA070705011      	2	20070705	G	7414	10160858	HOUSING         	BENDIX      																MAGNETO	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2000 								(CAN) MAGNETO SENT IN AS A CORE, BUT HAS SAME CRACK AS 3 OTHER MAGNETOS RECEIVED FOR REPAIR. THIS CRACK IS IN A NEW STYL	E OF CASTING PUT INTO PRODUCTION BY MFG.																		 
2007082000087	20070820	00087	SW  	2007	8	20	CA070705012      	1	20070705	G	2434	ALU8521LS	ALTERNATOR      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  						FAILED          	W				E				ENGINE SHUTDOWN         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA			400  								(CAN) ALTERNATOR FAILED ON STARTUP.  FOUND ROTOR JAMMING AND PULLEY HAD OVERHEATED.  LOOSE PARTS HEARD INSIDE ALTERNATOR	.  NO PREVIOUS INDICATIONS OF IMPENDING FAILURE. (TC NR 20070705012)					1	G	7	1 	3O	3	O	O	4H12    	1E10				 
	20081104		SW  	2008	11	4	CA070705013      	1	20070702	G	7810		GASKET          			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360G1A   	41898	EA  					EXHAUST	CRACKED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			210  								(CAN) DURING ROUTINE INSP, IT WAS NOTICED THAT NEARLY ALL OF THE GASKET BETWEEN THE FWD FLANGE AND THE EXHAUST MUFF HAD 	CRACKED AND FALLEN AWAY, LEAVING THE POSSIBILITY OF A CABIN EXHAUST LEAK. (TC NR 20070705013)					1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2008022000323	20080220	00323	CE  	2008	2	20	CA070706001      	1	20070706	G	3230	AN33701	RELAY           			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION OF THE HYD LANDING GEAR INSTALLATION THE LANDING GEAR RELAY EXHIBITED SIGNS OF HEAVY PITT	ING AND METAL TRANSFER. THE LANDING GEAR RELAY WAS REPLACED. (TC NR 20070706001)					1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
2007082000088	20070820	00088	GL  	2007	8	20	CA070706002      	2	20070705	G	7230	23056109	SCROLL          	RROYCE      		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					COMPRESSOR	WARPED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7120 			CAC70614					(CAN) DURING A GROUND RUN AN AIR LEAK WAS FOUND AT THE SCROLL DIFFUSER SPLIT LINE.  COMPRESSOR ASSY WAS CHANGED OUT. (TC	 NR 20070706002)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007082000089	20070820	00089	EU  	2007	8	20	CA070706003      	1	20070703	G	3240		BRAKE ASSY      			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					MLG	OVERHEATED      	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) HOT BRAKE INDICATION ON TAXI IN OF 460 CELSIUS.  BRAKE OVERTEMP INSPECTION CARRIED OUT WITH NO FAULTS.  CMC MESSAG	E BRAKE TEMP SENSOR OVERHEAT.  IAW FIM, REPLACE TEMP SENSOR.  PLACED ON MEL DUE NO STOCK. FOLLOWING DAY, RT IB/OB BRAKE 	TEMPERATURES CREPT UP TO 110/ 195 CELSIUS. THERE IS A HISTORY OF HYDRAULIC CONTROL PROBLEMS, POSSIBLE CAUSE IN THIS CASE	 MAY BE THE BRAKE CONTROL VALVE. (TC NR 20070706003)			2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2007082000090	20070820	00090	GL  	2007	8	20	CA070706004      	2	20070705	G	7320	23065144	FUEL CONTROL    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14467	1070 							(CAN) FUEL CONTROL WAS INTERMITTENT ON ENGINE LIGHT-OFF DURING A START.  FUEL CONTROL CHANGED OUT. (TC NR 20070706004)						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2008022000324	20080220	00324	NM  	2008	2	20	CA070706005      	1	20070703	G	5280	450530501	SHEAR PIN       			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LG DOOR	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE PILOT SELECTED GEAR UP, THE GEAR UP LIGHT FAILED TO ILLUMINATE. THE LANDING GEAR WAS EXTENDED AN	D THE AIRCRAFT LANDED AT AIRPORT. UPON INVESTIGATION THE LANDING GEAR DOOR SHEAR PIN WAS FOUND SHEARED. THE PIN WAS REPL	ACED, THE AIRCRAFT WAS PLACED ON JACKS AND A FUNCTION CHECK OF THE LANDING GEAR AND INDICATING SYSTEM WAS COMPLETED WITH	 NO FAULTS. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070706005)			1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2007082000091	20070820	00091	EA  	2007	8	20	CA070707001      	1	20070706	G	2910	0860163002	ACCUMULATOR     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HYD SYSTEM	SEPARATED       	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			25942								(CAN) DURING TAXI-OUT, HYD 1 LO PRESS MESSAGE CAME ON.  THE CREW REPORTED LOUD BANG FROM AFT PART OF CABIN.  CREW EXECUT	ED RELEVANT ABNORMAL CHECKLISTS AND RETURNED TO RAMP.  AFTER VERIFICATION BY THE MTCE CREW, THEY FOUND OUT THAT THE NR 2	 HYDRAULIC ACCUMULATOR SEPARATED. (TC NR 20070707001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081104			2008	11	4	CA070708001      	4	20070421	G	2562	ELT10	ELT             			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					CABIN	MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) ELT FOUND DEFECTIVE DURING ROUTINE INSP. ELT WAS FOUND MAKING SQUELCHING SOUND THROUGH RADIO, ON FURTHER INVESTIGA	TION IT WAS FOUND THAT ELT WAS ACTIVATED WHICH COULD NOT BE SWITCHED-OFF EVEN AFTER DISCONNECTING THE CONNECTOR/POWER. E	LT WAS REMOVED FROM ACFT AND BATTERY WAS DISCONNECTED TO DEACTIVATE THE ELT.  ELT WAS SENT  FOR REPAIR. (TC NR2007070800	1)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082000092	20070820	00092	WP  	2007	8	20	CA070709001      	1	20070706	G	2700	24031404021	SHAFT           			CVAC  	30    	30          	2423202	WP  	ALLSN 	501D  	501D13H     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	ROLL FORCE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ROLL FORCE MODIFICATION WAS BEING INSTALLED IN THE  AIRCRAFT IAW STC SA05-49.  UPON TORQUING THE PILOT`S YOKE 	ASSEMBLY SHAFT IAW THE INSTRUCTIONS CONTAINED IN DOCUMENT K130-102-001-012, THE FLANGE ON THE SHAFT P/N 240-3140402-1 CR	ACKED.  THE REMAINING AIRCRAFT IN THE FLEET WERE INSPECTED FOR SIGNS OF PLAY WITH NO DEFECTS NOTED. THE AIRCRAFT ARE ALS	O BEING INSPECTED FOR EXCESSIVE BREAK AWAY TORQUE OF CONTROL YOKE SHAFT NUT. ANY ADDITIONAL FINDINGS WILL BE FORWARDED U	PON COMPLETION OF THE INSPECTIONS. (TC NR 20070709001)		2	L	7	4 	4J	4	T		4A30    	E282	6	C	P898	 
2007082000093	20070820	00093	NM  	2007	8	20	CA070709002      	1	20070707	G	2420	HCAIN022	GENERATOR       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 2	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) AT THE END OF EXTENSIVE POST BLOCK CHECK GROUND RUNS; THE NR 2 ENG GEN FELL OFF LINE AND NR 1 TRU AND AC BUS FELL 	OFF LINE; TRIED TO POWER BACK AND RESET IT WAS NOTICED THAT THE AC GEN CAUTION LIGHT WAS NOT SHOWING. SO THE AIRCRAFT WA	S SHUTDOWN AND AFTER SOME INVESTIGATION IT WAS FOUND THAT THE AC GEN CONTACTOR HC-AIN-022 HAD FAILED INTERNALLY MELTING 	THE RELAY AND ASSOCIATED WIRING. (TC NR 20070709002)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008031900147	20080319	00147	NE  	2008	3	19	CA070709003      	2	20070705	G	7320	5018T64G02	MANIFOLD        			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					LT FUEL	FRACTURED       	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA			10521	209  				280140MA			(CAN) THE PILOTS NOTICED A WARM SEMI SMOKE SMELL, AND OBSERVED A T5 RISE IN NR 1 ENGINE. THE FIRE LIGHT ACTIVATED ON NR 	1 ENGINE. THE ENGINE WAS SHUT DOWN AS WELL AS A THE FIRE BOTTLES WERE ACTIVATED. THE AC LANDED WITH ONE ENGINE WITH NO I	NCIDENT. THE ENGINE WAS REPLACED. ENGINE TSN 23764.8, TSO 2373.5, (TC NR 20070709003)				2	G	7	2 	4U	4	U		1H15    	1E3				 
2007082000094	20070820	00094	NM  	2007	8	20	CA070709004      	1	20070706	G	3244	DR7622T	TIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LT INNER TIRE BLOWN AFTER TAKEOFF. UNSCHEDULED LANDING CARRIED OUT. A/C TOWED TO HANGER.  INSPECTION AND NR 1 AND 	NR 2 MAINWHEELS REPLACED.  TIRE WAS A RETREAD R2. (TC NR 20070709004)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081104		CE  	2008	11	4	CA070710001      	1	20070705	G	2434	DOFF10300JR	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA				351  							(CAN) ALTERNATOR NOT CHARGING . (TC NR 20070710001)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082000095	20070820	00095	NM  	2007	8	20	CA070710002      	1	20070615	G	3510	17426008	OXYGEN MASK     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) F/O`S OXYGEN MASK WHEN DONED, WEARER COULD NOT EXHALE WHEN BREATHING. ENGINEERING INVESTIGATION INDICATES THAT THE	 MASK EXHALE VALVE IS DEFECTIVE. MASK REPLACED. AIRCRAFT RETURNED TO SERVICE SATISFACTORY. MASK HAS BEEN RETURNED TO THE	 MANUFACTURER FOR REPAIR AND WITH A REQUEST FOR A STRIP REPORT. (TC NR 20070710002)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007082000096	20070820	00096	NM  	2007	8	20	CA070710003      	1	20070531	G	3150	301450301	PSEU            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROXIMITY SENSOR	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE CLIMBING THROUGH 9000 FT, THE ENGINE DISPLAY POWERPLANT ADVISORY ILLUMINATED. FOLLOWING DISCUSSIONS W	ITH BASE ENGINEERING THE CREW DECIDED TO RETURN THE AIRCRAFT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHO	UT INCIDENT. THE POWERPLANT ADVISORY FAULT CODE 338 IS THE 3RD OCCURRANCE ON THIS AIRCRAFT. FOLLOWING ADVICE FROM THE MF	G AND DETAILED TROUBLESHOOTING THE AIRCRAFT`S PSEU WAS REPLACED. AIRCRAFT WAS RELEASED BACK TO SERVICE WHERE IT HAS OPER	ATED SINCE WITHOUT INCIDENT. (TC NR 20070710003)		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007082000097	20070820	00097	EA  	2007	8	20	CA070710004      	2	20070426	G	7230	3034051	GUIDE VANE      			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				73   				86123			(CAN) DURING FLIGHT, THE TURBINE TEMPERATURE ROSE SUDDENLY FROM 738 TO 785 DEGREES CELSIUS. A BORESCOPE INSPECTION REVEA	LED DAMAGE TO THE CT GUIDE VANE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE HOT SECTION WAS REMOV	ED FROM THE ENGINE AND FURTHER INSPECTED. ONE OF THE CT GUIDE VANES AIRFOIL-COOLING DUCT SURFACE HAD BEEN PREVIOUSLY RE	PAIRED. THE VANE CRACKED/FAILED AROUND THE WELDS ALLOWING THE COOLING DUCT TO OPEN UP AND BREAK AWAY.  WITHOUT THE PROPE	R COOLING THE VANE BURNED THROUGH. THE HOLE IN THE VANE CHANGED THE AIRFLOW ALLOWING DIRECT FLOW TO THE CT BLADES IN TUR	N CAUSING THEM TO OVERHEAT. GUIDE VANE CSO 48.  THIS IS THE SECOND FAILURE OF THIS NATURE AS  THE OTHER FAILURE OCCURRED	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2007082000098	20070820	00098	CE  	2007	8	20	CA070711001      	1	20070605	G	7120		TUBE            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	RT NACELLE	CRACKED         	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			2590 								(CAN) ONE TUBE CRACKED NEAR RT REAR ENGINE LOAD MOUNT.  NEW MOUNT INSTALLED. (TC NR 20070711001)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2008022000325	20080220	00325	CE  	2008	2	20	CA070711002      	1	20070708	G	3020	1013800019	BOOT            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	HORIZ STAB	DAMAGED         	W				A				UNSCHED LANDING         				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT DEPARTED AND BEGAN TO CLIMB TO CLEARED ALTITUDE. AS THE AIRCRAFT PASSED 5500 FEET THERE WAS A VIBRATI	ON OR BUFFETING FELT THROUGH THE CONTROL COLUMN. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. A THROUGH INSPECTION WA	S CARRIED OUT WHICH REVEALED A DAMAGED LT HORIZONTAL DE-ICE BOOT. SEVERAL HOLES WERE FOUND AND REPAIRED IAW APPROVED PRO	CEDURES. THE AIRCRAFT WAS RETURNED TO SERVICE AND OPERATED WITHOUT ANY FURTHER PROBLEMS. (TC NR 20070711002)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007082000099	20070820	00099	EA  	2007	8	20	CA070711003      	1	20070711	G	2810	215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  		LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1924 								(CAN) FUEL CELL NR 7 RT, LEAKING BY THE LOWER INTERCONNECT CORNER.   A/C HOURS: 1924 CYCLES: 1236 DROPS: 9808  (TC NR 20	070711003)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007082000100	20070820	00100	EA  	2007	8	20	CA070711004      	1	20070711	G	2810	K215T6400212	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  											LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) TESTED BEFORE INSTALLATION, THE CELL HAS BEEN FOUND WITH LOOSE LOWER PROBED ADAPTOR AND LEAKING BY THE TOP CORNER 	REPAIR PATCH . THE CELL HAS BEEN REJECTED. (TC NR 20070711004)					2	H	7	2 	4T			RT	A14EA   					 
2007082000101	20070820	00101	CE  	2007	8	20	CA070711005      	1	20070711	G	2510	05142031	SEAT            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DEFECT REPORTED IN THE JOURNEY LOG BOOK THAT RT SEAT WOULD NOT ADJUST.  REMOVED SEAT, INSPECTED, AND FOUND THE SEA	T BOTTOM FRAME CRACKED COMPLETELY IN (2) PIECES.  AREA IS DIFFICULT TO INSPECT BECAUSE OF UPHOLSTERY INSTALLATION.  LOWE	ST TIME IN THE FLEET. (TC NR 20070711005)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082000102	20070820	00102	EA  	2007	8	20	CA070711006      	1	20070711	G	2810	K215T6400212	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  											LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) TESTED BEFORE INSTALLATION, THE CELL HAS BEEN FOUND LEAKING BY A PIN HOLE NEAR UPPER PROBE ADAPTOR AND REJECTED. (	TC NR 20070711006)					2	H	7	2 	4T			RT	A14EA   					 
2007082000103	20070820	00103	GL  	2007	8	20	CA070711007      	1	20070710	G	2823	TC17300	SELECTOR        			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUEL	STIFF           	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) REMOVED CABLE DRUM FROM FUEL SELECTOR, LUBRICATED SELECTOR WITH YIELD AND REINSTALLED CABLE DRUM. (TC NR 200707110	07)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007082000104	20070820	00104	NM  	2007	8	20	CA070712001      	1	20070709	G	6120	699018002	CONTROLLER      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR1 ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F	Y	J	FLT CONT AFFECTED         	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA			3109 								(CAN) DURING CRUISE AT 25,000 FT, THE NR 1 POWERPLANT AND NR 1 PEC (PROP ELECTRONIC CONTROLLER) CAUTION LIGHTS ILLUMINAT	ED. THE NR 1 ENGINE WENT INTO THE AMBER.  PILOTS CARRIED OUT AN IN-FLIGHT SHUTDOWN, DECLARED AN EMERGENCY AND RETURNED T	O BASE.  FAULT CODES 161 AND 157 WERE LOGGED IN THE CDS. PROPELLER ELECTRONIC CONTROL UNIT REPLACED, OVERSPEED GOVERNOR 	(OSG) FAULTS HAVE BEEN SINCE BEEN CLEARED AND FUNCTIONAL CHECKS HAVE BEEN COMPLETED. (TC NR 20070712001)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007082000105	20070820	00105	EU  	2007	8	20	CA070712002      	1	20070710	G	2910	TC2500065500	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	HYDRAULIC SYS	PERFORATED      	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER DEPARTING, THE CREW OBSERVED BOTH THE LT AND RT HYDRAULIC PRESSURE LOSS INDICATION LIGHTS WERE ILLUMINATED. 	THE AIRCRAFT DIVERTED  AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND THE NR 2 HYDRAULIC PRESSURE RETURN LINE TO 	THE HP FILTER IN THE WHEEL WELL PERFORATED DUE TO CONTACT WITH A BROKEN CLAMP WHICH SUPPORTS THE GENERATOR COOLING BLEED	 AIR LINE. BOTH ITEMS WERE REPLACED AFTER WHICH THE AIRCRAFT WAS SATISFACTORILY GROUNDED AND RETURNED TO SERVICE. FIRST 	AIR CONDUCTED A CHECK OF THE REMAINING SAME TYPE AIRCRAFT OPERATED AND FOUND NO SIMILAR CONDITION PRESENT. (TC NR 200707	12002)	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
	20081104			2008	11	4	CA070712003      	4	20070712	G	2562	ELT97A256	ELT             																		ACTIVATED       	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) ELT ACTIVATED ON FIRST ENGINE START. DIDN`T LEAVE THE GROUND.  (TC NR 20070712003)																			 
2007082000106	20070820	00106	EA  	2007	8	20	CA070713001      	1	20070710	G	3010	14463108	PICCOLO TUBE    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						RUPTURED        	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW RECEIVED AN ANTI-ICE DUCT WARNING MESSAGE DURING FLIGHT. THE APPLICABLE SYNOPTIC PAGE SHOWED THE R	T WING LEADING EDGE BEING AT FAULT. WING ANTI-ICE SWITCH WAS SELECTED FROM NORMAL TO STAND-BY WITHOUT SUCCESS. DURING TR	OUBLESHOOTING, MAINTENANCE DISCOVERED THE RT WING OB ANTI-ICE DUCT (PICCOLO TUBE) REF IPC 30-11-00-10-240C END CAP MISSI	NG. THE WELDED PICCOLO TUBE END CAP HAS RUPTURED FROM THE ASSY. THE ANTI-ICE DUCT ASSY WAS REPLACED IAW AMM 30-11-41 AND	 THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20070713001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000326	20080220	00326	EU  	2008	2	20	CA070713002      	1	20070712	G	6510	350A34021006	DRIVE SHAFT     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					TAIL ROTOR	OUT OF ROUND    	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			2473 								(CAN) UNABLE TO BALANCE SHORT SHAFT, RUNOUT CHECK OF FWD END OF SHAFT WAS .017 INCH. PREVIOUS T-CHECK REVEALED A RUNOUT 	OF .009 INCH WITH TROUBLES OF SAME NATURE AND SHORT SHAFT WAS INSPECTED AND FOUND TO BE BENT, AND REPLACED WITH BALANCE 	OBTAINED. (TC NR 20070713002)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007082000107	20070820	00107	EA  	2007	8	20	CA070713003      	2	20070706	G	7313	252416314	SERVO           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL INJECTOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1225 				L653661A			(CAN) FUEL INJECTOR SERVO ON LT ENGINE FOUND TO HAVE AN INTERNAL LEAK AND WOULD NOT SHUTDOWN PROPERLY.  SERVO WAS REMOVE	D AN OVERHAULED UNIT INSTALLED ENGINE GROUND RUN. (TC NR 20070713003)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007082000108	20070820	00108	GL  	2007	8	20	CA070715001      	2	20070714	G	7261		FITTING         			LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	OIL SYSTEM	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE CREW NOTICED A LOSS OF OIL QUANTITY ON THE NR 3 ENGINE. THIS LOSS WAS FOLLOWED BY A FLUCTUATION IN THE REDUCTI	ON GEARBOX PRESSURE. THE ENGINE WAS SHUTDOWN PRIOR TO LANDING. IT WAS DETERMININED THAT A FITTING ON THE TURBINE SECTION	 WAS LEAKING. THERE WAS 3-4 GALLONS OF OIL REMAINING IN THE RESEVOIR, THE AIRCRAFT WAS FERRIED FOR AN ENGINE CHANGE. (TC	 NR 20070715001)			2	L	7	4 	4T	4	T		4A22    	E282	6	C	P898	 
2007082000109	20070820	00109	EA  	2007	8	20	CA070716001      	1	20070714	G	5343	215340711	MOUNT           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	R2800CA3    	52026	NE  	HAMSTD	43E	43E60       	NE  	LANDING GEAR	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE LANDING GEAR WAS RETRACTED AND THE RT/MAIN GEAR DID NOT INDICATE UP AND LOCKED. THE GEAR WAS SE	LECTED DOWN AND ALL (3) GEAR INDICTED DOWN AND LOCKED. MAINTENANCE HAS FOUND THE RT MAIN GEAR ACTUATOR MOUNTING DAMAGED.	 PARTS 215-34071-1,215-34071,215-34014-3,215-34014-2 ON ORDER. (TC NR 20070716001)				2	H	7	2 	4R	4	R	RT	A14EA   	5E8	6	C	P871	 
2007082000110	20070820	00110	EU  	2007	8	20	CA070716002      	1	20070713	G	3150		WARNING MESSAGE 			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					STAB TRIM	ACTIVATED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			51519	37472							(CAN) AFTER DEPARTURE, AN ECAM MSG INDICATED STAB TRIM FAILURE.  NEITHER OF THE AUTOPILOTS COULD BE RE-ENGAGED.  AN EMER	GENCY WAS DECLARED WITH ATC AND THE FLIGHT LANDED APPROX 7.5 TONS OVERWEIGHT. (TC NR 20070716002)					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007082000112	20070820	00112	NM  	2007	8	20	CA070717001      	1	20070626	G	2497		WIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	EDU	DAMAGED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) LATE IN THE AIRCRAFT`S LANDING SEQUENCE, THE FLIGHT DECK ENGINE DISPLAY SUFFERED A FAILURE CAUSING THE DISPLAY TO 	GO BLANK. THE LANDING WAS COMPLETED WITHOUT INCIDENT. ONCE SHUTDOWN ON THE RAMP, THE CREW IDENTIFIED THAT ONE OF THE ESI	D CIRCUIT BREAKERS WAS (POPPED).  FOLLOWING ADVICE FROM ENGINEERING, ATTEMPTS TO RESET THE CIRCUIT BREAKER WERE UNSUCCES	SFUL. ON SITE ENGINEERING INVESTIGATION IDENTIFIED THAT BOTH POWER WIRES TO THE EDU WERE DAMAGED DUE CHAFING RESULTING I	N A SHORT CIRCUIT TO GROUND. DAMAGED WIRES WERE REPAIRED IAW MM PROCEDURES. IT WAS ESTABLISHED THAT THE WIRE CHAFING WAS	 DUE TO INCORRECT FACTORY INSTALLATION OF THE WIRING LOOM EDU CONNECTOR BACKSHELL WHICH IN TURN ALLOWS THE LOOM WIRES TO	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007082000113	20070820	00113	NE  	2007	8	20	CA070717002      	2	20070704	G	7321	4120T01P02	FMU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					NR 1 ENGINE	UNSERVICEABLE   	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) STARTING T/O, NR 1 ENGINE DID NOT RESPOND TO THROTTLE IN TOGA POSTION.  ENGINE REMAINED AT IDLE. AFTER 10 SECONDS 	L ENGINE FLAMEOUT CAUTION MSG. T/O ABORTED AT 40 KNOTS.  MDC (MAINTENANCE DIAGNOSTICS COMPUTER) INTERROGATED BY MAINTENA	NCE. FAULT CODE 353 BIT 29 SET, FMU CMD/POS DISAGREE (WF METERING VALVE ACTUAL POSITION DOES NOT MATCH EXPECTED POSITION	 BASED ON COMMAND).   SUSPECT WF METERING VALVE TORQUE MOTOR. SUSPECT FAULTY COMPONENT: FMU 4120T01P02).  FMU P/N4120T01	P02  S/N12391265 REMOVED AND CHANGED IAW AMM 73-21-02-400-801-A01. ENGINE LEAK CHECKED AND FUNCTIONED SATISFIED. AIRCRAF	T RETURNED TO SERVICE. (TC NR 20070717002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000327	20080220	00327	SW  	2008	2	20	CA070717003      	1	20070629	G	5210	2050314352	BRACKET         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					PAX DOOR	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO THE LANDING AREA, THE (DOOR LOCK) LIGHT ON CAUTION PANEL ILLUMINATED. AIRCRAFT LANDED SAFELY WITHOU	T ANY FURTHER INCIDENT. UPON LANDING THE ENGINEER EXITED THE AIRCRAFT AND PHYSICALY CHECKED ALL DOORS AND PANELS TO ENSU	RE THAT THEY WERE CORRECTLY SECURED. NO DOORS OR PANELS WERE FOUND OPEN.  UPON INVESTIGATION OF THE RT PASSENGER/CARGO D	OOR, IT WAS FOUND TO BE LOOSE IN THE DOOR TRACK. FURTHER INVESTIGATION REVEALED THAT THE UPPER FWD ROLLER BRACKET HAD FA	ILED. THIS ALLOWING THE MICRO-SWITCH TO BE DEACTIVATED, AND THE LIGHT COMING ON.   THE BRACKET WAS REPLACED AND NO FURTH	ER PROBLEMS EXISTED. (TC NR 20070717003)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2007082000114	20070820	00114	EA  	2007	8	20	CA070717004      	1	20070628	G	5210	85210240055	ROD             			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	PAX DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PASSENGER DOOR AFT SUPPORT STRUT BROKE MAKING IT DIFFICULT TO OPEN THE MAIN CABIN DOOR.  EXPLANATION CODES: 7(A) S	PECIAL OPS- AIRCRAFT HAD ALREADY LANDED AND PASSENGERS WERE ABOUT TO DISEMBARK. 7(B)  DOOR WAS DIFFICULT TO OPEN. 7(C) D	OOR WAS OPENED BY (2) CREW MEMBERS. (TC NR 20070717004)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000115	20070820	00115	NE  	2007	8	20	CA070717005      	2	20070619	G	7310	021578201	FILTER          			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	FUEL PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION THE INLET FILTER WAS REMOVED. THE FILTER COVER (CAP) WAS FOUND CRACKED UNDER THE O-RING LOCAT	ION ALL THE WAY AROUND. IT APPEARS TO HAVE BEEN OVER TORQUED. IT WAS NOT LEAKING AT THIS TIME. THE INLET FILTER ASSEMBLY	 WAS REPLACED. (TC NR 20070717005)				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	5	C	P60GL	 
2008030600046	20080306	00046		2008	3	6	CA070717006      	4	20070705	G	3197		WIRE HARNESS    			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  						BURNED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, PILOT NOTED THE V/A INDICATION ON THE VEMD WAS OSCILLATING INTERMITTENTLY BETWEEN PARAMETERS	, AS WELL, THE LOW ROTOR AURAL WARNING WAS INTERMITTENTLY SOUNDING AND AT TIMES WAS ON STEADY. AT NO TIME WERE ANY ANOMO	LIES NOTICED IN THE COCKPIT ENGINE INDICATIONS OR ENGINE PERFORMANCE. UPON LANDING, THE PILOT NOTED THE VEMD CIRCUIT BRE	AKER ON THE COCKPIT PANEL WAS TRIPPED. AFTER SUBSEQUENT TROUBLESHOOTING, IT WAS FOUND THAT THE WIRE HARNESS LEADING UP T	O THE VEMD WAS PINCHED BETWEEN THE TOP AFT LT CORNER OF THE VEMD (VIEWED LOOKING FORWARD WITH VEMD INSTALLED AND GLARESH	IELD REMOVED) AND THE GLARESHIELD ITSELF. SEVERAL WIRES WERE FOUND CHAFED THROUGH AND/OR BURNED THROUGH ALTOGETHER. UPON	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2007082000116	20070820	00116	CE  	2007	8	20	CA070717007      	1	20070623	G	3230	NAS464P6A16	BOLT            			CESSNA	177   	177RG       	2073709	CE  										MLG	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3940 								(CAN) MAIN GEAR JAMMED ON RETRACTION FROM TAKEOFF. LANDED WITH MAIN GEAR PARTIALLY EXTENDED. (TC NR 20070717007)						1	H	7	1 	3O				A20CE   					 
2007082000117	20070820	00117		2007	8	20	CA070717009      	4	20070512	G	6113		BRACKET         			CESSNA	120   	120         	2071402	CE  	CONT  	C85   	C8512F      	17008	SO  	MCAULY	1B90	1B90CM      	GL  	SPINNER	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) V-BRACKET OF SPINNER BROKE ON ONE SIDE, THAT CAUSED OFFSET OF SPINNER WHICH CAUSED VIBRATION AND DECIDED TO CONDUC	T A PRECAUTIONARY LANDING ON A FARMERS FIELD. NO FURTHER DAMAGE. (TC NR 20070717009)					1	H	7	1 	3O	3	O		A768    	E233	5	N	P842	 
2007082000118	20070820	00118	NM  	2007	8	20	CA070717010      	1	20070703	G	2797	BACC63BV22F55PN	CONNECTOR       			BOEING	737   	737800*     	       	NM  	CFMINT	CFM56 	CFM567B26US 	 	NE  					TE FLAPS	CORRODED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			19956								(CAN) AFTER FLAP 25 TAKEOFF, WHEN FLAP RETRACTION INITIATED, FLAP ASYMMETRY INDICATED AND TE FLAP SKEW SENSOR CB POPPED.	 AIRCRAFT RETURNED TO JTR. SFCC BITE TEST CARRIED OUT, MSG 27-51407 INTERMITTENT. FIM TASK 27-51-00-810-848 CARRIED OUT 	WITH NO FINDINGS. VISUAL CHECK OF SLAT/FLAP SYSTEM CARRIED OUT WITH NO FINDINGS. OVERWEIGHT LANDING INSP CARRIED OUT WIT	H NO FINDINGS. AC DEPARTED TO DUB. ON APPROACH TO DUB, MACH TRIM LIGHT CAME ON MOMENTARY, FOLLOWED BY NO PITCH COMMANDS 	ON CAPTAIN`S FD, NO AP A AND MAGENTA IAS INDICATION ON CAPTAIN`S DU. WHEN FLAP SELECTED TO 1, FLAP ASYMMETRY INDICATION 	OBSERVED AND TE FLAP SKEW SENSOR CB WAS FOUND POPPED. AFTER EXTENSIVE TROUBLESHOOTING A SHORT WAS FOUND IN THE LT TE FLA	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007082000119	20070820	00119	CE  	2007	8	20	CA070717011      	1	20070621	G	3213	21A05000016	ARM             			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A1F6    	41514	EA  	MCAULY	1A200	1A200FA     	GL  	FLOATS	BENT            	W				E				ENGINE SHUTDOWN         				O			OTHER                     			LD	LANDING        	1			CA			244  			23076					(CAN) ON ROLL OUT AFTER LANDING THE RT MAIN LANDING GEAR COLLAPSED. INVESTIGATION FOUND THAT THE ACTUATING CYLINDER BENT	 (P/N D68194-A-4). FURTHER INVESTIGATION FOUND THE RETRACT ARM P/N 21A05000-016 HAD WORN ELONGATED BOLT HOLES NOT ALLOWI	NG A DOWN LOCK OVER CENTRE POSITION. (TC NR 20070717011)				1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P874	 
2007082000120	20070820	00120	NE  	2007	8	20	CA070717012      	2	20070611	G	8510	288935	THRUST BEARING  			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	PROPELLER	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			851  								(CAN) WHILE TAXIING FROM DOCK, THE AIRCRAFT ENGINE STARTED SHAKING AND THE PILOT SHUT THE ENGINE DOWN. AIRCRAFT TOWED BA	CK TO DOCK. AFTER RE-STARTING, STRANGE NOISES FROM NOSE CASE, AND PROPELLER LOOKED (OUT OF TRACK).  PROPELLER REMOVED FR	OM COVER ON NOSE CASE REMOVED. BEARING SEPARATOR HAD STARTED TO BREAK UP. (TC NR 20070717012)				1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
2007082000121	20070820	00121	EA  	2007	8	20	CA070717014      	2	20070711	G	7261	061040M0240180	LINE            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE OIL	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE CREW OF FLOATPLANE EXPERIENCED A 10 LB LOSS OF TORQUE IN CRUISE ALONG WITH LOWERED OIL PRESSURE AND AN INCREAS	E IN OIL TEMP.  THE PILOT CONTINUED THE FLIGHT TO A MAINTENANCE BASE USING REDUCED POWER ON THE AFFECTED ENGINE.  AN UNE	VENTFUL LANDING AND DOCKING WAS MADE.  MAINTENANCE INVESTIGATION REVEALED THAT THE MAJORITY OF THE ENGINE OIL SUPPLY HAD	 BEEN EJECTED THROUGH THE ENGINE BREATHER SYSTEM.  INSPECTION OF THE ENGINE OVERBOARD BREATHER LINE INTERNALLY REVEALED 	THAT IT HAD BROKEN DOWN AND PARTIALLY PLUGGED THE ACCESSORY CASE VENTING SYSTEM.  THIS CAUSED THE ACCESSORY CASE TO PRES	SURIZE AND THE ENGINE OIL TO VENT OVERBOARD.  THE BREAKDOWN OF THE LINE RESULTED FROM THE LINE BEING POORLY ROUTED DURIN	1	H	7	2 	3T	3	T	RT	A9EA    	E2NE	6	C	P15EA	 
2007082000122	20070820	00122	NE  	2007	8	20	CA070717015      	2	20070711	G	7321	806304101A	FUEL CONTROL    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA			590  	63   							(CAN) ON TAKEOFF, THE FULL ENGINE POWER (43 PSI) WAS NOT ACHIEVABLE, 35 PSI WAS ALL THE ENGINE WOULD PRODUCE. THE PILOT 	REPORTED ENGINE WAS NOT CONTROLABLE WITH POWER LEVER WHEN PULLED TO IDLE (ENGINE AT 35 PSI TORQUE). ADVISED NOT TO TRY A	ND START THE ENGINE AND TO REPLACE THE FCU. FCU WAS REPLACED AND ALL ENGINE RUNS CHECKED SERVICEABLE. (TC NR 20070717015	)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007082000123	20070820	00123		2007	8	20	CA070717016      	4	20070705	G	2562	C5895120103	ELT             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CABIN	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA				91   							(CAN) EARLY ACTIVATION. SELF-ACTIVATION REPORTED TWICE. (TC NR 20070717016)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007082000124	20070820	00124	NM  	2007	8	20	CA070717017      	1	20070703	G	5753	NAS679A3W	NUT             			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TE FLAPS	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, CREW SELECTED FLAPS FROM 2 TO 5 AND HAD AN AMBER LIGHT INDICATION FOR THE NR 1 KRUGER FLAP INDICATING	 STILL RETRACTED. FELT MODERATE VIBRATION AND DECLARED AN EMERGENCY.  UNEVENTFUL LANDING.  MAINTENANCE CYCLED SYSTEM AND	 COULD NOT FAULT. FURTHER INSPECTION FOUND THE NR 1 KRUGER FLAP SWITCH LINK BOLT/NUT LOOSE.  (TC NR 20070717017)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007082000125	20070820	00125	GL  	2007	8	20	CA070717019      	1	20070717	G	5270	SAL2D864	PLUNGER         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	DOOR SWITCH	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1090 								(CAN) AT INSPECTION OBSERVED THE FRONT DOOR HANDLE IN OPEN POSITION BUT STILL ABLE TO START ENGINE.   UPON INSPECTION, F	OUND WITH DOOR OPEN MANUALLY OPERATING PLUNGER ON FORWARD DOOR LOCK OUT SWITCH ON LOWER DOOR SILL, FOUND SWITCH PLUNGER 	SEIZED IN CLOSED POSITION. THIS CAN ALLOW AIRCRAFT TO BE STARTED WITH FORWARD DOOR NOT LATCHED PROPERLY. RECTIFICATION I	S TO REPLACE SEIZED SWITCH PLUNGER AND LUBRICATE SWITCHES ON A REGULAR BASIS. (TC NR 20070717019)			1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007082000126	20070820	00126	NM  	2007	8	20	CA070718001      	1	20070708	G	7931	310573501A	REGULATOR       			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE OIL	FLUCTUATES      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA				8278 				121242			(CAN) DURING FLIGHT, THE OIL PRESS INDICATOR NR 1 ENGINE, DROPPED TO 50 PSI. QRH DRILL COMPLETED, UNSCHEDULED LANDING CO	MPLETED. OIL PRESSURE REGULATOR ASSEMBLY REPLACED IAW AMM 71-01-50, SYSTEM TESTED SERVICEABLE AND AIRCRAFT RETURNED TO S	ERVICE. (TC NR 20070718001)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000127	20070820	00127	CE  	2007	8	20	CA070718002      	1	20070717	G	3230	2317100016	ACTUATOR        			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					NLG	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			4538 	4538 							(CAN) DURING ARRIVAL, NOSE LANDING GEAR WOULD NOT INDICATE DOWN AND LOCK.  ALTERNATE GEAR EXTENSION WAS PERFORMED.  AIRC	RAFT WAS FERRIED, FUNCTIONAL CHECK OF THE EMERGENCY GEAR EXTENSION WAS CHECKED, NOSE GEAR STAYED IN WHEEL WELL.  FREE FA	LL PRESSURE TESTED AND FOUND TO BE BETWEEN 85 TO 90 LBS (MAX LIMIT 20 LBS).  GEAR DOOR AND GEAR ACTUATOR WAS DISCONNECTE	D AND GEAR FREE FALL WAS CHECKED AND FOUND TO BE WITHIN LIMITS.  SUSPECT FAULTY INTERNAL GEAR ACTUATOR LOCKING SLEEVE.  	NOSE GEAR ACTUATOR REPLACED.  FUNCTIONAL CHECK CARRIED OUT-SERVICEABLE. (TC NR 20070718002)		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007082000128	20070820	00128		2007	8	20	CA070718003      	4	20070717	G	3418	906100004	COMPUTER        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	STALL WARNING	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			8277 								(CAN) DURING CRUISE, THE NR 2 STALL SYSTEM FAIL AND PUSHER SYSTEM FAIL CAUTION LIGHTS ILLUMINATED.  QRH CHECKLIST WAS PE	RFORMED.  UNSCHEDULED LANDING COMPLETED. DUAL STALL WARNING COMPUTER DETERMINED TO BE THE CAUSE OF THE REPORTED DEFECT. 	 DUAL STALL WARNING COMPUTER REPLACED IAW AIRCRAFT MM CHAPTER 27-33-00 AND SYSTEM TESTED SERVICEABLE.  AIRCRAFT RETURNED	 TO SERVICE. (TC NR 20070718003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000129	20070820	00129	CE  	2007	8	20	CA070718004      	1	20070714	G	6120	022A431113	LEVER           			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROP PITCH	LOOSE           	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			4539 	4539 							(CAN) THE PPC LEVER WAS FOUND SEPARATED FROM THE PPC INPUT SHAFT.  THE BOLT WAS OF THE CORRECT P/N, YET WAS THREAD BOUND	 WITHOUT PRODUCING ENOUGH TENSION TO HOLD THE PPC ARM ONTO THE PPC SHAFT.  THE PPC ARM WAS REINSTALLED AND A WASHER WAS 	PLACED UNDER THE HEAD OF THE BOLT TO PROVIDE A BETTER GRIP ON THE SPLINED SHAFT.    THE PPC INPUT SHAFT HAS A THREADED B	ORE WHICH WOULD ALLOW THE USE OF AN ADDITIONAL BOLT AND WASHER AS A BACKUP RETAINER FOR THE PPC ARM IN THE EVENT THAT TH	E ARM WERE TO LOOSEN OFF.  THE AIRFRAME IPC DOES NOT SHOW A BOLT FOR THIS PURPOSE.  (TC NR 20070718004)		1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P15EA	 
2007082000130	20070820	00130	GL  	2007	8	20	CA070718005      	2	20070715	G	7240	6899081	COMBUSTION LINER			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1008 							(CAN) COMBUSTION LINER REMOVED AND INSPECTED DURING UN-RELATED ENGINE MAINTENANCE. FOUND CRACKED AND WARPED BEYOND LIMIT	S. (TC NR 20070718005)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007082000131	20070820	00131	CE  	2007	8	20	CA070718006      	1	20070627	G	5312	05120151	BULKHEAD        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2884 								(CAN) DURING THE 200 HOUR INSPECTION, A ONE-INCH CRACK WAS NOTED RUNNING HORIZONTALLY ACROSS THE FLANGE BEND RADIUS AT T	HE LOWER LT CORNER OF THE BULKHEAD.  A SMALL DENT WAS NOTED AT THIS POINT, PROBABLY EXISTING SINCE MFG, STRESSING THE AL	UMINUM AND TIGHTENING THE BEND RADIUS SOMEWHAT.  THIS AREA CAN BE FELT TO FLEX SLIGHTLY WHEN THE TAIL IS MANUALLY MOVED 	SIDEWAYS. (TC NR 20070718006)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2008030600047	20080306	00047	SW  	2008	3	6	CA070719001      	1	20070716	G	7603	212060722001	MOUNT           			BELL  	412   	412EP       	1182205	SW  										THROTTLE	INTERFERENCE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			284  								(CAN) DURING A SCHEDULED INSPECTION, AN AREA OF INTERFERENCE BETWEEN THE A THROTTLE JACKSHAFT MOUNT ASSY AND THE LT AIR 	INLET DUCT WAS IDENTIFIED.					1	G	7	2 	4U				H4SW    					 
	20081104			2008	11	4	CA070719007      	4	20070718	G	2330	178661101	ELECTRICAL BOX  			BOEING	777   	777*        	UTILUSE	NM  										SEAT	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) THE VIDEO ENTERTAINMENT SYS ON 3 SEATS WAS NOT WORKING. WHEN THE SEAT ELECTRONICS BOX WAS ACCESSED AND REPLACED DA	MAGE WAS NOTED ON THE REMOVED UNIT. SOOT ASSOCIATED WITH WHAT APPEARED TO BE BURNED CIRCUIT CARD IN THE SEU WAS OBSERVED	. AN ELECTRICAL BURNING TYPE ODOR WAS PRESENT IN THE AREA. (TC NR 20070719007)				2	L	7	2 	4F			RT	T00001SE					 
2008030600048	20080306	00048	SW  	2008	3	6	CA070719008      	1	20070719	G	6320	206040581001	TUBE            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					XMSN OIL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL LINE CRACKED IN BEND JUST FWD TO FLARED FITTING. SUSPECT FATIGUE FROM IMPROPER TIGHTENING AT SOME POINT THROUG	HOUT THE LIFE OF THE LINE. SUSPECT THIS TUBE WAS ORIGINAL EQUIPMENT. UNABLE TO DETECT LEAK ON GROUNG RUN LEAK CHECK AS T	HE MAINROTOR TRANSMISSION WOULDN`T BE WARM ENOUGH TO BE SENDING OIL TO THE OIL COOLER. (TC NR 20070719008)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007082000132	20070820	00132	NM  	2007	8	20	CA070719009      	1	20070628	G	2750	745583A	FLEX DRIVE      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) FLIGHT CREW REPORTED (FLAP DRIVE) CAUTION LIGHT ILLUMINATED FROM 2-3 SECONDS WHEN FLAPS SELECTED. MAINTENANCE INSP	ECTION FOUND FLAP SECONDARY DRIVE, IN WING CENTER SECTION, CORE HAD UNWOUND AND SEIZED CAUSING THE CASING TO ROTATE AND 	DAMAGED SUPPORT BRACKET AND TORQUE SENSOR.  FLAP CORE APPEARED TO LACK LUBRICATION AND RUST WAS EVIDENT. FLAP SECONDARY 	FLEX SHAFT REPLACED. ALL OTHER FLAP SECONDARY DRIVES LUBRICATED.  BRACKET AND TORQUE SENSOR DAMAGE REPAIRED. AIRCRAFT RE	TURNED TO SERVICE. FLAP SECONDARY DRIVE IS CLASSIFIED AS AN EXPENDABLE PART AND TIME ON PART NOT TRACKED. (TC NR 2007071	9009)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000133	20070820	00133	NM  	2007	8	20	CA070720003      	1	20070717	G	2910	AE7128852	HOSE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG ACTUATOR	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING SELECTING GEAR UP, THE CAUTION WARNING AND NOSE GEAR INDICATED NOT UP, MAIN GEAR UP.  SUBSEQUENTLY NOTED (N	R 2 HYDRAULIC SYSTEM ZERO QUANTITY.  FLUID LOSS DUE TO DAMAGED HYDRAULIC PIPE IN NLG WELL. REPAIRS COMPLETED, AC RTS. (T	C NR 20070720003)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007082000134	20070820	00134	CE  	2007	8	20	CA070720004      	1	20070718	G	2730	EM21542	CURRENT LIMITER 			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ELEVATOR	FAILED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			2312 								(CAN) WHEN COMPLETING POST FLIGHT INSPECTION (DI), AN AMBER CAS MESSAGE, ELEVATOR DISCONNECT WAS NOTICED ON THE EICAS DI	SPLAY.  ELEVATOR DISCONNECT WAS NOT ACTUATED AT THIS TIME (THIS INDICATES THE ELEVATORS ARE DISCONNECTED ON THE GROUND).	  ELEVATOR DISCONNECT FUNCTION CHECKED AND IT WAS DISCOVERED THAT THE ELEVATORS WOULD NOT DISCONNECT.  SYSTEM TROUBLESHO	T AND FOUND THAT CURRENT LIMITER HAD FAILED.  A NEW LIMITER WAS ORDERED AND INSTALLED.  ELEVATOR DISCONNECT SYSTEM FUNCT	ION CHECKED SERVICEABLE.  MFG NOTIFIED OF FAILURE. (TC NR 20070720004)		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007082000135	20070820	00135	SW  	2007	8	20	CA070720005      	1	20070719	G	2742		ACTUATOR        			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	PITCH TRIM	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				898  							(CAN) AFTER FLAP RETRACTION, FLIGHT CREW DISCOVERED THAT THEY HAD NO CONTROL OF PITCH TRIM USING PRIMARY OR SECONDARY CI	RCUITS. AFTER DISCUSSION WITH MAINTENANCE, FLIGHT CONTINUED TO MAINTENANCE BASE WHERE MAINTENANCE REPLACED TRIM ACTUATOR	. (TC NR 20070720005)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2007082000136	20070820	00136	EU  	2007	8	20	CA070720006      	1	20070707	G	3240	03024400	BRAKE ASSY      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				825  							(CAN) WHILE AIRCRAFT WAS BEING PUSHED BACK USING A TOWING DEVICE PART OF THE BRAKE ROTORS CAME LOOSE ON THE RT MLG AND P	UNCTURED THE RIM ASSEMBLY.  CAUSED THE TIRE TO GO FLAT. BRAKE DISC AND WHEEL.  REPLACED AND THE AIRCRAFT WAS RETURNED TO	 SERVICE.  WAS INFORMED BY THE LOCAL DEALER THAT THE ROTORS USED IN THIS BRAKE DISC WERE SUPPOSED TO BE NEW AND IMPROVED	 JUST FOR THIS SITUATION. (TC NR 20070720006)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008030600049	20080306	00049	SW  	2008	3	6	CA070720007      	1	20070710	G	6230	212040136001	BEARING         	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					MAST	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2210 		A1212568					(CAN) THIS PN BEARING IS A (ON CONDITION) PART. THE MAST WAS LAST OVERHAULED 2210.4 HOURS AGO. THE ENGINEER FOUND FERROU	S METAL IN THE TRANSMISSION INTERNAL AND EXTERNAL FILTERS. A POWDER OR PASTE WAS FOUND ON THE TRANSMISSION CHIP DETECTOR	, NOT ENOUGH TO ACTIVATE A CHIP LIGHT. (TC NR 20070720007)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007082000137	20070820	00137	GL  	2007	8	20	CA070720008      	2	20070718	G	7230		COMPRESSOR      			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	ENGINE	ERODED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA				6233 				550195			(CAN) DEPARTING DESTINATION, THE CREW NOTED A COMPRESSOR STALL CONDITION ASSOCIATED WITH HIGH TGT ON NR 1 ENGINE. THE CR	EW CARRIED OUT A PRECAUTIONARY SHUTDOWN, RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM.   MAINTENANC	E FOUND SIGNIFICANT EROSION IN THE COMPRESSOR 5TH AND 10TH STAGE BY VISUAL INSPECTION AND ELECTED TO REPLACE THE ENGINE.	 (TC NR 20070720008)			2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007082000139	20070820	00139	EU  	2007	8	20	CA070720010      	1	20070718	G	2150	15310000	A/C PACK        			BAG   	JETSTM	JETSTM3212  	1500217	EU  										RIGHT	SEIZED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				328  							(CAN) PILOT REPORTED OVER TEMP LIGHT, AND CONTINUED FLIGHT IAW J-31 MEL.  UPON TROUBLESHOOTING IT WAS FOUND THAT THE RT 	CAU WAS SEIZED.  CAU WAS REPLACED WITH OVERHAULED UNIT AND AIRCRAFT RETURNED TO SERVICE.  THIS UNIT HAS A 6000 HOUR LIFE	 BETWEEN OVERHAULS, AND FAILED AFTER 327.5 HOURS IN SERVICE. SEIZED UNIT WILL BE SENT FOR WARANTY OVERHAUL. (TC# 2007072	0010)			2	L	7	2 	4T			RT	BA15CAA 					 
2008030600050	20080306	00050	SW  	2008	3	6	CA070720011      	1	20070710	G	6220	206011260103	BOLT            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1141 	1141 							(CAN) MAIN ROTOR PARTS SENT TO NDT FOR INSPECTION AND ON MAGNAFLUX INSPECTIION FOUND STRAP BOLT CRACKED ON SHANK ABOUT O	NE QUARTER WAY AROUND. PART SENT TO BELL HELICOPTER LAB FOR FURTHER INVESTIGATION. BOLT WAS PURCHASED NEW ON MARCH 14,20	05 (TC NR 20070720011)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007082000140	20070820	00140	EA  	2007	8	20	CA070721001      	1	20070718	G	3297		WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) THE A/C ARRIVED AND WAS TAXIING TO THE GATE WHEN IT WAS NOTED THAT NR 3 BTMS WAS ON THE RISE AND SUSPECTED DRAGGIN	G BRAKES.  THE FLIGHT CREW NOTICED THAT THE BRAKE TEMP MONITOR DROPPED TO ZERO.  THE CAPTAIN GOT OUT OF THE A/C TO CHECK	 THE RT GEAR WHEN HE SAW THAT IT WAS ON FIRE, AT THIS TIME THE RAMP CREW EXTINGUISHED THE FIRE WITH A FIRE EXTINGUISHER.	  MAINTENANCE ON THE SCENE REPLACED NR3 MAIN WHEEL AND FOUND THAT THE DISCONNECT ON NR3 BRAKE LINE WAS LOOSE AND ONLY TO	OK TWO TURNS TO REMOVE. IT IS SUSPECTED THAT THE QUICK DISCONNECT CONNECTOR MAY HAVE BACKED OFF CAUSING THE DRAGGING BRA	KE CONDITION LEADING TO OVERHEAT AND FLUID LOSS CAUSING THE FIRE.  NR 3 AND NR 4 BRAKES WERE REPLACED THE NIGHT BEFORE F	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008032000003	20080320	00003	CE  	2008	3	20	CA070723001      	1	20070719	G	3250	50820035	ROD             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	NLG STEERING	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			20586								(CAN) DURING THE REPLACEMENT OF RODEND P/N F4-19 ON THE NOSE LANDING GEAR STEERING BARREL ASSY. P/N 50820042-601 WAS DIS	ASSEMBLED TO FACILITATE THE REMOVAL OF THE RODEND FROM THE ROD ASSY P/N 50-820035 (ITEM 21). AFTER DISASSY IT WAS NOTICE	D THAT THE ROD ASSY WAS HEAVILY CORRODED. THE CORROSION SEEMED TO START FROM INSIDE THE ROD ASSEMBLY AND WORKED ITS WAY 	OUT, CAUSING THE HARD CHROME TO FLAKE OFF IN 4 SPOTS ALL NEAR THE CARTER OF THE HOLLOW TUBE REVEALING A HOLES IN THE PAR	ENT METAL COMPLETELY THROUGH THE WALL OF THE TUBE. THE ROD ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  	THERE IS NO CURRENT REQUIREMENT TO DISASSEMBLE THIS PART FOR INSPECTION AND THE CORRODED AREA IS NOT VISIBLE WITH THE PA	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2007091700075	20070917	00075	SW  	2007	9	17	CA070724001      	1	20070718	G	3233		O-RING          			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	GEAR ACTUATOR	LEAKING         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) INCIDENT/HAZARD DESCRIPTION: UNSAFE GEAR WARNING LIGHT ILLUMINATED. HYDRAULIC PRESSURE WAS DOWN TO 500 PSI.  ONCE 	ON GROUND, FOUND HYDRAULIC FLUID HAD LEAKED OUT IN THE RT WHEEL WELL, DETERMINED THE RT GEAR ACTUATOR FOR BRINGING GEAR 	UP HAD A O-RING FAIL (SPLIT)  AIRCRAFT SLOWED TO BELOW 200KTS, GEAR SELECTED DOWN AND (3) GEAR CONFIRMED AND GEAR VISUAL	LY DOWN AND LOCKED. ONCE GEAR WAS DOWN HYDRAULIC PRESSURE WAS BACK UP TO 1000 PSI, AND LANDING MADE . BRAKES WORKED FINE	, AIRCRAFT REPAIRED FOR ALERTS ON THE 19TH OF JULY. TEST FLIGHT COMPLETED (TC NR 20070724001)		1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
2007082000141	20070820	00141	EA  	2007	8	20	CA070724002      	1	20070711	G	2731	C3CF3487	CABLE           			DHAV  	DHC3  	DHC3        	2800202	EA  	GARRTT	TPE331	TPE33110R   	0517	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ELEV TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100/150 HOURS INSPECTION, THE ELEVATOR, LOWER TRIM CABLE (P/N: C3CF348-7) WAS FOUND FRAYED IN (2) LOCATIO	NS. THE FIRST LOCATION WAS IN THE PEDESTAL AREA WHERE THE TRIM CABLE ATTACHES TO THE ELEVATOR TRIM DRUM ASSEMBLY (P/N: C	3CF222-3). IT APPEARS THAT THE CABLE WAS WEARING ON THE FWD AND REAR GUARDS P/N: C3CF310-3 AND C3CF309-3. THE SECOND ARE	A FOUND FRAYING WAS LOCATED IN THE UPPER CABIN AREA WHERE THE TRIM CABLE PASSES THROUGH FAIRLEAD BETWEEN FS 171.8 TO FS 	194.8.  CABLE REPLACED, AIRCRAFT RETURNED TO SERVICE.  (TC NR 20070724002)		1	H	7	1 	3R	4	T		A815    	E4WE	6	C	P40EA	 
	20081104			2008	11	4	CA070724003      	4	20070724	G	2562	AK450	ELT             			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  		CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BATTERY CONNECTIONS HAD EXCESSIVE CORROSION AND EVEN THOUGH THE INDICATOR LAMP INDICATED THAT UNIT WAS WORKING THE	 UNIT HAD NO SWEEP OUTPUT (TC NR 20070724003)					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
2007082000142	20070820	00142	EA  	2007	8	20	CA070724004      	1	20070721	G	2797	CF61A22WHT	WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE GEAR/FLAPS/BTMS INDICATIONS APPEARED WITH FLAP INDICATION SHOWING BOTH SIDES. FLAPLESS LANDING WAS SAFEL	Y PERFORMED. MAINTENANCE FOUND WIRE CF61A22WHT AT CONNECTOR P2CF OF RT FLAP POSITION TRANSDUCER WITH DAMAGED INSULATION 	AND TOUCHING THE SHIELD OF THE HARNESS. WIRE REPAIRED (REO601R-20-12-001 AND REO601R-20-12-048); CONNECTOR P2CF (P/N D38	999-26WB355N) AND HARNESS (P/N HET-A-02B) REPLACED. (TC NR 20070724004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007082000143	20070820	00143	NE  	2007	8	20	CA070724005      	2	20070723	G	7323	204060765007	CONTROL LEVER   			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				R	F	J	PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN) THIS IS THE INITIAL REPORT. INFORMATION NOT HERE YET. THE PILOT COULD ONLY GET 92 PERCENT NR RP, LANDED THE AIRCRA	FT NO INCIDENT, AFTER SHUTDOWN THE ENGINEER OPENED THE GOVERNOR SIDE ENGINE COWLING AND FOUND THE THE GOVERNOR LEVER BRO	KEN BOTH ENDS OF THE LEVER OR ARM WERE SECURE AND SAFETY.  WE ARE STILL INVESTIGATING. (TC NR 20070724005)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007082000144	20070820	00144	GL  	2007	8	20	CA070724006      	2	20070723	G	7200		ENGINE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						OVERHEATED      	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			TX	TAXI/GRND HDL  	1			CA								821948			(CAN) THE PILOT HAD JUST TAKEN HIS FINGER OFF THE THE STARTER ON STARTUP AND WAS REVIEWING HIS COMPANY PILOT MINI LOG WH	EN HE NOTED A DIFFERENT ENGINE SOUND AS THOUGH IT HAD INCREASED. WHILE CHECKING THE THROTTLE AND SCANNING THE GAUGES THE	 PILOT NOTICED THAT THE TOT WAS AT 1000 DEGREES. THE ENGINE ASSEMBLY WAS REPLACED. (TC NR 20070724006)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007121300197	20071213	00197	SW  	2007	12	13	CA070724007      	1	20070721	G	7931		ENGINE          			KAMOV 	KA32  	KA32A1      	       	SW  	KLIMOV	TB3117	TB3117BMA   		EU  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			638  	346  							(CAN) THE LT ENG OIL PRESSURE CAUTION LIGHT WAS FLICKERING WHILE SLINGING A LOAD. THE OIL PRESSURE GAUGE WAS CROSSCHECKE	D AND INDICATED 2.5 KG/CM2 (THE CAUTION RANGE) AND THE OIL TEMPERATURE WAS NORMAL. THE LOAD WAS DROPPED OFF. AFTER THE L	OAD WAS DELIVERED AIRCRAFT BACK IN LEVEL FLIGHT, THE CREW REVIEWED THE CHECKLIST AND FLIGHT MANUAL. AS A PRECAUTIONARY M	EASURE THE ENGINE WAS BROUGHT BACK TO IDLE. AT IDLE THE LT ENGINE WAS STILL BEING MONITORED, A FEW MILES FROM SERVICE TH	E FLIGHT CREW ADVANCED THE THROTTLE TOWARDS AUTO TO CHECK THE OIL PRESSURE. THE LT OIL PRESSURE LIGHT ILLUMINATED STEADI	LY AND THE OIL PRESSURE REMAINED AT IDLE OIL PRESSURE (2 KG/CM2 MINIMUM ALLOWABLE AT IDLE) THE AIRCRAFT WAS AT A WEIGHT 	1	G	7	2 	4U	4	U	NC	        	EXPE4U				 
2007082000145	20070820	00145	WP  	2007	8	20	CA070724008      	1	20070724	G	7410	AH720	RELAY           			CVAC  	340   	34030       	2422702	WP  	ALLSN 	501D  	501D13D     	03004	GL  	HAMSTD	54H	54H60       	NE  	IGNITION POWER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 1 ENGINE FAILED TO START DUE TO NO IGNITION.  FOUND IGNITION RELAY P/N AH720 S/N CN-90127 FOUND CONNECTOR SEPAR	ATED FROM BODY OF RELAY.    RELAY REPLACED AND ENGINE GROUND RUN SERVICEABLE. (TC NR 20070724008)					2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2007091200057	20070912	00057	CE  	2007	9	12	CA070725001      	1	20070712	G	2752	995240257	ACTUATOR        			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAP	NOISY           	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA				2963 							(CAN) UPON LANDING AN ATTEMPT TO RETRACT THE FLAPS FROM APPROACH TO ZERO RESULTED IN THE MOVEMENT OF THE RT IB FLAP ONLY	. THE REMAINING (3) FLAPS DID NOT MOVE. A FLIGHT PERMIT WAS GRANTED AND THE A/C WAS FLOWN WITH THE FLAPS LOCKED IN THE Z	ERO POSITION. THE GEARBOX OPERATION WAS NOISY AND WAS REPLACED.  THE SYSTEM WAS RIGGED AND OPERATIONALLY CHECKED IAW MFG	 INSTRUCTIONS.  NO OTHER PROBLEMS WERE NOTED.  (TC NR 20070725001)			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007082000146	20070820	00146	NM  	2007	8	20	CA070725002      	1	20070322	G	3810	6BS10011	DRAIN VALVE     			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   	      	CFE73811B   	 	NE  						DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3626 	3626 							(CAN) THE AIRCRAFT POTABLE WATER SYSTEM WAS DAMAGED DUE TO HAVING THE WATER SYSTEM FULL OF WATER. THEN PARKING THE AIRCR	AFT ON THE RAMP FOR 8 HRS AT -14 DEGREES C. WITH NO ADDITIONAL HEAT TO KEEP THE WATER SYSTEM FROM FREEZING.  UPON ARRIVI	NG, THE PILOTS REPORTED (WATER APPEARS TO LEAKING FROM THE BELLY) THE MAINTENANCE PERSONAL INVESTIGATED THE PROBLEM AND 	FOUND THE WATER SYSTEM DRAIN VALVE WAS DAMAGED DUE TO THE SEVERE FREEZING OF THE WATER SYSTEM. THE DRAIN VALVE WAS REPLA	CED AND THE AIRCRAFT RETURNED TO SERVICE.  A REMINDER TO ALL PILOTS TO MONITOR THE POTABLE WATER SYSTEM AND THE OAT IN T	HE WINTER. (TC NR 20070725002)	2	K	7	2 	4F	4	F	RT	A50NM   	E44NE				 
2008030600051	20080306	00051	CE  	2008	3	6	CA070725003      	1	20070717	G	2750	3X5K8563A44172	FLEX DRIVE      			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAP CONTROL	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AN ATTEMPT TO LOWER THE FLAPS TO APPROACH SETTING FROM ZERO DEGREES RESULTED IN THE RT IB FLAP NOT MOVING AND THE 	(3) OTHERS MOVING TO FULL DOWN. THE PILOT LANDED WITHOUT INCIDENT AND A FERRY PERMIT WAS GRANTED FOR A FLIGHT WITH THE F	LAPS UP AND LOCKED. UPON DISASSEMBLY OF THE SYSTEM IT WAS FOUND THAT THE RT FLAP FLEX DRIVE WAS DAMAGED AND BINDING UP O	PERATION OF THE ACTUATOR. (TC NR 20070725003)			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007082000147	20070820	00147	NM  	2007	8	20	CA070725004      	1	20070504	G	3010	29S7D524007	BOOT            			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	HORIZONTAL STAB	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			55   								(CAN) PILOTS REPORTED LT HORIZONTAL STAB. DE-ICER BOOT APPEARS LOOSE.  MAINTENANCE INSPECTED THE DE-ICER BOOT AND FOUND 	THE BOOT HAD COME LOOSE FROM THE AIRCRAFT AT THE AFT EDGES. THE ADHESIVE (3M 1300L) DID NOT SECURE THE DE-ICER BOOT TO T	HE STAB. THE BOOT WAS RECENTLY REPLACED BY AC SERVICES, UNDER WO 15249.  TIME ON PART WAS 54.6 HOURS AND 73 LANDINGS THE	 DE-ICER BOOT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC 20070725004)			2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2008031900149	20080319	00149	EA  	2008	3	19	CA070725005      	2	20070711	G	7230	3027301	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE COMPRESSOR TURBINE BLADE (STRETCH) INSP, ONE CT BLADE WAS FOUND CRACKED DURING THE NDT PROCESS. T	HE CRACK WAS ACROSS THE BLADE FACE AND BACK. THIS TYPE OF CRACK SCRAPS THE BLADE AND THE SET IT WAS INSTALLED WITH. THIS	 SET OF BLADES HAD A TSN OF 9299.1 HOURS. THE BLADES WERE REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20070725005)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007082000148	20070820	00148	EA  	2007	8	20	CA070725006      	2	20070725	G	8520	0360A3A	CRANKCASE       								LYC   	O360  	O360A3A     	41514	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1800 							(CAN) OVERHAULED CYLINDER ASSY`S WERE INSTALLED APPROX 500 HRS AGO ONTO A FRETTED CRANKCASE.  THE CENTER MAIN BEARING TH	EN SPUN IN THE BEARING SADDLE.  METAL WAS DETECTED IN THE OIL SCREEN AND THE ENGINE WAS SUBSEQUENTLY TORN DOWN FOR OVERH	AUL.  THE CRANKCASE IS UNSERVICEABLE. (TC NR 20070725006)									3	O			E286				 
2007110200003	20071102	00003	GL  	2007	11	2	CA070726003      	2	20070709	G	7321	2542102	SLEEVE          	HONEYWELL   		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					FUEL CONTROL	CRACKED         	W				O				OTHER                   				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		TX	TAXI/GRND HDL  	1			CA				30   		333104					(CAN) PILOT STARTING A/C, THROTTLE OPENED, NO ENGINE LIGHT OFF OCCURED. OPENED ENGINE COWL TO INVESTIGATE, NOTICED FUEL 	DRIPPING FROM AROUND START DE-RICHMENT ADJUSTMENT OF FCU, ONTO THE STARTER GENERATOR. CONTACTED MAINTENANCE PERSONNEL TO	 INVESTIGATE. FUEL CONTROL UNIT WAS REMOVED, AND O/H`D UNIT INSTALLED - NO FURTHER DEFECT NOTED ON START-UP. OVERHAUL SH	OP WORK ORDER DETAILS REVEALED A CRACKED SLEEVE ASSY P/N 2542102, AND CRACKED SCREWS P/N 334S606 (TC NR 20070726003)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007082000149	20070820	00149	NE  	2007	8	20	CA070726004      	2	20070726	G	7230	4017T37P02	SEAL            								GE    	CT58  	CT581402    	30011	NE  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								280122KL			(CAN) MULTIPLE CRACKS THROUGH KNIFE EDGE SEALS. THIS REPORT WILL ALSO BE SUBMITTED TO MFG IAW SEI-183 SECTION 72-32-7 PA	GE 302.  (TC NR 20070726004)										4	U			1E3				 
2007082000150	20070820	00150	NE  	2007	8	20	CA070727001      	2	20070727	G	7310	AN81510	FITTING         			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	FUEL MANIFOLD	BROKEN          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE DRIVEN PUMP NR 1, INLET PRESSURE MANIFOLD FITTING AN 815-10 BROKEN IN FLIGHT.  FITTING HAS BEEN REPLACED AN	D A/C RETURNED TO SERVICE.  (TC NR 20070727001)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082000151	20070820	00151	SO  	2007	8	20	CA070727002      	2	20070725	G	8530	65354A10	CYLINDER HEAD   			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER ASSY FOUND CRACKED DURING INSPECTION. LEAK COULD BE HEARD FROM CRACK DURING DIFF COMPRESSION TEST. CYLIND	ER REMOVED AND LARGE CRACK OBSERVED IN HEAD CASTING (INTERIOR VIEW). THE S/N OF CYLINDER REMOVED IS E41375-4 (TC NR 2007	0727002)				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2008030600132	20080306	00132	SW  	2008	3	6	CA070727003      	1	20070725	G	2911	MS28775212	O-RING          	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ACCUMULATOR	FAILED          	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) LOST OF HYDRAULIC IN FLIGHT, EMERGENCY LANDING, FAULT FOUND IN THE ACCUMULATOR, O-RING P/N MS28775-212 REPLACED A/	C GROUND RUN AND LEAK CHECK COMPLETED AND RELEASED TO SERVICE. (TC NR 20070727003)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007082000152	20070820	00152	NM  	2007	8	20	CA070727004      	1	20070725	G	7920		FITTING         			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					GEARBOX OIL	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) TOP OF DESCENT, THE NR 1 LOW OIL PRESSURE LIGHT ILLUMINATED, QTY AT ZERO.  PRECAUTIONARY ENGINE SHUTDOWN CARRIED O	UT.   GEARBOX FITTING (OIL PRESSURE DIFFERENTIAL SWITCH) THREAD REPAIRED AND FITTING REPLACED. ENGINE INSPECTEED IAW MM 	AND RETURNED TO SERVICE.  (TC NR 20070727004)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007082000153	20070820	00153	NE  	2007	8	20	CA070727005      	2	20070726	G	8550		SEAL            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	IMPELLER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				255  							(CAN) ENGINE REMOVED DUE TO EXCESSIVE OIL CONSUMPTION.  UPON REMOVING NR 7 CYLINDER INTAKE TUBE, OIL WAS NOTED. THIS IND	ICATES POSSIBLE IMPELLER SEAL FAILURE. ENGINE WAS REMOVED FROM SERVICE. (TC NR 20070727005)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007082000154	20070820	00154	CE  	2007	8	20	CA070727006      	1	20070723	G	7120		WEB             			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				536  							(CAN) CRACK FOUND AT LOWER WELD WEB LT SIDE. (TC NR 20070727006)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2007082000155	20070820	00155	SW  	2007	8	20	CA070727008      	1	20070717	G	3243	VI151000	MASTER CYLINDER 			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	BRAKES	FAULTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				7753 							(CAN) AIRCRAFT ABORTED TAKEOFF DUE TO A DRAGGING BRAKE. UPON MAINTENANCE INSPECTION THE RT BRAKE MASTER CYLINDERS WERE F	OUND AT FAULT.  BRAKE PRESSURE COULD NOT BE RELEASED BY THE AFFECTED MASTER CYLINDERS.  BOTH NR 2 AND NR 4 BRAKE MASTER 	CYLINDERS WERE REPLACED.   NR 2 CYLINDER P/N V-1000 S/N 3187 TSO - 4382.9,  NR 4 CYLINDER P/N VI-15-1000 S/N 13008 TSO- 	7753.3. (TC NR 20070727008)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2007082000156	20070820	00156	WP  	2007	8	20	CA070727009      	1	20070723	G	3234	340315061627	LEVER           			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	LANDING GEAR	DISTORTED       	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			10869	10869							(CAN) UPON SELECTION OF (GEAR DOWN), THE LOCKING ARM OF THE LANDING GEAR SELECTOR HANDLE STUCK IN THE EXTENDED POSITION,	 PREVENTING ASSOCIATED FUNCTION OF DEPRESSING THE GEAR WARNING LIGHT SWITCH.  THE RESULT WAS NO GEAR DOWN INDICATING LIG	HTS ON THE ANNUNCIATOR PANEL.  EMERGENCY PROCEDURES FOLLOWED AND AC LANDED WITHOUT INCIDENT.  MAINTENANCE FOUND LANDING 	GEAR ACTUATING LEVER LOCKPIN JAMMED AND CONTROL HANDLE BEYOND THE 90 DEGREE POSITION. LEVER DISASSEMBLED, DAMAGE FOUND W	AS A DISTORTED (CUPPED) INTERNAL ALUMINUM 960D10L WASHER. CUPPED WASHER REMOVED. NEW WASHER AND ONE EXTRA WASHER INSTALL	ED FOR SUPPORT DURING RE-RIG OF HANDLE WITHOUT COMPROMISING TRAVELS PER CONVAIR MAINTENANCE MANUAL LANDING GEAR MECHANIC	2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2007091200058	20070912	00058	GL  	2007	9	12	CA070729001      	1	20070717	G	3220	203220080	FORK            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	NOSE GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3109 								(CAN) DURING ROUTING INSPECTION, A CRACK SIMILAR TO THE ONE IN THE ATTACHMENT WAS FOUND.  FORK WAS REPLACED.  FLEET INSP	ECTION REVEALED (3) OTHER AIRCRAFT WITH VARYING CRACK PROGRESSION ALL FORKS WERE REPLACED. (TC NR 20070729001)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007082000157	20070820	00157	NE  	2007	8	20	CA070729002      	2	20070712	G	8520	39892	COUNTERWEIGHT   			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA				251  				42121964			(CAN) AIRCRAFT WAS IN CRUISE, ALL SYSTEMS NORMAL WHEN A VIOLENT VIBRATION HAPPENED IN THE LT ENGINE.  ENGINE SEIZED DURI	NG SHUTDOWN/FEATHER PROCESS AND FEATHERING WAS UNAVAILABLE. A SAFE LANDING WAS MADE ON A LAKE. INVESTIGATION REVEALED NR	 1 CYLINDER COMPLETELY REMOVED FROM THE ENGINE AND NR 9 PARTIALLY REMOVED.  FORWARD COUNTERWEIGHT HAD SEPARATED COMPLETE	LY FROM ITS ARM AND WAS FOUND LODGED IN THE TOP PART OF THE ENGINE AFTER BLOWING OUT A SECTION OF THE NOSE SIDE OF THE C	RANKCASE COVER.  AN ENGINE CHANGE WAS CONDUCTED ON SITE AND AIRCRAFT RETURNED TO RED LAKE WITH A LOANER PROP INSTALLED. 	(TC NR 20070729002)	1	L	7	2 	3R	3	R		A765    	5E1	5	C	P736	 
2007082000158	20070820	00158	EA  	2007	8	20	CA070729003      	1	20070728	G	5210	601R319119	STRUT           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ARRIVAL IT WAS DISCOVERED THAT THE PAX AIRSTAIR HAD BEEN DAMAGED WHEN CLOSED.  MAINTENANCE FOUND A SMALL PUNCTU	RE IN THE MAIN CABIN DOOR INNER SKIN BESIDE UPPER STEP.  MAINTENANCE DISCOVERED THE GAS STRUT ON THE MCD FAILED CAUSING 	THE SKIN PUCTURE BY CABLE ATTACHMENT ON THE DOOR BRACKET NOT RETRACTING.  NDT C/O NO CRACKS FOUND, STRUT AND COUNTER BAL	ANCE REPLACED AND REO 601R-52-11-1295 C/O WITH A RE-INSPECT OF THE SPEED TAPE EVERY 50 HRS.  PRESENT A/C HOURS 25062:54 	AND CYCLES 20668. (TC NR 20070729003)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081104			2008	11	4	CA070730001      	4	20070730	G	2562		G SWITCH        																	ELT	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ANNUAL INSP IT WAS FOUND THAT THE G-SWITCH OPERATION WAS OVERSENSITIVE. UNIT REJECTED AND RETURNED TO MFG F	OR REPAIR (TC NR 20070730001)																		 
2007082000159	20070820	00159	EU  	2007	8	20	CA070730002      	1	20070723	G	3240	30244	BRAKE DISC      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1848 								(CAN) AT THE TIME OF TAKEOFF THE WHEEL OF BLOCKED LT A AND A CAUSED THE EXIT OF TRACK OF THE APPARATUS. APPARATUS A DOES	 NOT SUFFER ANY DAMAGE AND AT SUMMER MOVED TO THE AIR OF PARKING. A TEAM OF MAINTENANCE OF THE COMPANY EAST GONE ON THE 	SPOT AND A FOUND THAT A DISC OF THE LT BRAKE WAS BROKEN. REPLACED BRAKE. (TC NR 20070730002)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081104		EU  	2008	11	4	CA070730003      	1	20070716	G	5610		WINDSCREEN      			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R333	R333482F12  	GL  	COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AFTER LEVELLING OFF AT 20000 FT, THE RT PILOTS WINDSCREEN CRACKED.  A/C BEGAN A DESCENT TO 5500 FT AND RETURNED TO	 BASE UNPRESSURIZED WITH NO FURTHER INCIDENT. WINDSHIELD HEAT WAS IN USE WITH NO OVERHEAT CAPTIONS.A NEW WINDSCREEN WAS 	INSTALLED WITH NO ABNORMALITIES IN ITS REMOVED AND REPLACED. (TC NR 20070730003)				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
	20081104			2008	11	4	CA070730004      	1	20070102	G	2421	6431041	ROTOR           	HONEYWELL   																GENERATOR	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN) RECENT DASH 8 400 AC GENERTOR (P/N1152218-3,-4,-5) FAILURE INVESTIGATIONS AT MFG HAVE IDENTIFIED THE MAIN ROTOR BA	NDS AS THE INITIAL FAILURE LOCATIONS FOR FIVE GENERATORS INVESTIGATED (S/N 062C-0420, 062C-0421, 1152218-00026, 1152218-	00062, 1152218-00064). FIELDED AC GENERATORS MAY HAVE A WELD JOINT NONCONFORMANCE ASSOCIATED WITH INTERNAL ROTOR BANDS (	QTY 2 IAW GENERATOR). THE NONCONFORMANCE IDENTIFIED IS AN INCOMPLETE FUSION OF THE WELD JOINT. THIS CONDITION WAS INITIA	LLY IDENTIFIED IN EARLY JAN 2007 ON GENERATOR S/N 1152218-00064 ORIGINALLY SHIPPED ON FEB 20, 2006. (TC NR 20070730004)															 
2007082000160	20070820	00160	SO  	2007	8	20	CA070730005      	1	20070728	G	5753		STRUCTURE       			LKHEED	188   	188C        	5262604	SO  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	TE FLAPS	SEPARATED       	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) FIRE SUPPRESSION OPERATIONS IN RUGGED MOUNTAINOUS TERRAIN. FINISHED LAST OF 4 DROPS. APPLIED MAX POWER AND FLAPS T	O 78 PERCENT AND PROCEEDED WITH CLEAN UP CHECKLIST.  NOTICED ABNORMAL OF CONTROL COLUMN ( MORE AILERON).  ADJUSTED TRIMS	 AND POWER SETTINGS.   PNF WENT TO THE BACK NOTICED DAMAGE TO RT OB PORTION OF FLAP. PILOT SLOWED AIRCRAFT.   ADVISED FS	S OF PROBLEM. PILOT RAN FLAPLESS CHECKLIST AND REQUESTED EMERGENCY VEHICLES. PILOT SLOWED AIRCRAFT TO DETERMINE CONTROLL	ABILITY. REVIEWED BRAKE FIRE PROCEDURES PRIOR TO LANDING AND THEN FLEW APPROACH AT MARKED BUG TO RUNWAY AND LANDED WITHO	UT INCIDENT.  MAINTENANCE FOUND 5 FT OF THE RT FLAP PANEL SEPARATED FROM THE ASSEMBLY AND TRAILING ON THE FLAP RAIL. MAI	2	L	7	4 	4T	4	T		4A22    	E282	6	C	P898	 
	20081104		CE  	2008	11	4	CA070730006      	1	20070730	G	2497	1013841069	METER           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ELECTRICAL LOAD	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				100  							(CAN) DURING START UP FOR SERVICE CHECK THE VOLTAGE WAS CHECKED BUT THERE WAS NO INDICATION ON THE METER.  METER WAS REM	OVED AND THE PUSH TO TEST SWITCH WAS FOUND DISCONNECTED FROM THE BODY OF THE METER. THE METER WAS REPLACED WITH REPAIRED	 UNIT. THIS METER WAS JUST INSTALLED AFTER A REPAIR. UNIT HAD ABOUT 100 HOURS ON IT, NUT THAT HOLDS SWITCH IN PLACE HAS 	STRIPPED OR BACKED OFF. UNIT SENT BACK FOR REPAIR. (TC NR 20070730006)			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007082000161	20070820	00161	NE  	2007	8	20	CA070731001      	2	20070727	G	7320		SEAL            			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					HMU	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			2538 								(CAN) DURING TAXI-IN AT THE GATE, A LARGE FUEL LEAKAGE WAS OBSERVED COMING FROM THE HMU FUEL DRAIN BELOW NR 2 ENGINE. EN	GINE WAS SHUTDOWN, BUT LEAKAGE CONTINUED.  NR 2 ENGINE FIRE HANDLE WAS PULLED AND LEAKAGE STOPPED.   FOUND LEAKAGE WAS F	OM THE MEC SHAFT SEAL. MEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070731001)				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2007091200059	20070912	00059	SO  	2007	9	12	CA070731002      	1	20070727	G	2750	486597	FLEX COUPLING   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FLAP MOTOR	SEIZED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA						6059					(CAN) ON CLIMB OUT PILOT FOUND HIS FLAP CIRCUIT BREAKER HAD POPPED AND HIS FLAPS WOULD NOT RETRACT.  HE MADE AN UNEVENTF	UL LANDING.  UPON TROUBLE SHOOTING, IT WAS FOUND THAT THE R/H FLAP FLEX SHAFT (MOTOR TO TRANSMISSION) WAS SEIZED.  AS A 	RESULT OF THE SEIZED SHAFT, THE MOTOR WAS ALSO DAMAGED.  THE MOTOR AND SHAFT HAVE BOTH BEEN REPLACED AND THE AIRCRAFT RE	LEASED FOR SERVICE. (TC NR 20070731002)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008032400416	20080324	00416	CE  	2008	3	24	CA070801001      	1	20070727	G	2810	369200157	FUEL CELL       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	RT WING	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT WING LEADING EDGE FUEL CELL WAS REMOVED BECAUSE OF A FUEL LEAK. A REPLACEMENT FUEL CELL WAS ORDERED. PRIOR 	TO INSTALLATION OF THE NEW (OVERHAULED) CELL, IT WAS INSPECTED AND FOUND TO CONTAIN A LARGE QUANTITY OF SAWDUST-LIKE PAR	TICLES. ON FURTHER INSPECTION, THE FUEL CELL STILL HAD THE FOAM FILLED FUEL RESERVOIR INSIDE. THIS FOAM WAS BREAKING DOW	N. AFTER DISCUSSIONS WITH MFG TECH SUPPORT IT WAS CONCLUDED THAT AD68-26-06 HAD BEEN COMPLIED WITH AT SOME POINT OF TIME	 WHICH REQUIRED THE INSTALLATION OF FUEL RESERVOIRS TO PREVENT ENGINE POWER LOSS DURING STEEP TURNS ON TAKEOFF. THESE RE	SERVOIRS HAD A FOAM INSERT WHICH WAS COMPATIBLE WITH 100/130 FUEL. THE USE OF 100LL HOWEVER CAUSES THE FOAM TO BREAK DOW	1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P25EA	 
2007082100081	20070821	00081		2007	8	21	CA070801002      	4	20070731	G	2330	3088510101	ENTERTAIN SYS   			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					CABIN	SMOKE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE LOADING THE AFT BAGGAGE PIT, A BURNING ELECTRICAL ODOR AND SMOKE WERE NOTICED AND TRACED TO THE LIVE-TV ELEC	TRICAL RACK COMPONENT WIRELESS AIRCRAFT UNIT.  POWER WAS REMOVED FROM THE AIRCRAFT AND THE WIRELESS AIRCRAFT UNIT WAS RE	MOVED.  THIS COMPONENT WILL BE RETURNED TO THE MFG AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UP	DATED ONCE THAT INFORMATION IS AVAILABLE.   (TC NR 20070801002)			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007082100083	20070821	00083	SO  	2007	8	21	CA070801003      	2	20070725	G	8550	635616	PAN             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE OIL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OIL PAN FOUND CRACKED DURING INSPECTION. (TC NR 20070801003)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2007082100084	20070821	00084	SO  	2007	8	21	CA070801004      	2	20070720	G	8530	AEC65385	CYLINDER        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NR 6	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FOUND 6 CYLINDER CRACKED AT SPARK PLUG HOLE. (TC NR 20070801004)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2007082100085	20070821	00085	SO  	2007	8	21	CA070801005      	2	20070720	G	8530	AEC65385	CYLINDER        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	NR 5	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FOUND NR 5 CYLINDER CRACKED AT SPARK PLUG HOLE. (TC NR 20070801005)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P25EA	 
2007082100086	20070821	00086	EU  	2007	8	21	CA070801006      	1	20070729	G	3320	BR6303121	LIGHT           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	CABIN	OVERHEATED      	W				A				UNSCHED LANDING         				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) CABIN OVERHEAD FLOURESCENT LIGHTING FIXTURE OVERHEATED.  BURNED OUT BULB FOUND AND CONTACTS IN FIXTURE THAT CONDUC	T ELECTRICITY TO BULB FOUND LOOSE AND OVERHEATED, CAUSING PLASTIC PART OF ASSY TO OVERHEAT. PARTS REPLACED AND A/C RELEA	SED TO SERVICE WITHOUT ANY FURTHER INCIDENT. (TC NR 20070801006)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2007091200060	20070912	00060	SW  	2007	9	12	CA070801007      	1	20070731	G	6510	476205561	BEARING         			BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1E    	41516	EA  					DRIVE ASSY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				889  							(CAN) ON WALK AROUND TAIL ROTOR OUTPUT SHAFT AT TRANSMISSION WAS NOTED TO HAVE LOTS OF PLAY, FWD DRIVESHAFT WAS REMOVED 	TO CHECK FOR COUPLING SPLINE WEAR WHICH WAS GOOD SO THE DRIVE ASSY WAS REMOVED FOR FURTHER INVESTIGATION. IT WAS DETERMI	NED THAT ONE OF THE DUPLEX BEARINGS WAS ROUGH AND THE ROLLER BEARING P/N 47-620-929-1 WAS WORN AND THE DRIVE GEAR WAS SH	OWING SIGNS OF UNEVEN WEAR CAUSED BY THE DUPLEX BEARING STARTING TO FAIL WHICH IN TURN MADE THE SHAFT MOVE IN AN UNEVEN 	PATTERN DAMAGING THE GEAR AND ROLLER BEARING. THE ROUGH FEELING DUPLEX BEARING WAS TAKEN APART AND FOUND THAT THE INNER 	RACE WAS STARTING TO SPALL ABOUT A THIRD OF THE WAY AROUND, NO METAL OR FLAKES HAD BEEN FOUND AND THE SCREEN WAS PULLED 	1	G	7	1 	3O	3	O		H1      	E279				 
2007082100087	20070821	00087	NE  	2007	8	21	CA070801008      	2	20070720	G	8530	327626	CYLINDER HEAD   			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		FF	FIRE FIGHTING  	1			CA				76   				P35411			(CAN) DURING A NORMAL WATER PICKUP FOR FIRE FIGHTING OPERATIONS, THERE WAS A NOTICEABLE LOSS OF MANIFOLD PRESSURE(MP) AN	D BMEP INDICATIONS. ON NR 1 POWER REDUCTION THERE WAS A SMALL BACKFIRE AND FURTHER LOSS OF MP AND BMEP.  WATERLOAD WAS J	ETTISONED AND FLIGHTCREW REDUCED POWER TO CLIMB. THEY CLIMBED TO CRUISE ALTITUDE AND NOTICED A SMALL OIL LEAK AND SMOKE 	TRAIL. ALL OTHER INDICATIONS WERE NORMAL EXCEPT FOR A COLD CYLINDER HEAD TEMP. AFTER APPROX.: 45 WITH A SMOKE TRAIL AND 	OIL LEAK APPARENTLY GETTING WORSE, THE FLIGHTCREW SHUT DOWN AND SECURED THE RT ENGINE.  AME FOUND CRACKED NR 2 CYCLINDER	 AND BROKEN PUSHROD AND HOUSING. CYLINDER WAS REPLACED, SCREEN CHECKED OK. ENGINE GROUND RUN AND FOUND SERVICEABLE.  (TC	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2007082100088	20070821	00088	EA  	2007	8	21	CA070801009      	1	20070722	G	2612	41493	ELBOW           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	FIRE DETECTION	CRACKED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA			4816 	4816 		1003					(CAN) DURING BOMBING OPERATIONS, FLIGHTCREW HAD AN INTERMITTENT RT, ZONE 1 FIRE INDICATION.  THEY LEFT THE FIRE CIRCUIT,	 CLIMBED TO ALTITUDE, AND SECURED RT ENGINE IAW CHECKLIST.  SHORTLY AFTERWARD (APPROX 5 MINUTES)THE LT GENERATOR FAILED.	 UPON ENTERING THE ZONE, ELECTRICAL POWER LOST TO RADIOS,   MADE A LANDING WITHOUT INCIDENT.  AMES FOUND CRACKED CERAMIC	 ELBOW ON FIRE DETECTION SYSTEM THE FOLLOWING DAY AFTER ANOTHER FALSE INDICATION. ELECTRICAL POWER CHARGING SYSTEM LOST 	WHEN LT ENGINE GENERATOR FAILED ON OPERATING ENGINE DURING SINGLE ENGINE OPERATIONS. GENERATOR REPLACED. SYSTEM CHECKED,	 FOUND SERVICEABLE. (TC NR 20070801009)	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2007091200061	20070912	00061	CE  	2007	9	12	CA070802001      	1	20070214	G	5311	11543008435	FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19854								(CAN) ON INSPECTION WE NOTICED THE FRAME WAS CRACKED ON THE LT AND THE RT SIDE.  A NEW FRAME WAS INSTALLED. (TC NR 20070	802001)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007091200062	20070912	00062	CE  	2007	9	12	CA070802002      	1	20070213	G	5210	504300431397	CABLE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	DOOR STEP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION IT WAS NOTICED THAT THE UPPER AND THE LOWER CABLES WERE FRAYED. THEY WERE REPLACED AND ADJUSTED. (TC	 NR 20070802002)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007091200063	20070912	00063	CE  	2007	9	12	CA070802003      	1	20070312	G	5344		HINGE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	LT DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION THE LT DOOR WAS FOUND CRACKED ALONG THE FRONT HINGE. (TC NR 20070802003)						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007091200064	20070912	00064	CE  	2007	9	12	CA070802004      	1	20070723	G	2810	1019200931	FUEL TANK       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	PURGE TANK	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) IT WAS NOTICED THAT ON SHUTDOWN THE LT ENGINE SMOKED.  NOTICE THAT THE COLLECTOR TANK WAS CRACKED ALONG THE WELD. 	(TC NR 20070802004)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007082100093	20070821	00093		2007	8	21	CA070802005      	4	20070726	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			380  								(CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATES	T SB. CRACKS WERE FOUND FORMING PARALLEL FROM THE PROP BOLT HEAD CONTACT SURFACE ON (3) OF THE (6) HOLES. HAVE TO LOOK V	ERY CAREFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND HIDE UNDER THE FACTORY PRIMER. THE TORQ	UE OF THE PROP BOLTS IS SHEAR STRESSING THE BULKHEAD. A COVER PLATE IS NEEDED TO OFFSET THE BOLTS FROM THE THIN ALUMINUM	 SHEET METAL BULKHEAD. THIS PROBLEM IS CONSTANTLY RE-OCCURRING WITH THIS SPINNER ASSY. (TC NR 20070802005)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082100095	20070821	00095	EA  	2007	8	21	CA070802006      	2	20070724	G	8530	LW12416	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2019 								(CAN) (2) CRACKS FOUND DURING ENGINE ON-CONDITION INSPECTION. CRACKS START FROM BOTTOM SPARK PLUG HOLE AND EACH CRACK GO	ES TO A VALVE SEAT. THESE CRACKS WERE NOT DETECTED DURING DIFFERENTIAL PRESSURE INSPECTION OR LEAK TEST. INTERNAL BORESC	OPE INSP WAS DETECTION METHOD IAW LATEST B041. (TC NR 20070802006)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007091200002	20070912	00002	SO  	2007	9	12	CA070802007      	1	20070722	G	7810	65442003	CLAMP           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	EXHAUST PIPE	WORN            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PIN THAT PROTRUDES THROUGH THE MUFFLER AND EXHAUST PIPE WAS WORE ALLOWING THE THEM TO SEPARATE. OTHER AIRCRAFT IN 	THE FLEET WERE CHECKED AND FOUND OK.  (TC NR 20070802007)					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007082100097	20070821	00097	GL  	2007	8	21	CA070802008      	3	20070727	G	6197	MS3126E1419S	CONNECTOR       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WIRE HARNESS	UNSERVICEABLE   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT SHORTLY AFTER TAKEOFF, THE BETA WARNING LIGHTS (BOTH) CAME ON AND THE NR 2 PROPELLER STARTED TO FEATH	ER.  THE PILOT PULLED THE BETA SYSTEM CIRCUIT BREAKER BUT THE LIGHTS DID NOT GO OFF, BUT THE PROPELLER STOPPED GOING TO 	FEATHER.  THE PILOT LANDED AND CONTACTED MAINTENANCE.  WHEN MAINTENANCE DID A GROUND RUN THE NR 2 PROPELLER WOULD NOT CO	ME OUT OF FEATHER.  TROUBLESHOOTING THE SYSTEM FOUND THAT THE CONNECTOR ON THE BETA SYSTEM CONTROL BOX WAS SHORTED OUT I	NTERNALLY, WHICH CAUSED FAULTS IN THE BETA CONTROL AND CAUTION LIGHT DIMMING CIRCUITS.  THE BETA SYSTEM WAS CAUSED TO (T	HINK) THE NR 2 PROPELLER WAS GOING INTO BETA, WHEN ACTUALLY IT WAS NOT, AND THEREFORE STARTED TO FEATHER THE PROPELLER. 	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007082100099	20070821	00099	NM  	2007	8	21	CA070802009      	1	20070702	G	6123	30005000056	TSCU            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AUTOFEATHER ARM LIGHT FAILED TO ILLUMINATE DURING TAKEOFF ROLL (AUTO FEATHER SYSTEM INOP).  REPLACED THE NR 2 TSCU	 IAW P/W MM 72-01-10, PAGE 420-424, PARAGRAPH 7. GROUND RUNS COMPLIED WITH.  OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED T	O SERVICE. (TC NR 20070802009)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007082100101	20070821	00101	EA  	2007	8	21	CA070802010      	1	20070801	G	5270	SAL2D864	PLUNGER         			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CARGO DOOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, FOWARD CARGO DOOR SWITCH PLUNGER WAS FOUND SEIZED. (TC NR 20070802010)						1	H	7	1 	3T	4	T		A806    	E4EA	6	C	P15EA	 
2007091200004	20070912	00004	CE  	2007	9	12	CA070803001      	1	20070420	G	5753	052323113	FLAP TRACK      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LT TE FLAP	SEPARATED       	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			CA											(CAN) DURING HARD MANEUVERING WITH FLAPS DOWN, A LOUD BANG WAS HEARD BY THE PILOTS WHO NOTICED THE LT FLAP BEING PUSHED 	BACK AT A STRANGE ANGLE.  THE FLAPS WERE LEFT IN THE DOWN POSITION AND THE AIRCRAFT WAS RETURNED WITHOUT INCIDENT.  UPON	 INVESTIGATION THE LT IB FLAP TRACK WAS FOUND SEPARATED AND CRACKED FROM THE AIRFRAME AT THE LOWER FLANGE.  THE CAUSE AP	PEARS TO BE THE CHERRYMAX RIVETS ATTACHING THE LOWER FLANGE OF THE WING RIB FRETTING, BECOMING WORN, AND WEARING THE RIV	ET HOLES IN THE WING SPAR UNTIL THE HIGHER STRESSES OF MANEUVERING TORE THEM FREE.   THE FLAPS AND TRACKS WERE REMOVED, 	SPAR INSPECTED WITH NO DAMAGE NOTED.  THE FLAP TRACK RIB ASSY`S WERE REPLACED, USING STRUCTURAL SCREWS AND NUTS TO ATTAC	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007082100102	20070821	00102	EA  	2007	8	21	CA070803002      	1	20070802	G	6123	3014403	TSCU            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RIGHT	INOPERATIVE     	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			667  								(CAN) AUTOFEATHER DID NOT ARM DURING THE TAKEOFF ROLL. TAKEOFF WAS ABORTED AND AN AUTOFEATHER TEST PERFORMED ON THE TAXI	WAY WHICH ALSO DID NOT ARM THE AUTOFEATHER. RETURNED TO BLOCK WHERE MAINTENANCE PERFORMED TROUBLESHOOTING AND REPLACED T	HE RT TSCU.   (TC NR 20070803002)				1	H	7	2 	3T	4	T	RT	A9EA    	E20NE	6	C	P7NE	 
2007082100104	20070821	00104	EU  	2007	8	21	CA070803003      	1	20070601	G	6123	3004800001	AUTOFEATHER SYS 			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					PROP CONTROL	DEFECTIVE       	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN.  AUTOFEATHER CONTROL UNIT WAS SUBSEQUENTLY REPLA	CED. (TC NR 20070803003)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007082100107	20070821	00107	EA  	2007	8	21	CA070803004      	2	20070601	G	7261		OIL SYSTEM      			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								PT0001			(CAN) ENGINE OIL TEMPERATURE WAS OBSERVED TO INCREASE IN FLIGHT AND THE PILOT ELECTED TO SHUT THE ENGINE DOWN.  OIL WAS 	SUBSEQUENTLY SEEN LEAKING FROM THE ENGINE EXHAUST.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMI	NED. (TC NR 20070803004)				1	G	7	2 	4U	4	U		H1NE    	E4EA				 
2007082100110	20070821	00110	NE  	2007	8	21	CA070803005      	2	20070530	G	7250		TURBINE BLADES  			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  					ENGINE	FRACTURED       	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								RD0007			(CAN) THE ENGINE LOST POWER ON TAKEOFF ROLL AND THE TAKEOFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED FRACTUED POWER 	TURBINE BLADES AND A DISCONNECTION BETWEEN THE POWER TURBINE AND PROP.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROO	T CAUSE ONCE ESTABLISHED. (TC NR 20070803005)				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2007091200005	20070912	00005	CE  	2007	9	12	CA070803006      	1	20070803	G	3244	0213500	TIRE            			RAYTHN	C90   	C90GT       	7150062	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	MLG	DELAMINATED     	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			223  								(CAN) VIBRATION REPORTED ON TAKEOFF AND LANDING STARTING/ENDING AT 60-70 KNOTS, VIBRATION INCREASED AT HIGH SPEEDS ON GR	OUND AND DISAPPEARED AFTER LANDING GEAR WAS RETRACTED.  LT AND RT MAIN WHEEL TIRE BALANCE PATCHES WERE FOUND DELAMINATED	 AND FLOATING INSIDE WHEEL ASSEMBLIES.  RT TIRE P/N 021-350-0 S/N 6121W00482 REPLACED WITH TIRE P/N 850T06-3, LT TIRE P/	N 021-350-0 S/N 6200W00106 ALSO REPLACED WITH NEW TIRE P/N 850T06-3  2) HIGH SPEED TAXI CHECKS COMPLETED WITH PILOTS UP 	TO 100 KNOTS, NO VIBRATIONS NOTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070803006)		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	P10NE	 
2007091200006	20070912	00006	NE  	2007	9	12	CA070803007      	2	20070617	G	7200	PT6A67R	ENGINE          			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  						DAMAGED         	W				O				OTHER                   				B	R	J	SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) ON SHORT FINAL, THE ENGINE LOST POWER AND SMOKE WAS SEEN EXITING THE ENGINE EXHAUST.  POST-FLIGHT INSPECTION REVEA	LED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE COMPLETED. (TC NR 20070803007)					2	H	7	2 	4T	4	T		A41EU   	E26NE				 
2007091200007	20070912	00007	NE  	2007	9	12	CA070803008      	2	20070618	G	7210		TOWERSHAFT      			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					REDUCTION GB	SEIZED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED A SEIZED TOWER S	HAFT AND DEBRIS IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 200	70803008)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007091200008	20070912	00008	CE  	2007	9	12	CA070803009      	1	20070803	G	3244	0763670	TIRE            			RAYTHN	C90   	C90GT       	7150062	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	NLG	OUT OF ROUND    	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			187  								(CAN) NOSE WHEEL SHIMMY TIRE PN 076-367-0 SN 4190W00091 FOUND OUT OF ROUND .5 INCH. TIRE REPLACED AND REBALANCED.  NOSE 	WHEEL STEERING DAMAGE CAUSED BY SHIMMY REPAIRED AS REQUIRED ALL WORN BOLTS, BUSHINGS, BEARINGS AND NOSE STEERING IDLER A	SSY. REPLACED NEW.  (TC NR 20070803009)				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	P10NE	 
2007091200009	20070912	00009	GL  	2007	9	12	CA070803010      	1	20070227	G	7931	2279300004	TRANSMITTER     			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE OIL PRESS	DEFECTIVE       	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) OIL PRESSURE REPORTED LOW WHEN ENGINE BROUGHT BACK TO IDLE FOR LANDING. INSTALLED NEW OIL PRESSURE SENDER AND AIRF	RAME GAUGE CALIBRATION CHECK COMPLETED.  LOGBOOK NOT AT CURRENTLY CLOSE AT HAND, FOR TOTAL TIME ON OIL SENDER, OPERATOR 	HAS REPLACED THEM IN THE PAST DUE TO SIMILAR TROUBLE.  (TC NR 20070803010)				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007091200010	20070912	00010	NE  	2007	9	12	CA070803011      	2	20070615	G	7210	MS949034	BOLT            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  					REDUCTION GEAR	SHEARED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB, ENGINE OIL PRESSURE WAS SEEN TO FALL TO ZERO AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIG	ATION REVEALED A SHEARED 1ST STAGE REDUCTION GEAR CARRIER BOLT. (TC NR 20070803011)					2	H	7	2 	4T	4	T		A41EU   	E26NE				 
2007091200011	20070912	00011	SO  	2007	9	12	CA070803012      	1	20070728	G	2720	63420006	TORQUE TUBE     			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT RUDDER	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			11513								(CAN) THE LT RUDDER CABLE TORQUE TUBE CONNECTION BROKE OFF FROM THE TUBE.  RUDDER CONTROL WAS LIMITED TO THE TRIM. (TC N	R 20070803012)					1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
2007091200012	20070912	00012	NE  	2007	9	12	CA070803013      	2	20070625	G	7250		TURBINE BLADES  			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								BB0113			(CAN) THE ENGINE WAS REPORTED TO HAVE SHUTDOWN IN CRUISE.  SUBSEQUENT INSPECTION REVEALED POWER TURBINE BLADE DAMAGE.  M	FG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070803013)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2007091200013	20070912	00013	NE  	2007	9	12	CA070803014      	2	20070627	G	7200		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  						POWER LOSS      	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								124152			(CAN) THE ENGINE LOST POWER IN FLIGHT AND WAS SHUTDOWN BY THE CREW.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROO	T CAUSE ONCE ESTABLISHED. (TC NR 20070803014)					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007091200014	20070912	00014	GL  	2007	9	12	CA070803015      	1	20070730	G	7931	2279300004	TRANSMITTER     			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE OIL PRESS	DEFECTIVE       	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA			194  								(CAN) PILOT REPORTED LOW OIL PRESSURE DURING DESCENT WITH ENGINE RPM REDUCED TO IDLE.  COMPLEATED OIL PRESSURE GUAUGE CA	LIBRATION CHART USING CABIBRATED GAUGE. INDICATED 30PSI -> ACTUAL 38PSI, INDICATED 20 -> ACTUAL 27PSI, INDICATED 15PSI -	> ACTUAL 20PSI, INDICATED TOP OF RED LINE 12PSI -> ACTUAL 18PSI, MIDDLE OR REDLINE 10PSI -> ACTUAL 16PSI.  (TC NR 200708	03015)			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007091200015	20070912	00015	NE  	2007	9	12	CA070803016      	2	20070626	G	7230		COMPRESSOR      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	SEIZED          	W				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA								114113			(CAN) ON APPROACH, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS OF OIL PRESSURE AND AN INCREASE IN INTER-TURBIN	E TEMPERATURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED COMPRESSOR SEIZURE AND INTERNAL OIL L	EAKAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070803016)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007091200017	20070912	00017	CE  	2007	9	12	CA070804001      	1	20070801	G	2840	AG112	SIGHT GLASS     			BOEING	75    	A75N1       	1380134	CE  	CONT  	R670  	R670*       	17016	SO  					FUEL TANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			351  								(CAN) AD CF61-7 CALLS FOR AN ANNUAL REPLACEMENT OF THIS TUBE, HOWEVER THIS OPERATOR HAS OBTAINED AN AMOC TO ALLOW OPERAT	ING UNTIL FAILURE.  IT HAS BEEN FOUND THAT THIS TUBE WILL FAIL AT ANY TIME, REGARDLESS OF REPLACEMENT OR TIME IN SERVICE	.  IT WILL FAIL AT THE BASE WHERE IT IS INSERTED INTO THE TANK FITTING, AND WILL MANIFEST ITSELF AS A MINOR (WEEP).  THE	 DANGER OF COURSE IS IF IT BREAKS OFF ENTIRELY.  THEREFORE, CONTINUED VIGILENCE IS PARAMOUNT. (TC NR 20070804001)			1	Q	7	1 	3R	3	R		A743    	E162				 
2007091700041	20070917	00041	SO  	2007	9	17	CA070805001      	1	20070803	G	3240	17766110	HOSE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT MLG BRAKE	FAILED          	W				E				ENGINE SHUTDOWN         				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			CA			2564 								(CAN) WHILE THE PILOTS WHERE TAXIING THE AIRCRAFT, IT WAS NOTED THAT THE RT BRAKES WHERE U/S.  AS THEY WHERE TAXIING BAC	K TO THE FBO ANOTHER AIRCRAFT REPORTED SMOKE COMING FROM THE RT BRAKE AREA.  THE FIRE WAS PUT OUT BY THE AIRPORT FIRE DE	PARTMENT QUICKLY.  AFTER THE INITIAL INSPECTION WAS CARRIED OUT, IT WAS FOUND THAT THE RT LOWER FLEXIBLE BRAKE LINE WAS 	U/S THAT ATTACHES TO THE CALIPER.  THE RT TIRE WAS U/S DUE TO THE FIRE.  THE WHEEL ASSY WAS REPLACED AND THE AIRCRAFT WA	S TOWED TO THE FBO`S HANGER WHERE IT WAS JACKED AND A DETAILED INSPECTION WAS CARRIED OUT.  AFTER THE INSPECTION WAS CAR	RIED OUT, THERE WAS NO DAMAGE TO THE RT MLG, SURROUNDING PARTS AND STRUCTURE OTHER THAN THE FLEXIBLE BRAKE LINE, CALIPER	1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2007091200018	20070912	00018	NM  	2007	9	12	CA070807001      	1	20070727	G	3230	651781914	LOCK ACTUATOR   			BOEING	737   	73735B      	13844BM	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, THE NOSE LANDING GEAR DID NOT RECEIVE A DOWNLOCK INDICATION IN THE COCKPIT. IT WAS BELIEVED BY TH	E CREW THAT THE GEAR FAILED TO EXTEND. A SECOND ATTEMPT WAS MADE AND THE NOSE GEAR EXTENDED AND LOCKED AS NORMAL.  NOTE:	 THE EMERGENCY EXTENSION WAS NOT USED.  WITH THE LANDING GEAR EXTENDED, THE AIRCRAFT WAS REMOVED FROM SERVICE AND FERRIE	D TO DESTINATION.  MAINTENANCE INSPECTED THE SYSTEM AND CONDUCTED TROUBLESHOOTING IAW THE AMM. AFTER CONSULTATION WITH M	FG, THEY REPLACED THE LOCK ACTUATOR AS IT IS RESPONSIBLE FOR LOCKING THE LANDING GEAR IN THE UP AND DOWN POSITIONS. ITS 	REPLACEMENT WAS RECOMMENDED BY MFG. AS A PRECAUTION, THE NOSE GEAR ACTUATOR WAS ALSO REPLACED. THE LANDING GEAR UNDERWEN	2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2007091200019	20070912	00019	NM  	2007	9	12	CA070807002      	1	20070803	G	2611	CGAB140000	SMOKE DETECTOR  			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  					FWD CARGO BAY	MALFUNCTIONED   	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) ENROUTE, IT WAS LESS THEN AN HOUR INTO THE FLIGHT WHEN AN ORANGE DETECT LIGHT FOR THE FORWARD CARGO SMOKE DETECTIO	N SYSTEM CAME ON. THE EXTINGUISHER SYSTEM WAS ACTIVATED AND THE FLIGHT DIVERTED TO CLOSEST AIRPORT AND LANDED SAFELY.  A	N INSPECTION OF THE FORWARD CARGO COMPARTMENT FOUND NO EVIDENCE OF FIRE OR SMOKE. AN OVERWEIGHT LANDING INSPECTION WAS C	ARRIED OUT.  THE AIRCRAFT WAS FERRIED BACK TO BASE WHERE THE SYSTEM WAS EXAMINED.  NO SYSTEM FAULTS WERE FOUND, BOTH FOR	WARD SMOKE DETECTORS WERE REPLACED AS A PRECAUTION AND THE DIVERTER VALVE AND METERING VALVE WERE REPLACED DUE TO THE SY	STEM BEING ACTIVATED.  THE CARGO SMOKE AND FIRE EXTINGUISHER SYSTEM INSTALLED ON THIS AIRCRAFT IS AN AAE STC ST01674AT. 	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2007091200020	20070912	00020	EU  	2007	9	12	CA070807003      	3	20070804	G	6111	697071003	BLADE           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			3425 	360  							(CAN) DURING APPROACH, AN AIRCRAFT EXPERIENCED IMPACT STRUCTURE DAMAGE DUE TO LOSS OF THE PROPELLER BLADE EROSION STRIP.	 THE PROPELLER COMPONENT CAME OFF AND STRUCK THE FUSELAGE ICE SHIELD AND DAMAGED THE FUSELAGE.   INSPECTION FOUND THAT T	HE COMPLETE EROSION STRIP (LEADING EDGE GUARD) WAS MISSING, FROM THE NR 5 BLADE ON LT PROPELLER. THIS BLADE HAD 308 FLIG	HT HOURS AND 36O CYCLES SINCE IT WAS REPAIRED DUE TO A BLADE TIP CRACK.  (TC NR 20070807003)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007091200021	20070912	00021	SO  	2007	9	12	CA070807004      	1	20070801	G	3240	17700200	PIN             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PARKING BRAKE	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) PARKING BRAKE VALVE STOP PIN IN THE OFF POSITION WAS SHEARED OFF CAUSING THE BRAKE LEVER TO GO PAST THE STOP POSIT	ION. THIS CAUSE THE BRAKE TO BE IN A ON POSITION. ON LANDING THE PILOT TESTED HIS BRAKES BY PUMPING THE BRAKES AND BECAU	SE THE LEVER WAS PAST THE STOP POSITION IT CAUSE THE BRAKES TO LOCK ON.  WHEN THE PILOT LANDED, THE BRAKES WHERE BOTH LO	CKED ON CAUSING THE TIRES TO BURST INTO FLAMES. (TC NR 20070807004)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007091200022	20070912	00022		2007	9	12	CA070807005      	4	20070717	G	2397	MS3126E1419P	CONNECTOR       			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					NR 2 VHF RADIO	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) TRAINING FLIGHT, NOTICED SMOKE COMING UP FROM CENTER CONSOLE BEHIND VHF NR 2 RADIO.  PUT DOWN, A/C ON GROUND. CO-P	ILOT JUMPED OUT TO CHECK IN BATT COMPARTMENT.  NO ANOMALIES FOUND. FORCE TRIM CB POPPED. CARGO RELEASE LIGHT CAME ON AND	 STAYED ON. VHF RADIO INOPERATIVE TO TRANSMIT AND RECEIVE, BUT WAS ALWAYS LIVE. CONNECTOR AT BASE OF PILOT CYCLIC STICK,	 FOUND BURNED/SHORTING OUT, AFFECTING ALL 3 CIRCUITS. (TC NR 20070807005)			1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2007091200023	20070912	00023	EU  	2007	9	12	CA070807006      	1	20070714	G	6320	332A38101521	PIN             			SNIAS 	AS332 	AS332C      	8680808	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					M/R GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON MAIN ROTOR GEARBOX REMOVAL SMALL PIN P/N 332A38-1015-21 FOUND INSTALLED IN LIEU OF LARGE PIN P/N 332A38-1019-21	 IN LOWER POSITION OF FORWARD SUSPENSION BAR.  RESULTANT, RADIAL PLAY 6 MM APPROXIMATELY.  MFG CONTACTED TO DETERMINE FU	RTHER ACTION.  RECORDS INDICATE PIN INSTALLED FOR 40 FLIGHT HOURS.  (TC NR 20070807006)				2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2007091200024	20070912	00024	EA  	2007	9	12	CA070807007      	2	20070715	G	7322		CONTROL CABLE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CARBURETOR	WORN            	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		CL	CLIMB          	1			CA											(CAN) ONCE AIRCRAFT REACHED 5000 FT THE PILOT COMMENCED CRUISE CHECKLIST, LEANED THE MIXTURE OF THE ENGINE WHEN THE POWE	R REDUCED TO IDLE. PILOT COULD NOT REGAIN ENGINE POWER AND MADE THE DECISION TO LAND IN A FIELD APPROX 3 MILES NE OF AIR	PORT.  UPON LANDING THERE WAS NO APPARENT DAMAGE TO THE AIRCRAFT OR THE PEOPLE ON BOARD. UPON INSPECTION, THE AIRCRAFT W	AS NOT DAMAGED AND IT WAS FOUND THAT THE HARDWARE ATTACHING THE MIXTURE CABLE TO THE CARBURETOR WAS WORN, ALLOWING THE C	ABLE TO SLIDE IN THE CARBURETOR MIXTURE ARM. (TC NR 20070807007)		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007091200025	20070912	00025	SW  	2007	9	12	CA070807008      	1	20070805	G	2913		DRIVE SHAFT     	ROMEC       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYD PUMP	SHEARED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			2074 	2074 		00010494					(CAN) APPROX 1 HR INTO FLIGHT, COCKPIT NR WARNING HORN CAME ON INTERMITTENTLY.  NR GAUGE BEGAN GIVING ERRATIC INDICATION	S, BEFORE PROGRESSIVELY DECAYING DOWN TO A STABILIZED READING OF 30 PERCENT.  AFTER LANDING, A VISUAL INSP REVEALED A LA	RGE AMOUNT OF HYDRAULIC FLUID ON THE XMSN DECK, AND A SHEARED OFF INTERNALLY WRENCHING SOCKET HEAD FROM THE UPPER LT COR	NER OF MOUNTING PLATE OF THE NR TACH DRIVE ASSY TO THE HYDRAULIC PUMP.  PILOT OPENED UP HYDRAULIC RESERVOIR AND FOUND AP	PROX 20 PERCENT OF FLUID REMAINING.  ENGINEER WAS CALLED AND REMOVED THE NR TACH GENERATOR, REVEALING A SHEARED SHAFT AT	 THE DRIVE ADAPTER FOR THE TACH GENERATOR.  HYDRAULIC PUMP AND RESERVOIR ASSEMBLY WAS REPLACED, AND AIRCRAFT DEPARTED FO	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007091200026	20070912	00026	WP  	2007	9	12	CA070808001      	1	20070807	G	7820	C16932	MUFFLER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TAILPIPE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			609  								(CAN) DURING SCHEDULED INSPECTION.  AD CF90-03R2 BEING ACCOMPLISHED, A LARGE CRACK WAS FOUND AT THE TAILPIPE ATTACHMENT 	POINT, IN THE MUFFLER SUB-ASSY.  IT WAS DIFFICULT TO DETERMINE ROOT CAUSE OF CRACK ORIGINATION, BUT POSSIBLE CAUSE WAS I	MPACT WITH FOREIGN OBJECT WHEN AIRCRAFT LANDED IN AN UNPREPARED LANDING AREA.  MUFFLER SUB-ASSEMBLY P/N C169-32 REPLACED	 WITH NEW ASSY, SAME P/N, A/C RELEASED FOR CONTINUED OPERATION (TC# 20070808001)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081104		CE  	2008	11	4	CA070808002      	1	20070807	G	3244	10X3504	TIRE            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	MLG	BULGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TIRE CORDS DELAMINATING FROM THE INSIDE ALL AROUND THE TIRE.  NO EXTERNAL FAULTS COULD BE DETECTED VISUALLY UNTIL 	TIRE BEGAN TO BULDGE. (TC NR 20070808002)					1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P47GL	 
2007091700042	20070917	00042	CE  	2007	9	17	CA070808003      	1	20070807	G	5610	10138402523	WINDSCREEN      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT, PILOTS WINDSCREEN SHATTERED/CRACKED.  DEVIATED TO ANOTHER AND DEPLANED PASSENGERS.  THE PILOTS INSPEC	TED THE WINDSCREENS AND DECIDED, BASED ON INFORMATION PROVIDED BY MAINTENANCE, OUT OF MM CHAPTER 5, THAT IT WOULD BE ACC	EPTABLE TO FERRY FOR WINDSCREEN REPLACEMENT.  MAINTENANCE PERSONNEL DETERMINED THAT THE COPILOTS WINDSCREEN WAS DELAMINA	TED AND HAD SMALL CRACKS IN THE LOWER INSIDE CORNER.  IT HAS BEEN CONCLUDED THAT AT SOME POINT IN TIME THE WINDSCREEN HE	AT HAD BEEN LT ON AND HAD DELAMINATED THE RT WINDSCREEN,  IT WAS UNDETERMINED WHAT HAD OCCURRED TO THE LT WINDSCREEN TO 	CAUSE IT TO SHATTER. (TC NR 20070808003)	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
	20081112			2008	11	12	CA070808004      	2	20070808	G	7414	10400576	CAPACITOR       																	MAGNETO	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN REMOVED FROM PACKAGE (NEW) THE FLAG TERMINAL THAT CONNECTS TO THE POINTS IN THE MAGNETO DID NOT HAVE ANY WIRE	 VISIBLE OUTSIDE THE CRIMP AREA OF THE TERMINAL. ACCORDING TO MFG, THE WIRE MUST BE FLUSH OR EXTENDED SLIGHTLY BEYOND TH	E CRIMP AREA. ALL 54 CAPACITORS IN STOCK WERE CHECKED AND FOUND TO HAVE THE SAME DEFECT. THESE CAPACITORS WILL BE SENT B	ACK TO TCM FOR WARRANTY EVALUATION.																 
2007091700043	20070917	00043		2007	9	17	CA070809001      	4	20070806	G	3442		CDU             			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					WX RADAR	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE AFTER DEPARTURE, THE CREW OBSERVED A FAILURE WITH THE WEATHER RADAR.  DUE TO FORECAST CONDITIONS THE CRE	W ELECTED TO RETURN TO POINT OF DEPARTURE.  MAINTENANCE REPLACED THE DISPLAY UNIT AND THE SYSTEM TESTED SERVICEABLE.  TH	E AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER PROBLEM REPORTED. (TC NR 20070809001)				2	L	7	2 	4F	4	F		A16WE   	E2EA				 
	20081105		CE  	2008	11	5	CA070809002      	1	20070809	G	3233	ADI79990021A	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOSE GEAR ACTUATOR SENT IN TO HAVE SEALS REPLACE DO TO UNIT BECAUSE IT WAS SITTING ON SHELF FOR 6 YEARS. ACTUATOR 	WAS OVERHAULED AND HAD NEVER BEEN USED. UNIT WAS DISASSEMBLED TO REPLACE SEALS AND INTERIOR OF CYLINDER WAS SCORED AND A	 SPRING BROKEN. ACTUATOR HAS BEEN SENT BACK FOR OVERHAUL.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007091700044	20070917	00044	NM  	2007	9	17	CA070809003      	1	20070805	G	2622	898052	EXTINGUISHER    			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	LEAKING         	W				G				O2 MASK DEPLOYED        				K			FLUID LOSS                			CR	CRUISE         	1			CA			12530								(CAN) FLIGHT DECK FIRE EXTINGUISHER LEAKED IN CRUISE.  CAPTAIN AND F/O HEARD A HISSING SOUND COMING FROM THE FIRE EXTING	UISHER BEHIND AND LEFT OF THE F/O. CAPTAIN AND F/O DONNED O2 AND ASSESSED THE SITUATION IE; FEELING THE LEAK NEAR THE EX	TINGUISHER`S NECK.  CAPTAIN THEN RELEASED FIRE EXTINGUISHER FROM ITS HOLDER AND STOWED THE UNIT IN THE FORWARD LAVATORY	 FOR THE REMAINDER OF THE FLIGHT.  CAPTAIN OPENED VENTS AND PUT PACKS ON HIGH AND ENQUIRED AS TO HOW THE FO WAS FEELING.	 FO SEEMED FINE AND LATER COMMENTED THAT HE MAY HAVE BEEN A BIT DIZZY.  A DETAILED REPORT HAS BEEN REQUESTED FROM THE RE	PAIR FACILITY AND DETAILS WILL BE UPDATED TO THIS REPORT AS THEY ARE OBTAINED. (TC NR 20070809003)	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
	20081104		NM  	2008	11	4	CA070809004      	1	20070610	G	2622	898052	EXTINGUISHER    			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			10279								(CAN) FOUND A FLIGHT DECK FIRE EXTINGUISHER THAT WAS REMOVED FROM THE AIRPLANE FOR LOSS OF PRESSURE. BOTTLE WAS FOUND CO	MPLETELY EMPTY AND THE TOP WAS LOOSE. YOU COULD SPIN THE TOP RIGHT OFF. STRIP REPORT REQUESTED FROM REPAIR FACILITY FOR 	INFORMATION. THIS REPORT WILL BE UPDATED AS INFORMATION BECOMES AVAILABLE. (TC NR 20070809004)				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
	20081105		EA  	2008	11	5	CA070810001      	1	20070809	G	3212	6A05158019	COVER           			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG FLOATS	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			CA			220  								(CAN) THIS TURBO OPERATING AMPH FLOATS WAS ON DESCENT TO LAND AT ITS HOME AIRPORT WHEN THERE WAS NO GEAR DOWN INDICATION	 ON RT MAIN WHEEL. PILOT ASKED PASSENGER IN THE RT SEAT TO LOOK AT THE TOP OF FLOATS TO CHECK TIE-DOWN ROPES, AND IT WAS	 NOTICED THAT THE END OF THE FLOAT ROPE WAS IN INSP HOLE ABOVE MAIN GEAR LOCKING MECHANISM. PILOT RETRACTED THE LANDING 	GEAR TO UP POSTION AND WHEN THERE WAS ALL 4 GEAR UP INDICATION, HE LANDED SAFELY IN THE WATER. ACFT WAS THAN TRANSPORTED	 TO ITS MAINT BASE WHERE PROBLEM WAS IDENTIFIED AS A DAMAGED UP LOCK CARRAIGE COVER, IT WAS THAN REPLACED WITH A NEW UNI	T. THE SYSTEM WAS FUNCTION TESTED SERVICEABLE AND ACFT WAS RETURNED TO SERVICE. NOTE: THE PILOT IN COMMAND WILL BE MORE 	1	H	7	1 	3T	4	T		A806    	E4EA	6	C	P15EA	 
2007091200027	20070912	00027	EA  	2007	9	12	CA070812001      	1	20070809	G	3230	4622	PRIORITY VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			12320	3214 							(CAN) ON APPROACH, GEAR WAS SELECTED DOWN AND THE NOSE GEAR DID NOT COME DOWN.  THE CREW THEN CYCLED THE GEAR, BUT THE N	OSE GEAR STILL DID NOT COME DOWN.  THE CREW SWITCHED 3B HYDRAULIC PUMP FROM AUTO TO ON AND 30 SECONDS LATER THE NOSE GEA	R CAME DOWN.  THE LANDING GEAR WAS DEFERRED FOR THE A/C TO RETURN FOR REPAIR.  MAINTENANCE T/S DISCOVERED NLG PRIORITY V	ALVE TO BE AT FAULT.  PRIORITY VALVE WAS REPLACED AND GEAR SWINGS C/O AND A/C WAS CHECKED SERVICEABLE. (TC NR 2007081200	1)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007091200028	20070912	00028	NE  	2007	9	12	CA070813001      	2	20070727	G	8520	27056CA1	PISTON          			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	CRACKED         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA											(CAN) THE PILOT MADE A PRECAUTIONARY LANDING WHEN HE NOTICED OIL DROPS ON THE WINDSHIELD AND SAW SOME SMOKE COMING OUT F	ROM THE REAR OF THE COWLING. THE ENGINE WAS INSPECTED TO DETERMINE THE CAUSE OF THE OIL LEAK. A DIFFERENTIAL COMPRESSION	 SHOWED THAT THE NR 2 CYLINDER WAS FLAT. THE CYLINDER ASSEMBLY WAS REMOVED AND REVEALED THAT THE PISTON WAS CRACKED FROM	 HALFWAY ACROSS THE TOP, DOWN TO THE PISTON PIN HOLE AND THAT THERE WAS ALSO A .3750 INCH RAGGED HOLE THROUGH THE PISTON	 ON THE TOP EDGE OF IT ALLOWING THE PRESSURIZATION OF THE CRANKCASE AND PUSHING OIL OUT THE FRONT CASE AROUND THE PROPEL	LER SHAFT. A COMPLETE CYLINDER AND PISTON ASSEMBLY WERE INSTALLED.  THE PART IS AVAILABLE IF REQUESTED. (TC NR 200708130	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007091200029	20070912	00029	NM  	2007	9	12	CA070813002      	1	20070730	G	3411		PITOT TUBE      			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  						BLOCKED         	W				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			CA											(CAN) THE AIRCRAFT BEGAN TO DEPART ON THE TAKE-OFF ROLL WHEN THE FLIGHT CREW OBSERVED THAT THE CAPTAINS AIRSPEED INDICAT	ION HAD FAILED. THE TAKE-OFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE WITH NO ADDITIONAL PROBLEMS. UPON INSPECT	ION OF THE CAPTAINS PITOT-TUBE A PARTIAL BLOCKAGE WAS NOTICED. AN INSECT AND SOME DEBRIS WAS REMOVED FROM THE PITOT-TUBE	 AND A LEAK TEST WAS CARRIED OUT ON THE CAPTAINS PITOT-STATIC SYSTEM, IAW THE AIRPLANE MM, AND NO FAULTS WERE FOUND. THE	 AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070813002)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2007091200030	20070912	00030	SO  	2007	9	12	CA070813003      	2	20070719	G	8520	0200	PISTON          			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					NR 2 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1314 								(CAN) TOP RING BROKEN.  ALL CYLINDERS REPLACED WITH NEW CYLINDER, PISTONS RINGS VALVES.  COMPRESSION TEST AT INSPECTION 	ON MIN - 60 OVER 80. (TC NR 20070813003)					1	H	7	1 	3O	3	O		3A19    	E252				 
2007091200031	20070912	00031	CE  	2007	9	12	CA070813004      	1	20070615	G	3110	6227876011	DISPLAY         			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	LOOSE           	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROTATION THE MFD SLID OUT OF ITS RACK. THE DISPLAY WAS LIMITED IN MOVEMENT AFT BY THE F/O. THE UNIT	 WAS PUSHED BACK INTO PLACE AND THE FLIGHT CONTINUED WITHOUT FURTHER INCIDENT. THE MFD HAD RECENTLY BEEN REPLACED. UPON 	INVESTIGATION THE LOCKING CLIPS THAT RETAIN THE MFD WERE FOUND IN THE LATCHED POSITION, HOWEVER, THEY HAD FAILED TO ENGA	GE THE RACK. THE MFD IS FLUSH ROUTED. THAT IS TO SAY ONCE INSTALLED THERE IS LITTLE TO NO EDGE UPON WHICH TO PULL THE UN	IT IN ORDER TO CHECK ITS SECURITY. NORMAL OPERATION OF THE LOCKING FEATURE IS FOR THE LOCKING TAB TO ROTATE DUE TO THREA	D FRICTION IN A CLOCKWISE MOTION AS THE LOCKING SCREW IS TURNED. WHEN THIS LOCK FAILS, IT IS NORMALLY DUE TO MISALIGNMEN	2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20081104			2008	11	4	CA070813005      	4	20070803	G	3420	LUN1241E8G8R	INDICATOR       			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ATTITUDE	UNRELIABLE      	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			225  	120  							(CAN) MFG INSTALLED MICROTECHNA ELECTRIC ATTITUDE INDICATORS IN A FLEET OF 9 AIRCRAFT USED FOR FLIGHT TRAINING. AFTER 18	 MONTHS, ONE ORIGINAL ATTITUDE INDICATOR IS STILL FUNCTIONING AFTER 500 HOURS (9) INSTRUMENTS AVERAGED 225 HOURS BEFORE 	FAILING THE FIRST TIME. (6) HAVE FAILED WITH AN AVERAGE OF 120 HOURS TSO. (3) AIRCRAFT HAVE BEEN GROUNDED WAITING FOR RE	PLACEMENT INTSTRUMENTS.			1	L	7	1 	3O	3	O	RT	A49CE   	1E4	5	C	P25EA	 
2007091200032	20070912	00032	SW  	2007	9	12	CA070814002      	1	20070710	G	6210	206015001107	BLADE           			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MAIN ROTOR	DAMAGED         	W				E				ENGINE SHUTDOWN         				C			F.O.D.                    			LD	LANDING        	1			CA			3143 								(CAN) UPON LANDING IN A BRUSH AREA, THE PILOT LOWERED THE COLLECTIVE, WHICH IN TURN RAISED (2) TREES THAT WERE SITUATED 	ON THE LEFT AND THEN HIT THE ROTOR DISK. THE PILOT THEN DISPLACED THE  AIRCRAFT TO THE RT. AN ENGINE SHUTDOWN WAS PERFOR	MED AND VISUAL INSPECTION CARRIED OUT.  THE ROTOR RPM DID NOT DECREASE UPON IMPACT WITH THE TREES, ONLY A COLLISION SOUN	D WAS NOTED. PRIOR TO ENGINE SHUTDOWN, ALL ENGINE PARAMETERS WERE NORMAL. THE VISUAL INSPECTION REVEALED THAT THE BLADE 	WEIGHTS WERE MISSING AT THE BLADE TIPS (3.5 - 4 INCHES). (TC NR 20070814002)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007091200033	20070912	00033	SO  	2007	9	12	CA070814003      	1	20070707	G	3230	487312	SPRING          			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	DOWNLOCK HOOK	BROKEN          	W				E	L			ENGINE SHUTDOWN         	ABORTED APPROACH        			O			OTHER                     			AP	APPROACH       	1			CA											(CAN) RT LANDING GEAR DOWN LOCK SPRING (P/N 487-312) BROKE AND LODGED ITSELF BETWEEN THE HOOK AND THE LOCK OF THE UPLOCK	 BOX.  THE GEAR COULD NOT MOVE AND THEN THE GEAR LIGHT DID NOT COME ON. (TC NR 20070814003)					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2007091200034	20070912	00034	SO  	2007	9	12	CA070814004      	1	20070718	G	2910	460635	BOWL            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD FILTER	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) THE RT POWERPACK FILTER BOWL HAD A HYDRAULIC LEAK IN FLIGHT, THE POWERPACK WAS PARTIALLY EMPTY. THE LANDING GEAR W	AS MANUALLY DESCENDED AND THE PILOT DECLARED AN EMERGENCY.   MECHANIC REPLACED FILTER ASSY (460635) WITH O-RING (MS 2877	8-16) THE POWER PACK WAS SERVICED, GEAR SWING CARRIED OUT, LEAK CHECKED SERVICEABLE. (TC NR 20070814004)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007091200035	20070912	00035		2007	9	12	CA070814005      	1	20070812	G	7810	89P11985	CLAMP           								WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	EXHAUST PIPE	BROKEN          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA								PC10184C			(CAN) AIRCRAFT WAS ENROUTE TO A FIRE, DURING CRUISE, THE NR 2 ENGINE FIRE WARNING SYSTEM ACTIVATED. THE ENGINE POWER WAS	 REDUCED AND THE FIRE WARNING WENT OUT. WHEN POWER WAS RE-APPLIED THE FIRE WARNING CAME ON AGAIN. THE RETARDANT LOAD WAS	 JETTISONED AND THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION BY MAINTENANCE CREW, AN EXHAUST CLAMP HAD BROKEN, ALLO	WING THE EXHAUST STACK TO SEPARATE FROM THE CYLINDER CAUSING A FALSE FIRE WARNING INDICATION. A SECOND EXHAUST CLAMP WAS	 FOUND BROKEN ON THE NR 1 ENGINE WHICH HAD ALSO CAUSED A FIRE WARNING. ALL REMAINING AIRCRAFT IN THE FLEET WILL BE INSPE	CTED FOR EXHAUST CLAMP CONDITION. (TC NR 20070814005)						4	R			E259	6	C	P8879	 
2007091200036	20070912	00036	GL  	2007	9	12	CA070814006      	1	20070810	G	5511	C2TP160A	BRACKET         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION ON FRONT TAILPLANE PICKUP BRACKET, FOUND AT INSPECTION WHILE DOING CF-1991-42R1.   (TC NR 20070814006)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2007091200037	20070912	00037	CE  	2007	9	12	CA070814007      	1	20070813	G	7810	3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				390  							(CAN) DURING ROUTINE MAINTENANCE ON THE ENGINE, AN INSPECTION OF THE POWER TURBINE BLADES INDICATED LARGE CRACKS AND MIS	SING SECTIONS OF THE EXHAUST DUCT. THIS ENGINE WAS INSTALLED ON APRIL 02, 2007 AFTER OVERHAUL. THE CAUSE OF THE CRACKS A	RE UNDER INVESTIGATION. (TC NR 20070814007)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007091200038	20070912	00038	GL  	2007	9	12	CA070814008      	1	20070809	G	3250	C2UT473	POST            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	TILLER	SHEARED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) TILLER POST FOUND SHEARED AT TOP, UNDER CABLE ATTACH FLANGE. (TC NR 20070814008)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007091200039	20070912	00039	CE  	2007	9	12	CA070814009      	1	20070813	G	2560		SEAT BELT       			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEAT BELT LOOPS THAT SECURE THE FRONT SEAT LAP BELTS TO THE SEAT FAILED.  THIS ALLOWED THE SEAT BELT, WHILE BEING 	SECURED, TO LOOP OVER THE SEAT BACK ADJUSTMENT LEVER.  WHEN THE PILOT ADJUSTED HIS SEAT PRIOR TO TAXI, THE SEAT BACK ADJ	UST LEVER WAS ACTIVATED AND THE SEAT BACK RECLINED TO ITS FULL BACK POSITION. (TC NR 20070814009)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007091200040	20070912	00040	NE  	2007	9	12	CA070814010      	2	20070807	G	7200		ENGINE          			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA								295178			(CAN) ROTORCRAFT WAS LOGGING AT THE TIME OF THE ENGINE SHUTDOWN.  THE AIRCRAFT WAS HOVERING ABOVE A LOG GETTING READY TO	 PULL THE LOG FROM THE SETTING.  NR 1 ENGINE INDICATIONS DROPPED OFF (IE OIL PRESSURE, FUEL PRESSURE, NG). THE AIRCRAFT 	RELEASED ITS LONGLINE AND BEGAN AN UNSCHEDULED LANDING.  THE AIRCRAFT LANDED WITHOUT INCIDENT AND THE ENGINE WAS REMOVED	 FOR INSPECTION. (TC NR 20070814010)			2	G	7	2 	4U	4	U		1H15    	1E3				 
2007110200004	20071102	00004	SO  	2007	11	2	CA070815001      	1	20070813	G	3230	487495	SPRING          	PIPER       	7872322     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	DOWNLOCK SPRING	BROKEN          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON A LANDING APPROACH, THE PILOT NOTICED THAT THE LT (GREEN) GEAR DOWN AND LOCKED LIGHT WAS NOT ILLUMINATED. AS TH	E AIRCRAFT WAS SLOWED DOWN ON FINAL THE (GEAR) UNSAFE LIGHT CAME ON. THE PILOTS ELECTED TO GO AROUND AND INFORMED FLIGHT	 SERVICES ABOUT THEIR CIRCUMSTANCES AND THE LOCAL FIRE DEPARTMENT WAS INFORMED ALSO. MAINTENANCE WAS NOTIFIED AND SPOKE 	DIRECTLY TO THE PILOTS. IT WAS LEARNED THAT AN EMERGENCY EXTENSION WAS CARRIED OUT AND THE RESULT WAS THE SAME. IT WAS A	LSO ESTABLISHED THAT THE LT MAIN GEAR WAS GOING FULL TRAVEL AND JUST NOT LOCKING DOWN. IT WAS DECIDED TO HAVE THE EMERGE	NCY EXTENSION KNOB PUSHED BACK INTO ITS NORMAL POSITION AND THE GEAR RETRACTED AND EXTENDED HYDRAULICALLY. IT WAS AT THI	1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2007091200041	20070912	00041	GL  	2007	9	12	CA070815002      	3	20070813	G	6110	B1843	SEAL            	HARTZL      	HCB3TN3     											HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BUA24432					(CAN) PROPELLER WAS RECEIVED BY SHOP BECAUSE OF GREASE LEAKAGE AROUND BLADE CLAMPS. UPON DISASSEMBLY TO PERFORM REPAIRS 	IT WAS NOTICED THAT THE DUST SEAL WAS MISSING FROM THE PROPELLER PISTON ASSEMBLY. SINCE THIS ITEM CAN`T PHYSICALLY FALL 	OUT IT IS ASSUMED THAT IT WAS INADVERTENTLY LEFT OUT AT A PREVIOUS REPAIR. (TC NR 20070815002)														6	C	P15EA	 
2007091700045	20070917	00045	EA  	2007	9	17	CA070815003      	2	20070809	G	7200		ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			12676	3595 				PCE51741			(CAN) DURING TAKEOFF ROLL, (JUST PRIOR TO VR) A LOUD POP WAS HEARD. THE AC CONTINUED WITH THE TAKEOFF AND ONCE AIRBORNE 	THE CREW DIVERTED BACK TO DEPARTURE AIRPORT FOR LANDING. AS THEY WERE COMING AROUND, THE PROP RPM, TORQUE, AND FUEL FLOW	 ON THE RT ENGINE BEGAN TO FLUCTUATE BUT REMAINED WITHIN LIMITS. POWER WAS REDUCED AND AN UNEVENTFUL LANDING CARRIED OUT	. FLIGHT CREW CONTACTED MAINTENANCE AND WERE INSTRUCTED TO CARRY OUT A GROUND RUN. THE ENGINES WERE RUN UP AND ALL PARAM	ETERS WERE WITHIN LIMITS, WHEN POWER WAS ADVANCED BEYOND 85 PERCENT NG ON THE RT ENGINE, TORQUE AND FUEL FLOW BEGAN TO F	LUCTUATE. AS THIS SEEMED TO INDICATE IT WAS A FUEL SCHEDULING PROBLEM, IT WAS DECIDED, IN CONSULTATION BETWEEN THE FLIGH	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2007091200042	20070912	00042	    	2007	9	12	CA070816001      	3	20070810	G	6110		CONNECTOR       			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	STC	STCA6441    	   	OIL PROP FILLER	UNSECURE        	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) ENGINE NR 1 RPM UNSTABLE, REDUCED RPM TO 13,600.  AIRCRAFT DIVERTED TO NEAREST AIRPORT. ENGINE WAS SHUTDOWN IN FIN	AL APPROACH, DUE TO RPM REDUCTION TO 13500 RPM.  MAINTENANCE WAS SENT ON SITE AND FOUND THAT OIL PROPELLER FILLER PLUG W	AS NOT SECURED PROPERLY AND ONE GALLON OF OIL HAD LEAKED OUT.   PROPELLER REFILLED AND ENGINE RUN C/O (SERVICEABLE). AIR	CRAFT RETURN TO SERVICE.  (TC NR 20070816001)			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2007091200043	20070912	00043	EA  	2007	9	12	CA070816002      	1	20070816	G	2730	215T9250446	CONTROL CABLE   			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A VISUAL INSPECTION ( 50 HRS),  A TECH FOUND AN ELEVATOR CABLE BADLY WORN, ALMOST CUT AT FUS STN 726 ZONE 3	10 FRONT OF THE PULLEY (TC NR 20070816002)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007091200044	20070912	00044	EA  	2007	9	12	CA070816003      	1	20070815	G	2721	6018610017	POTENTIOMETER   			CNDAIR	CL604 	CL604       	1900301	EA  										RUDDER TAB CONTR	INOPERATIVE     	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			7    								(CAN) ON TAKEOFF ROLL, AS THE AC WAS ACCELERATING AND PRIOR TO 80 KTS. FULL RUDDER INPUT WAS APPLIED TO MAINTAIN CENTERL	INE. CENTERLINE WAS UNABLE TO BE MAINTAINED AND THE TAKEOFF WAS ABORTED. THE AIRCRAFT TAXIED WITHOUT INCIDENT BACK TO BA	SE.  AIRCRAFT IS OPERATED BY MFG. MARKING N605JP (TC NR 20070816003)				2	L	7	2 	4F			RT	A21EA   					 
2008012900019	20080129	00019		2008	1	29	CA070817001      	4	20070718	G	3197	E321A	CONNECTOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CONTROL PANEL	BURNED          	W				H	D			DEACTIVATE SYST/CIRCUITS	RETURN TO BLOCK         			B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			15304				317952033				(CAN) SMOKE WAS REPORTED FROM THE OVERHEAD SWITCH PANEL WHEN TAXIING FOR TAKEOFF. THE CONNECTOR BEHIND THE PANEL WAS FOU	ND IN A BURNED CONDITION. THE CONNECTOR WAS REPLACED BY REMOVING THE BURNED WIRING AND SPLICING IN A NEW CONNECTOR. (TC 	NR 20070817001)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007091700047	20070917	00047	NM  	2007	9	17	CA070817002      	1	20070813	G	5753	85780009011	FLAP TRACK      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40546								(CAN) EXCESSIVE CORROSION FOUND ON FLAP TRACKS NR 4 AND NR 5 ON BOTH LT AND RT WINGS DURING 60K REPLACEMENT OF FLAP TRAC	KS. SUPPORT BRACKETS REMOVED FOR TRANSFER TO NEW BEAMS, CORROSION FOUND IN RECESSES OF TRACKS BEHIND BRACKETS. LT NR 4 T	RACK FOUND FULL OF WATER, BOTH SIDES OF BRACKET APPEARS TO BE NEWER BRACKET. RUST STARTING TO FORM BELOW PAINT.  NR 4 LT	: P/N 85780009-011; NR 4 RT: P/N 85780009-112; NR 5 LT: P/N 85780010-007;  NR 5 RT: P/N 85780010-008.   RECTIFICATION: F	LAP TRACKS REPLACED AS PART OF THE 60K WORK PACKAGE REQUIREMENT. FURTHER INSPECTION OF CORROSION AND CAUSE SHOULD BE CAR	RIED OUT.  (TC NR 20070817002)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008032400418	20080324	00418	GL  	2008	3	24	CA070817003      	1	20070816	G	3246	8834040	PIN             			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	12D	12D40       	NE  	TAIL WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4917 								(CAN) DURING 50 HOUR INSP, EXCESSIVE ROTATIONAL MOVEMENT WAS NOTED ON THE TAIL WHEEL KNUCKLE (FORK), WITH THE TAIL WHEEL	 CONTROL LOCK ON. TAIL WHEEL MAST WAS DISMANTLED AND PIN HOLDING THE UPPER AND LOWER EXTENSION PIECES TOGETHER WAS FOUND	 SHEARED. THIS COULD HAVE RESULTED IN THE LOSS OF THE ENTIRE TAIL WHEEL, OR POTENTIALLY IN THE LOSS OF CONTROL ON THE GR	OUND. UNIT WAS REPAIRED AND RETURNED TO SERVICE. THIS PIN COULD HAVE BEEN DAMAGED BY IMPROPER GROUND HANDLING OF THE AIR	CRAFT IE: PUSHING AC IN REVERSE WITH THE CONTROL LOCKS OFF. (TC NR 20070817003)		1	L	7	1 	3R	3	R		EXPA1L71	5E2	5	C	P257	 
2007091200045	20070912	00045	WP  	2007	9	12	CA070817005      	1	20070816	G	3246	CON1194515	WHEEL           			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN (A) INSPECTION, A 6 INCH LONG CRACK WAS NOTED ON THE MAIN WHEEL OUTER HALF. THE CRACK WAS RUNNING AROUND	 THE CIRCUMFERENCE OF THE WHEEL. THE WHEEL ASSEMBLY WAS REMOVED AND A SERVICEABLE WHEEL ASSEMBLY WAS INSTALLED. THE AIRC	RAFT WAS RETURNED TO SERVICE. (TC NR 20070817005)				2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2007091200046	20070912	00046	WP  	2007	9	12	CA070817006      	1	20070814	G	2620		MANIFOLD        			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	EXTINGUISHER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, AT APPROXIMATELY 7000 FEET AND THE RETARDANT SYSTEM DE-ARMED, THE RETARDANT TANK CONTENTS EXITED TH	E TANK. THE CREW RETURNED TO BASE.  MAINTENANCE TROUBLESHOT THE SYSTEM AND THE HYDRAULIC MANIFOLD FOR THE RETARDANT TANK	 WAS REPLACED. THE TANK DOOR OVER CENTERS WERE CHECKED. THE RETARDANT TANK SYSTEM WAS FUNCTION CHECKED, THE AIRCRAFT WAS	 TEST FLOWN AND RETURNED TO SERVICE. (TC NR 20070817006)			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2007091200047	20070912	00047	EA  	2007	9	12	CA070817007      	1	20070814	G	5280		DOOR            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					LT MLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LT MAIN GEAR DOOR WAS MISSING AND HAD CAUSED DAMAGE TO THE LT IB FLAP WHEN IT EXITED THE AIRCRAFT. (TC NR 2007	0817007)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022100013	20080221	00013		2008	2	21	CA070819001      	4	20070817	G	3421	6224565001	VERTICAL GYRO   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	EFIS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PILOT`S EFIS DISPLAYED ATT AND FD FLAGS, CO-PILOT FINISHED FLIGHT. REPLACED GYRO, PROBLEM SOLVED. (TC NR 200708190	01)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2007091200048	20070912	00048	NM  	2007	9	12	CA070820001      	1	20070801	G	3231	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT MLG DOOR	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, RT GEAR DOOR LIGHT REMAINED ON. LOWERED GEAR, RT MAIN GEAR DID NOT EXTEND.  ACCOMPLISHED ALTERNATE 	GEAR EXTENSION.  MAINTENANCE REPLACED RT MLG DOOR SOLENOID SEQUENCING VALVE AND SECONDARY MLG SELECTOR VALVE FITTING. BL	EED NR 2 HYD SYSTEM.  A/C RETURNED TO SERVICE. (TC NR 20070820001)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007091200049	20070912	00049	CE  	2007	9	12	CA070821001      	1	20070820	G	3233	12810016	HOUSING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5458 								(CAN) 500 HOUR LIQUID PENETRANT INSPECTION IAW MFG SEB 01-2 REVEALED, CRACK AT INDICATED AREA (TC NR 20070821001)						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
2007091200050	20070912	00050	NM  	2007	9	12	CA070821002      	1	20070815	G	2710	82740162101	LINK ASSY       			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LT AILERON	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1753 								(CAN) WHILE MAINTENANCE WAS DOING A OVERNIGHT CHECK TO THE AIRCRAFT, THEY OBSERVED THE LINK-ASSY AILERON LVDT WAS HANGIN	G DOWN.  THE ROD LINK HAD BROKEN AT THE AILERON END. (TC NR 20070821002)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007091200051	20070912	00051	EA  	2007	9	12	CA070821003      	3	20070608	G	6111	76EM8S5060	BLADE           	SNSNCH      	76EM8S5060  	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						16514K					(CAN) WELDED PROPELLER, AIRCRAFT IMPORTED, NO LOG FOR FIXED-PITCH PROP.  PROP REMOVED FOR 5 YR CORROSION INSPECTION AS A	 PRECAUTIONARY MEASURE - SINCE PROP WAS ONLY ALODINED, PROP WAS ANODIZED DURING INSPECTION AT HOPE AERO, TIP FOUND STAIN	ED AFTER ANODIZING.  CONFIRMED WELDING OF PROP BY EDDY CURRENT. (TC NR 20070821003)				1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
2007091200052	20070912	00052	EA  	2007	9	12	CA070821004      	1	20070821	G	3246	215850026	WHEEL           			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			140  								(CAN) THE (6) DOWEL PINS ON NOSE WHEEL HAS BEEN FOUND PROTRUDED FROM HUB AND THE RETAINING WASHER DEFORMED OR BENDED.   	(TC NR 20070821004)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008031900152	20080319	00152	SW  	2008	3	19	CA070821005      	1	20070820	G	7500		B-NUT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					BLEED AIR	LOOSE           	W				R				AUTOROTATION            				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			CA											(CAN) THE ROTORCRAFT DEPARTED AT LANDING AREA AT APPROX 4500 FT WITH ALL NORMAL PARAMETERS. AT APPROX 4300 FT THE PILOT 	NOTICED A DIFFERENCE IN ENGINE NOISE LEVELS. THE DIFFERENCE IN NOISE LEVELS WERE ACCOMPANIED BY ACTIVATION OF THE ENGINE	 AUTO RE-LIGHT SYS AND A DROP IN NG TO GROUND IDLE. THE PILOT ELECTED TO ENTER INTO AUTOROTATION AND LANDED WITH NO DAMA	GE TO THE AC.  THE CAUSE WAS DETERMINED TO BE AN AIR LEAK TO THE GOVERNOR FROM A LOOSE B-NUT. (TC NR 20070821005)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008030600133	20080306	00133	CE  	2008	3	6	CA070821006      	1	20070820	G	7110	101910016651	INTAKE          	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COWL ASSY LOWER FWD P/N 101-910024-1 WAS ONCE MODIFIED. (TC NR 20070821006)						1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007091200053	20070912	00053	EA  	2007	9	12	CA070822001      	1	20070822	G	2810	215640026	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 5	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK ON CELL, RT, NR 5.  DROPS 9963 (TC NR 20070822001)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007091200054	20070912	00054	EA  	2007	9	12	CA070822002      	1	20070822	G	2810	215640011	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  		LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			834  								(CAN) FUEL LEAKING FROM PATCH ON BOTTOM SURFACE OF CELL.  A/C HOURS 1889 CYCLES 1142 DROPS 9727  (TC NR 20070822002)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007110200005	20071102	00005	NM  	2007	11	2	CA070822003      	1	20070805	G	2910	AS11510K0324	HOSE            			BOEING	767   	767306      	1385148	NM  										HYDRAULIC SYS	DAMAGED         	W				A				UNSCHED LANDING         				J	F	J	WARNING INDICATION        	FLT CONT AFFECTED         	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS ONE HOUR OUT OF DEPARTURE PLACE AND ON ROUTE TO ENGLAND WHEN EICAS ILLUMINATED WITH THE FOLLOWING MES	SAGES: C HYD SYS FLUID LOSS - C HYD SYS PRESS AIRCRAFT DIVERTED TO NEAREST AIRPORT WHERE IT WAS FOUND THAT THE LT MAIN L	ANDING GEAR TRUCK TILT ACTUATOR RETURN FLEX HOSE WAS DAMAGED. THE FOLLOWING MAINTENANCE ACTIONS WERE PERFORMED: - DAMAGE	D HYDRAULIC HOSE REPLACED (TC NR 20070822003)			2	L	7	2 	4F			RT	A1NM    					 
2007091200055	20070912	00055	NE  	2007	9	12	CA070822004      	2	20070822	G	7210	311294501	CASE            								PWA   	PT6   	PT6A67D     	 	NE  					RGB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS PART WAS DECLARED UNSERVICEABLE DURING A TENTATIVE REPAIR AT MFG,  HOWEVER, IT WAS REINSTALLED INTO THE ENGIN	E BY MISTAKE AND DELIVERED TO THE CUSTOMER.  THE PART WAS CORRODED ON THE EXTERNAL WALL AND FURTHER PROGRESSION OF THIS 	DAMAGE COULD HAVE RESULTED IN A SUBSTANTIAL OIL LEAK FROM THE REDUCTION GEARBOX.  MFG DISCOVERED ITS MISTAKE PRIOR ENGIN	E USE AND THE ENGINE WAS IMMEDIATELY RECALLED FOR PART REPLACEMENT.  MFG IS CURRENTLY EXAMINING THE MAINTENANCE RECORDS 	OF SPECIFIC ENGINES TO MAKE SURE THAT A SIMILAR MISTAKE DID NOT HAPPEN ELSEWHERE.  (TC NR 20070822004)							4	T			E26NE				 
2007110200006	20071102	00006	CE  	2007	11	2	CA070822005      	1	20070816	G	5797	65280042	WIRE HARNESS    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					WING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9022 								(CAN) WHILE DOING SKIN REPAIRS ON RT WING WE FOUND WIRES CHAFED IN THE FLAP BAY AREA WHERE THE BUNDLE WAS TY WRAPPED TO 	A NYLON ANCHOR. THE TY WRAP WAS ONLY PUT THROUGH ON LEG OF THE ANCHOR NOT BOTH. THE CONDITION WAS FOUND AT 4 ANCHORS. TH	E LT WING WAS INSPECTED. THE WIRE BUNDLE THERE WAS TY WRAPPED THROUGH BOTH LEGS OF THE ANCHOR AND NO DEFECT WAS FOUND. T	HE P/N OF THE ANCHOR IS S1471-4. THE TY WRAPS ANCHORING THE WIRE BUNDLES SHOULD BE REMOVED TO REALLY INSPECT FOR DAMAGE 	AS THE AREA IS DIFFICULT TO INSPECT AND THE DAMAGE IS AT THE BOTTOM OF THE WIRE BUNDLE. (TC NR 20070822005)		2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2008030600134	20080306	00134	SW  	2008	3	6	CA070822006      	1	20070820	G	6320	206040004	TRANSMISSION    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			6670 	2778 							(CAN) SHORTLY AFTER TAKEOFF THE PILOT RECEIVED A CHIP LIGHT ON THE TRANSMISSION.  LANDED THE AIRCRAFT.  METAL WAS DISCOV	ERED ON THE SENSOR. THE AIRCRAFT WAS REMOVED FROM SERVICE AND THE TRANSMISSION WAS REPLACED WITH A SERVICEABLE UNIT. AIR	CRAFT RETURNED TO SERVICE (TC NR 20070822006)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007110200007	20071102	00007	CE  	2007	11	2	CA070822007      	1	20070816	G	8011	87818	RELAY           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	STARTER	BURNED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) STARTER RELAY STUCK CLOSED AFTER ENGINE START. SUBSEQUENT DAMAGE WAS NOTED ON STARTER AS WELL. (TC NR 20070822007)						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2008030600136	20080306	00136	SO  	2008	3	6	CA070822008      	1	20070821	G	2912	AN62341	FILTER HOUSING  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON THE 21ST OF AUGUST 2007, MAINTENANCE RECEIVED A CALL THAT AN AC HAD A HYDR FLUID LEAK. A RESCUE MISSION WAS DIS	PATCHED TO THE AC. UPON INVESTIGATION ONCE MAINT ARRIVED AT LOCATION IT WAS FOUND THAT THE NR 1 ENG HYDR FILTER HSG WAS 	LEAKING. AFTER DISASSEMBLY, IT WAS NOTED THAT THERE WAS A CRACK IN THE TREADS RUNNING .5 AROUND THE DIAMETER. THE HYDR F	ILTER WAS ISOLATED FROM THE SYS, THE SYS TOPPED UP WITH FLUID, AND A LEAK RUN PERFORMED BEFORE RETURNING TO DEPARTURE WI	THOUT PASSENGERS. IT HAS BEEN DETERMINED THROUGH AN INVESTIGATION THAT THE FAILURE WAS A DIRECT RESULT OF THE USAGE OF T	HE WRONG PN O-RING. THE O-RING THAT WAS FOUND INSTALLED ON THE FILTER HOUSING IS OF THE SAME OUTER DIAMETER AS THE PROPE	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007091200056	20070912	00056	EU  	2007	9	12	CA070823001      	1	20070816	G	2750	59128437	SENSOR          			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E6    	30015	NE  					TE FLAP	DEFECTIVE       	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, FLIGHT EXPERIENCED A FLAP FAIL MESSAGE.  SLAT WENT TO 3 GREEN, FLAP INDICATION BECAME YELLOW, AND SHO	WED BELOW THE 2 MARKER.  FLIGHT DID GO AROUND, AND DECLARED EMERGENCY WITH TOWER.  CFR WAS AVAILABLE, AND FLIGHT LANDED 	AT HIGHER THAN NORMAL SPEED.  INFLIGHT PERFORMED ABNORMAL LANDING PROCEDURE AFTER THEY WERE BRIEFED BY FLIGHT CREW THAT 	THEY WERE GOING TO LAND AT HIGHER THAN NORMAL SPEED.  PRIOR TO TAXI, CFR INSPECTED AIRCRAFT. ON INVESTIGATION, FOUND RT 	OB FLAP SKEW SENSOR AT FAULT, SENSOR REPLACED IAW AMM 27-53-06-400.  MOC REQUESTED THAT NR 4 AND NR 3 RT FLAP ACTUATORS 	BE REPLACED AS WELL.  (TC NR 20070823001)	2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008030600137	20080306	00137		2008	3	6	CA070823002      	4	20070821	G	2564		JETTISON SYSTEM 			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL2S2   	60036	NE  					LIFE RAFT	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) EXTERNAL LIFERAFT JETTISON SYS FAILED TO OPERATE. WHEN LEVER ACTUATED, CABLE BROKE AND PULLEY BRACKET ON LT SIDE O	F CENTER PEDESTAL DETACHED. (2) BRACKETS UNDER FLOOR FOUND TO BE LOCATED INCORRECTLY.  INSTALLATION WAS CARRIED OUT IAW 	ASI-500-100 REV.G. (TC NR 20070823002)				1	G	7	2 	3U	4	U	NC	H1NE    	E00054EN				 
2007110200008	20071102	00008	CE  	2007	11	2	CA070823003      	1	20070821	G	2510	SPL19251	LOCK            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	SEAT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			366  								(CAN) RT SEAT LOCKING PIN SHEATH FOUND BROKEN AT THE SEAT LEG ATTACH POINT. THE LOCKING PIN WOULD RETRACT BUT NOT ENGAGE	 ON THAT SIDE. THE SEAT LOCK MECHANISM COMPRISES OF A SPRING LOADED HANDLE , WITH TWO CABLES ATTACHED AND TWO SHEATHS SE	CURED TO THE SEAT LEG WHICH SURROUND THE LOCKING PINS. PART REPLACED. (TC NR 20070823003)				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P58GL	 
2007091700049	20070917	00049	SW  	2007	9	17	CA070823004      	1	20070821	G	6310	M2742630150	RETAINER        			BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A6724					(CAN) UPON QUALIFYING A FREEWHEELING UNIT, IT WAS DISCOVERED THAT THE WRONG RETAINING RINGS WERE USED IN (2) PLACES.  SU	SPECT RETAINING RINGS M27642/3-0152C WERE INSTALLED IN ASSEMBLIES INSTEAD OF M27426/3-0150C RETAINING RINGS.  THIS OCCUR	RED DURING APRIL 07. (TC NR 20070823004)				1	G	7	1 	3U			O	H2SW    					 
2007091700050	20070917	00050	NE  	2007	9	17	CA070823005      	2	20070819	G	7261		IMPELLER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA			10758	10758				TM120329			(CAN) ON TAXI, THE F/O NOTICED SMOKE IN THE FLIGHT DECK AND F/A CONFIRMED HAZE IN CABIN. BLEEDS WERE TURNED OFF. AS AIRC	RAFT TURNED ONTO GATE LAV SMOKE DETECTOR WENT OFF. CREW STOPPED 10 FEET SHORT OF THE GATE SHUT DOWN AIRCRAFT AND DEPLANE	D PASSENGERS.   IT WAS NOT A RAPID DEPLANEMENT AS THERE WAS NO PANIC AMONG PASSENGERS BUT CONCERN AS THEY COULD SEE SMOK	E. FIRE FIGHTERS BOARDED AIRCRAFT AFTER PASSENGERS DEPLANED AND REPORTED NO VISIBLE SMOKE OR OIL SMELL. A LITTLE LATER M	AINTENANCE WENT ON BOARD AND NO SMOKE ODOR WAS EVIDENT. A VERY SLIGHT OIL/HYDRAULIC ODOR WAS NOTICED AROUND THE CENTER C	ABIN AREA. MAINTENANCE TROUBLE SHOOTING CONSISTED OF A SERIES OF ENGINE RUNS WHICH ISOLATED PROBLEM TO NR 2 ENGINE. REPL	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007091700051	20070917	00051	GL  	2007	9	17	CA070823006      	1	20070713	G	5100	2224121400	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ALTERNATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			95   								(CAN) ALTERNATOR BRACKET IS BREAKING ON THESE AIRCRAFT AROUND 100 HOURS T/S.  THE FACTORY HAS RUN OUT OF STOCK AND IS RO	BBING THE PART FROM NEW PRODUCTION AIRCRAFT.  SUGGEST RE ENGINEERING AND POSSIBLE AD. (TC NR 20070823006)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007110200009	20071102	00009	CE  	2007	11	2	CA070823007      	1	20070821	G	2822	A10055B	PUMP            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	FUEL BOOST	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			366  								(CAN) FUEL DYE RESIDUE NOTED ON ELECTRIC FUEL BOOST PUMP HOUSING, FOUND TO BE FROM AN AUX PORT PLUG. PLUG RESEALED, FURT	HER CHECK FOR SEEPING SATISFACTORY. (TC NR 20070823007)					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P58GL	 
2008030600138	20080306	00138	SW  	2008	3	6	CA070823008      	1	20070818	G	2810	EA4703587	TANK            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TANK UNIT WAS INSTALLED FOR AN INACCURATE FUEL INDICATION. AFTER INSTALLATION OF THE REPAIRED TANK UNIT WE APPLIED	 GROUND POWER FOR THE FUEL CALIBRATION AND FOUND THE GAUGE TO BE INOPERATIVE. AFTER TROUBLESHOOTING IT WAS DETERMINED TH	AT THE TANK UNIT WAS FAULTY.  THE TANK UNIT WAS REMOVED AND A RESISTANCE CHECK WAS PERFORMED IAW THE MM, THE TANK UNIT F	AILED THE TEST. (TC NR 20070823008)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007091700052	20070917	00052	CE  	2007	9	17	CA070823009      	1	20070724	G	7931	IO360G	ENGINE          			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  		FAILED          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			CR	CRUISE         	1			CA				1990 							(CAN) REAR ENGINE EXPERIENCED A LOSS OF OIL PRESSURE DURING FLIGHT. ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO BASE. 	ENGINE WAS REPLACED.  UNABLE TO DETERMINE OIL PRESSURE PROBLEM WITH FAILED OIL PRESSURE ON ENGINE. ENGINE WAS SHIPPED TO	 ENGINE SHOP. (TC NR 20070823009)				1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2007110200010	20071102	00010	CE  	2007	11	2	CA070823010      	1	20070725	G	5520	07341102	TORQUE TUBE     	CESSNA      		CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3830 								(CAN) MINOR PLAY (UP AND DOWN) ON THE RT ELEVATOR CAUSE BY LOOSE RIVETS ON THE TORQUE TUBE (TC NR 20070823010)						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P880	 
2007091700053	20070917	00053	NM  	2007	9	17	CA070823011      	1	20070822	G	5610	001A561A0000218	WINDOW          			DORNER	DO32  	DO328100    	2996000	NM  										COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			6521 	6088 							(CAN) ENROUTE AT FLIGHT LEVEL 27,000 THE PILOTS LT SIDE WINDOW CRACKED WITH A LOUD POP.  INITIATED DESCENT TO 8,000 FEET	 AND MANUALLY RAISED CABIN PRESSURE TO ZERO DIFFERENTIAL PRESSURE AND CONTINUED.  ADVISED COMPANY OF THE FAILURE PRIOR T	O ARRIVAL.  AN ENGINEER INSPECTED THE WINDOW AND FOUND IT WITHIN LIMITS FOR A FERRY FLIGHT. AUGUST 23,2007  FOR REPLACEM	ENT OF THE WINDOW. (TC NR 20070823011)			2	H	7	2 	4T			RT	A45NM   					 
2007110200011	20071102	00011	EA  	2007	11	2	CA070823012      	1	20070821	G	2612	14034012	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT FIRE DETECT	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			9156 	9156 							(CAN) DURING LANDING ROLLOUT CREW RECEIVED MOMENTARY ILLUMINATION OF (BOTTLE ARMED PUSH TO DISCH) FOR RT ENG. CREW WAS C	HECKING FOR TRAFFIC AS HAD BEEN CLEARED ACROSS ANOTHER RUNWAY. WHEN ACROSS THIS RUNWAY NOTICED RED (R ENG OIL PX) AND RT	 ENG N1 AND N2 (ZERO). CREW CARRIED OUT RT ENG SHUTDOWN PROCEDURE. MAINTENANCE INSPECTION FOUND RT ENG FIRE PUSH SWITCH 	FAULTY. SWITCH REPLACED, FUNCTION CHECKS CARRIED OUT, AIRCRAFT RETURNED TO SERVICE. NOTE: ACTIVATION OF ENG FIRE PUSH SW	ITCH WILL SHUT OFF FUEL/HYD CAUSING ENGINE TO SHUT DOWN. (TC NR 20070823012)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600139	20080306	00139	SO  	2008	3	6	CA070823013      	1	20070810	G	3297		CONNECTOR       			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6D   	42305	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	DOWNLOCK	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) WIRE FOUND BROKEN ON DOWNLIMIT SWITCH CONNECTOR. (TC NR 20070823013)						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
2007110200012	20071102	00012	EU  	2007	11	2	CA070824001      	1	20070803	G	2752	1703911	ACTUATOR        			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, SLAT FAIL AND COUNTLESS MESSAGES ON EICAS ON INITIAL SELECTION. SLAT 0, FLAP 1. FOUND LT NR 4 ACTUATO	R RT NR 4 ACTUATOR AND RT NR 7 ACTUATOR TRIPPED.  ACTUATORS CHANGED IAW AMM 27-81-01. OPERATION CHK C/O, FOUND SYS SERVI	CEABLE. OTHER P/NS AFFECTED: 1703909, S/N 216 1703911, S/N 229 (TC NR 20070824001)				2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2007091700054	20070917	00054	EA  	2007	9	17	CA070824002      	1	20070819	G	3246	6A07116002	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLOAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A WHEELS DOWN LANDING OF AN AMPHIBIOUS EQUIPPED AIRCRAFT, THE LANDING GEAR COLLAPSED.   UPON INSPECTION, CO	RROSION WAS NOTED UNDER THE (ZAP STRAPS), WHICH WERE INSTALLED BY THE MANUFACTURER, ON BOTH LT AND RT NOSE GEAR ACTUATIN	G CYLINDERS.  ON THE LT CYLINDER, THE CORROSION WAS EXTENSIVE ENOUGH THAT HYDRAULIC FLUID WAS LEAKING THROUGH A PIN HOLE	 THAT HAD FORMED. (TC NR 20070824002)			1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
2007110200013	20071102	00013	EA  	2007	11	2	CA070824003      	1	20070824	G	2810	215640751	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  		LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEAK FROM BOTTOM SURFACE ON FUEL CELL NR 8 RT.  A/C HOURS 3381     CYCLES 2237.  DROPS 15187 MFG. (TC NR 200708240	03)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008030600141	20080306	00141	CE  	2008	3	6	CA070824004      	1	20070810	G	5520	115610010325	TORQUE TUBE     			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16   								(CAN) ON INSPECTION, THE ELEVATOR WAS FOUND TO HAVE .75 INCH PLAY AT T/E. THE ELEVATOR WAS REMOVED AN THE TORQUE TUBE WA	S INSPECTED. ALL 4 TAPER PINS WERE FOUND LOOSE, AND FOUND INSTALLED TO MAXIMUM ALLOWED PENETRATION. UPON DISASSEMBLY THE	 HOLES WERE FOUND OVERSIZED AND FILLED WITH PAINT FROM MFG. NEW TORQUE TUBE WAS INSTALLED AND AIRCRAFT RETURNED TO SERVI	CE. (TC NR 20070824004)			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007091700055	20070917	00055	EU  	2007	9	17	CA070824005      	1	20070730	G	2910	373Q2277	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE FLYING BOTH HYDRAULIC PUMP LIGHTS CAME ON.  THE AIRCRAFT LANDED USING ITS BACKUP SYSTEM.  IT WAS FOUND THAT 	THE HYDRAULIC LINE THAT RUNS BETWEEN THE PUMP AND FILTER ON THE LT NACELLE.  THE LINE WAS REPLACED AND THE AIRCRAFT WAS 	RETURNED TO SERVICE.  THE LEAK CAME FROM A SPOT WHERE THE LINE WAS CLAMPED. (TC NR 20070824005)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007091700056	20070917	00056	NE  	2007	9	17	CA070824006      	3	20070813	G	6110	8173881	SEAL            		14SF23      	DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER	TORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			85   			20060114			20060114		(CAN) CREW NOTICED A LARGE AMOUNT OF OIL ON THE LT NACELLE WHICH APPEARED TO ORIGINATE FROM THE PROPELLER. THE ENGINE WA	S SHUTDOWN DUE TO THE EXCESSIVE LEAKAGE AND THE AIRCRAFT RETURNED TO BASE.  THE PROPELLER NR 1 BLADE SEAL WAS REPLACED A	ND GROUND LEAK CHECKS CARRIED OUT.  THE SEAL (WHICH WAS FURTHER DAMAGED DURING REMOVAL) APPEARS TO HAVE HAD A TEAR ON TH	E SURFACE WHICH FACES OB AND IS EXPOSED WHEN INSTALLED. (TC NR 20070824006)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007091700057	20070917	00057	WP  	2007	9	17	CA070824007      	1	20070725	G	7921	315341	DOOR            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	OIL COOLER	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				26   							(CAN) AIRCRAFT WAS DISPATCHED FOR FIRE ACTION. AFTER DEPARTURE, THE RT OIL TEMPERATURE GAUGE WAS OBSERVED TO BE AT THE B	OTTOM OF THE RED ARC, APPROXIMATELY 100 DEGREES C. THE FLIGHT CREW IMMEDIATELY SHUTDOWN THE RT ENGINE AS A PRECAUTION AN	D RETURNED TO BASE. DURING INSPECTION BY MAINTENANCE, THE RT OIL COOLER DOOR WAS OBSERVED TO BE NOT FUNCTIONING AND POSI	TIONED FULLY CLOSED. THE RT OIL COOLER DOOR ACTUATOR WAS REMOVED AND INSPECTED. DURING DISASSEMBLY, SEVERAL WIRES AND A 	TERMINAL BLOCK WERE FOUND TO BE BROKEN IN THE ELECTRICAL BOX. THE OIL COOLER DOOR ACTUATOR WAS REPLACED AND RIGGED IAW M	M. AFTER GROUND CHECKED SERVICEABLE, THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070824007)	2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2008012900020	20080129	00020	CE  	2008	1	29	CA070826000      	1	20070825	G	3245		TUBE            	MICHEL      		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	TIRE	DETACHED        	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA						6196W00409					(CAN) ON TAKEOFF THE CREW NOTICED A STRONG VIBRATION. THEY DECIDED TO CANCEL THE FLIGHT AND LAND BACK AT AIRPORT.  FOUND	 THE NOSE TIRE BALANCE PATCH (FACTORY INSTALLED) HAD COME DISCONNECTED AND WAS TUMBLING LOOSE INSIDE THE TIRE. (TC NR 20	070826000)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2007091700060	20070917	00060	NE  	2007	9	17	CA070827001      	2	20070823	G	7250	311666801	GASKET          			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 4 BRG HSG	LEAKING         	W				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		AP	APPROACH       	1			CA				1840 							(CAN) NR 4 BEARING GASKET LEAKED CAUSING COKING AND BLOCKAGE OF THE OIL SCAVENGE TUBE. (TC NR 20070827001)						1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2007110200014	20071102	00014	NM  	2007	11	2	CA070827002      	1	20070725	G	2761	A44700009	HOUSING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ACTUATOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						001677					(CAN) WHILE DOING A LAYOVER INSPECTION A HYDRAULIC LEAK WAS FOUND IN THE LT FLAP AREA. THE LEAK WAS FOUND TO BE COMING F	ROM THE LT OB ROLL SPOILER ACTUATOR.  UPON REMOVAL OF THE ACTUATOR IT WAS FOUND THAT THE HOUSING HAD CRACKED IN THE AREA	 SUROUNDING ONE OF THE PLUGS CAUSING THE PLUG TO DISLODGE. THE CRACK EXTENDED AROUND THE ENTIRE CIRCUMFERENCE OF THE ACT	UATOR BODY WHERE THE PLUG IS THREADED IN. THE ACTUATOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE (TC NR 20070827	002)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007091700061	20070917	00061	EU  	2007	9	17	CA070827003      	1	20070808	G	5200	SP915C16	SEAL            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					BUTTON	DETERIORATED    	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA			6436 								(CAN) UPON CLIMB OUT WITH CABIN DIFFERENTIAL PRESSURE APPROACHING APPROXIMATELY 6 PSI, A DISTINCT AUDIABLE DISCERNING NO	ISE WAS HEARD FROM THE CENTER AREA OF THE CABIN. DURING DESCENT WHERE CABIN DIFFERENTIAL PRESSURIZATION FELL BELOW 6 PSI	, NOISE WOULD SUBSIDE AND GO AWAY. NUMEROUS MAINTENANCE ACTIONS WERE CONDUCTED IN ORDER TO ISOLATE CAUSE INCLUDING PRESS	URIZATION CHECKS AND CABIN LEAK RATES. NOISE COULD NOT BE REPRODUCED ON THE GROUND WHICH LED TO THE CONCLUSION THAT AIRS	PEED WAS ALSO A FACTOR.  FINALLY THE RUBBER RING SEAL WHICH IS HOUSED IN THE EXTERNAL RELEASE BUTTON MECHANISM OF THE EM	ERGENCY ESCAPE HATCH WAS REPLACED AND THE MECHANISM LUBRICATED. NOISE DISSAPEARED.  CONCLUSION WAS THAT THE BUTTON WAS V	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007110200015	20071102	00015	EA  	2007	11	2	CA070827004      	1	20070824	G	3320	BR95005	BALLAST         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CABIN LIGHT	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) CREW REPORTED WHEN THEY APPLIED EXT AC POWER TO THE AIRCRAFT AND TURNED ON THE SWITCH IN THE COCKPIT, THEY COULD S	MELL SOMETHING BURNING AND SAW A BLUE HAZE IN THE AIR. THEY IMMEDIATELY TURNED POWER OFF AND CALLED MAINTENANCE CONTROL.	  MAINTENANCE INSPECTION REVEALED THAT LIGHT BALLAST AT 7DF WAS FOUND TO BE THE SOURCE OF THE SMOKE/SMELL. THE BALLAST W	AS REMOVED AND THE LIGHT WAS DIFFERED SO THE A/C COULD RETURN TO DEPARTURE FOR REPAIRS. ONCE IN THE AREA WHERE BALLAST W	AS INSTALLED WAS INSPECTED AND BURNED INSULATION WAS FOUND.  AN INSULATED TAPE REPAIR WAS CARRIED OUT AND THE BALLAST AT	 7DF WAS REPLACED.  THE APU WAS RUN FOR HALF HOUR WITH PACKS ON TO VERIFY NO OIL SMELL. THE A/C WAS THEN DEODORIZED AND 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100038	20080131	00038	CE  	2008	1	31	CA070827006      	1	20070727	G	2497	MS33491	CONNECTOR       	SAFT        		BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	BATTERY	MELTED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA						111597					(CAN) WHILE IN FORMATION FLIGHT, THE LT (BATTERY CHARGE) LIGHT CAME ON AND STAYED ON FOR 15 MINUTES AND THEN EXTINGUISHE	D. AFTER LANDING AND ENGINES SHUTDOWN, THERE WAS NO MORE POWER COMING FROM THE BATTERIES.  AN INSPECTION WAS CARRIED OUT	 AND THE LT BATTERY WAS DISCOVERED (TOASTED) INCLUDING THE BATTERY COMPARTMENT. THE CAUSE WAS DETERMINED TO BE A BAD CON	TACT ON THE NEGATIVE POLE. (TC NR 20070827006)			1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2007110200016	20071102	00016	SW  	2007	11	2	CA070827008      	1	20070823	G	7697		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CONNECTOR	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER AIRCRAFT LANDED AND WAS TAXING THE SPEED LEVERS WERE PULLED BACK INTO LOW IDLE THE RT ENGINE OIL LIGHT CAME 	ON AT WHICH POINT THE CREW REALIZED THE RT ENGINE HAD SHUT ITSELF DOWN. CREW CONTACTED MAINTENANCE. MAINTENANCE INVESTIG	ATED AND REPAIRED WIRING ON CONNECTOR  PLUG AND RAN AIRCRAFT WHICH THEY WERE NOT ABLE TO DUPLICATE ENGINE SHUT DOWN. TES	T FLIGHT WAS COMPLETED AND UPON LANDING ENGINE SHUTDOWN AGAIN WHEN SPEED LEVERS WERE BROUGHT BACK INTO LOW IDLE. FUEL SH	UT OFF WAS REPLACED AT THIS TIME AND ENGINE SHUTDOWN COULD NOT BE DUPLICATED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070	827008)	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007110200017	20071102	00017	EA  	2007	11	2	CA070827009      	1	20070808	G	2711	2776016105	ACTUATOR        			FRCHLD	22    	22C7A       	3370104	EA  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT AILERONS	STIFF           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) PILOT COMPLAINED ABOUT AILERON STIFF TO MOVE AND WOULD OCCASIONALLY STICK IN THE FULL RT POSITION.  UPON MAINTENAN	CE TROUBLESHOOTING IT WAS NOTICED THAT THE LT AILERON TRIM ACTUATOR THAT WAS RECENTLY REPLACED, APPROXIMATLY 80 HOURS PR	EVIOUS, WAS AGAIN STIFF TO OPERATE. IT WOULD ALSO STICK IN THE FULL EXTENDED POSITION. TRIM ACTUATOR WAS REPLACED AND AI	RCRAFT RETURNED TO SERVICE. TRIM ACTUATOR WAS PASSED INTO QA WHO SENT TRIM ACTUATOR FOR FURTHER INVESTIGATION.			1	H	7	1 	3I	3	T		ATC438  	E2WE	6	C	3PNE	 
2007091700062	20070917	00062	NE  	2007	9	17	CA070827011      	2	20070731	G	7300	25766304	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			1765 								(CAN) DURING START UP, THE AIRCRAFT COULD DEVELOP AND POWER ABOVE 80 TO 85 PERCENT POWER INPUTS. THE SERVO WAS INSTALLED	 AND REMOVED WITH A TOTAL OF 3.7 HRS IN OPERATION ON THIS AIRCRAFT. SERVO WAS SENT FOR REPAIR AND CONTAMINATION WAS REPO	RTED TO BE THE CAUSE OF LACK OF POWER. NO ISSUE WERE NOTED IN AIRCRAFT FUEL SYSTEM AND REPLACEMENT OF SERVO FIXED THE PR	OBLEM. (TC NR 20070827011)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110200018	20071102	00018	NE  	2007	11	2	CA070827012      	2	20070729	G	7414		MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					BL600646201	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA				168  							(CAN) DURING START UP THE AIRCRAFT THE RT MAGNETO FAILED.  MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR	 20070827012)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110200019	20071102	00019	EA  	2007	11	2	CA070827013      	2	20070827	G	8530	AEL11800	VALVE SPRING    			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A200	1A200DFA    	GL  	INTAKE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			313  								(CAN) ALUMINUM PARTICLES WERE FOUND IN THE OIL FILTER. UPON TEARDOWN OF THE ENGINE, A BROKEN INTAKE VALVE SPRING (OUTER)	 HAS DAMAGED THE ALUMINUM CYLINDER HEAD. (TC NR 20070827013)					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P874	 
2007110200020	20071102	00020	WP  	2007	11	2	CA070827014      	1	20070626	G	2842	A5501	TRANSMITTER     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX FUEL CELL	ERRATIC         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			813  								(CAN) DURING A 50 HR INSPECTION IT WAS NOTED THAT THE AUX FUEL TANK INDICATION SYSTEM HAD ERRATIC MOVEMENT. THE SENDER W	AS REPLACED, FUEL SYSTEM CALIBRATION WAS CARRIED AND NO FURTHER ISSUES WERE NOTED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110200021	20071102	00021	WP  	2007	11	2	CA070827015      	1	20070810	G	2410	ALX8521	ALTERNATOR      			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA				1760 							(CAN) DURING LANDING THE ALTERNATOR LIGHT FAILED TO EXTINGUISH. CHARGING SYSTEM WAS CHECKED AND THE ALTERNATOR WAS THE D	EFECTIVE PART. THE ALTERNATOR WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20070827015)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2007110200022	20071102	00022	WP  	2007	11	2	CA070827016      	1	20070626	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FLT CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1042 								(CAN) DURING A 50/300 HR INSPECTION, IT WAS NOTED THAT THE AFT SERVO WAS LEAKING.  SERVO WAS REPLACED AND NO FURTHER DEF	ECTS WERE NOTED. (TC NR 20070827016)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110200023	20071102	00023	WP  	2007	11	2	CA070827017      	1	20070626	G	2822	D7431	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1042 								(CAN) DURING A MAINTENANCE INSPECTION A FUNCTION CHECK WAS CARRIED OUT ON THE AUX FUEL PUMP AND SOUNDS BEGAN TO COME FRO	M THE PUMP WHICH IS NOT PART OF IT`S NORMAL OPERATION. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 200708	27017)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110200024	20071102	00024	EA  	2007	11	2	CA070828002      	1	20070824	G	2910	601R75239463	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27240								(CAN) DURING C-CHECK INSPECTION, CHAFING DAMAGE WAS NOTED ON THE HYDRAULIC PUMP 3B SUCTION LINE P/N 601R75239-463. THIS 	HYDRAULIC TUBE LINE WAS RUBBING AGAINST THE UPLOCK NR 3 HYDRAULIC TUBE LINE (P/N 601R75239-273) THAT FEEDS INTO THE EXTE	ND LINE FOR THE RHS MAIN LANDING GEAR RETRACTION ACTUATOR. THE HYDRAULIC LINE HAS BEEN ORDERED AND WILL BE REPLACED BEFO	RE THE AIRCRAFT LEAVES THE HEAVY CHECK. (TC NR 20070828002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110200025	20071102	00025	EA  	2007	11	2	CA070828003      	1	20070824	G	2910	601R75239463	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27240								(CAN) DURING A C-CHECK INSPECTION IN THE RT MAIN LANDING GEAR WHEEL WELL, THE HDRAULIC SUCTION TUBE ASSY(P/N 601R75239-4	63) OF HYDRAULIC PUMP 3B WAS FOUND WITH CHAFING DAMAGE. THIS TUBE WAS RUBBING AGAINST THE HYDRAULIC LINE(P/N 601R75239-2	73),WHICH IS THE UPLOCK NR 3 LINE FEEDING INTO THE RT MAIN LANDING GEAR RETRACTION ACTUATOR.THE HYDRAULIC LINE HAS BEEN 	ORDERED AND WILL BE REPLACED BEFORE THE AIRCRAFT LEAVES THE HEAVY MAINTENANCE CHECK. (TC NR 20070828003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110200026	20071102	00026	SW  	2007	11	2	CA070828004      	1	20070821	G	6420	204011761001	BEARING         			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL ROTOR HEAD	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) PILOT WAS FLYING HELICOPTER AND FELT TWO SLIGHT YAWS TO THE RT APPROXIMATELY 30 TO 40 SECONDS APART. AT FIRST THE 	PILOT SUSPECTED IT MIGHT HAVE BEEN A GUST OF WIND, BUT THE SECOND YAW ALERTED THE PILOT TO A PROBLEM WITH THE TAIL ROTOR	 AS IT WAS ACCOMPANIED BY A NOTICEABLE RELUCTANCE OF THE AIRCRAFT TO RECOVER TO THE NOSE POINTED IN THE DIRECTION OF FLI	GHT. THE PILOT MADE A SUCCESSFUL UNSCHEDULED LANDING WITH NO DAMAGE TO THE AIRCRAFT.  UPON A MAINTENANCE INSPECTION OF T	HE T/R CROSSHEAD, IT WAS DETERMINED THAT THE DUPLEX BEARING INSIDE THE CROSSHEAD, BEARING P/N 204-011-761-001, HAD SEIZE	D. NEW PARTS WERE SUBSEQUENTLY ORDERED AND INSTALLED.  PARTS HAVE BEEN SHIPPED TO MAIN BASE FOR FURTHER INVESTIGATION. (	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008013100039	20080131	00039	SW  	2008	1	31	CA070828005      	1	20070726	G	5753	240014901	BLOCK           			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	FLAP HINGE BLOCK	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING CENTER FLAP HINGE BLOCK HAD SERIOUS INTER-GRANULAR CORROSION. CORROSION APPEARS TO HAVE STARTED IN THE POR	TION OF THE BLOCK THAT IS USED AS A STOP. THE STOP IS NOT EMPLOYED IN THE LOCATION THIS HINGE BLOCK WAS INSTALLED, (AFFE	CTED HINGE BLOCK, CENTER HINGE LOCATION). (TC NR 20070828005)				1	L	7	1 	3O	3	O		2A3     	E286	5	C	P25EA	 
2007110200027	20071102	00027	NE  	2007	11	2	CA070828006      	2	20070827	G	7250		BLADES          			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF34*       	 	NE  					NR 1 ENGINE	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			TX	TAXI/GRND HDL  	1			CA			6692 					194299			(CAN) ON WALK AROUND ON THE RAMP, IT WAS DISCOVERED THAT NR 1 ENGINE HAD BLADE AND STATOR DAMAGE CAUSED BY UNKNOWN FOD. 	THE A/C WAS TAXIED TO THE HANGER FOR INSPECTION AND BOROSCOPE. THE INSPECTION REVEALED THAT NR 14 BLADE HAD A SMALL DENT	, FURTHER INVESTIGATION REVEALED DAMAGE AT THE 1ST STAGE STATOR AT THE 5 O-CLOCK POSITION AND A PUNCTURE TO THE ENGINE L	INER. (APPROX 1.4X1.0 HOLE JUST AFT THE NR1 FAN AND JUST FORWARD OF STATOR AT APPROX 4 OCLOCK POSITION LOOKING AFT.) DU	E TO THE SKIN CONTAINMENT DAMAGE 1 INCH X .40 , MM DOES NOT ALLOW FOR ANY DAMAGE IN THIS AREA. ENGINE CHANGE HAS BEEN C/	O. PRESENT A/C HOURS:6692:52 AND CYCLES:3126.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110200028	20071102	00028	SO  	2007	11	2	CA070828007      	2	20070827	G	8530	637781	EXHAUST VALVE   			CESSNA	185   	185A        	2072804	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	NR 2 CYLINDER	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION, FOUND THE NR 2 CYLINDER LOW COMPRESSION, RESULT WAS THE EXHAUST VALVE EDGE WAS BURNE	D. (TC NR 20070828007)					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2008013100041	20080131	00041	WP  	2008	1	31	CA070829001      	1	20070819	G	2435	BC3151004	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1038 								(CAN) DURING AN ATTEMPTED START THE STARTER FUNCTION WAS INTERMITTENT. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE N	OTED. (TC NR 20070829001)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100044	20080131	00044	EA  	2008	1	31	CA070829002      	2	20070714	G	7323	D2781	GOVERNOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1144 								(CAN) DURING CRUISE, THE GOVERNOR CONTROL SETTING BECAME HIGHER. MAINTENANCE INVESTIGATED AND NO ISSUES COULD BE FOUND. 	GOVERNOR WAS REPLACED AND NO ISSUES WERE NOTED. (TC NR 20070829002)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2007110200029	20071102	00029	EA  	2007	11	2	CA070829004      	1	20070827	G	7160	75420022101	INTAKE DUCT     			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NACELLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33785								(CAN) LEVEL 3 CORROSION WAS FOUND BETWEEN THE LOWER INTAKE FORWARD LIP AND THE NACELLE STRUCTURE.  (TC NR 20070829004)						2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2008022100014	20080221	00014	SW  	2008	2	21	CA070830001      	1	20070827	G	5320	NAS50134A	BOLT            			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	DISPERSAL GATE	BROKEN          	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) RETARDANT WAS DISCOVERED LEAKING FROM AROUND THE TANK DOORS. UPON INVESTIGATION, IT WAS NOTED THAT THE BOLT SECURI	NG THE ANGLE INSIDE THE RT DISPERSAL GATE ASSY WAS BROKEN. THE BOLT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVIC	E. (TC NR 20070830001)				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2007110200030	20071102	00030	GL  	2007	11	2	CA070830002      	3	20070719	G	6114	2339	HUB             			CESSNA	180   	180E        	2072612	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1251 	441  					61822		(CAN) HUB THREADS FOUND CRACKED DURING OVERHAUL PROCESS (TC NR 20070830002)						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P880	 
2007110200031	20071102	00031	EA  	2007	11	2	CA070830003      	1	20070819	G	2810	215640024	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			1407 								(CAN) FUEL LEAK, RT WING FUEL CELL, NR 2 REPLACED DUE TO LEAKS IN FUEL CELL (TC NR 20070830003)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007110200032	20071102	00032	EA  	2007	11	2	CA070830004      	1	20070819	G	2810	2156400212	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											(CAN) FUEL LEAK RT WING, FUEL CELL NR 3 REPLACED DUE TO HOLE IN THE CELL. (TC NR 20070830004)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007110200033	20071102	00033	EA  	2007	11	2	CA070830005      	1	20070819	G	2810	2156400212	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			1407 								(CAN) FUEL LEAK RT WING FUEL CELL NR 7 REPLACED DUE TO HOLES IN THE FUEL CELL. (TC NR 20070830005)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2007110200034	20071102	00034	EA  	2007	11	2	CA070830006      	1	20070823	G	2760	72740251001	ROD             			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	SPOILER IND	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING, A PFCS INDICATOR PROBLEM, IT WAS NOTICED THAT THE ROD FOR THE RT IB ROLL SPOILER TRANSMITT	ER HAD SHEARED INSIDE OF THE ROD END AT THE SPOILER END. THERE WAS NO INDICATIONS OF THE ROD CONTACTING ANY OTHER SURFAC	E TO CAUSE IT TO BREAK, THE BREAK MAY HAVE DEVELOPED FROM A CRACK.  THE ROD WAS REPLACED AND THE AIRCRAFT RETURNED TO SE	RVICE. (TC NR 20070830006)			2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2008022100015	20080221	00015	EU  	2008	2	21	CA070831001      	1	20070726	G	6220		RING            			SNIAS 	350   	AS350D      	8680803	EU  	TMECA 	ARRIEL	ARRIEL1D    	60048	NE  					M/R HEAD	LOOSE           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING ENGINE SHUTDOWN THE MAIN ROTOR BLADE DROOP STOP RING FELL DOWN THE MAST ASSY. THE HARDWARE HOLDING THE RING	 BRACKET ALL CAME OFF ALLOWING THE RING TO FALL DOWN THE MAST TO THE SWASHPLATE DRIVE LINK.   SINCE THIS WAS REPORTED, I	T HAS BEEN DETERMINED THAT THIS IS NOT THE FIRST TIME THE HARDWARE FOR THE DROOP RING HAS COME LOOSE AFTER INSTALLATION.	 THE MAINTENANCE REVIEW BOARD HAS NOTIFIED TO SEE IF ANY ADDTION MAINTENANCE REQUIREMENTS ARE NECESSARY. (TC NR 20070831	001)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008030600143	20080306	00143	CE  	2008	3	6	CA070831002      	1	20070830	G	2752	503801535	DRIVE ASSY      	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	FLAP ACTUATOR	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			240  								(CAN) ON LANDING, WHEN FLAPS SELECTED FROM 40 PERCENT TO 100 PERCENT, FLAPS STOPPED AT APPROXIMATELY 60 PERCENT, LT OB F	LAP WAS SPLIT APPROXIMATELY 10 PERCENT. FLAP WOULD NOT EXTEND OR RETRACT.  LT OB FLAP ACTUATOR FOUND TO HAVE COME APART 	AT THE 90 DEGREE DRIVE ASSY ATTACH POINT. CLOSER VISUAL EXAMINATION REVEALED THAT IT HAD NOT BEEN PROPERLY ASSEMBLED DUR	ING AC AND/OR PART MFG.  RETAINING KEYWAY HAD DAMAGED THE SLOTTED COLLAR BY NOT BEING FULLY ENGAGED WHEN RETAINING NUT W	AS TIGHTENED. THIS SHOULD HAVE BEEN EVIDENT WHEN PART WAS ASSEMBLED AS THE RETAINING NUT WOULD NOT HAVE BEEN IN SAFETY A	FTER BEING TIGHTENED. ALSO THE RETAINING KEYWAY WOULD NOT HAVE BEEN RECESSED (APPROX .1250 INCH ON PROPERLY ASSEMBLED PA	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2007110200035	20071102	00035	NE  	2007	11	2	CA070831005      	2	20070829	G	8520	39785A	PIN             	PWA         		BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	MASTER ROD	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				575  							(CAN) CREW ATTEMPTED TO CHECK FOR HYDRAULIC LOCK PRIOR TO START, AND WAS UNABLE TO TURN THE ENGINE MORE THAN 180 DEGREES	. THROUGH DIAGNOSIS AND DISCUSSION WITH ENGINE OVERHAUL FACILITY, IT WAS ELECTED TO REMOVE A CYLINDER AND CONFIRM THE IN	TEGRITY OF THE MASTER ROD ASSEMBLY. ONE OF THE LINK PINS SECURING THE LINK RODS TO THE MASTER ROD WAS FOUND BACKED OUT O	F ITS HOLE AND WAS STRIKING THE INSIDE OF THE CRANKCASE, PREVENTING THE FULL ROTATION OF THE CRANKSHAFT. FAILURE OF THIS	 LINK PIN WOULD HAVE BEEN CATASTROPHIC FOR THIS ENGINE. (TC NR 20070831005)		1	L	7	2 	3R	3	R		A765    	5E1	5	C	P736	 
2007110200036	20071102	00036	EA  	2007	11	2	CA070902001      	1	20070813	G	2100	GG670950093	ACM             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RIGHT	FAILED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			7563 								(CAN) RT PACK GOES FULL HOT AND FAILS WITH BURNING ODOR. (TC NR 20070902001)						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2007113000087	20071130	00087	EA  	2007	11	30	CA070902002      	1	20070812	G	2730	BA6709260213	CONTROL ROD     			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	30015	NE  					VERTICAL STAB	UNKNOWN         	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN)  AFTER ENGINE START FOR DEPARTURE FLIGHT AF 7836 ,THE ELEVATOR WAS FOUND JAMMING DURING CHECK LIST . AIRCRAFT RETU	RNED TO THE GATE. THE EFFORTS ARE NORMAL ON CONTROL COLUMN UNTIL HALF WAY THE BECOMES HARD. EICAS INDICATION FOR THE ELE	VATOR SHOWS FULL DEFLECTION WHEN THE CONTROL COLUMN REACHES HALF WAY .  IN REFERENCE TO  N16/07 THE ACFT WAS IN CHECK AN	D COMPLETED ALL GROUND AND FLT TESTS SATISFACTORY . THE ACFT WAS REPOSITIONED.  THE SB 670BA-27-022 WAS DONE AND INSPECT	ED BUT A BUSHING REPLACEMENT WAS PENDING TO FULLY COMPLETE THE SB . DURING THIS BUSHING REPLACEMENT AN INVERSION OF THE 	ACTUATING RODS WAS DONE BETWEEN UPPER AND LOWER POSITION ON THE LEVER.  THE RODS WERE REPOSITIONED IN NORMAL CONFIGURATI	2	L	7	2 	4F	4	F	RT	A21EA   					 
2007110200037	20071102	00037	EA  	2007	11	2	CA070902003      	1	20070824	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FL 330 LT, WINDSHIELD CRACKED. AIRCRAFT CONTINUED TO DESTINATION. NO FURTHER REPORTED DETAILS. (TC NR 20070902003)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110200038	20071102	00038	NM  	2007	11	2	CA070903001      	1	20070902	G	3233	8400105	ACTUATOR        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE THE LANDING GEAR RETRACTED NORMALLY. APPROXIMATELY 20 SECONDS LATER, THE NOSE GEAR CYCLED UNSAFE AND 	THEN RETRACTED. APPROXIMATIVE 10 SEC. LATER IT OCCURRED AGAIN BUT THIS TIME DID NOT RETRACT. FLIGHT CREW CYCLED GEAR DOW	N MANUALLY IAW QRH BOOK, RECEIVED 3 GREEN LIGHTS (DOORS CLOSED) AND WHEN SELECTED GEAR UP, THE GEAR RETRACTED NORMALLY A	ND LOCKED. ON LANDING AT DESTINATION, LANDING GEAR EXTENDED NORMALLY AND AIRCRAFT LANDED NORMALLY. MAINTENANCE REPLACED 	THE NLG DRAG STRUT ACTUATOR.  (TC NR 20070903001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110200039	20071102	00039	EA  	2007	11	2	CA070904001      	2	20070902	G	8530	LW19001	EXHAUST VALVE   			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					NR 1 CYLINDER	WORN            	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA			1836 								(CAN) AN INTERMITENT SLIGHT POWER LOSS WAS INITIALY MISDIAGNOSED AS A FAULTY GOVERNOR CONTROL BOX. WHEN THE PROBLEM PERS	ISTED, IT WAS DETERMINED THAT THE EXHAUST VALVE IN THE NR 1 CYLINDER WAS WORN AND HAD A SMALL PIECE MISSING. THE CYLINDE	R ASSEMBLY IS CURRENTLY BEING REPLACED. (TC NR 20070904001)				1	G	7	1 	3O	3	O		H11NM   	E295				 
2007110200040	20071102	00040	NM  	2007	11	2	CA070904002      	1	20070902	G	2760	85770068003	LEVER           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GROUND SPOILER	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW SNAGGED THAT THE GROUND SPOILER LIGHT ILLUMINATED IN FLIGHT. UPON INVESTIGATION MAINTENANCE FOUND 	THE LT OB GROUND SPOILER LEVER BROKEN AT THE SPOILER ACTUATOR ATTACH POINT. THE LEVER WAS REPLACED AND THE AIRCRAFT RETU	RNED TO SERVICE. (TC NR 20070904002)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007102600114	20071026	00114	SO  	2007	10	26	CA070904003      	1	20070829	G	5343		TRUNNION        			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			39503								(CAN) DURING THE A-CHECK INSPECTION, MAINTENANCE DETECTED A CRACKED RT NOSE LANDING GEAR TRUNNION FITTING. THE AIRCRAFT 	WAS RE- POSITIONED FOR PART REPLACEMENT. (TC NR 20070904003)					2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
2007102600115	20071026	00115	GL  	2007	10	26	CA070905001      	2	20070811	G	7250	TBA	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 5	DISINTEGRATED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			X	E	J	ENGINE FLAMEOUT           	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			CA			3576 	758  							(CAN) FLIGHT CREW ENCOUNTERED A NR 2 ENGINE CHIP WARNING LIGHT FOLLOWED BY COMPLETE ENGINE FAILURE WITHIN 1 MIN EMERGENC	Y LANDING EXECUTED.  NR 2 ENGINE AND OIL COOLER REPLACED, A/C RETURNED TO SERVICE.  SUBSEQUENT INVESTIGATION CARRIED OUT	 AT AMO REVEALED FAILURE OF THE NR 5 BEARING. THE BEARING FAILURE CAUSED POWER TURBINE ROTOR VIBRATION AND OSCILLATION R	ESULTING IN SUBSEQUENT DAMAGE AND DECOUPLING OF TURBINE TO COMPRESSOR (N1) COUPLING. THE GAS GENERATOR TURBINE ENTERED O	VER-SPEED OF UNKNOWN VALUE. THE GP TURBINE OVER SPEED CAUSED NR 2 TURBINE BLADES TO PROGRESSIVELY SEPARATE FROM THE DISK	. THE NR 5 BEARING HAD BEEN OVERHAUL INSPECTED BY THIS AMO APPROXIMATELY 757.9 HRS PRIOR TO FAILURE AND RE-INSTALLED AS 	1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2007110200041	20071102	00041	EU  	2007	11	2	CA070905002      	1	20070828	G	2421		ALTERNATOR      			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 2	INOPERATIVE     	W				A	D			UNSCHED LANDING         	RETURN TO BLOCK         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER DEPARTING AND ENROUTE, THE CREW OBSERVED NR 2 ALTERNATOR HAD TRIPPED OFFLINE AND DID NOT RESET. THE AIRCRAFT	 RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE NR 2 ALTERNATOR. THE AIRCRA	FT COMPLETED A SATISFACTORY GROUND RUN AND WAS RETURNED TO SERVICE. (TC NR 20070905002)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007102600116	20071026	00116	EA  	2007	10	26	CA070905003      	1	20070904	G	2750	601R9310511	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) WING FLAPS FAILED TO FULLY EXTEND FOR LANDING. AFTER SELECTING FLAPS 8 THE CREW RECEIVED A FLAP FAULT CAUTION MESS	AGE AND THE FLAPS WOULD NOT MOVE ANY FURTHER. THE CREW LANDED WITH FLAPS AT 8 DEGREES UNEVENTFULLY. FECU SHOWS LT BPSU A	T FAULT. BPSU REPLACED, RIGGED AND FUNCTIONAL TEST COMPLETED SUCCESFULLY.  AIRCRAFT RETURNED TO SERVICE. (TC NR 20070905	003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007102600117	20071026	00117	EU  	2007	10	26	CA070905004      	1	20070828	G	7930	810710000	TRANSMITTER     			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	OIL PRESSURE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) WHILE INBOUND, THE CREW OBSERVED LOW OIL PRESSURE ON THE NR 1 ENGINE WITH A LOCAL ALERT LIGHT INDICATION THE CREW 	SHUT THE ENGINE DOWN AND LANDED WITHOUT FURTHER PROBLEM.  MAINTENANCE VERIFIED THAT THERE WAS NO OIL LOSS AND REPLACED T	HE NR 1 OIL PRESSURE TRANSMITTER. THE AIRCRAFT WAS GROUND RUN SATISFACTORILY AND RETURNED TO SERVICE. FULL P/N IS 8107-1	00-00-10 (TC NR 20070905004)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007102600118	20071026	00118	EU  	2007	10	26	CA070905005      	1	20070830	G	3240	30Z10322	LEVER           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	PARK BRAKE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ARRIVING AT AIRPORT, THE AIRCRAFT ROLLED FORWARD AFTER THE PARK BRAKE WAS APPLIED WITH ENGINES STILL RUNNING	 AND THEN CONTACTED GROUND EQUIPMENT.  MAINTENANCE DETERMINED THAT THERE WAS A FAULT WITH THE PARK BRAKE SYSTEM AND THE 	HANDLE ASSEMBLY WAS REPLACED.  THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070905005)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007102600119	20071026	00119	CE  	2007	10	26	CA070905006      	1	20070810	G	5312	051218712	CHANNEL         	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2923 			17263199					(CAN)  SEB 97-1 ADDRESSES THE POSSIBILITY OF CRACKING OF THE AFT DOORPOST CHANNELS AT THE LOWER END, IN THE SMALL CUTOUT	 RADIUS BETWEEN THE VERTICAL AND HORIZONTAL FLANGE BENDS. THE CRACK IS VERY DIFFICULT TO SEE. BOTH DOORPOSTS WILL CRACK,	 AND IT IS THE SUBMITTERS OPINION THAT THIS CRACKING IS CAUSED CHIEFLY BY TAXIING OVER ROUGHER GROUND SO THAT THE FUSELA	GE BULKHEAD THAT INCORPORATES THE AFT DOORPOSTS FLEXES MORE THAN IN MOST OTHER OPERATIONS. THIS IS THE THIRD AC WE HAVE 	FOUND WITH THIS DEFECT WITHIN THE LAST 7 YEARS. (TC NR 20070905006)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007102600120	20071026	00120		2007	10	26	CA070905007      	4	20070831	G	3170	6229820009	DCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 3	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, CREW REPORTED A (L ENG MISCOMP) MESSAGE FOLLOWED BY A HIGH ITT. THE CREW ELECTED TO SHUTDOWN THE	 ENGINE. AFTER SHUTDOWN THE ITT REMAINED AT 998 DEGREES CELSIUS. AT TIME OF THE INCIDENT, THE AIRCRAFT WAS OPERATING UND	ER MEL31-41-01 DUE TO AN INOPERATIVE DCU NR 3.   DURING TROUBLESHOOTING, IT WAS DISCOVERED THAT SEVERAL SNAGS OCCURRED F	OLLOWING THE REPLACEMENT OF ONE DCU WITH A P/N 622-9820-009. ALL OTHERS DCU WERE P/N 622-9820-008. ACCORDING TO SL RJ-SL	-31-011 BOTH P/N ARE INTERCHANGEABLE AND INTERMIXABLE.   DCU NR 1 AND NR 3 WERE REPLACED AND THE AIRCRAFT WAS RELEASED I	NTO SERVICE. NO SIMILAR INCIDENT TO DATE HAS BEEN NOTED. (TC NR 20070905007)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110200042	20071102	00042	EU  	2007	11	2	CA070905009      	1	20070904	G	2121		FAN             			AIRBUS	330   	A330300     	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  						MELTED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER T/O, SMOKE AND UNUSUAL SOUND COMING FROM L2 AREA. HAZE REPORTED IN THE CABIN. FLT RETURNED TO AIRPORT. ELECT	RICAL ODOR WAS COMING FROM THE L2/R2 AREA WITH HAZE VISIBLE AT 5 DIFFERENT TIMES. IT WOULD APPEAR AND THEN DISAPPEAR.  A	REA INSPECTED AND FOUND MID-GALLEY CHILLER DUCT CLAMP ADRIFT, CAUSING UNUSUAL SOUND (S513) AND THE PROJECTOR 7DG (B-CLAS	S) OVERTEMP LIGHT ON. FOUND COOLING FAN MELTED. CONNECTOR PLUG REMOVED. NEW CHILLER CLAMP INSTALLED. PROJECTOR REPLACED.	 (TC NR 20070905009)		2	L	7	2 	4F	4	F	RT	        	A12EU				 
2007102600121	20071026	00121	NM  	2007	10	26	CA070905010      	1	20070903	G	2910	15E0803003	PIPE            			EMB   	ERJ170	ERJ170100SU 	3260403	NM  	GE    	CF34  	CF348E5A1   	30015	NE  					HYD SYSTEM	CUT             	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE A CHECK INSPECTION A CUT APPROXIMATELY 1 CM LONG WAS NOTICED ON THE ENGINE HYDRAULIC PUMP SUPPLY PI	PE. THIS CUT WAS APPROXIMATELY .050 DEEP AND WAS THE RESULT OF CHAFFING WHEN THE COWLS WERE CLOSED. (TC NR 20070905010)					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2007102600122	20071026	00122	EA  	2007	10	26	CA070905011      	1	20070903	G	7500	16673301	DUCT            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	BLEED AIR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABIN PACK REPORTED AS UNCONTROLLABLE AT LOW POWER SETTINGS. MAINTENANCE GROUND RUNS NOTED NON SUPPLY OF BLEED AIR	 AT FLIGHT IDLE SETTINGS, ALSO NOTED BLEED AIR LEAK FROM CEILING OF ACM COMPARTMENT. ACCESS GAINED TO INTERNAL OF DORSAL	 FIN AND FOUND BLEED AIR DUCT P/N 16673-301 CONNECTS TO FUSELAGE DUCT, CRACKED AND SPLIT OPEN APPROX HALF OF ITS DIAMETE	R. DUCT REPLACED, GROUND RUNS COMPLETED AND AIRCRAFT RETURNED TO SERVICE.  PART IS CONSIDERED AS AN EXPENDABLE AND TIMES	 NOT TRACKED. AIRFRAME TIMES 36419HR/51123CY (TC NR 20070905011)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007102600123	20071026	00123	SO  	2007	10	26	CA070905012      	2	20070831	G	8530	TSIN712ACA	CYLINDER HEAD   			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			1343 					282939R			(CAN) CRACKED FROM SPARK PLUG HOLE TO EXHAUST VALVE (TC NR 20070905012)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
2007102600124	20071026	00124	EU  	2007	10	26	CA070906001      	1	20070827	G	5531		SPAR            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7617 								(CAN) CRACKS DISCOVERED ON BOTH SIDES OF STABILIZER THROUGH LOWER DOUBLER AT SPAR. FOUR RIVETS FOUND MISSING FROM FORWAR	D SPAR ATTACHMENT OF LOWER STABILIZER FRAME. (VISISBLE UPON REMOVAL ONLY) SUSPECT INCORRECT SHIMMING AT THIS TIME. (TC N	R 20070906001)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2008030600144	20080306	00144	CE  	2008	3	6	CA070906002      	1	20070905	G	5520	115610010325	TORQUE TUBE     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			209  								(CAN) DURING A ROUTINE INSPECTION THE LT ELEVATOR TORQUE TUBE WAS FOUND TO HAVE AN EXCESSIVE AMOUNT OF PLAY AT THE TAPER	 PINS ON BOTH COLLARS. THE TORQUE TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS TORQUE TUBE ONLY HAD 209.	2 HOUR SINCE NEW AND IT IS ONLY REQUIRED TO BE INSPECTED EVERY 1000 HOUR. (TC NR 20070906002)				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2007110200043	20071102	00043	NM  	2007	11	2	CA070906003      	1	20070902	G	5340	85311176009	ATTACH FITTING  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED NOSE LANDING GEAR CHANGE, IT WAS DISCOVERED THAT THE NLG UPLOCK ACTUATOR FITTING ASSEMBLY P/N 853	11176-009 WAS CRACKED. FITTING REPLACED AND FITTING FASTENERS INSTALLED IAW RD8-53-3805. AFTT: 42865 HRS. TOTAL CYCLES: 	50005. (TC NR 20070906003)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110200044	20071102	00044	NM  	2007	11	2	CA070906004      	1	20070904	G	3231	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LEFT NACELLE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			1411 								(CAN) ON DEPARTURE FROM AIRPORT, THE LEFT MAIN LANDING GEAR DOORS REMAINED OPEN. VISUALY CONFIRMED BY THE PURSER THAT TH	E LT GEAR DOORS WERE LEFT OPEN. CREW SELECTED GEAR DOWN AND LEFT GEAR DOORS CLOSED WHILE THE OTHER GEAR DOORS OPENED. CR	EW PERFORMED ALTERNATE EXTENSION OF THE MAIN LANDING GEAR AND RETURNED TO CYUL. MAINTENANCE INVESTIGATION REVEALED THAT 	WHEN THE LEFT GEAR DOOR CLOSED THE MAIN LANDING GEAR CAME DOWN DAMAGING THE LEFT MAIN OUTBOARD GEAR DOOR.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007110200045	20071102	00045	GL  	2007	11	2	CA070906006      	2	20070903	G	7210		GEARBOX         			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	HAMSTD	54H	54H60       	NE  	NR 2	UNKNOWN         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			192  								(CAN) NR 2 ENGINE OIL PRESSURE AND QUANTITY INDICATION BOTH SHOWED A DECREASE UPON REACHING CRUISE ALT.  NR 2 ENGINE SHU	TDOWN AND RETURNED TO DEPARTURE.  NR 2 REDUCTION GEARBOX BEING REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 2007090	6006)				2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2008030600145	20080306	00145	CE  	2008	3	6	CA070906007      	1	20070904	G	2750	1005240741	GEARBOX         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	TE FLAPS	WORN            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) FLAPS WOULD NOT RETRACT AFTER LANDING. GEARBOX FOUND EXCESSIVELY WORN. (TC NR 20070906007)						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007102600125	20071026	00125	EA  	2007	10	26	CA070906008      	1	20070903	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			11434								(CAN) CREW REPORTED THAT ON SHORT FINAL, CAPTAIN LT SIDE WINDOW CRACKED.  REPLACED SIDE WINDOW IAW AMM (TC NR 2007090600	8)					2	L	7	2 	4F			RT	A21EA   					 
2007102600126	20071026	00126	NE  	2007	10	26	CA070906009      	2	20070813	G	7250		BLADES          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA			25122								(CAN) A/C DIVERTED DUE TO NR 2 ENG. VIBRATION AND LOUD NOISE. NR 2 ENGINE WAS SHUTDOWN IN FLIGHT. PILOT DECLARED AN EMER	GENCY. CONTRACT MAINTENANCE FOUND THE EXHAUST TURBINE BLADES DAMAGED.   PRELIMINARY INSPECTION THAT THE LAST STAGE TURBI	NE WITH TOTAL DAMAGE TO ALL BLADES. APPEARS THAT SOMETHING IN BETWEEN THE FIRST STAGE HPT AND LAST STAGE LPT CAME LOOSE 	AND DEPARTED THROUGH THE TURBINE.  ENG WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. ENG IS IN ENG SHOP AND IS BEING PR	EPPED FOR SHIPPING. (TC NR 20070906009)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007102600127	20071026	00127	NM  	2007	10	26	CA070907001      	1	20070906	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, GEAR WOULD NOT RETRACT RESULTING IN AN AIR TURNBACK. DURING GROUND INSPECTION FOUND NOSE GEAR HARNE	SS TO BE INTERMITTENT DURING TESTING. DETAILED INSPECTION OF HARNESS FOUND IN SHARP BEND OF CONDUIT BOTH WOW SENSOR HARN	ESS AND NOSE WHEEL CENTERING HARNESS CRACKED AND SHIELDING EXPOSED. NLG WOW 2/CENTERING HARNESS HARNESS REPLACED. (TC NR	 20070907001)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007110200046	20071102	00046	SO  	2007	11	2	CA070907002      	1	20070906	G	3411	LPMILH55934	HOSE            			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	GARRTT	TFE731	TFE73140    	29001	NE  					STATIC SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			985  								(CAN) DURING PITOT STATIC CHECKS IT WAS FOUND THE SYSTEM WAS SLIGHTLY LEAKING. FURTHER VISUAL INSPECTION FOUND THE STATI	C HOSE GOING TO THE ADC WAS WEATHER CRACKED AND LEAKING NEAR THE FITTING. THE HOSE WAS MFG THE FIRST QUARTER OF 2001.(1Q	01).(25W752005-063H) PREVIOUSLY G100 C-FHRL SN NR 150 HAD 3 HOSES REPLACED FOR THE SAME REASON AND BY ERROR AN SDR WAS N	OT SUBMITTED. ALSO 1 OF THE SAME BASE NR HOSES WAS REPLACED ON C-FHNS G100 SN NR 156. ASTRA SPX (G100) NR 087 C-FRJZ WER	E LOOKED AT AND THE HOSES WERE FINE. THIS SEAMS SOMEWHAT PREMATURE AGING FOR THESE HOSES. THE HOSES ARE LOCATED IN THE N	OSE COMPARTMENT AREA AND THERE ARE 2 IAW ADC HAVING THE SAME BASE NR AND DIFFERENT DASH NRS. (TC NR 20070907002)	2	L	7	2 	4F	4	F	RT	A12EA   	E1NM				 
2008030600146	20080306	00146	SW  	2008	3	6	CA070907003      	1	20070906	G	5740	31692	ATTACH FITTING  			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235K2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	WING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1000 								(CAN) AD 96-18-02 AND THE AIRWORTHINESS LIMITATIONS FOR THIS AC REQUIRE THAT THE WING SPAR/STRUT ATTACH FITTINGS BE REMO	VED AND NDI WITH FLUORESCENT DYE PENETRANT EVERY 1000 HOURS.  NDI DISCLOSED A FLAW WITHIN THE METAL, APPARENTLY EXISTING	 WITHIN THE RAW STOCK WHEN MFG, AND THE AMOUNT OF DYE THAT BLED OUT INDICATES THAT THE FLAW EXTENDS DEEPLY INTO THE META	L. IT IS NEAR THE TOP BOLT HOLE WHERE THE STRESSES ARE MINIMAL, AND NO CRACKING WAS NOTED BETWEEN THE FLAW AND THE HOLE.	 (TC NR 20070907003)		1	H	7	1 	3O	3	O		A759    	E223	5	N	P9045	 
2008012900026	20080129	00026	EA  	2008	1	29	CA070907004      	2	20070906	G	7310	3040637	FUEL LINE       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE BAY	CHAFED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								PCE32232			(CAN) FUEL LINE ASSY WAS FOUND TO HAVE BEEN CHAFED BY THE STARTER GENERATOR VENT HOSE, CAUSING A VERY SMALL PIN HOLE IN 	THE RIGID STAINLESS FUEL LINE, RESULTING IN A FUEL LEAK. (TC NR 20070907004)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007110200047	20071102	00047	NM  	2007	11	2	CA070907005      	1	20070907	G	5751	85740337105106	HINGE FITTING   			DHAV  	DHC8  	DHC8301     	1386003	NM  										AILERON	MIGRATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22128								(CAN) THE BEARINGS ON THE AILERON HINGE FITTINGS LOCATED AT YW515.19 WERE FOUND TO BE MIGRATED. IT WAS FOUND THAT THE HI	NGE FITTING P/N`S 85740337-105/-106 WERE MANUFACTURED INCORRECTLY SINCE THE DISTANCE BETWEEN THE TWO LUG FACES (0.850 IN	CH NOMINAL) MEASURES 0.970 INCH. (TC NR 20070907005)				2	H	7	2 	4T			RT	A13NM   					 
2008013100045	20080131	00045	SW  	2008	1	31	CA070909001      	1	20070908	G	2421	LW10382	BRACKET         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360*     	41514	EA  					ALTERNATOR	BROKEN          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ALTERNATOR BRACKET FOUND WITH BROKEN ATTACHMENT LUG. ALTERNATOR BELT TENSION LOSS AND SUBSEQUENT SYSTEM UNSERVICEA	BILITY. CAUSE OF FAILURE UNDER INVESTIGATION. (TC NR 20070909001)					1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2007102600128	20071026	00128	EA  	2007	10	26	CA070909002      	2	20070904	G	7314	RG908054AM	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA				7    							(CAN) DURING START UP THE ENGINE WOULD NOT MAINTAIN FUEL PRESSURE AT 700 RPM. ENGINE WOULD NOT SUSTAIN POWER AT 2000 RPM	 AND PRESURE DROPS AND ENGINE QUITS. ENGINE DRIVEN FUEL PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. ENGINE WAS P	REVIOUS OVERHAULED ALONG WITH FUEL PUMP. (TC NR 20070909002)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007102600129	20071026	00129	GL  	2007	10	26	CA070910001      	3	20070907	G	6110	1A101	PROPELLER       			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100*      	GL  		CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1343 							(CAN) WHILE PERFORMING A 5 YEAR CORROSION INSPECTION ON SUBJECT PROPELLER IAW CAR 625 APPENDIX C, PARA.5, CORROSION WAS 	NOTED IN THE MOUNTING HOLE BORE. IN CONSULTATION WITH THE PROPELLER OVERHAUL AMO, IT WAS DECIDED TO SEND IT TO THEM FOR 	FURTHER EVALUATION. CURRENTLY AWAITING THEIR REPORT AS TO IT`S STATUS. (TC NR 20070910001)				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2008022500080	20080225	00080	NE  	2008	2	25	CA070910002      	2	20070905	G	7314	D7431	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX FUEL SYS	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AUX FUEL PUMP FOUND UNSERVICEABLE DURING DI REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20070910002)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110200048	20071102	00048	EU  	2007	11	2	CA070910003      	1	20070906	G	2910	T2C5000605500	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					HYDRAULIC SYS	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) 10 MINUTES PRIOR TO LANDING, THE PORT AND STARBOARD HYDRAULIC PUMP LIGHTS ILLUMINATED WITH MAIN PRESSURE DEPLETING	 AND STOPPING AT ACCUMULATOR PRESSURE. THE CREW CARRIED OUT THE APPROPRIATE PROCEDURES AND LANDED WITH NO FURTHER INCIDE	NT. MAINTENANCE FOUND A HYDRAULIC FLEX LINE, IN THE RT WHEEL BAY, WHICH GOES TO THE HIGH-PRESSURE HYDRAULIC FILTER RUPTU	RED. THE FLEX LINE, ALONG WITH BOTH HYDRAULIC PUMPS, WAS REPLACED AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC NR 20	070910003)		2	L	7	2 	3T	4	T		A24EU   	A196				 
2007102600130	20071026	00130	CE  	2007	10	26	CA070910004      	1	20070909	G	2510	110195203	BUCKLE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEATBELT	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 CREW SEAT BELT BUCKLE INSPECTION, (REFER TO FAA SAIB NM	-06-29)INTERFERENCE BETWEEN THE COCKPIT SEATBELT BUCKLES AND THE CONTROL COLUMN WOULD UNLATCH THE SEATBELT BUCKLE WHEN T	HE YOKE WAS MOVED THROUGH FULL TRAVEL LT AND RT.   THERE ARE NO CURRENTLY APPROVED SEAT BELT REPLACEMENTS AVAILABLE TO E	LIMINATE THIS HAZARDOUS SITUATION. (TC NR 20070910004)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008022500081	20080225	00081	CE  	2008	2	25	CA070910005      	1	20070822	G	5720	6147514435	WASHER          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING CF-1981-25R6 LOWER FWD WING ATTACH FITTINGS YOU MUST REPLACE THE LOWER FWD. WING BOLT WASHER ASSY UPON	 RE-INSTALL OF BOLTS. NEW WASHER KITS WERE INSTALLED, BUT WERE UNABLE TO TORQUE IAW THE MFG SIRM., THE TORQUE WAS TOO GR	EAT TO GET THE REQUIRED READING OF THE SPRING SCALE, THE THREADS ON THE NUTS WERE DAMAGED AND SO WERE THE THREADS ON THE	 BOLTS. THE BOLTS AND NUTS WERE REPLACED WITH NEW, AND THE WASHER KITS WERE ALSO REPLACED, AND NORMAL TORQUE WAS ATTAINE	D. (TC NR 20070910005)		1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007110200049	20071102	00049	SO  	2007	11	2	CA070910006      	2	20070901	G	8530	641917	CYLINDER        			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	EXHAUST VALVE	STUCK           	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA								21468372A			(CAN) ON CLIMB OUT AFTER TAKEOFF, THE PILOT NOTICED MILD TO MODERATE ENGINE VIBRATION WITH A PARTIAL LOSS OF POWER. A RE	TURN TO THE AIRSTRIP WAS CARRIED OUT WITH A SUCCESSFUL LANDING. ON INVESTIGATION BY AN AME, THE PROBLEM WAS NOTICED AS A	N EXHAUST VALVE STUCK OPEN ON THE NR 3 CYLINDER. THE CYLINDER WAS REMOVED AND WAS SENT TO AN ENGINE OVERHAUL SHOP FOR RE	PAIRS. THE CYLINDER IS STILL BEING REPAIRED AND WILL BE REINSTALLED UPON RETURN FROM THE SHOP. (TC NR 20070910006)			1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2007102600131	20071026	00131	GL  	2007	10	26	CA070910007      	2	20070910	G	7321	23070606	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA				147  							(CAN) OVERSPEED OCCURED DURING FLIGHT, FUEL CONTROL REPLACED WITH SERVICEABLE UNIT. WHEN REMOVED, IT WAS NOTED THAT THE 	FCU INPUT SHAFT BEARING WAS DAMAGED. FCU SENT OUT FOR INSP/REPAIR. (TC NR 20070910007)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007110200050	20071102	00050	WP  	2007	11	2	CA070910008      	2	20070827	G	7322	8978012	FCU             			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT ENGINE	MALFUNCTIONED   	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				2302 							(CAN) AFTER AIRCRAFT LANDED AND SPEED LEVERS WERE PULLED BACK INTO LOW IDLE THE RT ENGINE LIGHT CAME ON AT WHICH POINT T	HE CREW REALIZED THAT THE ENGINE HAD SHUTDOWN. THE FCU AND FUEL PUMP WERE REPLACED. AIRCRAFT CHECKED OUT SERVICIBLE AND 	NO FURTHER REPORTED INCIDENCES. (TC NR 20070910008)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007110200051	20071102	00051	WP  	2007	11	2	CA070910009      	1	20070907	G	3240	147515	BRAKE           			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA				177  							(CAN) ON LANDING RT BRAKE FAILED. RT BRAKE FOUND TO BE LEAKING A LARGE QUANTITY OF HYDRAULIC FLUID. BRAKE WAS REPLACED. 	(TC NR 20070910009)					2	H	7	2 	4R	4	R		A25WE   	E259	6	C	P8879	 
2007110200052	20071102	00052	EU  	2007	11	2	CA070911001      	1	20070906	G	2435	8260123	STARTER GEN     			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER DEPARTING, THE CREW OBSERVED A NR 2 GENERATOR FAULT AND THE CREW ELECTED TO RETURN TO POINT OF DEPARTURE. MA	INTENANCE REPLACED THE NR 2 GENERATOR CONTROL UNIT (GCU) AN THE AIRCRAFT WAS CHECKED SERVICEABLE AN RETURNED TO SERVICE.	 THE PROBLEM REOCCURRED APPROXIMATELY ONE HOUR AFTER THE AIRCRAFT HAD MADE A SECOND DEPARTURE. THE AIRCRAFT RETURNED TO 	POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE NR 2 STARTER GENERATOR AND THE AIRCRAFT RETURNED TO	 SERVICE WITHOUT FURTHER PROBLEM REPORTED.  (TC NR 20070911001)		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008022500082	20080225	00082	EU  	2008	2	25	CA070911002      	1	20070906	G	3240		BRAKE ASSY      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	MLG	LOCKED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING TOUCH DOWN THE RT MLG IB TIRE WENT FLAT. THE FAILURE WAS ATTRIBUTED TO BRAKE LOCKUP. THE AC WAS TOWED FROM 	THE RUNWAY. MAINT CHECKED THE NR 3 AND NR 4 POSITION BRAKE AND ANTISKID SYSTEMS WITH NO FAULT FOUND. THE NR 3 AND NR 4 W	HEEL TIRE ASSEMBLIES WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070911002)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007102600132	20071026	00132	NM  	2007	10	26	CA070911003      	1	20070907	G	7312	32015	VALVE           			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUEL HEAT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 25 MINUTES AFTER DEPARTING, THE CREW OBSERVED THE NR 1 ENGINE OIL TEMPERATURE CLIMBING THROUGH THE Y	ELLOW BAND. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 FUEL 	HEAT VALVE AND CONDUCTED THE APPROPRIATE OVERWEIGHT LANDING INSPECTION BEFORE THE AIRCRAFT WAS RETURNED TO SERVICE. (TC 	NR 20070911003)			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2007110200053	20071102	00053	NE  	2007	11	2	CA070911004      	2	20070827	G	7250	FW35594	TURBINE BLADES  			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					HP1	FAILED          	W				C				ABORTED TAKEOFF         				M	J		OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			CA			2693 					13318			(CAN) DURING ENGINE THROTTLE FOR TAKEOFF, ISSUED (TGT-OVRTP, MAX=1146 LIMIT=900) AND ENGINE SURGE. THE PILOT THROTTLED D	OWN, THE AIRCRAFT WAS RETURNED TO THE GATE AND PASSENGERS WERE UNLOADED.  METAL (TURBINE BLADE PARTICLES) WERE FOUND IN 	THE TAILPIPE UPON VISUAL INSPECTION. ENGINE JUST BEING INDUCTED AT MFG FOR INVESTIGATION. FURTHER DETAILS WILL BE SUBMIT	TED AFTER ENGINE DISSASSEMBLY. (TC NR 20070911004)			2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2007110200054	20071102	00054	NM  	2007	11	2	CA070911005      	1	20070906	G	2421	31708500	ADAPTER         	LUCAS       		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GENERATOR	PULLED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			11421	1454 		874					(CAN) WHILE ENROUTE FLIGHT CREW RECEIVED A NR 1 ENGINE OIL PRESSURE LOW INDICATION AND ALSO HAD A VISUAL INDICATION OF D	ECLINING OIL PRESSURE. CREW SHUTDOWN NR 1 ENGINE AND DIVERTED TO AN ALTERNATE AIRPORT. CREW DID NOT DECLARE AN EMERGENCY	 AND LANDED SAFELY WITHOUT FURTHER INCIDENT. MAINTENANCE TROUBLESHOOTING FOUND THAT THE AC GENERATOR ATTACH STUDS HAD PU	LLED THROUGH THE ADAPTOR MOUNTING PLATE CAUSING THE AC GENERATOR TO BECOME LOOSE AND LEAK OIL. MOUNTING PLATE AND AC GEN	ERATOR WERE REPLACED. ENGINE WAS SERVICED WITH OIL, FUNCTION AND LEAK CHECKS COMPLETED WITH NO FURTHER FAULTS FOUND. (TC	 NR 20070911005)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007102600133	20071026	00133	EU  	2007	10	26	CA070911007      	1	20070907	G	3240	10903000	PAD             	PARKER      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				552  		1172					(CAN) PILOT REPORTED SPONGY FEELING WHEN RT BRAKE PEDAL ACTUATED. UPON FURTHER INSPECTION FOUND BRAKE WEAR PADS PREMATUR	ELY WORN IN A CUPPING SHAPE BEYOND LIMITS. BRAKE ASSEMBLY REPLACED AND RETURNED TO STORES. (TC NR 20070911007)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008030600147	20080306	00147	CE  	2008	3	6	CA070911008      	1	20070907	G	3233	99810057652	ACTUATOR        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	STRIPPED        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF GEAR SELECTED UP RT GEAR DID NOT COME UP.   GEAR SELECTED DOWN,  (3) GREEN INDICATIONS OBSERVED AC L	ANDED.  AC BROUGHT INTO HANGER AND PUT ON JACKS RT MLG ACTUATOR REMOVED.  FOUND THAT NUT, ACTUATOR P/N 115-810029-24 HAD	 NO TREADS IN IT. PART SENT OUT FOR TEARDOWN REPORT (TC NR 20070911008)				1	L	7	2 	3T	3	T		A14CE   	E4EA	6	C	P15EA	 
2007110200055	20071102	00055	CE  	2007	11	2	CA070911009      	1	20070830	G	5730	652230553	SKIN            			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3401 								(CAN) DE-ICE BOOT REPLACEMENT AT MFG. AFTER REMOVAL OF DE-ICE BOOT NOTED AREA OF FUEL STAINING, CORROSION NOTED. DISCONT	INUED BOOT REPLACEMENT, OBTAINED FERRY PERMIT AND RELOCATED AIRCRAFT.  FURTHER INVESTIGATION SHOWS: SEVERAL LOCATIONS OF	 CORROSION DAMAGE WERE NOTED ON THE IB, LT WING, LEADING EDGE SKIN (P/N 6522305-53) BETWEEN WS 86.20 AND WS 91.00. THE D	AMAGE WAS SUCH THAT THE SKIN PANEL WAS REQUIRED TO BE REPLACED. CORROSION DAMAGE WAS ALSO NOTED ON THE OB, LT WING, LEAD	ING EDGE SKIN (P/N 5522300-45) BETWEEN WS 91.00 AND WS 91.50. SEE PAGE 2.1 ATTACHED FOR DAMAGE LOCATION. MFG HAS INDICAT	ED OTHER SAME TYPE AIRCRAFT HAVE NEEDED SKIN REPAIRS DUE TO THE SAME TYPE CORROSION PROBLEM. THIS SEVERE CORROSION OCCUR	1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
2007110200056	20071102	00056	WP  	2007	11	2	CA070911010      	2	20070829	G	7321	307080022	FUEL CONTROL    			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			663  					P84414			(CAN) - MANUAL MODE SELECTION PROVIDES IDLE ONLY FUEL. NO SPOOL UP WITH POWER LEVER INCREASE.   ENGINE FUNCTIONS NORMALL	Y IN AUTO - COMPUTER (ON) MODE. (TC NR 20070911010)					2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2007110200057	20071102	00057	NE  	2007	11	2	CA070911011      	2	20070910	G	7414		UNKNOWN         			CURTIS	C46   	C46DAIRLIFT 	       	SO  	PWA   	R2800 	R280051M1   	52026	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	UNKNOWN         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) PRECAUTIONARY SHUTDOWN DUE TO ROUGH RUNNING, ENGINE RUNUP ON GROUND BY MAINTENANCE AND SUSPECT BAD MAGNETO. THE EN	GINE WILL BE INSPECTED AND TIMED ACCORDINGLY. (TC NR 20070911011)					2	L	7	2 	4R	4	R		3A2     	5E8	6	C	P603	 
2007110200058	20071102	00058	NE  	2007	11	2	CA070911012      	2	20070905	G	7260	547344P3	STUD            			BOEING	727   	727260      	138408K	NM  	PWA   	JT8   	JT8D17      	52049	NE  					GEARBOX	DISLODGED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE NR 2 OIL QUANTITY SLOWLY DECREASED TO ZERO. WHEN THE OIL QUANTITY WENT BELOW THE GREEN ARC THE 	FLIGHT CREW SHUTDOWN THE ENGINE USING THE APPROPRIATE CHECKLIST AND AN EMERGENCY WAS DECLARED INTO AIRFIELD. THE AIRCRAF	T LANDED WITHOUT FURTHER INCIDENT.  MAINTENANCE INVESTIGATED AND A STUD WAS FOUND ADRIFT FROM THE ACCESSORY DRIVE GEARBO	X, FORWARD LOWER SPLIT LINE. THE THREADS WERE INSPECTED AND FOUND TO BE SERVICEABLE. THE STUD WAS REINSTALLED AND TORQUE	D. THE ENGINE OIL FILTER WAS REMOVED AND INSPECTED. NO CONTAMINATION WAS FOUND AND THE OIL FILTER WAS REPLACED WITH A NE	W UNIT. ENGINE GROUND RUN AND LEAK CHECK WAS CARRIED OUT AND WAS CHECKED SERVICEABLE WITH NO LEAKS.  THE AIRCRAFT DEPART	2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2007110200059	20071102	00059	EA  	2007	11	2	CA070911013      	1	20070908	G	2750		BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						FAULTED         	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) THE CREW RECEIVED A FLAP FAIL MESSAGE AFTER SELECTING THE FLAP TO 0 DEGREE AFTER LANDING. THE FECU TO LT BPSU WIRI	NG WAS INSPECTED AND NO FAULT WAS FOUND. FECU WAS REPLACED, FUNCTIONAL TEST COMPLETED AND THE AIRCRAFT RELEASED INTO SER	VICE,   FOUR FLIGHTS LATER THE CREW EXPERIENCED A FLAP FAIL MESSAGE WHEN FLAP WERE SELECTED FROM 0 TO 8 DEGREES IN PREPA	RATION FOR TAKE OFF. THE FECU FAULT CODE WAS AGAIN INDICATING PROBLEM WITH WIRING BETWEEN THE LT BPSU AND FECU. WIRING W	AS INSPECTED AND NO FAULT WAS NOTICED. FURTHER INVESTIGATION REVEALED THAT THE RT BPSU WAS AT FAULT. R/H BPSU WAS REPLAC	ED, FUNCTIONAL TEST COMPLETED AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20070911013)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600149	20080306	00149	GL  	2008	3	6	CA070911014      	1	20070816	G	2720	2027220100	RUDDER PEDAL    			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  		WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4050 								(CAN) THE LT PILOT SIDE RUDDER CABLE PASSES THROUGH A TUBE ON THE PILOT RUDDER PEDAL. THIS TUBE WEARS AWAY DUE TO CHAFIN	G AND IS UNDETECTABLE UNTIL THE CABLE HAS TOTALLY WORN THROUGH RESULTING IN BOTH PEDAL ASSY AND CABLE DAMAGE. (TC NR 200	70911014)				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2007110200060	20071102	00060	EA  	2007	11	2	CA070911015      	2	20070907	G	8530	72877	TAPPET          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	BROKEN          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE HAS BEEN DOWN ON POWER FOR QUITE SOMETIME. UPON OVERHAUL TEARDOWN, IT WAS DISCOVERED THAT THE NR 1 AND 	NR 2 EXHAUST AND INTAKE TAPPET BODIES HAD BROKE. THE PIECES WERE TOO BIG TO BE DISCOVERED IN THE OIL SCREEN. (TC NR 2007	0911015)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2007110200061	20071102	00061	SO  	2007	11	2	CA070912001      	2	20070827	G	8520	536421	GEAR            								CONT  	O520  	IO520F      	17032	SO  					CRANKSHAFT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLESHOOTING A STARTER PROBLEM. THE CRANKSHAFT GEAR WAS FOUND TO BE MISSING 2 TEETH. ENGINE WAS DISASSEMB	LED, INSPECTED AND REPAIRED AS NECESSARY. PART OF THE MAGNETO IMPULSE CAM BROKE OFF, FELL DOWN INTO THE CRANK AND CAMSHA	FT GEARS. THE GEARS JAMMED AND BROKE THE TEETH OFF. (TC NR 20070912001)									3	O			E5CE				 
2007110200062	20071102	00062	EA  	2007	11	2	CA070912002      	2	20070824	G	8530		EXHAUST VALVE   								LYC   	O360  	AEIO360A1E  	41514	EA  	HARTZL	HCC2Y	HCC2YK4     	GL  	ENGINE	BROKEN          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			1170 								(CAN) EXHAUST VALVE BROKE AT HEAD. BROKEN PART EJECTED THROUGH EXHAUST PORT.  CYLINDER/VALVES/PISTON REPLACED.  NEW VALV	ES ON ORDER FOR REMAINING CYLINDER.  ENGINE HAS SPENT MOST OF ITS TOTAL TIME AT HIGH POWER AEROBATIC USE. (NEGLECTABLE W	EAR ON PISTON CYLINDER). (TC NR 20070912002)									3	O			1E10	5	C	P920	 
2007110200063	20071102	00063	SO  	2007	11	2	CA070912003      	2	20070830	G	8520	536421	GEAR            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					CRANKSHAFT	DAMAGED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA				940  				826612R			(CAN) PILOT/OPERATOR CONVEYED A STARTING ABNORMALITY. TROUBLESHOOTING FOUND THAT TWO TEETH WERE MISSING FROM CRANKSHAFT 	GEAR. ENGINE REMOVED AND SENT FOR FURTHER EVALUATION AT ATC  AMO NR 59-96. SEE SDR NR 20070912001 FROM AMO 59-96 FOR FUR	THRER FOLLOW UP. (TC NR 20070912003)				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007110200064	20071102	00064	CE  	2007	11	2	CA070912005      	1	20070823	G	5711	1217029	SPAR            			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3225 								(CAN) DURING A MAINTENANCE FUNCTION SEVERE CORROSION WAS DISCOVERED ON THE BOTTOM OF THE WING SPAR ENTRE SECTION. THIS S	ECTION OF THE SPAR HAS HIGH DENSITY FOAM GLUED TO THE SPAR WHICH PREVENTS ADEQUATE INSPECTION. THE CORROSION WAS SUCH TH	AT THE WING SPAR CENTRE SECTION REQUIRED REPLACEMENT. (TC NR 20070912005)				1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
2008030600150	20080306	00150	CE  	2008	3	6	CA070912007      	1	20070908	G	2750	1013800002	FLEX DRIVE      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	TE FLAP	SEIZED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ABOUT 2 MINUTES INTO A FLIGHT THE CREW DETECTED AN ELECTRICAL ODOR. THE PILOTS TURNED OFF THE VENT BLOWER SYS WHIC	H HELPED FOR A BIT BUT NOT LONG. NO SMOKE WAS NOTICED, JUST THE ODOR. ALL OTHER NON-ESSENTIAL ELECTRICS WERE TURNED OFF.	  THE SMELL STAYED SO AN EMERGENCY WAS DECLARED AND THE AC PREPARED TO LAND AT ITS INTENDED AIRPORT. WHEN THE AC WAS PRE	PARING TO LAND 17 DEGREES OF FLAP WAS SELECTED, THE AC INDICATOR SHOWED THAT THEY ONLY MADE IT TO 12 DEGREES. THE FLAPS 	WERE TRIED AGAIN AND DEEMED FAILED. THE GEAR WAS SELECTED DOWN AND THE LANDING WAS COMPLETED WITHOUT FURTHER INCIDENT. A	FTER MAINT ARRIVED AND ASSESSED THE SITUATION IT WAS FOUND THAT THE LT INNER FLAP DRIVE CABLE HAD SLOWLY BOUND UP AND SE	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2007110200065	20071102	00065	GL  	2007	11	2	CA070912008      	2	20070910	G	7314	6899253	PUMP            			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	250C  	250C20F     	03013	GL  					FUEL SYSTEM	DEFECTIVE       	W				B				EMER. DESCENT           				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA				3338 							(CAN) ENGINE AUTO-REIGNITION ACTIVATED IN FLIGHT. REPORTS OF SOFT (BANG) PRECEEDING DECEL. INVESTIGATION REVEALED AIR IN	 FUEL SYSTEM, SUBSEQUENT TROUBLESHOOTING FOUND ENGINE DRIVEN FUEL PUMP DEFECTIVE. (TC NR 20070912008)					1	G	7	2 	3U	3	U		H11EU   	E4CE				 
2007110200066	20071102	00066		2007	11	2	CA070912009      	4	20070910	G	3460	7013270936	RMU             			DORNER	DO32  	DO328100    	2996000	NM  											FAILED          	W				O				OTHER                   				J	B		WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			7960 								(CAN) ENROUTE RMU NR1 FAIL CAS MESSAGE, QRH PROCEDURES COMPLETED, THE ODOR OF ELECTRICAL FIRE/SMOKE WAS DETECTED IN THE 	COCKPIT.  DECLARED AN EMERGENCY AND INITIATED ODOR OF SMOKE IN COCKPIT DRILL.  PROCEEDED WITHOUT FURTHER INCIDENT.PAX DE	PLANED AT GATE ,NORMALLY,FIRE DEPARTMENT INVESTIGATED FOR FURTHER DAMAGE.  MAINTENANCE DETERMINED THAT THE RMU HAD SHORT	ED INTERNALLY AND CAUSED A SMOKE ODOR IN THE COCKPIT. THE NR 1 RMU WAS DISCONNECTED AND THE CIRCUIT BREAKER PULLED AND C	OLLERED.THE A/C WAS FERRY FLOWN, THE FOLLOWING DAY, A REPLACEMENT RMU IS IN TRANSIT. (TC NR 20070912009)		2	H	7	2 	4T			RT	A45NM   					 
2007110200067	20071102	00067	CE  	2007	11	2	CA070912010      	1	20070910	G	8011	MMU4001	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  						STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				179  							(CAN) STARTER FOUND STICKING. (TC NR 20070912010)						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007110200068	20071102	00068	EA  	2007	11	2	CA070913001      	1	20070910	G	2421	820465	ADG             			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					LEFT	UNWANTED DEPLOY 	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CA				1    							(CAN) DURING TAKEOFF, AS SOON AS A/C LEFT GROUND ADG DEPLOYED. CREW DECIDED TO CONTINUE FLIGHT USING ADG DEPLOY FLIGHT P	ROCEDURES. A/C LANDED WITHOUT INCIDENT.  ADG AUTODEPLOY UNIT WAS FOUND TO HAVE BEEN REPLACED A FEW HOURS BACK DUE TO FAI	LURE OF UNIT`S SELF TEST. THE INSTALLED SERVICEABLE REPAIRED UNIT WAS FOUND TO BE AT FAULT. UNIT WILL BE REPLACED AND A/	C RETURNED TO SERVICE. (TC NR 20070913001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600151	20080306	00151	CE  	2008	3	6	CA070913002      	1	20070913	G	2421	ES4118	BRUSHES         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ALTERNATOR	CONTAMINATED    	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				220  		G104183					(CAN) EXCESSIVE GREASE WAS APPLIED TO THE REAR ROTOR BEARING DURING OVERHAUL. SOME OF IT ESCAPED AND WAS FLUNG ONTO THE 	BRUSHES AND SLIP RINGS, FOULING THEM AND CAUSING A BUILDUP OF GREASE AND CARBON ON THE SLIP RINGS AND BRUSH FACES. THE E	LECTRICAL RESISTANCE INCREASED AND THE FIELD CURRENT WAS REDUCED TO THE POINT THAT THE ALTERNATOR WAS UNABLE TO KEEP UP 	WITH THE AIRCRAFT`S REQUIREMENTS. (TC NR 20070913002)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007110200069	20071102	00069	WP  	2007	11	2	CA070913004      	1	20070820	G	3246	NAS14651	TIE BOLT        	LORAL       	9540512     	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	HAMSTD	54H	54H60       	NE  	MAIN WHEEL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				358  		285955					(CAN) DURING DAILY INSPECTION OF AIRCRAFT, THE NR3 MAIN WHEEL ASSEMBLY WAS FOUND TO HAVE 4 MISSING TIE BOLTS. THE WHEEL 	ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT, AN AXLE INSPECTION WAS CARRIED OUT AND THE AIRCRAFT WAS RETURNED TO SERVI	CE. AFTER INVESTIGATION, THE OVERHAUL PROCEDURE HAS BEEN REVISED TO DISCARD TIE BOLTS AND NUTS DURING WHEEL OVERHAUL/REP	AIR. THE WHEEL OVERHAUL TASK CARD HAS ALSO BEEN REVISED TO INCLUDE THIS INFORMATION. (TC NR 20070913004)			2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2008030600152	20080306	00152	SO  	2008	3	6	CA070913005      	1	20070705	G	5741	6244802	FITTING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4998 								(CAN) ON A SCHEDULED 100 HOUR INSPECTION, BOTH THE LT AND RT LOWER COCKPIT FITTINGS THAT THE REAR WING SPARS ATTACH TO W	ERE FOUND TO BE HEAVILY CORRODED. THE PARTS WERE REMOVED, THE AREA DECORRODED AS REQUIRED AND NEW FITTINGS INSTALLED. LT	 P/N 62448-02 AND RT P/N 62448-03. (TC NR 20070913005)				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
2007110200070	20071102	00070	NM  	2007	11	2	CA070913007      	1	20070911	G	3234	574205A	SELECTOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) IN DESCENT, THE PILOT SELECTED GEAR DOWN. THE GEAR FAILED TO EXTEND AND THE PILOT CYCLED THE GEAR 4 TIMES WITH NO 	RESULT, ON THE 5 CYCLE, THE GEAR EXTENDED. MAINTENANCE PLACED THE AIRCRAFT ON JACKS AND NOTED THAT WHEN GEAR EXTENSION W	AS SELECTED, IT TOOK ABOUT 10 SECONDS BEFORE THE GEAR INITIATED THE COMMAND. THE LANDING GEAR SELECTOR WAS FOUND TO BE C	AUSING THE DELAY, THE SELECTOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070913007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008031900154	20080319	00154	EA  	2008	3	19	CA070913008      	2	20070911	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  		OVERHEATED      	W				E				ENGINE SHUTDOWN         				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	LD	LANDING        	1			CA			13899	459  				PCE81089			(CAN) SHORTLY AFTER LANDING, THE PILOT NOTICED AN UNUSUALLY HIGH ITT INDICATION FOLLOWED BY SPARKS EXITING THE RT ENGINE	. THE PILOT SHUTDOWN THE ENGINE AND CONTINUED TAXING WITHOUT FURTHER INCIDENT. FURTHER REPORT TO FOLLOW PENDING TEARDOWN	 REPORT. (TC NR 20070913008)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2007110200071	20071102	00071	EU  	2007	11	2	CA070913009      	1	20070913	G	7120		MOUNT           			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF34*       	 	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT ENGINE MOUNT. THE REVERSER THERMAL BLANKETS CONTACT THE MOUNT AND WITH ENGINE VIBRATION, CAUSE THE DAMAGE. THE	 MOUNT INSTALLED ON THE SPARE ENGINE SHOWED THE SAME TYPE OF DAMAGE.  THE WEAR DAMAGE WAS APPROXIMATELY .080 IN TO .210 	IN IN WIDTH X.600 IN LONG WITH A DEPTH OF .008 IN. THE DAMAGE WAS BEYOND LIMIT IAW THE CF34-10E ENGINE MANUAL. AT THE PR	ESENT TIME NO DAMAGE LIMIT IS ALLOWED. GE IS PRESENTLY REVISING THE SITUATION.  THE ROOT CAUSE HAS BEEN DETERMINED THAT 	THE THERMAL BLANKETS HAD NO CLEARANCE WHEN THE ENGINE COWL IS CLOSED.  MFG DIDNT DETERMINE A SOLUTION YET. (TC NR 20070	913009)	2	L	7	2 	4F	4	F	RT	A57NM   	E15NE				 
2007110200072	20071102	00072		2007	11	2	CA070914001      	4	20070912	G	3416	066030620010	ALTIMETER       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		MALFUNCTIONED   	W				K				NONE                    				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH THE PILOTS ENCODING ALTIMETER WAS STICKING AND THE FLAG DISPLAYED. THE ALTIMETER WAS REPLACED AND 	THE AIRCRAFT RETURNED TO SERVICE (TC NR 20070914001)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007110500016	20071105	00016	NE  	2007	11	5	CA070914002      	2	20070713	G	7250		TURBINE BLADES  			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA								104012			(CAN) THE ENGINE SHUTDOWN IN FLIGHT ON APPROACH. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL	 INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070914002)					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2007110500017	20071105	00017	NE  	2007	11	5	CA070914003      	2	20070718	G	7320	3035466	TUBE            			BAG   	ATP   	ATP         	       	EU  	PWA   	PW120 	PW126A      	 	NE  					FUEL P3 AIR	FRACTURED       	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE SHUTDOWN UNCOMMANDED IN CRUISE. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL P3 AIR SUPPLY T	UBE. (TC NR 20070914003)					2	L	7	2 	4T	4	T	RT	A27NM   	E2ONE				 
2007110500018	20071105	00018	NE  	2007	11	5	CA070914004      	2	20070702	G	7200		ENGINE          			AYRES 	S2    	S2RT15RESTD 	       	SO  	PWA   	PT6   	PT6A15AG    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION DURING SPRAYING OPERATIONS RESULTING IN A FORCED LANDING AND	 SUBSTANTIAL AIRFRAME DAMAGE. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC 	NR 20070914004)				1	L	7	1 	3T	4	T		A4SW    	E4EA				 
2007110500019	20071105	00019	NE  	2007	11	5	CA070914005      	2	20070710	G	7323	3032490B	SEAL            			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					O/SPEED GOVERNOR	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE LOW ENGINE OIL PRESSURE WARNING ACTIVATED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTI	ON REVEALED A LEAKING OVERSPEED GOVERNOR HIGH PRESSURE PUMP SEAL. (TC NR 20070914005)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007110500020	20071105	00020	NE  	2007	11	5	CA070914006      	2	20070709	G	7321	324485516	HMU             			AEROSP	ATR72 	ATR72201    	8680943	EU  	PWA   	PW120 	PW124B      	 	NE  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CLIMB FOLLOWING TAKE-OFF.  SUBSEQUENT INVESTIGATION IDENT	IFIED A FAULTY HYDROMECHANICAL FUEL CONTROL UNIT. (TC NR 20070914006)					2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2007110500021	20071105	00021	EA  	2007	11	5	CA070914007      	2	20070622	G	7250		TURBINE BLADES  			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FRACTURED       	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								TH0729			(CAN) THE ENGINE COULD NOT BE RELIGHT IN FLIGHT FOLLOWING A SIMULATED ENGINE-OUT TRAINING EXERCISE. SUBSEQUENT INSPECTIO	N REVEALED FRACTURED TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2007110500022	20071105	00022	NE  	2007	11	5	CA070914008      	2	20070708	G	7321	32448716	FCU             			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA			10416	5095 							(CAN) THE ENGINE LOST POWER ON APPROACH AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY MECHANICAL F	UEL CONTROL UNIT. (TC NR 20070914008)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007110500023	20071105	00023	EA  	2007	11	5	CA070914009      	2	20070713	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								FA0067			(CAN) ENGINE OIL PRESSURE REDUCED IN FLIGHT FOLLOWED BY A CHIP DETECTOR WARNING INDICATION. THE ENGINE WAS SHUTDOWN IN F	LIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE TURBOMACHINE OIL SYSTEM. MFG WILL INVESTIGATE THE INCIDENT AND	 ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR  20070914009)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007110500024	20071105	00024	NE  	2007	11	5	CA070914010      	2	20070717	G	7321	10078001	FCU             			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					ENGINE	FAULTY          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA			60   								(CAN) ON TAKEOFF ROLL, THE ENGINE CONTROL FAULT LIGHT ILLUMINATED AND ENGINE POWER WOULD NOT INCREASE TO THROTTLE INPUT.	 THE TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20070914010)					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007110500025	20071105	00025	NE  	2007	11	5	CA070914011      	2	20070703	G	7261		ENGINE          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  						LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								118318			(CAN) ON CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTI	ON REVEALED INTERNAL ENGINE OIL LEAKAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR	 20070914011)				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007110500026	20071105	00026	NE  	2007	11	5	CA070914012      	2	20070723	G	7200		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								125236			(CAN) THE CREW OBSERVED SMOKE IN THE CABIN AND ENGINE OIL PRESSURE FLUCTUATIONS IN FLIGHT. THE ENGINE WAS SHUTDOWN IN FL	IGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE TURBOMACHINERY OIL SYSTEM. MFG WILL INVESTIGATE THE EVENT AND A	DVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070914012)				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007110500027	20071105	00027	NE  	2007	11	5	CA070914013      	2	20070723	G	7320		LINE            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWC   	PW206C	PW206C      		NE  					FUEL SYS P3 AIR	CONTAMINATED    	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON TAKEOFF ENGINE POWER REDUCED UNCOMMANDED. SUBSEQUENT INSPECTION REVEALED CONTAMINATION / BLOCKAGE OF THE FUEL C	ONTOL P3 AIR PRESSURE FITTING AT THE NR 8 BEARING CARBON SEAL LOCATION. (TC NR 20070914013)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2007110500028	20071105	00028	NE  	2007	11	5	CA070914014      	2	20070721	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						UNKNOWN         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								19278			(CAN) FOLLOWING TAKEOFF A LOUD NOISE WAS HEARD ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN ENGINE POWER. A FORCED LANDING	 WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS	HED. (TC NR 20070914014)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007110500029	20071105	00029	NE  	2007	11	5	CA070914015      	2	20070714	G	7314		PUMP            			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL SYSTEM	FAULTY          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL, THE ENGINE WAS FOUND NOT TO PRODUCE COMMANDED POWER AND THE TAKEOFF WAS ABORTED. THE ENGINE FUEL 	PUMP AND MFCU WERE SUBSEQUENTLY REPLACED. (TC NR 20070914015)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007110500030	20071105	00030	EA  	2007	11	5	CA070914016      	1	20070727	G	7712	311555701	TORQUE SENSOR   			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA			2231 								(CAN) IN LEVEL FLIGHT, THE ENGINE LOST POWER ACCOMPANIED BY A LOUD NOISE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT 	INSPECTION REVEALED A FAULTY TORQUE SENSOR. (TC NR 20070914016)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
2007110500031	20071105	00031	NM  	2007	11	5	CA070914017      	1	20070730	G	6120		CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					PROPELLER	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) ON LEVELING OFF FROM DESCENT, THE PROPELLER WENT TO AN OVERSPEED CONDITION AND THE ENGINE WAS FOUND NOT TO RESPOND	 TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE MFG PROPELLER ELECTRIC CONTROL, SPEED SENSOR AND ASSOCIATED E	NGINE HARNESS WERE SUBSEQUENTLY REPLACED. MFG WILL MONITOR INVESTIGATION OF THESE COMPONENTS AND ADVISE OF ROOT CAUSE ON	CE ESTABLISHED. (TC NR 20070914017)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007110500032	20071105	00032	EU  	2007	11	5	CA070914018      	1	20070907	G	2997		WIRE HARNESS    			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	HYD PUMP	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DEFECT - BLUE HYDRALULIC PUMP U/S. RECTIFICATION, AC WILD BLUE PUMP WIRING SHORTED AND BURNED IN HYDRAULIC BAY DUR	ING TROUBLESHOOTING OF UNSERVICEABLE BLUE HYDRAULIC PUMP. (TCNR 20070914018)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008012900032	20080129	00032	NE  	2008	1	29	CA070914019      	1	20070911	G	6210	6117020201	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					MAIN ROTOR	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			5456 								(CAN) BIM WARNING LIGHT ILLUMINATED IN FLIGHT. SPAR PRESSURE WAS FOUND TO BE .25 LBS BELOW MINIMUM CHECKING PRESSURE. SP	AR PRESSURE WAS SERVICED APPROXIMATELY 80 DAYS PREVIOUS. (TC NR 20070914019)					2	G	7	2 	4U	4	U		1H15    	1E3				 
2008013100047	20080131	00047	SW  	2008	1	31	CA070917001      	1	20070914	G	6730	30000556001	PIN             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					CYCLIC SERVO	BRINELLED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4523 	2276 		344					(CAN) DURING ROUTINE MAINTENANCE, FLIGHT CONTROL CHECKS REVEALED A RATCHET SENSATION DURING MOVEMENT OF SHOULDER PIN ON 	LT LATERAL SERVO. PIN REMOVED AND INSPECTED REVEALING INDICATIONS OF BRINELLING AND THE POSSIBILITY OF PLATING WHICH HAS	 BEEN ADDRESSED BY AD CF95-11 R2 ( ASB 206-95-84).SERVO AND PIN WILL BE FORWARDED FOR FURTHER INSPECTION. (TC NR 2007091	7001)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007110500033	20071105	00033	CE  	2007	11	5	CA070917002      	1	20070915	G	3245	302039402	TUBE            	GOODYEAR    	650C063     	CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	TIRE	DESTROYED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			120  			62710247					(CAN) UPON LANDING EITHER THE TIRE WAS ALREADY FLAT OR IT BLEW OUT. THE PILOT CONTROLLED THE AIRCRAFT TO A STOP WITH OUT	 ANY HARM TO THE AIRCRAFT. THE LT MAIN TIRE, TUBE WERE DESTROYED DURING THE ROLLOUT. NO DEFINITE CAUSE HAS BEEN DETERMIN	ED TO THIS POINT, BUT THIS IS ONE OF MANY ISSUES WE HAVE HAD SINCE CHANGING AND NOW WILL BE REPLACING ALL PRODUCTS ON OU	R FLEET OF AIRCRAFT. (TC NR 20070917002)			1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
2007110500038	20071105	00038	CE  	2007	11	5	CA070917003      	1	20070827	G	3245	G156006	TUBE            	GOODYEAR    		CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	TIRE	SPLIT           	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			123  			42520008					(CAN) DURING GROUND HANDLING AFTER LANDING THE NOSE TIRE WAS NOTED TO BE LOW IN PRESSURE AND HISSING COULD BE HEARD FROM	 THE TIRE. T IRE / INNERUBE WAS DISASSEMBLED AND INNER TUBE WAS FOUND TO HAVE SMALL SPILT / CUTS AND PIN PUNCTURES IN SI	DE WALLS. TORE WAS INSPECTED FOR ANOMALIES AND NONE WERE FOUND. NEW ASSEMBLIES WERE INSTALLED. (TC NR 20070917003)				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
2007110500040	20071105	00040	CE  	2007	11	5	CA070917004      	1	20070913	G	3244	229K482	TIRE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					MLG	OUT OF BALANCE  	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			231  								(CAN) PILOTS REPORTED VIBRATION DURING LANDING IN MAIN WHEELS. INSPECTION AND DISASSEMBLY SHOWS LT MAIN WHEEL TIRE BALAN	CE PATCH IS FALLING OFF CAUSING THE MAIN TIRE TO BE IN AN UNBALANCE CONDITION. ASSEMBLY REPLACED AND NO FURTHER VIBRATIO	NS NOTED. (TC NR 20070917004)				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007110500041	20071105	00041	EA  	2007	11	5	CA070917005      	1	20070913	G	2700		UNKNOWN         			CNDAIR	CL601 	CL6013A     	8070802	EA  											MULTIPLE FAIL   	W				O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT EXPERIENCED FLAP FAILURE ON PREPARATION FOR LANDING, THEN FLEW APPROXIMATELY A FURTHER 10 MINUTES ATTEMPT	ING,UNSUCCESSFULLY, TO DEPLOY THE FLAPS. ON TOUCHDOWN THE THRUST REVERSERS (TR) DID NOT DEPLOY WHEREUPON THE CREW RECYCL	ED THE TR ARM SWITCH AFTER WHICH THE TRS DEPLOYED. AFTER LANDING THE AIRCRAFT WAS TAXIED TO THE RAMP AND PARKED. THE BRA	KE FIRE WAS OBSERVED POST CREW AND PASSENGER DEPLANE TO ATTEND CUSTOMS.  NR 2 BRAKE CAUGHT FIRE, NRS 3 AND 4 BRAKE FUSES	 BLEW WHILE NR 1 TIRE HELD PRESSURE. (TC NR 20070917005)		2	L	7	2 	4F			RT	A21EA   					 
2007110500042	20071105	00042	SO  	2007	11	5	CA070917006      	1	20070912	G	7603	12694002	THROTTLE CABLE  			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT ON FLOATS. PILOT DEPARTED RIVER AND WHEN THE PILOT PULLED THE ENGINE BACK THE RPM WOULD NOT RETARD. PILOT	 TURNED ONE MAG OFF AND HELD THE AIRCRAFT NOSE UP TO PREVENT ENGINE OVER-SPEED AND RETURNED TO STARTING POINT. PILOT PUL	LED MIXTURE WHEN HE KNEW HE COULD MAKE THE LANDING SUCCESSFULLY. THROTTLE CABLE REPLACED WITH NEW PART. (TC NR 200709170	06)			1	H	7	1 	3O	3	O		A780    	E274	5	N	P88614	 
2007110500043	20071105	00043	EA  	2007	11	5	CA070917007      	1	20070913	G	2750	1104SD100201	FLEX DRIVE      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CREW REPORTED THAT THE FLAPS OPERATED NORMALLY ON APPROACH, WHEN SELECTED TO FLAPS 45. AFTER LANDING AND DURING TA	XI, WHEN THE CREW SELECTED FLAPS 0, THEY RECEIVED A FLAP FAIL AND THE FLAPS REMAINED AT 45. CONTRACT MAINTENANCE RETRIEV	ED THE CODES FROM THE FECU AND THE IDENTIFIED A POSSIBLE MISRIG OF THE BPSU. THE FLAPS WERE THEN CYCLED THREE TIMES WITH	 NO FAULTS FOUND, A/C WAS RETURNED TO SERVICE. BPSU RIGGING WAS CHECKED SERVICEABLE. THE A/C WAS FLOWN FOR A BEAM REPAIR	 AND IT WAS DECIDED THAT TASK RJ2-275002 (FLAP LUBE AND INSPECTION WOULD BE COMPLETED.) IT WAS DISCOVERED THAT LT AND RT	 NR 2 FLAP FLEX DRIVES WERE UNSERVICEABLE, ONE WAS WORN, THE OTHER HAD A SLIGHT KINK AND REQUIRED REPLACEMENT. BOTH WERE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500044	20071105	00044	NE  	2007	11	5	CA070917008      	2	20070829	G	7414	BL60064620	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					RIGHT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				171  							(CAN) DURING START UP THE AIRCRAFT THE RT MAGNETO FAILED. MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 	20070917008)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100048	20080131	00048	EU  	2008	1	31	CA070917009      	1	20070901	G	6730	SC5083	SERVO CONTROL   			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				2003 							(CAN) M/R SERVO REMOVED FROM RT POSITION DUE TO LEAKAGE. (TC NR 20070917009)						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2007110500045	20071105	00045	EU  	2007	11	5	CA070917011      	1	20070417	G	2820	ST3367009	PACKING         			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL MANIFOLD	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ST3367-009 PACKINGS SUPPLIED, FOUND LEAKING AT FUEL MANIFOLD.  SUSPECTED UNAPPROVED PARTS - PACKINGS MANUFACTUED /	 SUPPLIED WITHOUT PMA AUTHORIZATION FROM MFG. ST3367 IS A MFG PROPRIETARY SPECIFICATION. (TC NR 20070917011)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2008022500131	20080225	00131	EA  	2008	2	25	CA070917013      	2	20070914	G	7322		SEAL            			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360A1P     	42259	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	INDUCTION SYS	DISLODGED       	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA			310  								(CAN) ON FINAL APPROACH THE ENGINE SUDDENLY EXPERIENCED A SEVERE LOSS OF POWER WHEN CARB HEAT WAS SELECTED. DURING INSPE	CTION, AFTER LANDING, A (3) INCH PIECE OF FOAM SEAL WAS FOUND LODGED IN THE CARB VENTURI. ON FURTHER INSPECTION, A CORRE	SPONDING GAP WAS FOUND IN THE SEAL BETWEEN THE COWL INTAKE SCOOP AND THE INDUCTION AIR FILTER.  THE REMAINING PIECES OF 	FOAM SEAL WERE REMOVED AND A SATISFACTORY GROUND RUN WAS CARRIED OUT. THE AC WAS RETURNED TO SERVICE. INSP OF A SECOND A	C OF THE SAME MODEL DISCOVERED SIMILAR PIECES MISSING FROM THE SEAL BETWEEN THE COWL AND THE INDUCTION AIR FILTER. (TC N	R 20070917013)	1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2008022500133	20080225	00133	EA  	2008	2	25	CA070918001      	2	20070914	G	7397	476284	CIRCUIT BOARD   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL COLLECTOR	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A SHORT ON THE NR 2 ENGINE FUEL COLLECTOR DRAIN PUMP CIRCUIT (TC NR 20070918001)						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2007110500046	20071105	00046	WP  	2007	11	5	CA070918002      	1	20070916	G	5730	8398011	PANEL           			LKHEED	188   	188A        	5262602	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A (WATER - FIRE SUPPRESSION) BOMBING MISSION, FUEL WAS FOUND LEAKING FROM A CRACK THAT WAS COMING FROM AN OL	D REPAIR. THE A/C WAS DOWN LOADED WITH WEIGHT AND THE A/C WAS FERRIED TO THE COMPANY MAINTENANCE STATION. (TC NR 2007091	8002)				2	L	7	4 	4T	4	T	RT	4A22    	E282	6	C	P898	 
2007110500047	20071105	00047	NE  	2007	11	5	CA070918003      	3	20070917	G	6111	8173881	SEAL            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROP BLADE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			104  			20060115					(CAN) AFTER FLIGHT, OIL LEAK NOTED FROM NR 2 PROP LEAK TRACED TO NR 2 BLADE SEAL. NR 2 SEAL REPLACED. ABRASION MARKS NOT	ED ON SEALING SURFACE. (TC NR 20070918003)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008030600153	20080306	00153	CE  	2008	3	6	CA070918004      	1	20070914	G	5340	1018200363	BRACKET         			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	NLG WW	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			11317								(CAN) THE AC WAS ON A RETURN LEG . UPON SELECTING THE LANDING GEAR TO THE DOWN POSITION, THERE WAS NO INDICATION OF A DO	WN AND LOCKED NOSE AS WELL AS THE (IN TRANSIT LIGHT) REMAINED ON IN THE GEAR HANDLE. THE CREW CARRIED OUT AN EMERGENCY L	OWERING AND STILL NO DOWN AND LOCKED INDICATION FOR THE NOSE. AT THIS TIME A (FLY BY) THE TOWER CONFIRMED THE NOSE GEAR 	HAD EXTENDED. AN EMERGENCY LANDING WAS CARRIED OUT WITHOUT INCIDENT. MAINTENANCE DISCOVERED THAT THE BRACKET P/N 101-820	036-3, WHICH HOLDS THE NOSE LANDING GEAR DOWN, MICROSWITCH HAD BROKEN AND CAUSED THE PROBLEM. THE BRACKET WAS REPLACED W	ITH A SERVICEABLE UNIT AND THE MICROSWITCH ADJUSTED. SEVERAL GEAR SWINGS WERE CARRIED OUT THE SYSTEM CHECKED SERVICEABLE	2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2008031900158	20080319	00158	EA  	2008	3	19	CA070918005      	2	20070907	G	8530	ST203	PISTON RING     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	CYLINDER ASSY	DAMAGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			296  			104573					(CAN) THE PROBLEM STARTED WITH HIGH OIL TEMP ON LT ENG, NEAR THE RED LINE IN TURBOBOOST AND WITH SMALL SPLIT OF MANIFOLD	 PRESS BETWEEN BOTH ENGINES. WE TROUBLESHOOT ALL SYS REGARDING HIGH OIL TEMP AND MANIFOLD PRESS UNTIL REPLACEMENT OF TUR	BO BY ITSELF BUT WITH NO CHANGE. ONLY WHAT WE FOUND WAS (2) CYLINDER WITH 65,67 OVER 80 PSID. MAKE THE DECISION TO REMOV	ED THOSE (2) CYLINDER ASSY. FOUND THE COMPRESSOR RING UNPLATING AT DIFFERENT LOCATIONS. THE ENG TSO IS 864.5 AND ALL THE	 CYLINDERS WAS OVERHAUL AT 568.5 FOR THE SAME SITUATION, RING UNPLATING. SO WE TOOK THE DECISION TO REMOVED THE OTHER 4 	CYLINDER LT ON THE ENGINE AND WE FOUND RING UNPLATING ALSO. WE REINSTALLED 6 O/H CYL ASSY ON LT ENGINE AND EVERY THING R	1	L	7	2 	3O	3	O		1A10    	E14EA	5	C	P9EA	 
2008030600154	20080306	00154	SO  	2008	3	6	CA070918006      	1	20070822	G	2731	41234028	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR TRIM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2440 				317952033				(CAN) DURING AN INSPECTION OF THE ELEVATOR TRIM SYSTEM, A CRACK WAS FOUND IN THE SWAGED END OF THE TRIM CABLE. THE SWAGE	D BARREL WAS CRACKED ALL THE WAY THROUGH TO THE CABLE ON ONE SIDE AND SHOWED INDICATIONS OF A CRACK ON THE OPPOSITE SIDE	. THE CRACK IS APPROXIMATELY 3 INCHES LONG AND PRETTY WELL RUNS THE LENGTH OF THE SWAGE. (TC NR 20070918006)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008030600155	20080306	00155	SW  	2008	3	6	CA070918007      	1	20070917	G	5412	26009121	BULKHEAD        	AEROCD      		GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R306	R306382F7   	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6654 	6654 							(CAN) DURING WINTER MAINTENANCE, REAR NACELLE BULKHEAD FOUND CRACKED IN THE RADIUS.  BULKHEAD TO BE REPLACED. (TC NR 200	70918007)					1	H	7	2 	4T	4	T		2A4     	E4WE	6	C	P8EU	 
2007110500048	20071105	00048	SO  	2007	11	5	CA070919001      	1	20070917	G	2820	641098	TUBE            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL DISCHARGE	BROKEN          	W				A				UNSCHED LANDING         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA				650  				305114			(CAN) FUEL DISCHARGE TUBE BROKE, ENGINE LOST POWER. SUSPECT MID-TUBE CLIP P/N: 626477-2 MAY HAVE FAILED FIRST. (TC NR 20	070919001)					1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920	 
2007110500049	20071105	00049	EA  	2007	11	5	CA070919003      	1	20070916	G	7714	311090801	PROBE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 2 TORQUE	FAULTED         	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) ON FIRST START OF THE DAY, THE NR 1 ENGINE OVERTORQUED TO AN UNDETERMINED VALUE. TORQUE WAS SEEN TO BE DECREASING 	THROUGH 70 PERCENT. IT WENT BACK TO 30 PERCENT AND THEN STARTED TO ACCELERATE AGAIN. ENGINE WAS SHUTDOWN AT 50 PERCENT T	ORQUE. FDR DOWNLOADED AND READ MAX TQ EXPERIENCED ON FDR READING IS 69 PERCENTS. TROUBLESHOOTING FOUND THE NR 2 TORQUE P	ROBE TO BE AT FAULT. TORQUE PROBE REPLACED ON NR1 ENGINE. GROUND RUNS COMPLETED, CHECKED SERVICEABLE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110500050	20071105	00050	GL  	2007	11	5	CA070919004      	2	20070919	G	7250	23062462	RING            			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					VANES	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			6979 					CAE330181			(CAN) DURING ENGINE DISASSEMBLY IT WAS FOUND THAT 1 OFF LOCATING PLUG WAS INTERCHANGE WITH THE BOROSCOPE PLUG. THE LPT2 	VANE RING IS HELD IN PLACE BY 3 LOCATING PLUGS, 2 PLUGS ONLY WERE FOUND CORRECTLY INSTALLED. LPT2 VANE RING WAS FOUND HE	AVILY RUBBED ON THE TRAILING EDGE AT THE OUTER SHROUD LOCATION OVER AN ARC OF 75 DEG. APPROX.. THE INNER SHROUD LOCATION	 WAS ALSO FOUND HEAVILY RUBBED AT THE INNER PLATFORM LOCATION OVER THE SAME ARC DISTANCE. THE LPT2 BLADES (L/E SIDE), WA	S FOUND HEAVILY RUBBED AT THE INNER AND OUTER SHROUD LOCATIONS, MATCHING THE LPT2 VANE RING RUB. THE LOCATING PLUG THAT 	WAS FOUND INSTALLED AT THE WRONG LOCATION WAS WORN. PREVIOUS SIMILAR EVENT HAD CAUSED A MAJOR ENGINE FAILURE AND ABORTED	2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2008030600156	20080306	00156		2008	3	6	CA070919006      	4	20070917	G	2562	200610	ANTENNA         	POINTER     		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ELT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						409016					(CAN) DURING A POST FLIGHT CHECK THE ELT ANTENNA CONNECTOR WAS FOUND BROKEN OFF THE ELT CASE. UPON FURTHER INVESTIGATION	 IT WAS ALSO NOTED THAT THE PORTABLE ANTENNA WAS MISSING. A THOROUGH SEARCH WAS CARRIED OUT FOR THE MISSING PARTS WITHIN	 THE AREA. NO PARTS WERE FOUND, THE ELT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070919006)				1	G	7	1 	3O	3	O		H11NM   	E295				 
2007110500051	20071105	00051	EU  	2007	11	5	CA070919007      	1	20070917	G	3213	1847L	ROD             			BAG   	JETSTM	JETSTM3101  	1500215	EU  										LT MLG	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA				1951 							(CAN) ON A WALKAROUND OF THE AIRCRAFT, THE LT MLG RADIUS ROD WAS FOUND TO BE LEAKING A SIGNIFICANT AMOUNT OF MIL-5606 HY	DRAULIC FLUID FROM THE PISTON SEAL AREA. THE OVERHAUL INTERVAL FOR THIS PART IS 10000 CYCLES OR 6 YEARS, AND THIS ROD WA	S INSTALLED FOR ONLY 1421 CYCLES AND APPROXIMATELY 21 MONTHS. THIS RADIUS ROD WAS PURCHASED ON PO NR 1609. THIS ROD WAS 	REMOVED FROM SERVICE 09/18/2007 AND REPLACED WITH AN OVERHAULED UNIT. (TC  20070919007)			2	L	7	2 	4T			RT	A21EU   					 
2007110500052	20071105	00052	GL  	2007	11	5	CA070919008      	2	20070914	G	7323		SHAFT           	HONEYWELL   		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GOVERNOR	SEIZED          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA				183  		19671					(CAN) WHILE THE PILOT WAS DOING HIS PREFLIGHT SYSTEM CHECKS, HE NOTICED THAT HIS GOVERNOR RANGE HAD SHIFTED DOWN FROM TH	E NORMAL RANGE OF 100 PERCENT DOWN TO 97 NR ROTOR RPM. THE GOVERNOR WAS INSPECTED BY THE ENGINEER AND HE FOUND THAT THE 	GOVERNOR LEVER SHAFT WAS SEIZED. HE CONTINUED INSPECTING THE GOVERNOR CONTROL LINKAGE AND NOTICED THAT THE DROOP COMPENS	ATION TORQUE SHAFT WAS TWISTED DO TO THE GOVERNOR SHAFT BEING SEIZED. THE GOVERNOR AND THE DROP COMPENSATION LEVER ASSEM	BLY WERE REPLACED, GOVERNOR RIGGED AND BEEP RANGE SET. THE HELICOPTER WAS TEST FLOWN AND FOUND SATISFACTORY. (TC NR 2007	0919008)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007110500053	20071105	00053	EU  	2007	11	5	CA070919009      	1	20070918	G	3211	B00A703066A	LANDING GEAR    			BAG   	JETSTM	JETSTM3212  	1500217	EU  										RIGHT	MISOVERHAULED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			18944	138  							(CAN)  (AD)2006-0087 WAS REVIEWED AS PART OF THE NEW AIRCRAFTS BRIDGING INSPECTION. DURING REVIEW OF THIS AD IT WAS FOUN	D THAT THE RT MAIN LANDING GEAR HAD BEEN REASSEMBLED AT OVERHAUL WITH THE WRONG PART NUMBER UPPER AND LOWER TOGGLES INST	ALLED. THE INSTALLED UPPER TOGGLE P/N 184514 IS OF THE WRONG EFFECTIVITY FOR THIS GEAR LEG AND SHOULD BE P/N 100A703090.	 THE INSTALLED LOWER TOGGLE P/N 184513 IS ALSO OF THE WRONG EFFECTIVITY FOR THIS GEAR AND SHOULD BE P/N 100A703093 OR 10	1A703093. THE AIRCRAFT WILL NOT ENTER SERVICE UNTIL THIS ISSUE HAS BEEN RECTIFIED. MLG LEG S/N BADL 479 WAS OVERHAULED O	N THE SECOND OF AUGUST 2006.  IT WAS THEN INSTALLED ON SEPTEMBER 1 2006. THE AIRCRAFT WAS OPERATED WITH THIS GEAR FROM D	2	L	7	2 	4T			RT	BA15CAA 					 
2007110500054	20071105	00054	NM  	2007	11	5	CA070921001      	1	20070917	G	3230	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  										NLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			2763 								(CAN) DURING LANDING GEAR `UP` SELECTION FOLLOWING TAKEOFF, THE NLG `RED` GEAR UNSAFE LIGHT REMAINED `ON`. CREW LOWERED 	THE LANDING GEAR BY ALTERNATE EXTENSION, WITH ALL LANDING GEARS INDICATING THREE GREENS GEAR SAFE, THE AIRCRAFT WAS RETU	RNED TO BASE WHERE A NORMAL APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT.  LINE MAINTENANCE INVESTIGATION IDENT	IFIED FAILURE OF THE NLG SOLENOID SEQUENCE VALVE. AFFECTED VALVE WAS REPLACED AND FOLLOWING APPROPRIATE CHECKS IAW THE A	IRCRAFT`S MM THE AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20070921001)		2	H	7	2 	4T			RT	A13NM   					 
2008030600157	20080306	00157	CE  	2008	3	6	CA070921002      	1	20070919	G	5531	10164000033	RIB             			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN VERTICAL STABILIZER AT RIB CSS 11.500. CRACK REPAIRED IAW SRM 51-70-17-001.  CRACKED RIB REPAIR (NO	N-PRESSURIZED AREA). (TC NR 20070921002)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2007110500055	20071105	00055	NE  	2007	11	5	CA070921003      	2	20070921	G	8530		CYLINDER        	PWC         		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				413  		4217366					(CAN) AIRCRAFT CAME IN FOR 100 HOUR INSPECTION WITH ENGINE OIL LEAK UPPER LT SIDE.  ON GROUND RUN ENGINE VIBRATION WAS E	VIDENT, MAG CHECKS WERE NORMAL, ONCE COWLINGS WERE REMOVED IT WAS DISCOVERED THAT THE CYLINDER HEAD OF NR 1 CYLINDER WAS	 LOOSE ON THE BARREL. FURTHER INVESTIGATION REVEALED THAT THE CYLINDER HEAD HAD COMPLETELY SEPARATED FROM THE CYLINDER B	ARREL.  ASSY WAS REMOVED AND REPLACED WITH SERVICEABLE CYLINDER ASSY. (TC NR 20070921003)			1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2008012900033	20080129	00033	GL  	2008	1	29	CA070921004      	1	20070921	G	7160		SEAL            			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360A1P     	42259	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	INDUCTION SYS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REFERENCED TO SDR NR 20070917013 AFTER FINDING COWLING SEAL LODGED IN THE CARB VENTURI. THE PILOT/OWNER OF THIS AI	RCRAFT WAS REQUESTED TO CHECK THE CONDITION OF THE COWLING SEAL, IT WAS FOUND TO BE LOOSE AND DETERIORATED AS WELL. ALL 	OF THE SEAL WAS REMOVED FROM THE COWLING.  (TC NR 20070921004)				1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2007110500056	20071105	00056	NM  	2007	11	5	CA070921005      	1	20070919	G	3251	SJ5049172	SWIVEL          	MENASCO     		BOMBDR	DHC8  	DHC8402     	1390042	NM  										MANIFOLD	LOOSE           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			2007 			MAL0178					(CAN) FLIGHT CREW NOTICED A PUDDLE OF FLUID AROUND THE NLG WHILE DOING A WALK AROUND. MAINTENANCE REPORTED THAT THE JAMB	 NUT FOUND ON THE STEERING MANIFOLD PRESSURE AND RETURN LINE WERE LOOSE. TIGHTEN JAMB NUTS. (TC NR 20070921005)					2	H	7	2 	4T			RT	A13NM   					 
2007110500057	20071105	00057	EA  	2007	11	5	CA070924001      	2	20070924	G	7314	RG9080JAM	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	WEAK            	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) RT ENGINE DRIVEN PUMP WEAK. (TC NR 20070924001)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008013100049	20080131	00049	WP  	2008	1	31	CA070924002      	1	20070911	G	6320	369D2512311	DRIVE GEAR      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					M/R TRANSMISSION	BROKEN          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			594  								(CAN) MAIN ROTOR TRANSMISSION REMOVED DUE TO CHIP LIGHT ILLUMINATION. TRANSMISSION RETURNED TO HELICOPTERS COMPONENT OVE	RHAUL SHOP FOR REPAIR. UPON DISMANTLE IT WAS DISCOVERED THAT THE I/P GEAR HAD FAILED AND EXHIBITED ONE COMPLETE TOOTH BR	OKEN OFF FROM THE GEAR. (TC NR 20070924002)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007110500058	20071105	00058	NM  	2007	11	5	CA070924004      	1	20070915	G	5610	8SC0043013	WINDSHIELD      			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			25492								(CAN) AN AIRCRAFT WAS CRUISING AT 23,000 FT WHEN THE LHS WINDSCREEN SHATTERED. THE OPERATOR BELIEVES THE HEATING ELEMENT	 FUSED, CREATING A HOT SPOT AND SHATTERING THE OUTER GLASS PAIN OF THE WINDSCREEN. LHS WINDSHIELD REPLACED AND THE AIRCR	AFT RETURNED WAS TO SERVICE. (TC NR 20070924004)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110500059	20071105	00059	EA  	2007	11	5	CA070924005      	1	20070924	G	2710		FITTING         	BOMBDR      		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CONTROL CABLE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NEW AILERON CABLE P/N JNL-C6CF1125-3 FROM JNL (W.O. 091) THE CSP FITTING ON IT MEASURES .4405. THE CSP FITTING WIL	L NOT ENGAUGE INTO THE RECEPTICAL ON THE QUADRANT. THE CABLE REMOVED MEASURES .4310. (TC NR 20070924005)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2007110500065	20071105	00065	EU  	2007	11	5	CA070924006      	1	20070923	G	2910		O-RING          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					PTU MANIFOLD	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FOLLOWING A YELLOW HYDRAULIC SYSTEM FAILURE, THE AIRCRAFT SUBSEQUENTLY EXPERIENCED A GREEN HYDRAULIC SYSTEM FAILUR	E, AND DIVERTED BACK TO DEPARTURE POINT. THE FLIGHT DECLARED AN EMERGENCY, AND LANDED 4000 KG OVERWEIGHT. AFTER LANDING,	 A NR 1 AND 3 BRAKE FIRE WAS ENCOUNTERED, WHICH WAS EXTINGUISHED BY CFR. THE AIRCRAFT WAS TOWED TO THE HANGAR. THE YELLO	W SYSTEM WAS WORKED ON THE 18TH, AND A CHECK VALVE PACKING WAS REPLACED FOLLOWING AN INFLIGHT PRESSURE LOSS. (TC NR  200	70924006)		2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2007110500066	20071105	00066	EA  	2007	11	5	CA070924007      	1	20070924	G	2710		FITTING         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CONTROL CABLE	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NEW AILERON CABLE P/N JNL-C6CF1153-3 FROM JNL (W/O 022. THE CSP FITTING MEASURES .4405. THE CSP FITTING WILL NOT E	NGAUGE INTO THE AILERON QUARDRANT. ORIGINAL CABLE CSP FITTING MEASURES .4320 (TC NR 20070924007)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008030600158	20080306	00158	GL  	2008	3	6	CA070925001      	1	20070922	G	3246	138892629	CONE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					NLG BEARING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			315  	315  							(CAN) TO COMPLY WITH SB 100-32-10 (NLG REPLACEMENT OF THE LOCKING SEGMENT WITH A LOCKING COLLAR) BOTH NOSE WHEEL ASSY. W	ERE REMOVED TO GAIN ACCESS, CORROSION WAS FOUND ON ALL BRG CONES AND ON ALL BEARING CUPS. THE AXLE WAS ALSO FOUND TO HAV	E CORROSION AND WAS REMOVED AND REPLACED. (2) SERVICEABLE NOSE WHEEL WERE ALSO INSTALLED. SINCE NO CAUSE WAS FOUND TO BE	 THE ROOT OF THE PROBLEM, THE OTHER CHALLENGER 300 SN 20107 303.3 TTSN FROM OUR FLEET WAS ALSO INSPECTED FOR CORROSION. 	THE LT NOSE WHEEL ASSY. WAS FOUND TO HAVE HEAVY BRG CONE AND CUP CORROSION. THE BRG CONE HAD TO BE DESTROYED TO REMOVE I	T FROM THE AXLE. THE AXLE WAS INSPECTED AND FOUND SERVICEABLE. NO NOSE WHEEL ASSY HAD BEEN REPLACED SINCE BOTH AC HAD BE	2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
2007110500067	20071105	00067	NE  	2007	11	5	CA070925002      	2	20070925	G	8550		ENGINE          			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  		LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ENGINE LEAKING EXCESSIVE OIL OUT OF GENERATOR DRIVE. ENGINE CASE FILLING WITH OIL. (TC NR 20070925002)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2007110500068	20071105	00068	EA  	2007	11	5	CA070925003      	1	20070923	G	3230	46193	PRIORITY VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE FOLLOWING MESSAGES WERE DISPLAYED IN THE COCKPIT: STEERING INOP, GEAR DISAGREE, W.O.W. SENSOR FA	ILURE AND W.O.W. STATUS. NOSE GEAR REMAINED IN DOWN POSITION WITH MAIN GEAR RETRACTED. AIRCRAFT TURNED-BACK AND LANDED U	NEVENTFULLY. MAINTENANCE REPLACED THE MLG PRIORITY VALVE AND THE ELECTRIC MOTOR DRIVEN PUMP HYDRAULIC SYSTEM 3B (P/N 848	847), FOLLOWED BY SUCCESSFUL GEAR SWINGS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500069	20071105	00069	CE  	2007	11	5	CA070926001      	1	20070924	G	7712	3012347	VALVE           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	TORQUE METER	WORN            	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA								PCE32270			(CAN) FOUND WORN TORQUE METER VALVE IN POWER SECTION OF ENGINE GIVING ERRATIC ENGINE TORQUE INDICATION AT COCKPIT INDICA	TOR. VALVE REPLACED. NO OTHER PROBLEMS NOTED. (TC NR 20070926001)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008030600159	20080306	00159	SW  	2008	3	6	CA070926002      	1	20070726	G	7930	206075187003	INDICATOR       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENG OIL PRESS	FLUCTUATES      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE AC WAS DEPARTING FROM BASE WHEN IT WAS NOTICED THAT THE ENGINE OIL PRESSURE INDICATOR WAS FLUCTUATING. THE PIL	OT RADIO A PAN TO ATC AND DID A PRECAUTIONARY LANDING. NO INCIDENT ON LANDING. THE ENGINEER WAS DISPATCHED TO THE LANDIN	G SITE AND IT WAS DETERMINED THAT THE INDICATOR WAS AT FAULT. REPLACED INDICATOR (TC NR 20070926002)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20080520		CE  	2008	5	20	CA070927001      	1	20070831	G	3246	4040A	WHEEL           			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINT THE RT MAIN WAS FOUND WITH PART OF THE BEAD MISSING, PILOT SAID THE WHEEL WAS OK PRIOR TO DEPARTURE A	ND LANDING NORMAL. TOWER ADVISED AND CREW SENT OUT FOR INSP, NO PIECES FOUND. (TC NR 20070927001)					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P25EA	 
2007110500076	20071105	00076	EU  	2007	11	5	CA070927002      	1	20070924	G	2434		GCU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2 GENERATOR	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA						813133					(CAN) AFTER DEPARTURE, THE CREW OBSERVED A NR 2 DC GENERATOR TRIP. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDE	D WITHOUT FURTHER DIFFICULTY. MAINTENANCE REPLACED THE NR 2 GENERATOR CONTROL UNIT AND THE AIRCRAFT WAS RETURNED TO SERV	ICE AFTER SATISFACTORY GROUND RUN. (TC NR 20070927002)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2007110500077	20071105	00077	EU  	2007	11	5	CA070927003      	1	20070925	G	3220	A1029E	BOLT            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION IAW AD 024-05-87 BAE SB 53-A-JA870510R1 PART B, IT WAS NOTED THAT THE TWO UPPER BOLTS WERE SHEAR	ED. THE AIRCRAFT WAS REMOVED FROM SERVICE AT THIS TIME. THE LOWER 2 BOLTS HAVE NOT YET BEEN REMOVED FOR INSPECTION.   DU	E TO THIS FINDING AND THE POSSIBLE SAFETY RISK, HAVE ELECTED TO CARRY OUT A DVI OF THE NLG RETRACT JACK ATTACH FITTINGS 	FOR THE REMAINING J-3112`S IN OUR FLEET. NO OTHER DEFECTS WERE FOUND. EVALUATING WHAT CHANGES TO THE INSPECTION FREQUENC	Y AND POSSIBLE BOLT LIFE LIMITS MAY BE REQUIRED.  REMAINING BOLTS AND SURROUNDING STRUCTURE WILL BE INSPECTED TODAY, A R	EPORT WILL FOLLOW. (TC NR 20070927003)	2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	3PNE	 
2008011400202	20080114	00202	WP  	2008	1	14	CA070927004      	2	20070926	G	7261	307481812	LINE            			RAYTHN	850   	HAWKER850XP 	7150016	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			307  	307  							(CAN) DURING SCHEDULE INSPECTION FOUND 2 OIL LINES CHAFING. THE SAME PROBLEM WAS ON BOTH ENGINES.THE PROBLEM COMES FROM 	THE FACTORY SINCE THE AIRCRAFT IS NEW AND LOW TIME. THE AIRCRAFT HISTORY DOES NOT SHOW ANY MAINTENANCE ACTION BEING PERF	ORMED IN THAT AREA SINCE THE AIRCRAFT WAS DELIVERED NEW AND IS STILL UNDER WARRANTY.  LINE PN 3074818-1 AND PN 3072083-2	  (BOTH ENGINES ARE TFE731-5BR SERIES) (TC NR 20070927004)			1	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007110500078	20071105	00078	SO  	2007	11	5	CA070927005      	2	20070926	G	7414	36066	GEAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			155  			07032007					(CAN) FOLLOWING A 50HR OIL CHANGE, IT WAS NOTED THE AC WAS VERY DIFFICULT TO START TO CARRY OUT THE REQUIRED LEAK CHECK.	 TROUBLESHOOTING REVEALED A DEFECTIVE MAGNETO. WHEN THE MAG WAS REMOVED IT WAS NOTED THAT THE DRIVE GEAR P/N 36066 WAS L	OOSE ON THE DRIVE GEAR SUPPORT CASTING (P/N N/A). UPON REMOVAL OF THE NUT P/N M3019 IT WAS NOTED THAT A AN960-616L WASHE	R WAS NEXT TO THE GEAR, AND BEHIND THE LARGE P/N M3172 WASHER. THIS INSTALLATION SEQUENCE WOULD NOT ALLOW FOR SUFFICIENT	 CLAMP UP OF THE P/N M3172 WASHER NEXT TO THE P/N 36066 DRIVE GEAR, AND OVER TIME WOULD LEAD TO THE LOOSENESS ENCOUNTERE	D. THE MAGNETO WAS REPLACED AND THE WASHER INSTALLATION REVERSED, WITH THE AN 960-616L WASHER PLACED NEXT TO THE NUT. TH	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007110500079	20071105	00079	SO  	2007	11	5	CA070927006      	2	20070926	G	7414	36066	GEAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			132  			07032004					(CAN) THE AIRCRAFT WAS HARD TO START WITH NO APPARENT REASON. AFTER TROUBLESHOOTING, A HARD STARTING PROBLEM ON ONE OTHE	R A/C IN THE FLEET AND FINDING A LOOSE DRIVE GEAR ON THE LT MAG IT WAS DECIDED TO CHECK THIS A/C FOR A SIMILAR PROBLEM. 	THE LT MAG WAS REMOVED AND IT WAS NOTED THAT THE MAG DRIVE GEAR WAS LOOSE AS WAS THE CASE WITH THE OTHER A/C. (REFER: SD	R 9/27/07 C-FNTJ) THE GEAR P/N 36066 AND WASHER P/N M3172 WERE REMOVED AND INSPECTED. AS WITH THE OTHER A/C IT WAS NOTED	 THAT A AN960-616L WASHER HAD BEEN PLACED ON THE BACKSIDE OF THE M3172 WASHER AND NEXT TO THE 36066 GEAR, RESULTING IN I	NSUFFICIENT CLAMP UP OF THE GEAR. THE GEAR WAS REASSEMBLED TO THE MAG WITH THE WASHER POSITIONS REVERSED AND THE NUT RET	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2007110500080	20071105	00080	GL  	2007	11	5	CA070927007      	2	20070905	G	7230		STATOR VANE     	ALLSN       		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				389  		CAC30263F					(CAN) NR 6 STATOR VANE FAILURE (1 VANE ONLY). NO EROSION TO NEIGHBORING VANES OR PLASTIC COATING. FOUND BY HELICOPTER OP	ERATOR. (TC NR 20070927007)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007110500081	20071105	00081	GL  	2007	11	5	CA070928001      	2	20070831	G	7230	23057142	STATOR VANE     	ALLSN       		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				389  		CAC30263F					(CAN) PILOT REPORTS UNUSUAL NOISE COMING FROM AIRCRAFT DURING GROUND RUN.  AIRCRAFT IS GROUNDED UNTIL ENGINEER INVESTIGA	TES THE UNUSUAL NOISE. NOISE IS DESCRIBED AS A (KNOCKING NOISE COMING FROM THE ENGINE) AND TOT HOTTER THAN USUAL. DURING	 THE GROUND RUN THE EXACT SYMPTOMS WERE DUPLICATED. THE ENGINEER DISASSEMBLED THE ENGINE TO FIND THE 6TH AXIAL ROW OF ST	ATORS IN THE COMPRESSOR HAD A MISSING BLADE. BOTH COMPRESSOR AND TURBINE WERE SENT INTO THE ENGINE SHOP FOR REPAIR. ENGI	NE REPAIR SHOP ALSO FILED SDR REPORT. (TC NR 20070928001)		1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007110500082	20071105	00082	NE  	2007	11	5	CA070928002      	2	20070927	G	7261	6087T04P05	SCAVENGE PUMP   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1 ENGINE OIL	FLUCTUATES      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			25148	25148							(CAN) SHORTLY AFTER TAKEOFF THE NR ONE ENGINE OIL HIGH TEMPERATURE/LOW PRESSURE CAUTION LIGHT CAME ON. FLIGHT RETURNED T	O DEPARTURE AIRPORT. FLIGHT LANDED APPROX 1000 POUNDS OVERWEIGHT. NO EMERGENCY DECLARED BUT EMERGENCY VEHICLES ON STANDB	Y. MAINTENANCE TROUBLESHOOTING DRAINED 1 LITER OF OIL FROM OIL TANK, INSPECTED OIL PRESSURE AND TEMPERATURE WIRE HARNESS	ES AND COMPLETED GROUND ENGINE RUNS. OIL PRESSURE SLOW TO RISE ON START. OIL TEMP ROSE 1 EVERY 2 SECONDS. TEMPERATURE RO	SE TO 156 WITH YELLOW CAUTION. FUEL FLOW ALSO FLUCTUATING. AFTER GROUND RUN FOUND OIL OVER SERVICED AGAIN. AGB FOUND WIT	H 5 LITERS OF OIL, SHOULD HAVE ONLY .75 LITERS. NR 1 LUBE/SCAVENGE OIL PUMP REPLACED AND OIL SYSTEM ADJUSTED TO CORRECT 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500083	20071105	00083	SO  	2007	11	5	CA070928003      	1	20070921	G	8120	LW16840	CONTROLLER      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA								6890550			(CAN) DURING TAKEOFF A VIBRATION AND LOW EGT WAS FELT ON THE LT ENGINE. TAKEOFF POWER WAS STILL ACHIEVED FOR THE FLIGHT.	 THE AIRCRAFT RETURNED TO LAND. BOTH THE DENSITY AND DIFFERENTIAL CONTROLLERS WERE FOUND TO HAVE OIL LEAKS. THE OIL WOUL	D CONTAMINATE THE AIR PASSAGES IN THE FCU AND CAUSE THE LOSS OF POWER AND VIBRATION. THE CONTROLLERS WERE REPLACED AND R	UNUPS COMPLETED WITH NO FURTHER PROBLEMS. (TC NR 20070928003)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008030600160	20080306	00160	GL  	2008	3	6	CA070928004      	2	20070925	G	7311	369D25623	BELT            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					OIL COOLER	WORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA			800  			HL8615					(CAN) ON LANDING, THE PILOT FELT A STRANGE VIBRATION. AFTER LANDING, THE AC WAS GROUNDED PENDING MAINTENANCE TROUBLESHOO	TING. A CLOSE INSP WAS COMPLETED AND DETERMINED TO BE A LOOSE COOLER BELT CAUSING EXCESSIVE VIBRATION AT 100  PERCENT.  	THE BELT WAS REPLACED SHIMED PROPERLY AND GROUND RUN AND FLIGHT TEST COMPLETED. (TC NR 20070928004)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2007110500091	20071105	00091	NE  	2007	11	5	CA071001001      	2	20070909	G	7250	FW35594	TURBINE BLADES  			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			3091 					13218			(CAN) DURING ENGINE THROTTLE FOR TAXI OVERTEMP SIGNAL, AIRCRAFT ABORTED TAKEOFF. VISUAL INSPECTION REPORTED METAL IN TAI	L PIPE, SUSPECT HP 1 TURBINE BLADE FAILURE. FURTHER INFORMATION WILL BE SUBMITTED AFTER ENGINE TEAR DOWN. ENGINE BEING I	NDUCTED AT RRC. (TC NR 20071001001)				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2008030600161	20080306	00161	SW  	2008	3	6	CA071001002      	1	20070712	G	2820	206063607101	TUBE            			BELL  	206   	206L4       	1182110	SW  										FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HELICOPTER DEVELOPED FUEL LEAK SITTING IN HANGER. BONDING MATERIAL BETWEEN ALUMINUM FLANGE AND RUBBER TUBE IS ALMO	ST NON-EXISTENT. THE RUBBER ALSO SEEMS TO HAVE SWELLED. (TC NR 20071001002)					1	G	7	1 	3U			NC	H2SW    					 
2007110500092	20071105	00092	EA  	2007	11	5	CA071001003      	1	20070929	G	3310	18271	POWER SUPPLY    			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT LIGHTS	DAMAGED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			7521 								(CAN) DURING CRUISE, THE INTERNAL COCKPIT LIGHTING WAS SWITCHED ON, OVERHEAD PANEL LIGHTS DID NOT ILLUMINATE. OVERHEAD P	ANEL LIGHT CIRCUIT BREAKER WAS OBSERVED AS TRIPPED. CIRCUIT BREAKER WAS RESET. A FEW MINUTES LATER A SUSPECTED ELECTRICA	L BURNING SMELL WAS OBSERVED.  F/A 1 WAS CONTACTED AND ASKED TO COME TO THE FLIGHTDECK. F/A 1 CONFIRMED THE SMELL AND ST	ATED IT WAS STRONGER NEAR THE WARDROBE. QRH ACTIONS FOR FIRE/SMOKE UNKNOWN SOURCE WERE CARRIED OUT. A UNSCHEDULED LANDIN	G COMPLETED. ENGINEERING INVESTIGATION REVEALED THAT THE NR 2 DC POWER SUPPLY EXHIBITED SIGNS OF OVERHEATING, AND DAMAGE	 DUE TO POSSIBLE EXCESSIVE CURRENT DRAW. UNIT ALSO HAD STRONG BURNED SMELL. THE NR 2 DC POWER SUPPLY WAS REPLACED IAW TH	1	H	7	2 	3T	4	T	RT	A9EA    	E20NE	6	C	P7NE	 
2007110500093	20071105	00093	NM  	2007	11	5	CA071001004      	1	20070930	G	2612	285T03855	WARNING SYSTEM  			BOEING	767   	767328      	1385290	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					FIRE/OVERHEAT	NO TEST         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY CHECK AN OPERATIONAL CHECK OF AUTOMATIC FIRE/OVERHEAT LOGIC TEST SYSTEM WAS CARRIED OUT AND WAS DISCO	VERED THAT AURAL WARNING IS INOPERATIVE. SYSTEM BELL AND CHIME MODULE REPLACED AND SYSTEM FUNCTION CHECKED SERVICEABLE. 	(TC NR 20071001004)				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2007113000091	20071130	00091	EU  	2007	11	30	CA071001005      	2	20070928	G	7230	RK49612	IMPELLER        			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	ENGINE	DAMAGED         	W				E	F	A		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		A	X	T	FLAME/FIRE                	ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   	CL	CLIMB          	1			CA			4842 	4842 				14796			(CAN) WHILE ON CLIMB AFTER DEPARTING, THE WAS A BANG FROM THE RT ENGINE, TOTAL LOSS OF POWER AND FIRE WARNING. THE FWD P	ART OF THE ENGINE WAS SEEN TO BE ON FIRE, WHICH WAS EXTINGUISHED BY (2) SHOTS OF THE EXTINGUISHER SYSTEM. THE AIRCRAFT R	ETURNED TO DEPARTURE AND MADE AN EMERGENCY LANDING WITH NO FURTHER INCIDENT. INSPECTION REVEALED THAT THE LP IMPELLER CA	SING WAS PUNCTURED IN SEVERAL PLACES AROUND ITS EDGE. THE COWLINGS WERE ALSO SEVERELY DAMAGED BY THE FIRE. THIS ENGINE W	ILL BE RETURNED TO MFG FOR INVESTIGATION.		2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2007110500094	20071105	00094	GL  	2007	11	5	CA071001006      	2	20070621	G	7250	23037413	SHAFT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			232  					CAT40248			(CAN) POWER TURBINE ACTION DISMANTLED TO DETERMINE CAUSE OF OIL CONSUMPTION AND SMOKING. UPON TEARDOWN AND DETAIL INSPEC	TION IT WAS NOTED THAT THE PT OUTER SHAFT HAD A LARGE CRACK ORIGINATING AT ROOT OF 1 CURVIC COUPLINGS AND SPLITTING INTO	 2 FURTHER DOWN SHAFT. CRACKING AND MATERIAL DAMAGE TO CURVIC RESULTED IN LOSS OF 1 OF CURVICS WHICH WAS NOT RECOVERED. 	FRETTING DAMAGE IS ALSO OBSERVED ON MATING CURVICS OF 3RD AND 4TH STAGE WHEELS. REPORTED OIL CONSUMPTION AND SMOKING ASS	OCIATED WITH THIS TURBINE LIKELY RESULT OF OIL AND OIL MIST MOVING THROUGH TIGHT FIT OF PT INNER AND OUTER SHAFT. NORMAL	 TIGHT FIT BETWEEN THESE COMPONENTS WOULD HAVE BEEN AFFECTED BY CRACKING OF OUTER SHAFT RESULTING IN OIL FLOW ACROSS THI	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007110500095	20071105	00095	EA  	2007	11	5	CA071001007      	1	20070928	G	5200	33130131	PISTON          			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	AWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	WATER DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A C CHECK OUR NDT CONTRACTOR ADVISED US THAT HE HAS BEEN FINDING CRACKS IN THIS AREA WHILE WORKING FOR	 OTHER CUSTOMERS. WE ARE CHECKING THE REST OF OUR FLEET AS THIS FAILURE WOULD RESULT IN A UNCOMMANDED BOMB DOOR OPENING.					2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2008031900160	20080319	00160		2008	3	19	CA071001008      	4	20070919	G	3457	GPS430WX2	GPS             			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			2    								(CAN) ON APPROACH, THE GPS430W UNITS INDICATED A DISTANCE OF 30 MILES WHICH THEN, SUDDENLY CHANGED TO AN INDICATED DISTA	NCE OF (2) TO (3) MILES CAUSING A LOSS OF CREW SITUATION AWARENESS. THE APPROACH WAS ABORTED. MFG WAS CONTACTED AND INFO	RMED OF THE PROBLEM. MFG REPLIED, STATING THE ERROR WAS CAUSED BY THE SOFTWARE VERSION IN USE WHICH WOULD BE CORRECTED A	SAP. A COPY OF THE PILOT`S REPORT IS ENCLOSED. (TC NR 20071001008)			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2008030600162	20080306	00162	SO  	2008	3	6	CA071001009      	1	20070907	G	3210	4028400	BRACE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			12435								(CAN) ON LANDING THE LT MLG COLLAPSED.  UPON INSPECTION IT WAS DETERMINED THAT THE MLG LOWER SIDE BRACE LINK ASSY HAD FA	ILED AT THE AFT HOLE CONTAINING MLG LOCK PIN. THE LOCK PIN WAS GONE AND UNABLE TO LOCATE.  MLG SIDE BRACE PN 40284-00 ML	G P/N 40376-00 (TC NR 20071001009)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008030600163	20080306	00163	SW  	2008	3	6	CA071001010      	1	20070922	G	6410	206310105101	BEARING RACE    	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					T/R BLADE	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			HO	HOVERING       	1			CA			1737 	764  		CS12475					(CAN) PILOT REPORTED AN INCREASE OF FORCE REQUIRED TO PUSH THE T/R PEDALS AT 100 PERCENT RPM WHICH EXCEEDED THE OPERATIO	NAL LIMITS. HOWEVER, AT ZERO RPM THE FORCE WAS NORMAL.  IT WAS DETERMINED THAT THE CAUSE WAS ASSOCIATED WITH THE T/R FEA	THERING BEARINGS.  INSPECTION SHOWED THAT THE BEARINGS ALTHOUGH SOMEWHAT WORN DID NOT HAVE EXCESSIVE WEAR.  FURTHER INSP	ECTION FOUND THAT ONE OF THE IB BEARINGS HAD A CRACKED INNER RACE RUNNING FULL LENGTH PARALLEL TO IT`S AXIS.  THE BEARIN	G IS THE ORIGINAL BEARING INSTALLED BY THE MFG.  INSTALLATION OF NEW T/R BLADES RECTIFIED THE EXCESSIVE T/R FORCE AT 100	 PERCENT RPM DEFECT. (TC NR 20071001010)	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2007110500105	20071105	00105	EA  	2007	11	5	CA071001011      	2	20070715	G	7240	310926302	DUCT            	PWC         	PT6A34      	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4180 			RB0196					(CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE L	ARGE EXIT DUCT (LED). THE LED WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THRO	UGH ONE LAYER OF THE DUCT. A CRACK THAT TRAVELED APPROXIMATELY .2500 OF THE CIRCUMFERENCE OF THE OUTER PORTION OF THE LE	D WAS ALSO NOTICED. (TC NR 20071001011)			1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
2007110500107	20071105	00107	GL  	2007	11	5	CA071001012      	2	20070928	G	7200		ENGINE          			EMB   	135   	EMB135ER    	3260203	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					NR 1	MAKING METAL    	W				B				EMER. DESCENT           				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA			16065					CAE311496			(CAN) N13992/145284 ENGINE NR 1 (A1P, CAE311496) EXPERIENCED AN UNCOMMANDED INFLIGHT SHUTDOWN ON APPROACH TO EWR FROM ME	M, FLIGHT 2144, ON 27 SEP. THE CREW OBSERVED AN ENG 1 OUT MESSAGE ON THE EICAS DURING FINAL APPROACHED AND ATTEMPTED AN 	UNSUCCESSFUL RESTART. UPON SAFE LANDING, MAJOR AMOUNTS OF METAL CHIPS AND FLAKES WERE FOUND ON BOTH OIL TANK MCDS WITH L	IGHT AMOUNTS OF DEBRIS ON REMAINING MCDS. ENGINE ALLOCATED TO ROLLS-ROYCE CANADA FOR INVESTIGATION, FURTHER DETAIL WILL 	BE SUBMITTED FOLLOWING ENGINE TEARDOWN (TC NR 20071001012)		2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2007110500108	20071105	00108	NM  	2007	11	5	CA071002002      	1	20071002	G	2910	DSC1896	CHECK VALVE     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 HYD SYS	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AN AIRCRAFT EXPERIENCED A LOSS OF HYDRAULIC SYSTEM NR 2 DURING TAKEOFF. FLIGHT ABORTED. ALTERNATE LDG EXTENSION US	ED. MAINTENANCE FOUND SPU NR 2 CHECK VALVE WITH A CIRCUMFERENTIAL CRACK ON ITS BODY. (TC NR 20071002002)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008030600164	20080306	00164	CE  	2008	3	6	CA071002003      	1	20070925	G	3397		WIRE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	LANDING LIGHT	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF, ODOR NOTICED IN COCKPIT. FLIGHT CONTINUED. SMOKE AND SPARKS NOTICED FROM BEHIND AREA WHERE LANDING	 LIGHT SWITCH IS LOCATED. MASTER TUNRED OFF AND AC RETURNED TO FIELD. DURING THIS TIME, A FIRE HAD STARTED RIGHT BEHIND 	THE LANDING LIGHT SWITCH AND WAS EXTINGUISHED USING THE ONBOARD FIRE EXTINGUISHER. AC LANDED WITHOUT FURTHER INCIDENT.  	UPON INVESTIGATION, FOUND WIRES FROM BEHIND LANDING LIGHT HAD FALLEN OFF DUE TO LANDING LIGHT SWITCH OVER HEATING AND TE	RMINALS FROM THE SWITCH FALLING OFF. THIS ALLOWED THE SUPPLY WIRE FOR THE LANDING LIGHT SWITCH TO CONTACT GROUND AND STA	RT ARCING WHICH STARTED THE FIRE. THE CIRCUIT BREAKER WAS FOUND IN THE CLOSED POSITION INDICATING IT DID NOT OPEN DURING	1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2008031900161	20080319	00161	EA  	2008	3	19	CA071002004      	2	20070930	G	8530	16A23033	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NR 3	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENG COMPRESSION CHECK WAS COMPLETED DUE TO REPORTED ROUGH RUNNING ENG. CYL NR 3 FOUND TO HAVE NO COMPRESSION AND W	AS BOROSCOPED. DURING BOROSCOPE, A PIECE OF WIRE WAS FOUND TO BE HUNG UP BETWEEN THE INTAKE VALVE AND THE EXHAUST VALVE.	 CYLINDER WAS REMOVED. BOTH VALVES WERE REMOVED FROM THE CYL AND THE WIRE THAT WAS NOTICED DURING BOROSCOPING FELL OUT. 	UPON INVESTIGATION OF THE WIRE, IT WAS DETERMINED THAT THIS WIRE WAS FROM A SCAT HOSE WHICH WAS ATTACHED TO THE CARBURAT	OR AIR BOX. THE WIRE WAS APPROX 3 INCHES LONG AND WAS SUCKED UP THROUGH THE AIR BOX, CARBURATOR, INDUCTION SYS AND RT IN	TO THE CYL. DURING CLOSE INSP OF THE WIRE, CHAF MARKS WERE NOTICED ON THE WIRE WHERE IT HAD BEEN RUBBING ON THE EDGE OF 	1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2007110500109	20071105	00109	SO  	2007	11	5	CA071002005      	2	20070928	G	8530		PISTON          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCA3V	PHCA3VF2    	GL  	ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA			1414 	98   				297694R			(CAN) DURING CRUISE FLT, RT ENGINE BEGAN TO LOOSE OIL PRESSURE. OIL TEMP & CHT INCREASED. PILOT ELECTED TO SHUTDOWN ENGI	NE AS A VIBRATION BECAME APPARENT & OIL PRESSURE DECREASED TO NEAR ZERO. AN EMERGENCY DECLARED & AIRCRAFT LANDED WITHOUT	 FURTHER INCIDENT. UPON INSPECTION, NR 5 CYLINDER & PISTON FOUND DAMAGED. PISTON FOUND WITH A HOLE IN SIDE JUST BELOW CO	MPRESSION RINGS. HOLE DOES NOT APPEAR TO BE CAUSED BY OPERATIONAL DAMAGE & ONLY 98 HRS TSO IS UNLIKELY. LOOKS LIKE A MAN	UFACTURING DEFECT OR SOME TYPE OF MECHANICAL DAMAGE. HOLE CAUSED CRANKCASE TO PRESSURIZE & THERFORE CAUSE ENGINE TO VENT	 IT`S OIL OVERBOARD THROUGH BREATHER TUBE.  SAME AIRCRAFT & ENGINE EXPERIENCED SAME PROBLEM A WEEK PRIOR TO THIS EVENT B	1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P6EA	 
2007110500110	20071105	00110	NM  	2007	11	5	CA071002006      	1	20070930	G	2912	20011610	FILTER ADAPTER  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	CLOGGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, CREW HAD TROUBLES WITH LANDING GEAR, MAIN GEARS WOULD NOT RETRACT. NOSE RETRACTED NORMALLY. ALTERNA	TE LANDING GEAR EXTENSION ACC. CHECKLIST DONE. UNEVENTFUL LANDING. AIRCRAFT HANDED OVER TO MAINTENANCE.  NO FAULTS CODES	.  FOUND BYPASS VALVE FILTER COLLAPSED, FILTER REPLACED, A/C RTS. (TC NR 20071002006)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007110500111	20071105	00111	EA  	2007	11	5	CA071003001      	1	20071002	G	3230	750005000	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH (GEAR DISAGREE) WARNING MESSAGE AT LDG SELECTION. MLG`S WOULD NOT COME DOWN, NLG OK. CYCLED LDG SAME. 	ALTERNATE EXTENSION USED, OK. AIRCRAFT LANDED. SNAG CAN BE REPRODUCED ON JACKS. MLG SELECTOR VALVE FOUND INOPERATIVE. RE	PLACED VALVE. A/C RTS. (TC NR 20071003001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500112	20071105	00112	EA  	2007	11	5	CA071003002      	1	20071002	G	2497		BUSS BAR        			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF34*       	 	NE  					COCKPIT	OVERHEATED      	W				L	A			ABORTED APPROACH        	UNSCHED LANDING         			H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) ON APPROACH CREW RECEIVED WING ANTI ICE FAULT STS MSG FOLLOWED BY DC BUS 1 CAUTION MESSAGE. AIR TURN BACK MAINTENA	NCE FOUND CB`S D6, D7 AND THEIR BUS BAR OVERHEATED. REPLACED C/B`S AND BUS BAR.   PARTS REPLACED: BUS BAR CIRCUIT BREAKE	R D6 (80A) CIRCUIT BREAKER: D7 (3A)  BUS BAR: S6938-1 CIRCUIT BREAKER D6 (80A): MS25361-80 CIRCUIT BREAKER D7 (3A): MS22	073-3 (TC NR 20071003002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500113	20071105	00113	EA  	2007	11	5	CA071003003      	1	20071001	G	2752	852D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAP	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			11009								(CAN) FLAPS FAIL CAUTION MSG AND 40 DEG. RAN QRH PROCEDURES AS REQUIRED AND COMPLIED WITH INSTRUCTIONS. A/C DISPATCHED U	NDER PROVISIONS OF FAA AD 2006-12-21 (DEFERRAL FOR 72 HRS).  AT OVERNIGHT MAINTENANCE, FOUND RT WING FLAP DRIVE SYSTEM T	ORQUE VALUE AT 25 IN/LBS. FOUND RT IB ( NR 1 ACTUATOR) WITH HIGH TORQUE. REPLACED RT NR 1 FLAP ACTUATOR IAW CRJ AMM 27-5	3-01. (TC NR 20071003003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500114	20071105	00114	EA  	2007	11	5	CA071003004      	1	20071003	G	3213	21587525	PLATE           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	AWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	MLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ADJUSTING PLATE P/N 215-87525 MISSING ON A NEWLY OVERHAULED LOWER MEMBER P/N 160-600-35 S/N H126.  A/C HOURS 4658.	7 CYCLES 2973 DROPS16691 (TC NR 20071003004)					2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2008030600165	20080306	00165	SO  	2008	3	6	CA071003005      	1	20070920	G	3230	74087002	ROD END         	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MAIN GEAR DOOR	STIFF           	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) ON SEPT 12, THE DOWNLOCK HOOK ON THE RT GEAR DID NOT COMPLETELY LOCK TO ACTIVATE THE DOWNLOCK SWITCH. THE RETRACTI	ON SYS WAS TROUBLESHOT AND FOUND THE ROD END ON THE DOWNLOCK CABLE ASSY WAS STIFF AND THE SWITCH WAS STICKING. THE GEAR 	WAS CLEANED AND LUBRICATED.  RETRACTION TESTS CARRIED OUT AND AC RETURNED TO SERVICE. ON THE SEPT 20, THE SAME SNAG HAPP	ENED. THE ROD END HAD STIFFENED UP AGAIN. THE ROD END WAS CHANGED AND NO MORE PROBLEM. THE ROD END AT FAULT WAS LUBRICAT	ED AND FOUND TO MOVE FREELY BUT AFTER BEING LEFT ON THE BENCH FOR A FEW DAYS SEIZED UP AGAIN. (TC NR 20071003005)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007110500115	20071105	00115	NM  	2007	11	5	CA071003006      	1	20071002	G	5544	72760059101	MOUNT           			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			44877	44877							(CAN) DURING RIGGING OF LOWER RUDDER ACTUATOR SPRING STRUT, NOTICED ACTUATOR ADAPTOR FLEXING. ADAPTOR FOUND TO BE CRACKE	D FROM OUTER FLANGE HORIZONTALLY ACROSS RADIUS TO INNER FLANGE. ADAPTOR REPLACED. (TC NR 20071003006)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110500121	20071105	00121	EA  	2007	11	5	CA071003007      	2	20070810	G	8550	LW13383	BAFFLE          			FOUND 	FBA   	FBA2C2      	3640104	EA  	LYC   	O540  	IO540L1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	OIL SUMP	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			10   								(CAN) ENGINE OIL SUMP BAFFLE CONTACTING BOTTOM OF OIL SUMP. REPLACED OIL SUMP WITH A NEW ONE FROM MFG. INSPECTION ACCOMP	LISHED BECAUSE OF REQUEST FROM CUSTOMER WHO SUBMITTED FAA SDR NR 2007FA0000760 AND 1. (TC NR 20071003007)					1	H	7	1 	3O	3	O	NC	A7EA    	1E4	5	C	P25EA	 
2008030600166	20080306	00166	CE  	2008	3	6	CA071003008      	1	20070914	G	5540	0510128	BRACKET         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16797								(CAN) ON A 100 HOUR INSPECTION, MAINT DISCOVERED THE RUDDER PEDAL TORQUE TUBE SPRING ATTACHMENT BRACKET HOLE WAS WORN MO	RE THAN HALF THRU. THIS IS A HARD TO INSPECT AREA AT THE FWD TUNNEL CENTER SECTION UNDER THE DASH. THE BRACKET WAS REPLA	CED AND RUDDER RE-RIGGED AS REQUIRED. (TC NR 20071003008)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2007110500122	20071105	00122	NE  	2007	11	5	CA071003009      	2	20070802	G	7261	3034677	TUBE            			AEROSP	ATR72 	ATR72202    	8680940	EU  	PWA   	PW120 	PW124B      	 	NE  					ENGINE OIL	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS SEEN TO DECREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTIO	N REVEALED A LEAKING OIL PRESSURE TUBE AT THE REAR INLET CASE. (TC NR 20071003009)					2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2007110500123	20071105	00123	NE  	2007	11	5	CA071003010      	2	20070803	G	7200		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  						MAKING METAL    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) DURING DESCENT OIL ODOR AND SMOKE WERE EVIDENT IN THE CABIN. ENGINE BLEED WAS SELECTED OFF. SUBSEQUENT INSPECTION 	REVEALED METAL PARTICLES IN THE ENGINE OIL.					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007110500124	20071105	00124	EU  	2007	11	5	CA071003011      	1	20070805	G	7712		SENSOR          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					AUTOFEATHER SYS	MISINSTALLED    	W				O				OTHER                   				R	W	J	PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN) ON DESCENT THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER ACCOMPANIED BY FEATHERING OF THE PROPELLER. PR	ELIMINARY INSPECTION REVEALED IMPROPERLY TORQUED TORQUE SENSOR AND POOR CONTINUITY BETWEEN THE AFU AND FUEL CONTROL.					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007110500125	20071105	00125	NE  	2007	11	5	CA071003012      	2	20070808	G	7200		ENGINE          			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  		SMOKE           	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA								120696			(CAN) FOLLOWING TAKEOFF OIL ODOR AND SMOKE WERE EVIDENT IN THE CABIN. THE ENGINE WAS SHUTDOWN IN FLIGHT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110500126	20071105	00126	NE  	2007	11	5	CA071003013      	2	20070805	G	7200		ENGINE          			AGUSTA	A109  	A109E       	0260119	EU  	PWC   	PW206C	PW206C      		NE  						POWER LOSS      	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								BC0541BC0542			(CAN) DURING TAKEOFF, THE PILOT REPORTED A POWER LOSS ACCOMPANIED BY AN LOW TORQUE WARNING INDICATION. THE AIRCRAFT WAS 	DAMAGED IN THE RESULTING FORCED LANDING.					1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
2007110500127	20071105	00127	NE  	2007	11	5	CA071003014      	2	20070808	G	7321	8273002	FCU             			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	UNRESPONSIVE    	W				O				OTHER                   				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		DE	DESCENT        	1			CA											(CAN) ON DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE FUEL CONTROL UNIT WAS REPLACED.						2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007110500102	20071105	00102	NE  	2007	11	5	CA071003015      	2	20070807	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  						MAKING METAL    	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA								124623			(CAN) THE ENGINE FLAMED OUT IN CRUISE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE OIL SYSTEM.						2	H	7	2 	4T	4	T	RT	        	E2ONE				 
2007102600134	20071026	00134	EA  	2007	10	26	CA071003016      	2	20070630	G	7230	FRACTURE	BLADES          			AIRTRC	AT500 	AT502A      	0390306	SW  	PWA   	PT6   	PT6A65B     	52043	EA  					COMPRESSOR	FRACTURED       	W				C				ABORTED TAKEOFF         				R	A		PARTIAL RPM/PWR LOSS      	FLAME/FIRE                		TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF, THE ENGINE EXPERIENCED A POWER LOSS ACCOMPANIED BY FLAMES EXITING THE EXHAUST. THE AIRCRAFT WAS DAMAGE	D, RESULTING IN A FORCED LANDING. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR BLADES. MFG WILL MONITOR THE INVES	TIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003016)				1	L	7	1 	3T	4	T	NC	A17SW   	E4EA				 
2007102600135	20071026	00135	NE  	2007	10	26	CA071003017      	2	20070810	G	7200		ENGINE          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  						POWER LOSS      	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN FLIGHT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF R	OOT CAUSE ONCE ESTABLISHED. (TC NR 20071003017)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2007102600136	20071026	00136	NE  	2007	10	26	CA071003018      	2	20070813	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								70176			(CAN) IN CRUISE SMOKE BECAME EVIDENT IN THE AIRCRAFT CABIN REQUIRING THE ENGINE AIR BLEED TO BE SELECTED OFF.  MFG WILL 	INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003018)					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2007102600137	20071026	00137	NE  	2007	10	26	CA071003019      	2	20070813	G	7321	32448716	FUEL CONTROL    			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN) IN FLIGHT, ENGINE POWER REDUCED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN. AN IN-FLIGHT RELIGHT ATTEMPT WAS UNSUCCES	SFUL. SUBEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20071003019)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2007110500001	20071105	00001	NM  	2007	11	5	CA071003020      	1	20070930	G	2622		SEAL            			BOEING	737   	737800*     	       	NM  	CFMINT	CFM56 	CFM567B26US 	 	NE  					EXTINGUISHER	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			9918 			W856080					(CAN) ON SEPTEMBER 30, 2007 THE FLIGHT CREW REPORTED THAT THE PORTABLE FLIGHT DECK FIRE EXTINGUISHER PARTIALLY DISCHARGE	D DURING CRUISE ON A/C 803. THE FIRE EXTINGUISHER WAS REPLACED WITH NO FURTHER ACTION REQUIRED.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2007113000093	20071130	00093	NE  	2007	11	30	CA071003021      	2	20070807	G	7230		ENGINE          			CESSNA	510   	510         	2076617	CE  	PWC   	PW615 	PW615FA     	52282	NE  						MALFUNCTIONED   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								LB0013			(CAN) IN CRUISE IN LIGHT ICING CONDITIONS, ENGINE N1 SPEED REDUCED UNCOMMANDED. THE N1 RETURNED TO NORMAL SETTINGS IN DE	SCENT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.					1	L	7	2 	4F	4	F	RT	A00014WI	E00073EN				 
2007102600138	20071026	00138	NE  	2007	10	26	CA071003022      	2	20070819	G	7250		TURBINE BLADES  			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA								JA0236			(CAN) THE ENGINE FLAMED OUT IN FLIGHT AND AN ATTEMPTED RELIGHT WAS UNSUCCESSFUL.  SUBSEQUENT INSPECTION REVEALED DAMAGED	 POWER TURBINE BLADES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003022)					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007102600139	20071026	00139	NE  	2007	10	26	CA071003023      	2	20070812	G	7230	30B285501	FAN BLADE       			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					COMPRESSOR	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) IN CRUISE, THE ENGINE EMITTED A LOUD NOISE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED TWO FRACTURE	D FAN BLADES.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003023)					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007102600140	20071026	00140	CE  	2007	10	26	CA071003024      	1	20070824	G	7931		OIL SYSTEM      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	FLUCTUATES      	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA								114070			(CAN) ON APPROACH, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL MONITOR IN	VESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003024)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2007102600141	20071026	00141	EU  	2007	10	26	CA071003025      	3	20070825	G	6197		WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	ENGINE	UNKNOWN         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								FA0249			(CAN) IN CRUISE, THE PROPELLER ELECTRONIC CONTROL (PEC) AND POWER PLANT WARNINGS ACTIVATED. THE ENGINE WAS SHUTDOWN IN F	LIGHT. THE PEC, SENSOR AND RELATED HARNESS WERE SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROO	T CAUSE ONCE ESTABLISHED. (TC NR 20071003025)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2007102600142	20071026	00142	CE  	2007	10	26	CA071003026      	1	20070826	G	7603		COUPLING        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					THROTTLE	FRACTURED       	W				E				ENGINE SHUTDOWN         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) ON INITIATING DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. S	UBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL (PLASTIC) DRIVE COUPLING. (TC NR 20071003026)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007102600143	20071026	00143	EA  	2007	10	26	CA071003027      	2	20070829	G	7200		ENGINE          			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								TH0736			(CAN) AN ENGINE CHIP DETECTOR WARNING ACTIVED AND THE POWER SECTION WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEAL	ED METAL DEBRIS IN THE ENGINE OIL SYSTEM.  MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 200710	03027)				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2007102600144	20071026	00144	NE  	2007	10	26	CA071003028      	2	20070823	G	7261		STRAINER        			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 4 BEARING	BLOCKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) IN DESCENT, ENGINE OIL PRESSURE REDUCED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED OIL	 COKING AND BLOCKAGE OF THE NR 4 BEARING SCAVENGE OIL STRAINER. (TC NR 20071003028)					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2007102600145	20071026	00145	EU  	2007	10	26	CA071003029      	1	20070829	G	7720		THERMOCOUPLE    			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					ENGINE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE OVER-TEMPERATURE WARNING ACTIVATED IN FLIGHT AND THE ENGINE WAS SHUTDOWN. SUBSEQUENT INSPECTION REVEALE	D TWO UNSERVICEABLE T6 THERMOCOUPLES. (TC NR 20071003029)					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2007102600146	20071026	00146	WP  	2007	10	26	CA071004001      	1	20071003	G	8011	14924HTH	STARTER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ZERO TIMED STARTER INSTALLED ON AIRCRAFT.  WOULD NOT TURN OVER DURING FUNCTIONAL CHECK. (TC NR 20071004001)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2007110500010	20071105	00010	NM  	2007	11	5	CA071004002      	1	20070928	G	2497		WIRE HARNESS    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  						CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17156								(CAN) WIRE BUNDLE AT STATION FS 510 (BELOW FLOOR BOARD) CROSSING OVER FROM STARBOARD TO PORT SIDE. WIRE BUNDLE CURVES UP	WARD RUNNING BENEATH SEAT RAIL STRUCTURE THEN GOES FORWARD ONTRAY.  WIRE BUNDLE FOUND NOT PROTECTED AS IT CURVES UP BENE	ATH SEAT RAIL STRUCTURE (PORT SIDE). FOUR WIRES WERE CHAFING AGAINST THIS STRUCTURE OF WHICH 3 OF THEM HAD WORN THROUGH 	THE INSULATOR. WIRES WERE REPAIRED AND WIRE BUNDLE PROTECTED. (TC NR 20071004002)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008030600167	20080306	00167	CE  	2008	3	6	CA071004003      	1	20071001	G	5210	231127416	ARM             			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19829			1010					(CAN) DURING ROUTINE DAILY INSP, FOUND LOWER DOOR AFT LATCH ARM CRACKED ALL THE WAY THROUGH DUE TO CORROSION FATIGUE. (T	C NR 20071004003)					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2008012900036	20080129	00036	WP  	2008	1	29	CA071004005      	1	20070918	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYDRAULIC SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1123 	1123 							(CAN) DURING 50/100 HOUR INSPECTION HYDRAULIC SERVO FOUND LEAKING FROM PILOT VALVE.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008012900038	20080129	00038	CE  	2008	1	29	CA071004006      	1	20071001	G	7602	991027114	CABLE           			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MIXTURE CONTROL	BROKEN          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			10177								(CAN) DURING THE ENGINE RUN-UP, THE RT ENGINE DID NOT RESPOND TO MIXTURE CONTROL. THE MIXTURE CONTROL CABLE WAS FOUND BR	OKEN UNDER THE ENGINE CONTROL PEDISTAL. THE BRAKE WAS INSIDE THE CONTROL CABLE HOUSING AND COULD NOT BE SEEN WITH ANY IN	SPECTION. (TC NR 20071004006)				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2007110500034	20071105	00034	WP  	2007	11	5	CA071004007      	1	20070918	G	8011	14924HTH	STARTER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			227  	227  							(CAN) STARTER WOULD NOT DISENGAGE AFTER START. AFTER SHUTDOWN GEAR HAD TO BE PRYED BACK TO DISENGAGE. (TC NR 20071004007	)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008030600168	20080306	00168	EA  	2008	3	6	CA071004008      	2	20071001	G	8550	LW15628	SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CRANKCASE	UNSECURE        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL FOUND IN COWLING ON LT ENGINE NEAR FRONT, FWD CRANKCASE OIL SEAL FOUND TO HAVE POPPED OUT OVERHAUL INFORMED TH	IS COMPANY THAT THEY WERE HAVING PROBLEMS WITH THE ADHESIVE THAT THEY USE TO SECURE THIS SEAL (TC NR 20071004008)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007110500035	20071105	00035	EA  	2007	11	5	CA071005001      	1	20071004	G	5320	CA447	SHROUD          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					BS 559	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A HEAVY CHECK THE FUEL SHROUD ASSY AND FUEL LINES AT FRAME 559 WERE REMOVED TO FACILITATE A SHEET METAL REP	AIR. IT WAS DISCOVERED THAT BOTH SHROUD AND FUEL LINES HAVE CHAFING BEYOND LIMITS. THIS SAME REPAIR IS BEING C/O ON A/C 	C-FZSI(126) AND SIMILAR DAMAGE WAS FOUND IN THE SAME LOCATION. THE FUEL LINES AND SHROUD ASSY. HAVE BEEN ORDERED FOR BOT	H A/C AND WILL BE REPLACED BEFORE THE A/C LEAVES THE HEAVY CHECK. (TC NR 20071005001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600169	20080306	00169	EU  	2008	3	6	CA071005002      	1	20071003	G	6730	7050A4673006	SERVO CONTROL   			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ROTOR	UNLOCKED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1533 								(CAN) PILOT REPORTED, WHEN PREFLIGHT HYDRAULIC TEST ACTIVATED, CYCLIC MOTORED RT. CYCLIC SHOULD STAY CENTERED DURING HYD	 TEST. SERVO REPLACED WITH O/H UNIT. GROUND TESTED, SERVICEABLE.  AFTER REMOVAL OF SERVO, NOTICED THAT INPUT LEVER WAS S	LIGHTLY LOOSE. AFTER MOVING THE INPUT LEVER A FEW TIMES, LEVER APPEARED TO LOCK, AS REQUIRED. SUSPECT STICKY INTERNAL LO	CK PIN. (TC NR 20071005002)			1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008030600170	20080306	00170	EU  	2008	3	6	CA071005003      	1	20070928	G	3222	5321012193	RING            	PILATS      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	SHOCK ABSORBER	SWOLLEN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						IL512					(CAN) DURING ANNUAL INSPECTION IT WAS FOUND THAT STRUTS WERE STIFF, NOT EXTENDING ALL THE WAY. FOUND MICARTA GUIDE RINGS	 TOO TIGHT. SANDED MICARTA GUIDE RINGS SAME WAY AS MOD TO NOSE OLEO. SERVICED STRUTS WITH FLUID AND NITROGEN. RETURNED T	O SERVICE. (TC NR 20071005003)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2007110500036	20071105	00036	SW  	2007	11	5	CA071005004      	1	20071002	G	3210	AN17722	BOLT            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT MLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT CALLED AND REPORTED THAT THE BOLT WAS MISSING FROM THE RT MLG TORQUE KNEE.  MAINTENANCE INSPECTED TORQUE KNE	E ASSEMBLY AND NO SECONDARY DAMAGE WAS NOTED.  NEW BOLT WAS INSTALLED AND SECURED AND AIRCRAFT RETURNED OUT OF SERVICE. 	(TC NR 20071005004)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2007110500037	20071105	00037	EA  	2007	11	5	CA071009001      	1	20071005	G	2752	852D10021	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAPS	FROZEN          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) ON DESCENT CREW RECEIVED FLAP FAIL MESSAGE UPON SELECTION OF FLAPS DOWN. FLAPS FAILED AT ZERO DEGREES. FLIGHT LAND	ED WITHOUT INCIDENT. UPON INVESTIGATION IT WAS FOUND THAT THE ACTUATORS WERE FROZEN. ALL IB AND OB ACTUATORS REPLACED (8	), FLAP RIGGING CARRIED OUT AND SYSTEM OPERATIONAL CHECK CARRIED OUT WITH NO FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE.	 (TC NR 20071009001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500039	20071105	00039	EA  	2007	11	5	CA071009002      	1	20071007	G	5712	601R120474	RIB             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT WING	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REMNANTS OF A BIRD WAS FOUND ON ARRIVAL. INSP REVEALED A DENT IN THE RT WING LEADING EDGE AT WING. THE DENT WAS AP	PROXIMATELY 4 INCHES BY 2 INCHES AND .25 INCHES DEEP. MAINTENANCE REMOVED THE DENT AND REPLACED RIB AT WING STATION 167.	00 AND THE L/E WAS RE-INSTALLED AND WING ANTI ICE WAS FUNCTION CHECKED SERVICEABLE. (TC NR 20071009002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500060	20071105	00060	NM  	2007	11	5	CA071010001      	1	20071005	G	2824	1321536250	CONTROL VALVE   			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  					FUEL SYSTEM	OBSTRUCTED      	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			CA			21   								(CAN) DURING TEST FLIGHT, RT AUX TO MAIN FUEL TRANSFER SYSTEM STOPPED TRANSFERRING. BOLT FOUND IN LEVEL CONTROL VALVE CA	USING VALVE TO STOP TRANSFER SYSTEM. BOLT REMOVED, SYSTEM FUNCTIONED NORMALLY. SAME SNAG REPORTED DURING CUSTOMER ACCEPT	ANCE FLIGHTS AT MFG. THIS F.O.D. HELD THE VALVE CLOSED INTERMITTENTLY. (TC NR 20071010001)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008030600171	20080306	00171	CE  	2008	3	6	CA071010002      	1	20071008	G	7500	12991003315	HOSE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	BLEED AIR	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) BLEED AIR FAIL LIGHT CAME ON DURING THE TAKEOFF PROCESS. THE AC CAME AROUND AND LANDED. MAINTENANCE WAS CALLED. IT	 WAS DISCOVERED THAT A BLEED AIR LINE WAS CRACKED AT THE FLANGE. LINE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.	 (TC NR 20071010002)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008031900162	20080319	00162	GL  	2008	3	19	CA071010003      	2	20071009	G	7240	6870992	COMBUSTION CASE 			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE821328			(CAN) PILOT RETURNING TO BASE REPORTED HIGHER THAN NORMAL ENGINE TEMP. INSP OF THE ENG INDICATION SYS FOUND SERVICEABLE.	  INSP OF THE ENGINE FOUND A CRACK IN THE COMBUSTION CASE. COMBUSTION CASE REPLACED. AC GROUND RUN AND FOUND SERVICEABLE	 AND RETURNED TO SERVICE. (TC NR 20071010003)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008030600172	20080306	00172	CE  	2008	3	6	CA071010004      	1	20070926	G	2421		BRUSHES         			LEAR  	35    	31          	5170530	CE  										MOTOR	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						1080S					(CAN) BRUSH ASSEMBLIES BURNED. (TC NR 20071010004)						2	L	7	2 	4F			RT	A10CE   					 
2008030600173	20080306	00173	SW  	2008	3	6	CA071010005      	1	20070828	G	6210	204011250001	BLADE           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					MAIN ROTOR	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA			1851 								(CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WA	S A VIOLENT LATERAL VIBRATION. AT THIS TIME THE TRANSMISSION WAS OBSERVED SHAKING EXCESSIVELY AND IT WAS DECIDED TO SHUT	 THE AIRCRAFT DOWN WHERE IT SAT. AS THE MAIN ROTOR BLADES SPOOLED DOWN THE PILOT OBSERVED A LARGE CRACK IN ONE OF THE BL	ADES. FURTHER INSPECTION REVEALED A CRACK THROUGH THE ENTIRE THICKNESS OF THE BLADE. BOTH THE TOP AND BOTTOM SKIN ARE BR	OKEN. THE CRACK/BREAK IS LOCATED 98 INCHES FROM THE ROOT OF THE BLADE AND RUNS FROM THE T/E TO 6 INCHES FROM THE L/E (AS	CENDING, THE LEADING EDGE SPAR). AT THE START OF THE CRACK (THE TRAILING EDGE) THE SKIN HAS SPREAD APPROXIMATELY .1250 I	1	G	7	1 	4U	4	U		H1SW    	E1EA				 
2007110500061	20071105	00061	NE  	2007	11	5	CA071010006      	2	20070927	G	7250	500310401	TURBINE WHEEL   			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			20974					700585			(CAN) AT THE RUNWAY THRESHOLD THE FLIGHT CREW ADVANCED THE THROTTLES TO 1.2 EPR, STABLE ENGINES WERE CALLED. ADVANCED TH	RUST LEVERS AND APPROACHING TAKEOFF THRUST, BEFORE REACHING APPROXIMATELY 20 KTS, A LOUD BANG AND VIBRATION OCCURRED. TH	E FLIGHT CREW REJECTED THE TAKEOFF AND CLEARED THE RUNWAY. THE NR1 ENGINE WAS SHUT DOWN AFTER OBSERVING N2 SPOOL DOWN AN	D INCREASING EGT INDICATION. THE AIRCRAFT RETURNED TO THE GATE.  MAINTENANCE FOUND THAT THE ENGINE TURBINE HAD FAILED. T	HE ENGINE WAS REMOVED AND REPLACED WITH A SERVICEABLE ASSEMBLY. (TC NR 20071010006)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008030600174	20080306	00174	SO  	2008	3	6	CA071010007      	1	20070906	G	3260	2124800	RHEOSTAT        			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1C5    	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	MLG INDICATOR	MALFUNCTIONED   	W				B				EMER. DESCENT           				H	P		ELECT. POWER LOSS-50 PC   	NO WARNING INDICATION     		LD	LANDING        	1			CA											(CAN) PILOT SELECTED GEAR DOWN AND DID NOT SEE THE GREEN LIGHT, FOR THE GEAR DOWN POSITION. PILOT THEN STARTED EMERGENCY	 GEAR DOWN PROCEDURES. IT JAMMED WITH THE GREAR IN NEUTRAL POSITION, BECAUSE THE ELECTRIC SWITCH WAS NOT IN NEUTRAL. THE	 PILOT LANDED WITH THE GEAR UP. AFTER THE AIRPLANE WAS PUT ON THE JACKS AND THE GEAR WAS LOCKED. THE RHEOSTAT WAS TURNED	 TO THE DAYLIGHT RUNNING POSITION AND THE GREEN LIGHT, FOR THE GEAR DOWN LOCK POSITION CAME ON. (TC NR 20071010007)			1	L	7	1 	3O	3	O		1A15    	E295	5	C	P58GL	 
2008012900041	20080129	00041	CE  	2008	1	29	CA071010008      	1	20071003	G	2711	1295210325	ACTUATOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT AILERON TRIM	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			99948								(CAN) DURING A 50 HOUR ROUTINE INSPECTION MAINTENANCE PERSONEL DISCOVERED THAT THE AILERON TRIM WAS NOT MOVING. UPON INS	PECTION OF THE SYSTEM IT WAS DISCOVERED THAT THE AILERON TRIM ACTUATOR WAS SEIZED. THE ACTUATOR WAS REMOVED AND DISSASSE	MBLED. THERE WAS INTERNAL RUST IN THE TRIM ACTUATOR HOUSING AND ONE BEARING WAS SEIZED. (TC NR 20071010008)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008012900043	20080129	00043	SW  	2008	1	29	CA071010009      	1	20071005	G	2911	223002	ACCUMULATOR     			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			18203								(CAN) AIRCRAFT WAS INBOUND WHEN CREW REPORTED THE AIRCRAFT HAD LOST ALL HYDRAULIC PRESSURE. EMERGENCY GEAR EXTENSION WAS	 USED AND AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE DISCOVERED A 6 CENTIMETER CRACK LOCATED ON THE TOP SHOULDER AREA	 OF THE HYDRAULIC ACCUMULATOR CAP. (TC NR 20071010009)				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2008012900044	20080129	00044	SW  	2008	1	29	CA071010011      	1	20071005	G	3230	750069501	SHAFT           			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3600					(CAN) DURING ANNUAL INSPECTION, THE SHAFT THAT PIVOTS THE NOSE GEAR UPPER LINK ASSY P/N ES10107 WAS FOUND CRACKED. THE C	RACK IS LOCATED ON THE IB END OF THE SHAFT IN THE NOSE WHEEL WELL, WHERE IT IS FLUSH WITH THE EDGE OF THE HOLE IN THE UP	PER LINK ASSEMBLY. THE CRACK IS APPROXIMATELY .5 INCH IN LENGTH AND PROGRESSES TO THE THRU BOLT HOLE. THE PIECE WILL BE 	REPLACED WITH A SERVICEABLE PART. (TC NR 20071010011)			1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
2008012900046	20080129	00046	CE  	2008	1	29	CA071011001      	1	20070914	G	3230	1153800025	MOTOR           			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	LANDING GEAR	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) IN DESCENT FOR LANDING, THERE WERE ONLY 2 GREEN GEAR DOWN INDICATION LIGHTS INSTEAD OF THREE. AFTER RECYCLING THE 	GEAR, THE PROBLEM PERSISTED.  THE EMERGENCY LANDING GEAR SYSTEM WAS DEPLOYED AND THE 3 GREEN LIGHTS WERE ON AS REQUIRED.	 AIRCRAFT LANDED WITHOUT INCIDENT.  FURTHER INSPECTION REVEALED THE LANDING GEAR MOTOR WAS UNSERVICEABLE. (TC NR 2007101	1001)			1	L	7	2 	4T	4	T		A14CE   	E2WE	6	C	P40EA	 
2008012900048	20080129	00048	CE  	2008	1	29	CA071011002      	1	20071003	G	7820		MUFFLER         			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) MUFFLER CRACKED AROUND PIPE AFTER BACKFIRE. (TC NR 20071011002)						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2008030600175	20080306	00175		2008	3	6	CA071011006      	2	20071009	G	7320	6047T74P13	FCU             			CNDAIR	CL600 	CL600*      	1900302	EA  										ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE ENROUTE AND AT FL 400, THE NR 1 ENGINE FLAMED OUT.  AC DESCENDED TO FL200 AND RESTARTED IAW AFM.  AC ARRIVED	 SAFELY.  MFG REP IS ON SITE AND RECOMMENDED THAT THE FUEL CONTROL UNIT BE REPLACED. (TC NR 20071011006)					2	L	7	2 	4F			RT	A21EA   					 
2007110500062	20071105	00062	EU  	2007	11	5	CA071011007      	1	20070914	G	5343	25FN1609	ATTACH FITTING  			HWKSLY	DH125 	HS125600A   	4230158	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER REPAINT OF A/C INSPECTION REVEALED A CRACK ON SIDE OF ATTACH POINT. LDG WAS PULLED TO REPLACE ATTACH POINT B	RACKET AND ATTACH POINT BRACKET BOLTS. THESE BOLTS WERE SHOWING WEAR MARKS ON THE SHANK, SUGGESTING THE NUTS WERE THREAD	 BOUND, INDICATING NOT ENOUGH WASHERS WERE USED. THE LDG SIDEWALL WAS ALSO SHOWING WEAR DUE TO THE BRACKET VIBRATING. WI	TH ALL THESE FINDING IT WAS DECIDED TO CHECK BOLT HOLE CLEARANCE ON THE LDG SIDEWALL, ALL BOLT HOLES WERE ELONGATED. DUE	 TO INSUFFICIENT WASHER BUILD UP THE TORQUES WERE INACCURATE CAUSING THE BRACKET TO SHIFT WITH EACH LDG CYCLE. THE CRACK	S FOUND ON BRACKET COULD BE AN INDICATION OF EXCESSIVE SIDE LOAD POSSIBLY DURING CROSSWIND LANDING, INCORRECT TAXI PROCE	2	L	7	2 	4J	4	F		A3EU    	E6WE				 
2008030600176	20080306	00176	SO  	2008	3	6	CA071011008      	1	20071005	G	3000	50363007	INLET SCREEN    			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE EVENT INSPECTION, A SMALL 1.5 INCH CRACK WAS NOTED IN THE INLET ICE SCREEN. DURING THE NEXT EVENT	 INSPECTION IT WAS NOTED THAT THE CRACK HAD SPREAD SIGNIFICANTLY AND CAUSED SEPARATION FROM THE ASSEMBLY. THE STAINLESS 	STEEL AIR INLET WAS ALSO CRACKED AND NEEDED REPAIRS. THE SCREEN WAS REPLACED WITH A NEW UNIT. (TC NR 20071011008)				1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
2007110500063	20071105	00063	SO  	2007	11	5	CA071011009      	2	20071011	G	8530	652984	ROCKER SHAFT    			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	NR 4 CYLINDER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			400  								(CAN) POOR DIFF ON INSPECTION, EXH VALVE ROCKER SHAFT FOUND DAMAGED DUE TO LACK OF OIL, CAUSING OVERHEATING AND FAILURE 	OF ROCKER BUSHING. VALVE DAMAGED DUE TO LACK OF COOLING OIL ALSO.  CAUSE OF OIL LOSS TO ROCKER UNKNOWN, MAY POSSIBLY HAV	E BEEN A BLOCKED GALLERY AT SOME POINT. (TC NR 20071011009)				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
2008012900049	20080129	00049	CE  	2008	1	29	CA071011010      	1	20070514	G	3233	11013880141	ACTUATOR        			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG	BYPASSING       	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			473  								(CAN) WHILE CONDUCTING A LANDING, THE PILOTS NOTED THAT WHILE SELECTING THE GEAR DOWN THE GEAR MOTOR RAN LONGER THAN NOR	MAL. THEY THEN NOTED THAT THE RT GEAR INDICATION LIGHT HAD FAILED TO SHOW A DOWN AND LOCKED POSITION. THEY TRIED AN EMER	GENCY GEAR EXTENSION WITH NO LUCK. THEY FLEW THE AC TO A BIGGER CENTER WHERE EMERGENCY SERVICES WHERE AVAILABLE. CONDUCT	ED A FLYBY AND THE GEAR WAS VERIFIED TO BE IN THE DOWN AND LOCKED POSITION. THE AIRCRAFT LANDED WITH NO INCIDENT. MAINTE	NANCE CREW FLEW NORTH TO INVESTIGATE. DURING THIS TIME IT WAS NOTED BY THE ENGINEERS THAT THE GEAR ACTUATOR WAS BY-PASSI	NG INTERNALLY, FAILING TO BUILD SUFFICIENT PRESSURE TO COMPLETELY LOCK THE GEAR SYSTEM. THE AIRCRAFT WAS FLOWN BACK SOUT	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2007110500070	20071105	00070	EU  	2007	11	5	CA071012001      	1	20071010	G	5280	137414B100	BRACKET         			BAG   	JETSTM	JETSTM3212  	1500217	EU  										RT MLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT MAIN LANDING GEAR DOOR AFT HINGE BRACKET FOUND BROKEN (ONE LUG OF TWO) DURING INSPECTION. NEW BRACKET INSTALLED	, GEAR SWINGS CARRIED OUT. (TC NR 20071012001)					2	L	7	2 	4T			RT	BA15CAA 					 
2007110500071	20071105	00071	NE  	2007	11	5	CA071012002      	3	20071012	G	6111	6903A10	BLADE           	HAMSTD      	43E60583    	CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				405  		N196694					(CAN) DURING COMPLIENCE WITH AD 81-13-06R2 AND S/B 664 A CRACK WAS FOUND EMINATING FROM ONE OF THE BUSHING RETENTION SCR	EW HOLES. CRACK HAS BECOME LARGER DURING REWORK PROCEDURES RENDERING THE BLADE U/S. (TC NR 20071012002)					2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2008031900164	20080319	00164		2008	3	19	CA071012003      	2	20071009	G	7320	442324	HMU             	HONEYWELL   		BOMBDR	BD100 	BD1001A10   	1390044	GL  										ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA						118130					(CAN) PILOT REPORTED, THEY LINED UP FOR TAKEOFF WITH PASSENGERS ON BOARD. WHEN HE ADVANCED THE THROTTLES FOR TAKEOFF, TH	E RT ENGINE DID NOT COME OUT OF IDLE.  NO CAS MESSAGES. NO CURRENT FAULTS. NO CURRENT SERVICE MESSAGES.  ONCE BACK AT TH	E FBO PASSENGERS DEPLANED. THE PILOT STILL HAD THE RT ENG RUNNING. HE ADVANCED THE RT THROTTLE. AGAIN, NOTHING HAPPENED.	 SYS PARAMETERS SHOWED THE CORRECT TQA TLA. HE HIT THE EVENT BUTTON.  REMOVED RT ENGINE HMU AND INSTALLED A REPLACEMENT.	 OPS CHECK GOOD (TC NR 20071012003)		2	L	7	2 	4F			RT	T00005NY					 
2008012900050	20080129	00050	SO  	2008	1	29	CA071015001      	1	20070928	G	2560	010816811	SEAT BELT       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	COCKPIT	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA							317552130				(CAN) AFTER STARTUP THE CAPTAIN WENT TO ATTACH AND TENSION HIS LAPBELT. AT THAT POINT THE LAP BELT DISCONNECTED FROM THE	 SEAT. CLOSER INSPECTION SHOWED CORROSION IN THE AREA OF THE BOLT HOLE OF THE FEMALE SIDE. THE SEATS ARE PROVIDED WITH A	 COVER OVER THIS AREA FOR COSMETIC REASONS. IT MAKES THE AREA DIFFICULT TO INSPECT UNLESS THE BOLT IS REMOVED AND THE CO	VER ALSO REMOVED.  DURING FOLLOWUP INSPECTIONS WITH OTHER SEATS IN THIS AC, MORE CORROSION WAS FOUND ON THE ATTACHMENT B	RACKETS OF THE SEAT BELTS. IN ALL 3 SETS OF SEAT BELTS WERE REPLACED ON THE AIRCRAFT.  A FLEETWIDE INSPECTION OF SEAT BE	LTS IN THIS AREA IS BEING CARRIED OUT. AS WELL ALL COSMETIC COVERS THAT MAY INTERFERE WITH A PROPER INSPECTION HAVE BEEN	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2007110500072	20071105	00072	EA  	2007	11	5	CA071015002      	1	20071011	G	2750	855D10011	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FLAP SYSTEM	FAULTED         	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) EVENT OCCURRED AT GATE PUSHBACK, PREFLIGHT FLAP SELECTION. FLAP FAIL CAUTION ILLUMINATED WHEN SELECTED TO 20 DEGRE	ES. LT FLAPS SHOWING 2 DEGREES/RT SIDE SHOWING ZERO. BOTH FLAPS WERE PHYSICALLY AT 2 DEGREES. FAULT CODES SHOWED BPSU AT	 FAULT. DURING REPLACEMENT WAS ALSO FOUND THE FLAP DRIVE SHEARED. BOTH PARTS REPLACED AND RIGGED. FLAP SYSTEM TEST COMPL	ETED WITH NO FURTHER FAULT NOTED. SYSTEMS CHECKS SERVICEABLE. (TC NR 20071015002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2007110500073	20071105	00073	NM  	2007	11	5	CA071015003      	1	20071015	G	5720		BRACKET         			DHAV  	DHC8  	DHC8102     	2809003	NM  										SPOILER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ACCOMPLISHEMENT OF A PRE CHECK, A SPACE WAS OBSERVED BETWEEN THE SPOILER ACTUATOR AND THE SPOILER ACTUA	TOR BRACKET.   FURTHER INVESTIGATION FOUND THAT THE BRACKET WAS CRACKED. (TC NR 20071015003)					2	H	7	2 	4T			RT	A13NM   					 
2007110500074	20071105	00074	GL  	2007	11	5	CA071015004      	2	20071012	G	7323		SPLINE          	RROYCE      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					GOVERNOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				1844 		22451					(CAN) PILOT COMPLAINED OF EXCESSIVE (ROTOR) DROOPING. CHECKED AIRCRAFT RIGGING AND LOOSE ENGINE AIR LINES. REMOVED GOVER	NOR FOR BLEED CLEANING AND THE DRIVE ASSY ON THE GOVERNOR WAS COMPLETELY DISCONNECTED FROM THE PT GOVERNOR. COMPONENT WA	S SHIPPED FOR FURTHER ANALYSIS. (TC NR 20071015004)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2008012900051	20080129	00051	NE  	2008	1	29	CA071015005      	2	20071012	G	7420	CH5339906	IGNITION LEAD   			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A FUEL NOZZLE REPLACEMENT, FOUND A DAMAGED INSULATOR ON THE IGNITER END OF THE IGNITION LEAD. R	EPLACED IGNITION LEAD AND TESTED SERVICEABLE. (TC NR 20071015005)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008012900052	20080129	00052	GL  	2008	1	29	CA071015006      	2	20070920	G	7321	23065104	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	OUT OF ADJUST   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								CAE832736			(CAN) FCU SN 304536 REMOVED FOR OVERHAUL(RUNNING NORMAL)FCU SN 308210 TSO 0 INSTALLED (FROM SAE)AND REQUIRED MAXIMUM ADJ	USTMENTS,START DERICH AND START ACCEL.TO GET ENGINE TO START.  AFTER 7.3HRS, OUR AME DEEMED IT NECESSARY TO CHANGE IT FO	R A BETTER ONE. A LOANER FCU WAS RECEIVED AND SN 308210 WAS REMOVED AND SN 87041003 WAS INSTALLED AGAIN FROM SAE. THIS U	NIT WOULD NOT EVEN START THE AC EVEN AFTER ALL ADJUSTMENTS. ANOTHER FCU WAS RECEIVED FROM ESSENTIAL TURBINES SN BR54951 	AND IT WAS INSTALLED WHICH STARTED NORMALLY WITH LITTLE ADJUSTMENT.  NEEDS TO CHECK ITS FLOW BENCH FOR CALIBRATION. (TC 	NR 20071015006)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2007110500075	20071105	00075	NE  	2007	11	5	CA071016001      	2	20070831	G	7250		TURBINE BLADES  			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											(CAN) FOLLOWING TAKEOFF, THE ENGINE EMITTED A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRA	CTURED POWER TURBINE BLADES. ASSOCIATED FRACTURE OF THE EXHAUST DUCT CLAMP RESULTED IN EXHAUST IMPINGING ON THE LANDING 	GEAR STRUT IN THE AIRCRAFT WHEELWELL, TRIGGERING A FIRE WARNING INDICATION.  MFG WILL INVESTIGATE THE EVENT AND ADVISE O	F ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016001)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2007110500084	20071105	00084	NE  	2007	11	5	CA071016002      	2	20070902	G	7200		ENGINE          			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  						DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								120891			(CAN) ENGINE TORQUE AND OIL PRESSURE WERE SEEN TO FLUCTUATE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION	 REVEALED INTERNAL ENGINE DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071	016002)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007110500085	20071105	00085	NE  	2007	11	5	CA071016003      	2	20070905	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	E	J	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) IN CRUISE, THE ENGINE EMITTED A NOISE ACCOMPANIED BY VIBRATION AND A COMPLETE LOSS OF POWER. THE AIRCRAFT CRASHED 	DURING FORCED LANDING.  WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016003)					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007110500086	20071105	00086	NE  	2007	11	5	CA071016004      	2	20070620	G	7200		ENGINE          			AYRES 	S2    	S2RT15RESTD 	       	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  						POWER LOSS      	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AG	AGRICULTURE    	1			CA								56068			(CAN) DURING SPRAYING OPERATIONS, THE ENGINE LOST POWER AND THE AIRCRAFT SUBSEQUENTLY CRASHED. MFG WILL INVESTIGATE THE 	INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016004)					1	L	7	1 	3T	4	T		A4SW    	E4EA				 
2007110500087	20071105	00087		2007	11	5	CA071016005      	4	20070906	G	8300		GEARBOX         			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE POWER SECTION CHIP DETECTOR ACTIVATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED M	ETAL DEBRIS IN THE ACCESSORY GEARBOX.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 	20071016005)				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2007110500088	20071105	00088	NE  	2007	11	5	CA071016006      	2	20070802	G	7250		TURBINE BLADES  			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE AND THE TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED DAMAGE	D POWER TURBINE BLADES. (TC NR 20071016006)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2008012900053	20080129	00053	NE  	2008	1	29	CA071016007      	2	20070908	G	7250	311608001	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  	PWA   	PW206 	PW206A      	 	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE ENGINE CHIP DETECTOR ACTIVATED, ACCOMPANIED BY VIBRATION AND A TEMPERATURE INCREASE, AND THE ENGINE WAS SHUTDO	WN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A DAMAGED NR3 BEARING AND RESULTANT TURBOMACHINERY DAMAGE. (TC NR 200710	16007)				1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2007110500089	20071105	00089	NM  	2007	11	5	CA071016008      	1	20070906	G	2421		ADAPTER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GEARBOX	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF ENGINE OIL PRESSURE WAS LOST AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED 	A LEAKING GENERATOR MOUNTING PAD ADAPTER. (TC NR 20071016008)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2007110500090	20071105	00090	EU  	2007	11	5	CA071016009      	1	20070828	G	6123		AUTOFEATHER SYS 			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  						FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE PROPELLER FEATHERED UNCOMMANDED AND RECOVERED. SUBSEQUENT INSPECTION REVEALED A FAULTY AUTOFEATHE	R UNIT.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007110500096	20071105	00096	NE  	2007	11	5	CA071016010      	2	20070911	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								PC0605			(CAN) FOLLOWING TAKEOFF THE ENGINE LOST POWER. THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING.						1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007110500097	20071105	00097	NE  	2007	11	5	CA071016011      	2	20070831	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								PC0643			(CAN) THE ENGINE LOST POWER FOLLOWING TAKEOFF AND THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING.						1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2007110500098	20071105	00098	NE  	2007	11	5	CA071016012      	2	20070915	G	7200		ENGINE          			AEROSP	ATR72 	ATR72202    	8680940	EU  	PWA   	PW120 	PW124B      	 	NE  						MAKING METAL    	W				A				UNSCHED LANDING         				X	B	J	ENGINE FLAMEOUT           	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA								124371			(CAN) DURING CLIMB THE ENGINE FLAMED OUT AND OIL SMELL WAS EVIDENT IN THE CABIN. SUBSEQUENT INSPECTION REVEALED METAL DE	BRIS IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016012)					2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2007110500099	20071105	00099	NE  	2007	11	5	CA071016013      	2	20070914	G	7200		ENGINE          			AIRTRC	AT602 	AT602       	0390309	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								PN0060			(CAN) THE ENGINE LOST POWER IN FLIGHT AND THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING. MFG WILL INVESTIGATE	 THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016013)					1	L	7	1 	3T	4	T	NC	A19SW   	E4EA				 
2007110500100	20071105	00100	EU  	2007	11	5	CA071016014      	1	20070831	G	7931	310573401	REGULATOR VALVE 			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  					ENGINE OIL PRESS	FAULTY          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALE	D A FAULTY OIL PRESSURE REGULATING VALVE. (TC NR 20071016014)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2007110500101	20071105	00101	NE  	2007	11	5	CA071016015      	2	20070917	G	7200		ENGINE          			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			FF	FIRE FIGHTING  	1			CA											(CAN) THE ENGINE LOST POWER DURING FIREFIGHTING OPERATIONS RESULTING IN A FORCED LANDING.						1	L	7	1 	3T	4	T	NC	A19SW   	E4EA				 
2007110500106	20071105	00106	EA  	2007	11	5	CA071016016      	2	20070820	G	7200		ENGINE          			AIRTRC	AT400 	AT401       	0390204	SW  	PWA   	PT6   	PT6A34      	52043	EA  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AG	AGRICULTURE    	1			CA											(CAN) DURING SPRAYING OPERATIONS THE ENGINE EMITTED A LOUD NOISE AND LOST POWER, RESULTING IN A FORCED LANDING.						1	L	7	1 	3R	4	T		A17SW   	E4EA				 
2007110500116	20071105	00116	NE  	2007	11	5	CA071016017      	2	20070925	G	7240		LINER           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					COMBUST CHAMBER	DAMAGED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) THE ENGINE WAS REPORTED TO HAVE REPEATEDLY FLAMED OUT DURING TAXI OPERATIONS. INSPECTION REVEALED A DAMAGED/WORN C	OMBUSTION CHAMBER LINER. (TC NR 20071016017)					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007110500117	20071105	00117	EA  	2007	11	5	CA071016018      	2	20070927	G	7250		TURBINE BLADES  			PILATS	PC6   	PC6         	7090102	EU  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	FRACTURED       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING AIRCRAFT STALL RECOVERY TRAINING, THE ENGINE FLAMED OUT. SUBSEQUENT RE-LIGHT ATTEMPTS WERE UNSUCCESSFUL. IN	SPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES. (TC NR 20071016018)					1	H	7	1 	3O	4	T		7A15    	E4EA				 
2008012900055	20080129	00055	NE  	2008	1	29	CA071016020      	1	20071014	G	2820	7630700701041	HOSE            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL DIST	COLLAPSED       	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) FUEL HOSE INTERNAL COLLAPSE (TC NR 20071016020)						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2008012900067	20080129	00067	EU  	2008	1	29	CA071016021      	1	20071016	G	2810	257PV6589A	FLOAT VALVE     			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					VENTRAL TANK	STUCK           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			6452 			DHB97					(CAN) DURING REFUELLING USING SINGLE-POINT SYS & FILLING BOTH MAIN (WINGS) & VENTRAL TANK. AS VENTRAL TANK REACHED 1.5 T	O 3 QUARTERS CAPACITY FUEL WOULD FLOW THROUGH VENT SYS INTO LT SURGE TANK & SHUTDOWN BY CLOSING MAIN VALVE. COMPLETION O	F REFUELLING COULD ONLY RESUME ONCE SURGE TANK EMPTIED & VENTRAL TANK FUELED VIA FUELING CAP. ON REMOVAL OF VENTRAL TANK	, DISCOVERED RT VENT FLOAT INADVERTENTLY GLUED TO VALVE BODY & NEEDLE HARD TO OPERATE. BOTH CONDITIONS LEFT RT VENT VALV	E OPEN DURING ALL CONDITIONS CAUSING FUEL TO ENTER VENT PIPING THOUGH NONE EXISTED.  FLOAT REMOVED & NEW NEEDLE INSTALLE	D, OPS OF VALVE CHECKED FOR SMOOTHNESS & PROPER SEALING OF NEEDLE TO SEAT. MODIFICATION (25G137A) EMBODIED TO INCORPORAT	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007110500118	20071105	00118	GL  	2007	11	5	CA071017001      	1	20071016	G	2434	A3579101	GENERATOR       			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					RIGHT	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			330  								(CAN) IN CRUISE FLIGHT RT GENERATOR FAILED. AFTER FOLLOWING PROCEDURES A/C LANDED WITHOUT ANY MORE INCIDENT. TROUBLESHOO	TING WITH MDC REPORTED PCB6 AT FAULT FROM GCU P/N R608-003. FURTHER TROUBLESHOOTING REVEALED RT GENERATOR WAS AT FAULT N	OT THE GCU. GENERATOR WAS REMOVED AND REPLACED AND A/C RETURNED TO SERVICE. NORMAL TBO FOR GENERATOR IS 3000 HRS GENERAT	OR HAD ONLY 329.7 HRS. MANUFACTURER OF GENERATOR IS AUXILEC (F0296) TAKEN ON DATA PLATE. (TC NR20071017001)			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
2008030600177	20080306	00177	EA  	2008	3	6	CA071017002      	1	20071017	G	2810	21564002	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			1893 								(CAN) FUEL LEAK ON BOTTOM OF FUEL CELL NR 5 LT.    (TC NR 20071017002)						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008030600178	20080306	00178	EA  	2008	3	6	CA071017003      	2	20071012	G	7414	104001667	IMPULSE COUPLING	CONT        							LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			671  			G05KA029R					(CAN) IMPULSE CAM ASSEMBLY FOUND CRACKED AT KEY WAY AREA. REPLACED WITH NEW ASSY. (TC NR 20071017003)											3	O			E274				 
2007110500119	20071105	00119	SO  	2007	11	5	CA071018001      	2	20071016	G	8500	IO240B	ENGINE          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  		STALLED         	W				O				OTHER                   				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA			979  				C0416				(CAN) DURING POWER ON STALL THE PROPELLER CAME TO A FULL STOP, THROTTLE WAS AT 1700 RPM AND THE NOSE POINTED UP FOR A ST	ALL CONFIGURATION AND ON POWER APPLICATION THE ENGINE CAME TO A FULL STOP. THE AIRCRAFT WAS THEN POINTED NOSE DOWN, THE 	PROPELLER STARTED WIND MILLING AND ON THROTTLE APPLICATION THE ENGINE RE-STARTED.  A/C RETURNED TO BASE WITH NO PROBLEM.	 THIS WAS A NEW RETROFIT EQUIPPED A/C WITH A COMPLETE -54 ENGINE CONFIGURATION. MFG WERE INFORMED AND THE COMPONENTS ARE	 SCHEDULED TO BE TESTED AND REMOVED BY MFG AT THE END OF THIS WEEK. (TC NR 20071018001)		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2008013100051	20080131	00051	SW  	2008	1	31	CA071018003      	1	20071017	G	2911	223003	ACCUMULATOR     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACCUMULATOR WAS REMOVED FOR TROUBLESHOOTING HYDRAULIC LEAKS IN SYSTEM. IT WAS SUSPECTED THAT THE ACCUMULATOR WAS N	OT DOING ITS JOB OF ABSORBING THE HYDRAULIC SHOCKS. UPON REMOVAL IT WAS NOTED THAT THE INTERNAL PISTON WAS INSTALLED BAC	KWARDS. THE -3 ACCUMULATOR DOES NOT SHOW UP IN THE PRESENT IPC. THE ACCUMULATOR WAS INSTALLED IN 2002 AND CAME INTO INVE	NTORY IN 1999 AND WAS CERTIFIED IN 1997. (TC NR 20071018003)			2	L	7	2 	4T	3	T	RT	A8SW    	E2WE	6	C	3PNE	 
2008012900068	20080129	00068	EA  	2008	1	29	CA071018004      	1	20071015	G	5510	C6FSM181421	ADAPTER         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  						MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA		57RF	18455				688				(CAN)   WHILE REMOVING ATTACHMENT ADAPTER P/N C6FSM1814-21, IT WAS NOTED THAT THE RIVETS INSTALLED IN THE VERTICAL WEBS 	TO ADAPTER WERE THE INCORRECT TYPE. THE RIVETS REMOVED FROM THIS ADAPTER PLATE WERE A.D. RIVETS. THE CORRECT RIVET WOULD	 HAVE BEEN D.D.  ADAPTER SHOWS SIGNS OF FRETTING CORROSION CAUSED BY SLIGHT MOVEMENT.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2008012900069	20080129	00069	WP  	2008	1	29	CA071019001      	1	20071017	G	6520	B5631	SIGHT GLASS     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TAIL ROTOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			818  								(CAN) DURING INSPECTION, IT WAS NOTED THAT THERE WAS FLUID LEAKING AROUND THE TAIL ROTOR GEARBOX SIGHT GLASS. THE PART W	AS REMOVED AND REPLACED WITH A NEW PART. IT WAS FURTHER EXAMINED AND NOTED THE GLASS COULD ROTATE IN THE HOUSING, NO LON	GER SECURE ALLOWING FLUID TO BYPASS AND LEAKING. THERE IS NO ISSUE OF THE GLASS DEPARTING THE AIRCRAFT AND POSSIBLY STRI	KING THE T/R BLADES. (TC NR 20071019001)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008012900070	20080129	00070	CE  	2008	1	29	CA071019002      	1	20071019	G	5740	NAS680A08	NUT PLATE       			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	FUEL TANK BAYS	MISREPAIRED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTING THE FUEL TANKS, FOUND SEVERAL NUTPLATES PREVIOUSLY DAMAGED. UPON FURTHER INSPECTION FOUND THAT AT 	A PREVIOUS TIME, SOME SCREWS BROKE OFF IN THE NUTPLATES AND RATHER REPAIR/REPLACE THE NUTPLATES, IT APPEARS THE DAMAGED 	NUTPLATES WERE DRILLED AND SHEET METAL SCREWS WERE INSTALLED WHERE STRUCTURAL SCREWS SHOULD HAVE BEEN. THE REPAIR WAS SI	MPLE, DRILL OUT THE OLD NUTPLATES AND NEW NUTPLATES INSTALLED. AS THE FUEL TANK COVERS ARE A STRUCTURAL PART OF THE WING	 I RECOMEND KEEPING THIS AREA IN GOOD REPAIR. (TC# 20071019002)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2008030600179	20080306	00179	NE  	2008	3	6	CA071019003      	2	20071013	G	7314	C8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX FUEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1122 								(CAN) DURING AN ATTEMPTED START UP THE AIRCRAFT FAILED TO START. IT WAS FOUND THAT THE AUXILIARY FUEL PUMP HAD FAILED. P	UMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071019003)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008030600180	20080306	00180	NE  	2008	3	6	CA071019004      	2	20070712	G	7250		TURBINE BLADES  			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       	 	NE  					ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ENGINE FLAMEOUT OUT IN CLIMB. RELIGHT ATTEMPT WAS UNSUCCESSFUL. SUBSEQUENT INSPECTION REVEALED FRACTURED TOWERSHAF	T AND DAMAGED POWER TURBINE BLADES. (TC NR 20071019004)					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2008030600181	20080306	00181	NE  	2008	3	6	CA071022001      	2	20071019	G	7320	22852402115	TUBE            			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A2     	30067	NE  					FUEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5991 								(CAN) DURING POWER PLANT BUILD UP, FOUND LINE P/N 228-52402-115 FOR PYLON STATIC PRESSURE TO FCU CRACKED AT MIDDLE. THE 	CRACK WAS HIDDEN BY A LINE IDENTIFICATION DECAL. LINE WAS REMOVED AND REPLACED AIRCRAFT WILL BE RETURNED TO SERVICE. (TC	 NR 20071022001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600182	20080306	00182	EA  	2008	3	6	CA071022002      	2	20071009	G	8520	LW10292	IDLER GEAR      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	GEAR SHAFT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6311 	1154 				L41868A			(CAN) DURING A SCHEDULED INSP OF THE ENGINE, THE OIL FILTER WAS REMOVED AND DISASSEMBLED. IT WAS NOTED THAT THE FILTER M	EDIA CONTAINED AN ABNORMAL AMOUNT OF METAL. THE AIRCRAFT WAS FLOWN AN ADDITIONAL 10 HRS AND THE FILTER WAS AGAIN INSPECT	ED. UPON INSPECTION THE FILTER CONTAINED AN ABNORMAL AMOUNT OF METAL AND AS A RESULT THE ENGINE WAS REMOVED AND SENT TO 	AN OVERHAUL FACILITY. THE OVERHAUL FACILITY FOUND THE CRANKSHAFT IDLER GEAR HAD EXCESSIVE PLAY AND WAS CAUSING WEAR ON T	HE IDLER GEAR BUSHING. THE BUSHING GEAR WAS REPLACED AND ENGINE REASSEMBLED. (TC NR 20071022002)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008030600183	20080306	00183	WP  	2008	3	6	CA071022003      	1	20070930	G	8011	14924HTH	STARTER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			202  	202  							(CAN) REMOVED DUE TO CRACKED BASE. (TC NR 20071022003)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008012900071	20080129	00071	NE  	2008	1	29	CA071022004      	2	20071018	G	7320		SWITCH          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					HMU	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA		CGSGH	1275 	1275 							(CAN) DURING GROUND RUN THE FORCED IDLE FUNCTION OF THE TWIST GRIP WAS BEING TESTED WHEN IT WAS OBSERVED TO NOT ACCELERA	TE BACK TO FLIGHT IDLE WHEN RETURNED TO THE (VOL) POSITION. THIS FUNCTION IS USED TO SIMULATE ENGINE FAILURE DURING PRAC	TICE AUTOROTATION. SUCCESSIVE ATTEMPTS OF ROLLING THE THROTTLE FROM (VOL) TO (MIN) TO (VOL) PRODUCED ERRATIC RESULTS, TH	E ENGINE EITHER STAGNATED AT IDLE NG OR WAS SLOW TO RESPOND BACK TO FLIGHT IDLE, (NO ERROR CODES WERE RECORDED ON THE VE	MD). THE FORCED IDLE MICRO SWITCH WAS TESTED IAW MFG ALERT SB NR 05.00.49, NO ANOMALIES WERE FOUND. THE SWITCH IN QUESTI	ON PN DHS772-400.30 WAS REPLACED AS A TROUBLESHOOTING MEASURE. MFG MANDATORY SB A292 73 2814, INSPECTION AND LUBRICATION	1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008012900072	20080129	00072	SW  	2008	1	29	CA071022005      	1	20071018	G	3220	7500761	BOLT            			GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R306	R306382F7   	GL  	DRAG BRACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6654 	6654 							(CAN) DURING DISASSEMBLY OF NOSE LANDING GEAR FOR ITS 5 YEAR INSPECTION/OVERHAUL, BOLT P/N 750076-1 OF THE NOSE LANDING 	GEAR DRAG BRACE-NOSE LANDING GEAR STRUT WAS FOUND BENT WITH VISIBLE CRACK. CRACK WAS CONFIRMED BY NDT(LPI AND MPI). THIS	 WAS THE AIRCRAFTS FIRST OVERHAUL OF ITS LANDING GEAR SINCE COMPANY PURCHASED AIRCRAFT 2 YEARS AGO. RECORDS CHECK INDIC	ATED MINIMAL PARTS REPLACEMENT DURING PREVIOUS 5 YEAR OVERHAULS (TC NR 20071022005)			1	H	7	2 	4T	4	T		2A4     	E4WE	6	C	P8EU	 
2008012900073	20080129	00073	EU  	2008	1	29	CA071022006      	1	20071003	G	6320	6894171	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR1 ENGINE	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			6479 	3017 							(CAN) APPROXIMATELY 5 MILES FROM AIRPORT, MAGI NR1 LIGHT ILLUMINATED. PULSED OFF AND 2 MINUTES LATER LIGHT ILLUMINATED A	GAIN. AN EMERGENCY LANDING WAS CARRIED OUT. BOTH NR1 AND NR2 MAGNETIC PLUGS CHECKED AND FOUND CONTAMINATED WITH METAL. T	HE GEARBOX WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TIC NR 20071022006)				1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2008013100052	20080131	00052	WP  	2008	1	31	CA071022007      	1	20070909	G	6310	C0183	CLUTCH          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	SLIPPED         	W				A				UNSCHED LANDING         				L			NO TEST                   			CL	CLIMB          	1			CA			1864 	1864 							(CAN) CLUTCH REMOVED DUE TO PROBLEMS AT HIGH POWER SETTINGS. POSSIBLE CLUTCH SLIPPAGE. (TC NR 20071022007)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100053	20080131	00053	NE  	2008	1	31	CA071022008      	2	20071009	G	7322	25766304	ARM             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL CONTROL	BINDING         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			1470 	1470 							(CAN) INTERMITTENT ROTOR DROOP. FOUND BINDING ARM ON FUEL CONTROL CAUSING ERRATIC GOVERNOR OPERATION. (TC NR 20071022008	)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100055	20080131	00055	WP  	2008	1	31	CA071022009      	1	20070912	G	2913		LINE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYD PUMP	LEAKING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			301  	301  		0814					(CAN) PUMP REPLACED DURING TROUBLESHOOTING SMALL LEAK AT SPLIT LINE ON PUMP. (TC NR 20071022009)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100057	20080131	00057	WP  	2008	1	31	CA071022010      	1	20070912	G	2916	D2112	RESERVOIR       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYD SYSTEM	VENTING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			362  	362  							(CAN) HYDRAULIC RESERVOIR VENTING. (TC NR 20071022010)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100059	20080131	00059	EA  	2008	1	31	CA071022011      	2	20071019	G	7200		ENGINE          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RIGHT	MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA				1765 				PCE51107			(CAN) RT ENGINE CHIP DETECTOR LIGHT CAME ON IN FLIGHT SO WE SHUTDOWN THE RT ENGINE.  ENGINE BEING REMOVED AND SENT TO EN	GINE O/H FACILITY FOR REPAIR. LOANER ENGINE TO BE INSTALLED. (TC NR 20071022011)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2007110500120	20071105	00120	GL  	2007	11	5	CA071022012      	1	20071022	G	5511	C2TP57	SPAR            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4200 								(CAN) STAB SPAR FOUND CRACKED IAW AWD CF-1991-42R1 S.B 2/47. INSPECTED IAW PEN REQUIREMENTS, SPAR CRACKED ABOVE BOTH FWD	 ATTACH BRACKETS. ALL SPAR MODS C/W 4200HRS AGO ALONG WITH A NEW VIKING SPAR. (1992). CRACKS ABOUT .7500 INCH LENGTH RUN	NING HORIZONTALLY .2500 ABOVE TOP ATTACH BOLTS, NOT IN RADIUS OF SPAR. VIKING NOTIFIED OF CRACKS IAW SB. (TC NR 20071022	012)			1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P736	 
2008030600199	20080306	00199	SW  	2008	3	6	CA071023001      	1	20071022	G	7931		OIL SYSTEM      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LOW PRESSURE    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE821945F			(CAN) LOSS OF ENGINE OIL PRESSURE IN FLIGHT. ENGINE WILL BE REMOVED AND SENT FOR INVESTIGATION. (TC NR 20071023001)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900074	20080129	00074	SW  	2008	1	29	CA071023002      	1	20071022	G	6230	206040078103	NUT             	BELL        		BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					MAST ASSY	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			620  								(CAN) WHILE INVESTIGATING MAST BEARING PLAY. UNABLE TO REMOVE NUT (BEARING TORQUED). MAST ASSY SENT TO MFG FOR INVESTIGA	TION. NEW MAST ASSY PROVIDED BY MFG (TC NR 20071023002).					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2008012900075	20080129	00075	CE  	2008	1	29	CA071023003      	1	20071015	G	2750	1013800005	CABLE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT FLAP DRIVE	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			6577 								(CAN) ON APPROACH , PILOTS SELECTED APPROACH FLAP. FLAPS STOPPED MOVING JUST PRIOR TO 17 DEGREES APPROACH FLAP POSITION.	 THE FLAP ASYMMETRY SWITCH WAS ACTIVATED. UPON INSPECTION THE LT OB FLAP DRIVE CABLE WAS CEASED. THE FLAP DRIVE CABLE WA	S REMOVED AND REPLACED WITH A SERVICEABLE UNIT. FURTHER INSPECTION OF THE CABLE REVEALED IT WAS SHEARED AT APPROXIMATELY	 85 INCHES OB OF FLAP MOTOR AND TRANSMISSION ASSEMBLY. EVIDENCE OF CORROSION AND MOISTURE WERE FOUND IN THE FLAP DRIVE S	HEATHING AND CABLE WHICH LIKELY CONTRIBUTED TO THE CABLE FAILURE. (TC NR 20071023003)		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008012900076	20080129	00076	SW  	2008	1	29	CA071023004      	1	20071022	G	6230	206040078103	NUT             	BELL        		BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					MAST BEARING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			620  			52351					(CAN) WHILE INVESTIGATION MAST BEARING PLAY, UNABLE TO REMOVE NUT (BEARING TORQUE). MAST ASSEMBLY SENT TO MFG FOR INVEST	IGATION. NEW MAST ASSEMBLY PROVIDED BY MFG. (TC NR 20071023004)					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2008012900077	20080129	00077	SW  	2008	1	29	CA071023005      	1	20071022	G	7931		OIL SYSTEM      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LOW PRESSURE    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE821945F			(CAN) LOSS OF ENGINE OIL PRESSURE IN FLIGHT. ENGINE WILL BE REMOVED AND SENT FOR INVESTIGATION. (TC NR 20071023005)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900078	20080129	00078	EU  	2008	1	29	CA071023006      	1	20071003	G	6320	6894171	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 ENGINE	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			6473 	3017 							(CAN) APPROXIMATELY 5 MILES FROM DESTINATION, MAG NR1 LIGHT ILLUMINATED. PULSED OFF AND 2 MINUTES LATER LIGHT BACK ON. N	R1 THROTTLE ROTATED TO IDLE, CONTINUED APPROACH TO DESTINATION, CRASH TRUCK ADVISED. ON FINAL,  NR1 THROTTLE ADVANCED AN	D NORMAL LANDING CARRIED OUT. ENGINE SHUTDOWN AND MAINTENANCE ADVISED. UPON INSPECTION OF UPPER MAG PLUG, 7 SLIVERS OF M	ETAL WERE FOUND AND THE LOWER PLUG WAS COVERED WITH MANY PARTICLES AND FUZZ. THE ESCAPED OIL WAS CAPTURED AND METAL PART	ICLES WERE VISIBLE IN THE OIL. OIL TANK DRAINED, N1 CAP FILTER REPLACED, GEARBOX OIL FILTER INSPECTED AND SCAVEMGE LINE 	FLUSHED. GEARBOX REPLACE WITH OVERHAULED UNIT (TC NR 20071023006)	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2008030600200	20080306	00200	SO  	2008	3	6	CA071023007      	1	20071022	G	3710	441CC7	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	VACUUM SYS	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				473  							(CAN) WHILE PERFORMING AN COMPRESSION TEST, THE ENGINEER HEARD A SQUEAKING AS THE PROP WAS BEING ROTATED. THE SOURCE WAS	 INDENTIFED COMING FROM THE VACUUM PUMP. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071023007)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008030600201	20080306	00201	SW  	2008	3	6	CA071023008      	1	20071022	G	6420	206010743013	MECHANISM       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					PITCH CHANGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE TAIL ROTOR PITCH CHANGE MECHANISM PORTION OF THE 100 HOUR INSP, THE PITCH CONTROL TUBE BUSHING AND/OR B	EARING WERE FOUND WORN BEYOND LIMITS ON THE CONTROL TUBE ASSY.  AN EXHAUSTIVE CHECK OF PAPER WORK WAS CARRIED OUT FOR TH	E TSN AND TSO, THESE COULD NOT BE CONFIRMED. THE PITCH CHANGE MECHANISM HAS PASSED INSPECTION ON THE LAST (2) 600 HOUR I	NSPECTIONS. (TC NR 20071023008)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008030600202	20080306	00202	EA  	2008	3	6	CA071024001      	1	20071021	G	2750	855D10011	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THE AC SUFFERED FROM (2) SIMILAR FLAP PROBLEMS IN A SHORT PERIOD OF TIME.  THE 1ST OCCURRENCE HAPPENED ON OCTOBER 	20TH 2007. THE CREW REPORTED A FLAP FAIL CAUTION MESSAGE AFTER TAKEOFF WHEN FLAPS WERE SELECTED UP. THE AC TURNED BACK A	ND LANDED SAFELY. THE CREW COMPLETED A VISUAL INSP OF THE FLAPS, THE SYS WAS RESET AND SEVERAL CYCLES COMPLETED. UPON DE	STINATION, THE FAULT CODES WERE DOWNLOADED AND THE SYS CHECKED SERVICEABLE BY MAINT.  ON OCTOBER 21ST, CREW REPORTED A F	LAP FAIL CAUTION MESSAGE AFTER TAKEOFF. THE EICAS SECONDARY DISPLAY FLIGHT CONTROLS PAGE WAS INDICATING LT FLAP POSITION	 AT 6 DEGREES AND RT AT 8 DEGREES. THE FLIGHT CREW ELECTED TO CONTINUE THE FLIGHT AND LANDED WITHOUT INCIDENT AT DESTINA	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600203	20080306	00203	SW  	2008	3	6	CA071024002      	1	20071019	G	6310	CL422501	CLUTCH          	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FREEWHEEL UNIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			1045 			BLA20067					(CAN) THE A/C HAD A FREEWHEEL CHIP LIGHT AND LANDED AT MAIN BASE, AFTER DOING THE 2 MINUTE COOLDOWN THE ENGINE WAS SHUTD	OWN. WHILE SPOOLING DOWN A NOISE WAS NOTICED THAT WAS NOT NORMAL. THE FREEWHEEL WAS REMOVED AND DISASSEMBLED. THE CLUTCH	 CAGE WAS FOUND CRACKED ON ONE SIDE AND THE INNER SHAFT HAD BRINNELLING MARKS. THESE ITEMS HAVE BEEN SCRAPPED. (TC NR 20	071024002)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900079	20080129	00079	NE  	2008	1	29	CA071024003      	2	20071023	G	7314		DIAPHRAGM       	LYC         		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL PUMP	TORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1215 	1215 		3803					(CAN) FUEL PUMP CHANGED DUE TO EXTERNAL OIL LEAKAGE. THIS USER HAS HAD 14 OF THESE FUEL PUMPS FAIL OVER THE LAST 8 MONTH	S. THIS WAS THE FIRST PUMP DIASSEMBLED. IT WAS QUITE EVIDENT THAT THE UPPER DIAPHRAM HAD RUPTURED. THE SIDE OF UPPER DIA	PHRAM MATERIAL EXPOSED TO THE ENGINE OIL SHOWED A DEFINITE INDICATION OF DETERIORATION AND THE RUBBER MATERIAL BREAKING 	DOWN. WHEREAS THE MATERIAL ON THE FUEL SIDE SHOWS NO DETERIORATION, EXCEPT WHERE THE DIAPHRAM HAD TORN. THIS LEADS US TO	 WONDER IF THE FUEL COMPATIBLE DIAPHRAM MATERIAL IS NOT COMPATIBLE WITH THE W80 ENGINE OIL USED. (TC NR 20071024003)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008012900080	20080129	00080	NM  	2008	1	29	CA071024004      	1	20071023	G	2910	82920010265	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SELECTOR VALVE	SEVERED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE NR 2 HYDRAULIC ISOLATION VALVE CAUTION LIGHT ILLUMINATED APPROXIMATELY 27 NAUTICAL MILES AFTER TAKEOFF. SHORLT	Y FOLLOWING THIS, THE NR2 SYSTEM HYDRAULIC FLUID DEPLETED. THE CREW CARRIED OUT THE APPLICABLE QRH PROCEDURES AND RETURN	ED TO BASE. MAINTENANCE FOUND A SEVERED HYDRAULIC TUBE AT THE LANDING GEAR SELECTOR VALVE. THE HYDRAULIC TUBE WAS REPLAC	ED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20071024004)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008012900081	20080129	00081	SW  	2008	1	29	CA071024005      	1	20071023	G	6730	41103750017	SERVO           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HYDRAULIC SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1695 								(CAN) PLAY NOTED IN CYCLIC CONTROL. ONCE INVESTIGATED THE PILOT VALVE LINKAGE ON RT CYCLIC SERVO FOUND WORN BEYOND LIMIT	S. (TC NR 20071024005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900082	20080129	00082	GL  	2008	1	29	CA071024006      	1	20071004	G	2823	PV332010	SHUTOFF VALVE   			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			10229								(CAN) STRONG FUEL ODOR IN COCKPIT. INVESTIGATED AND FOUND FUEL SHUTOFF VALVE WAS LEAKING. OVERHAULED PN PV3320-10 INSTAL	LED AND SYSTEM CHECKED FOR LEAKS. AIRCRAFT SERVICEABLE. (TC NR 20071024006)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2008012900083	20080129	00083	NE  	2008	1	29	CA071024007      	1	20071022	G	3340	50316	BEACON          			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TS 	CT78A       	30136	NE  						FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FERRY FLIGHT (CRASH POSITION INDICATOR) DEPARTED AIRCRAFT FOR NO APPARENT REASON. UNIT DID NOT TRANSMIT.  T	HE DEPLOYABLE BEACON WAS INSTALLED IAW MFG DWG NR 92604-40331. (TC NR 20071024007)					2	G	7	2 	4U	4	U		R00024BO	E8NE				 
2008012900084	20080129	00084	NE  	2008	1	29	CA071024008      	2	20071004	G	7200		ENGINE          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  						FAILED          	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								93447			(CAN) AT FL260, ITT INCREASED TO NEAR MAXIMUM. POWER WAS REDUCED TO FLIGHT IDLE HOWEVER ITT REMAINED HIGH. HEAVY SMOKE W	AS OBSERVED COMING FROM EXHAUST. CREW ELECTED TO SHUTDOWN ENGINE AND PERFORM SINGLE ENGINE LANDING. POST FLIGHT INSPECTI	ON REVEALED OIL DRIPPING FROM EXHAUST AND SEIZED PROPELLER SHAFT.   MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CA	USE ONCE ESTABLISHED.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008012900085	20080129	00085	EU  	2008	1	29	CA071024009      	1	20071013	G	3246	MS2125006038	TIE BOLT        			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	MLG WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				398  		CAA10					(CAN) MAINTENANCE CREWS NOTED A BROKEN MAIN WHEEL TIE BOLT. THE MAIN WHEEL ASSEMBLY AND BRAKE ASSEMBLY WERE REPLACED. (T	C NR 20071024009)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008012900086	20080129	00086	CE  	2008	1	29	CA071024010      	1	20071021	G	3210	50810323	TORQUE KNEE     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	LANDING GEAR	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) AFTER LANDING, UPON DECELERATING THROUGH 60 KIAS THE AIRCRAFT BEGAN TO VIOLENTLY SHAKE, SHUDDER AND APPEAR TO SKIP	 WHILE VEERING TOWARD THE LT SIDE OF THE RUNWAY. CONTROL WAS MAINTAINED AND THE AIRCRAFT WAS BROUGHT TO A SLOW TAXI AT W	HICH TIME THE CONDITIONS CEASED. UPON EXAMINATION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE LT MAIN GEAR LOWER TORQUE 	KNEE HAD FAILED. THE TORQUE KNEE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS PART,4 YEARS SINCE INSPECTION, 	DUE EVERY 8000 LANDING OR 6 YEARS.  (TC NR 20071024010)		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2008012900087	20080129	00087	NM  	2008	1	29	CA071024011      	1	20070921	G	7931		OIL SYSTEM      			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								AG0054			(CAN) DURING CLIMB, LOW OIL PRESSURE WARNING ANNUNCIATED. PILOT INITIATED SHUTDOWN PROCEDURES AND SINGLE ENGINE LANDING.	 ENGINE WAS REMOVED FOR INVESTIGATION.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 	20071024011)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008012900090	20080129	00090	EU  	2008	1	29	CA071025001      	1	20071023	G	6200	V40G3911AA	SPRING          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					EJECTOR	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20   								(CAN) POOR METAL COMPOSITION IN PART CAUSES CRACKING. THESE PARTS WILL CRACK WITHOUT BEING SUBJECT TO FLIGHT. ONE BATCH 	HAS BEEN DISPOSED OF AND THE NEXT BATCH HAS THE SAME ISSUE. THE MFG HAS BEEN NOTIFIED. REF MBB-BO-105 IPC 60-00-00 FIG 8	 ITEM NR 440. (TC NR 20071025001)				1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2008012900091	20080129	00091	EA  	2008	1	29	CA071025002      	1	20071020	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			12986	12986							(CAN) DURING APPROACH, AIRCRAFT RECEIVED A FLAPS FAIL MESSAGE WITH FLAPS AT 30 DEGREES. FLAPS WERE NOT RESELECTED.  RECT	IFICATION: RT BRAKE POSITION SENSOR UNIT (BPSU) FOUND TO BE AT FAULT. BPSU REPLACED AND RIGGED IAW AMM. (TC NR 200710250	02)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008012900094	20080129	00094	NE  	2008	1	29	CA071025003      	2	20071004	G	7261	PT08001A01	OIL CAP         			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	OIL FILLER	MISINSTALLED    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	K	J	INADEQUATE Q C            	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			CA								120848			(CAN) DURING CLIMB, THE LOW OIL PRESSURE WARNING ILLUMINATED. THE CREW ELECTED TO PERFORM AN INFLIGHT SHUTDOWN OF THE EN	GINE AND RETURN TO POINT OF DEPARTURE.  GROUND INSPECTION REVEALED THAT THE OIL FILLER CAP HAD BEEN IMPROPERLY INSTALLED	, AND THAT THE SEALING FUNCTION OF THE POST-SB 21150 FILLER NECK CHECK VALVE HAD BEEN RENDERED INEFFECTIVE THROUGH FLATT	ENING OF THE O-RING AND MECHANICAL DAMAGE. (TC NR 20071025003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008012900097	20080129	00097	EU  	2008	1	29	CA071025004      	1	20071015	G	2820		HOSE            			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E5A1  	30022	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			4425 								(CAN) APU FUEL FEED LINE LEAK WITHIN THE HYDRAULIC SERVICE COMPARTMENT. FUEL LEAKS FROM HOSE CORE AND SOAKS FABRIC BRAID	. LEAK IS IN THE AREA OF SECOND AND THIRD SUPPORTING CLAMPS. SUGGEST THAT THIS MAY BE A MATERIAL SPECIFICATION PROBLEM. 	SUPPORT CLAMPS ARE INTACT AND DO NOT APPEAR TO BE CHAFFING LINE. (TC NR 20071025004)				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008012900100	20080129	00100	EA  	2008	1	29	CA071025005      	1	20071006	G	7931		O-RING          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PW120 	PW123       	 	NE  					OIL PRESSURE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								123357			(CAN) PILOT OBSERVED A SUDDEN DROP IN OIL PRESSURE AND ELECTED TO PERFORM AN IN FLIGHT SHUTDOWN. FLIGHT WAS DIVERTED.  G	ROUND INSPECTION REVEALED A DEFECTIVE O-RING ASSOCIATED WITH THE PCU (PROPELLOR CONTROL UNIT) ASSEMBLY. (TC NR 200710250	05)				1	H	7	2 	3T	4	T	RT	A9EA    	E20NE				 
2008012900107	20080129	00107	NE  	2008	1	29	CA071025006      	2	20071011	G	7200		ENGINE          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  						MAKING METAL    	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								93724			(CAN) 15 MINUTES INTO FLIGHT, THE ENGINE CEASED OPERATION AND SIMUTANEOUSLY ILLUMINATED THE CHIP DETECTOR INDICATOR. THE	 CHIP DETECTOR CIRCUIT BREAKER WAS THEN REPORTED TO HAVE `POPPED`. AIRCRAFT RETURNED TO POINT OF DEPARTURE.  POST FLIGHT	 INSPECTION REVEALED SUBSTANTIAL INTERNAL ENGINE DISTRESS. THE CHIP DETECTOR HAD `POPPED` ON THE PREVIOUS FLIGHT AND HAD	 BEEN RESET.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008012900108	20080129	00108	CE  	2008	1	29	CA071025007      	1	20071024	G	5753		ROLLER          	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	RT TE FLAP	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH WHEN FLAPS WERE SELECTED DOWN, THE RT WING BECAME HEAVY. AILERON CONTROL WAS REDUCED AND FELT DIFFEREN	T THAN NORMAL. THE PILOT LANDED WITHOUT FURTHER INCIDENT AND SELECTED FLAPS UP. THE FLAPS DID NOT MOVE WHEN SELECTED UP,	 SPLIT-FLAP SAFETY MECHANISM WAS ACTUATED.  THE RT OB FLAP, IB AFT ROLLER APPEARS TO HAVE SEIZED AND TORE OUT OF THE FLA	P BRACKET. WHEN THE AMO DRILLED APART THE FLAP FOR REPAIR, THEY NOTED THAT THE BRACKET WAS WORN THIN FROM THE ROLLER. TH	IS, WOULD ONLY BE VISIBLE ONCE THE ROLLER WAS REMOVED.  THE MM DOES NOT SPECIFICALLY REQUIRE REMOVAL OF FLAPS OR ROLLERS	 FOR INSPECTION OR LUBRICATION. A REGULAR REMOVAL OF ALL FLAPS TO INSPECT CONDITION OF ROLLERS AND FLAP BRACKETS WOULD L	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008012900109	20080129	00109	NM  	2008	1	29	CA071025008      	1	20071022	G	7931		OIL SYSTEM      			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	LOW PRESSURE    	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0060			(CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED FOLLOWED BY SURGING AND UNCOMMANDED SHUTDOWN. THE FLIGHT	 WAS DIVERTED.   MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071025008)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2008012900110	20080129	00110	NE  	2008	1	29	CA071025009      	2	20071020	G	7250		ACCESSORY UNIT  			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								123012			(CAN) THE ENGINE WAS REPORTED TO HAVE HAD AN IFSD. GROUND INSPECTION REVEALED THE POWER TURBINES DID NOT TURN FREELY AND	 THE ACCESSORY DRIVE WAS DAMAGED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071	025009)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008012900111	20080129	00111	NM  	2008	1	29	CA071025010      	1	20071015	G	3242		CABLE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					PARKING BRAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4928 								(CAN) AFTER PUSHBACK, PARKING BRAKE CABLE BROKE. EMERGENCY PARKING BRAKE CABLE ASSY REPLACED IAW AMM 32-44-03 (TC NR 200	71025010)					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2008012900112	20080129	00112	EA  	2008	1	29	CA071025011      	1	20071017	G	5410	22850080	COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					THRUST REVERSER	LOOSE           	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA			12626								(CAN) ACTUALLY WE HAVE A AOG A/C AT PRG. DURING THRUST REVERSER OPERATING AFTER TOUCHDOWN AT PRG WERE LOSING THE UPPER 	AND LOWER RT ENGINE COWLINGS. ONE OF THE COWLINGS HIT THE A/C AT FS 700 IN BETWEEN STR 5 TO 7 AND DAMAGED THE FUSELAGE A	ND ALSO THE FRAME FS STN 700.  (TC NR 20071025011)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008012900113	20080129	00113	SW  	2008	1	29	CA071026001      	1	20071012	G	2435	150SG117Q	STARTER GEN     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  						DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4132 	251  							(CAN) DURING SHUTDOWN, IT WAS NOTED THAT A NOISE WAS COMING FROM THE ENGINE BAY AREA. FURTHER INVESTIGATION NOTED THE ST	ARTER GEN REQUIRED TO BE REPLACED. STARTER GEN WAS REPLACED FOR NO FURTHER DEFECTS. (TC NR 20071026001)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900114	20080129	00114	EA  	2008	1	29	CA071026002      	1	20071024	G	5711	215003268	SPAR CAP        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	WS 50.0	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4279 								(CAN) WHILE PERFORMING AD 92-26R1 IAW SB 215-A454 REV 3, NO DEFECTS WERE FOUND IAW OUTLINED ULTRASONIC INSPECTION PROCED	URES. THE NDI TECH NOTED THAT HE WAS PICKING UP WHAT HE THOUGHT WAS A SUSPECTED CRACK OUTSIDE THE AREA OUTLINED IN THE S	B AND PROCEEDED TO ENQUIRE ABOUT THE SURROUNDING STRUCTURE WITH A COMPANY AME. FS 434.8 REAR SPAR WS 50.0 THE SUSPECTED 	CRACK ON THE ULTRASOUND WAS SHOWN TO THE AME AND A LINEAR MEASUREMENT WAS MADE AS TO THE SCALE ON THE INSTRUMENT. IT WAS	 BELIEVED THAT THE CRACK WOULD BE AT APPROXIMATELY LT WING WS 50.0 IN LINE WITH THE REAR OUTER VERTICAL PICK-UP ANGLE TO	 REAR SPAR CAP ATTACHMENT VIA LOCK FASTENER. NR 2 FUEL CELL AND FUEL BAY LINERS WERE REMOVED AND A CRACK IN THE PAINT PR	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2008012900116	20080129	00116	SW  	2008	1	29	CA071026003      	1	20071025	G	6710	204001363015	CYCLIC STICK    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24962								(CAN) PILOTS CYCLIC STICK DISASSEMBLED FOR PAINT AND REFURBISH. STEEL RING PN 204-001-369-001 IS RIVETED ON THE CYCLIC S	TICK. THE STEEL RING IS USED FOR APPLICATION OF FRICTION. THE STEEL RING WAS REMOVED AND EXTREME CORROSION PITTING WAS F	OUND IN THE CYCLIC STICK. IF THE CORROSION DEPTH COULD BE MEASURED ACCURATELY IT WOULD BE 40-50 PERCENT OF THE TUBE THIC	KNESS. PULLED A USED CYCLIC STICK ASSY OUT OF OUR STOCK INVENTORY DISASSEMBLED IT ONLY TO FIND IT CORRODED AS WELL NOT Q	UITE AS BAD BUT BEYOND SERVICEABLE. FINDING 2 HAS PROMPTED US TO CONSIDER THIS TO BE MORE THAN A ONE OF ISSUE CORROSION 	ISSUE. (TC NR 20071026003)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2008012900118	20080129	00118	WP  	2008	1	29	CA071026004      	1	20071023	G	3251		ACTUATOR        			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	NLG STEERING	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				2882 							(CAN) DURING APPROACH WHEN LANDING GEARS SELECTED DOWN, THE LANDING GEARS UNLOCK LIGHT CAME ON, HOWEVER, NO NOSE WHEEL D	OWN LIGHT CAME ON. THE CREW CONFIRMED VISUALLY GEAR NOT DOWN. AFTER A FEW CYCLES GEAR UP AND GEAR DOWN AND EMERGENCY UPL	ATCH RELEASE TO NO AVAIL. AFTER TURNING NOSE GEAR STEERING THE NOSE GEAR CAME DOWN AND LOCKED NORMALLY. THE NOSE GEAR ST	EERING ACTUATOR FOUND TO BE CREEPING TO THE RT ON ITS OWN INTERMITTENTLY. SUBSEQUENT INSPECTION FOUND THAT THE UPPER PIV	OT POINT WAS WORN. STEERING ASSY REMOVED AND SENT TO OVERHAUL SHOP FOR INVESTIGATION AND OVERHAUL.		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2008012900119	20080129	00119	EU  	2008	1	29	CA071026005      	1	20071016	G	2722	793500501	ACTUATOR        			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					RUDDER TRIM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AN A-CHECK, THE RUDDER TRIM ACTUATOR (PN: 793500-501) FAILED THE FREE PLAY CHECK IAW MM 5-20-06 P	ARA: 1.F.(4) AND MM 27-20-00 PAGE 503 PARA: 4.A. A NEW RUDDER TRIM LOWER ACTUATOR (PN: 793500-501) (ALTERNATE PN:1092AS1	00-3) WAS ORDERED. WHEN RECEIVED, THE NEW ACTUATOR 8130-3 RELEASE FORM STATED THAT THE UNIT WAS OVERHAULED. THE PART HAD	 3 DISCREPANCIES, BOTH ROD ENDS WERE WORN, CORRODED, SCORED, ALSO THE ELECTRICAL LEAD, CONNECTOR PLUG WAS CORRODED. THE 	UNIT WAS RETURNED TO VENDOR. (TC NR 20071026005)		2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2008013100060	20080131	00060	SW  	2008	1	31	CA071026006      	1	20071024	G	6210	4711012050	BLADE           			BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1D    	41516	EA  					MAIN ROTOR	BROKEN          	W				R	A			AUTOROTATION            	UNSCHED LANDING         			D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		AP	APPROACH       	1			CA				1664 							(CAN) DURING NORMAL TRAINING FLIGHT, VIBRATION WAS FELT AND AUTOROTATION LANDING CARRIED OUT. UPON SHUTDOWN AND INSPECTI	ON OF BLADES, A FIVE (5) FOOT SECTION OF BLADE COVERING WAS DISCOVERED MISSING FROM THE UNDERSIDE OF THE BLADE FROM THE 	TIP EXPOSING THE WOOD BLADE CORE CAUSING THE ABNORMAL VIBRATION. BLADES WERE REMOVED AND AIRCRAFT TRANSPORTED BACK TO TH	E MAINTENANCE FACILITY. NTSB WERE ON SITE SHORTLY AFTER AND REQUESTED THAT THE BLADES BE SHIPPED OFF FOR A DETAILED EXAM	INATION. (TC NR 20071026006)		1	G	7	1 	3O	3	O		H1      	E279				 
2008013100061	20080131	00061	EU  	2008	1	31	CA071026007      	1	20071018	G	3240	50028053	BRAKE ASSY      			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					RT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				3    							(CAN) A-CHECK INSPECTION COMPLETED AT AIRCRAFT. FOLLOWING INSPECTION A TEST FLIGHT WAS COMPLETED, ON RETURN TO BASE, IT 	WAS NOTED THAT THE RT BRAKE WAS DRAGGING. MAINTENANCE FOUND TOP AFT GRIP AND TUBE OUT OF ADJUSTMENT. REMOVED AND RESET A	SSEMBLY TO NEUTRAL POSITION, OPS CHECK BRAKE SERVICEABLE. AC DEPARTED, UPON LANDING THE PILOT NOTED THAT THE BRAKE WAS D	RAGGING, AND FOUND THE RT BRAKE WAS NOT FULLY RELEASING. MAINTENANCE WAS CALLED IN, REMOVED RT BRAKE ASSEMBLY (PN: 50028	05-3 S/N: S-MAR88-2), AND INSTALLED OVERHAULED BRAKE ASSEMBLY (PN: 5002805-3 S/N: OCT 85-522) PER MM 32-43-01. AIRCRAFT 	RETURNED TO SERVICE. UNSERVICEABLE BRAKE ASSEMBLY RETURNED TO VENDOR (TSO: 2.7 HRS, 2 LANDINGS).REQUESTING VENDER TO SUP	2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2008020400156	20080204	00156	EU  	2008	2	4	CA071026008      	1	20071023	G	2910	137311D1233	LINE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE 200 HOUR AIRFRAME INSP, HYD FLUID WAS FOUND TO BE LEAKING FROM ABOVE THE BAGGAGE POD ON THE BELLY	 OF THE AC. THE AIRCRAFT`S IMPENDING DEPARTURE WAS CANCELLED, AND THE POD REMOVED TO INVESTIGATE.   IT WAS FOUND THAT TH	ERE WAS A CLAMP MISSING ON THE MAIN HYD RETURN LINE, WHICH ALLOWED THE BACKSIDE OF AN ADELL CLAMP ON A HYD PRESS LINE TO	 CHAFF ON THE MAIN RETURN LINE. THIS CHAFFING ACTION WAS FOUND TO HAVE BREACHED THE RETURN LINE, P/N 137311D1233. THE RE	TURN LINE WAS REMOVED AND REPLACED WITH A SERVICEABLE LINE, ALL CLAMPS AND LINES IN THE AREA WERE INSPECTED FOR PROPER A	SSEMBLY AND CHAFFING AND NO OTHER DEFECTS WERE NOTED. THE AIRCRAFT HYDRAULIC SYSTEM WAS SERVICED AND BLED AND THE AIRCRA	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2008013100063	20080131	00063	NM  	2008	1	31	CA071026009      	1	20071026	G	5315	147A55067	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS 986.5	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CABIN BS 986.5 BEAM UPPER CAP CORRODED AT LBL24, LBL18, RBL10, RBL, RBL32, RBL28, RBL22, RBL17 REPAIRED IAW CU	STOMER EA. (TC NR 20071026009)					2	L	7	2 	4F			RT	A16WE   					 
2008013100064	20080131	00064	GL  	2008	1	31	CA071026010      	1	20071026	G	3246	C2US1285A	LINK ASSY       			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	AT SKI ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10   								(CAN) SKIS OLD SURPLUS PARTS, 0 HRS, PUT INTO SERVICE 1 YR AGO. SKIS INSPECTED TO REATTACH TO AIRCRAFT, DISASSEMBLED FOR	 MAINTENANCE. UPON REMOVAL OF LINK ASSY FROM SKI PIVOT ATTACHMENT, BASE OF LINK FOUND CORRODED OUT AND U/S. CORROSION WO	ULD HAVE ONLY BEEN APPARENT DURING FULL DISASSEMBLE OF SKI, NOT A NORMAL PRACTICE. SKIS APPEAR TO HAVE BEEN OILED IAW EN	GINEERING DWG, BUT 1 PLUG SCREW IS MISSING AND ANOTHER LOSE, LIKELY CAUSE OF WATER TO ENTER LINK ASSY. (TC NR 2007102601	0)		1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P736	 
2008013100066	20080131	00066	NM  	2008	1	31	CA071026011      	1	20071026	G	5320	453A26113	STRIP           			BOEING	737   	737790      	13844CN	NM  										BS 847-947	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION ON CAP STRIP BETWEEN BS 847 AND BS 947 RT SIDE AFT CARGO REPAIRED IAW CUSTOMER EA. (TC NR 20071026011)						2	L	7	2 	4F			RT	A16WE   					 
2008013100067	20080131	00067	NM  	2008	1	31	CA071029002      	1	20070815	G	2701	MS21919WDG9	CLAMP           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					COLUMN ROD	LOOSE           	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) PRIOR TO PUSHBACK, WHEN TOE BRAKES WERE PRESSED TO RELEASE PARK BRAKE, THE CONTROL COLUMN YOKE MOVED AFT APPROX 1 	INCH. REF: LOAD CELL INSTALLATION. THE CLAMP IS INSTALLED ON THE CONTROL COLUMN ROD ASSY ON THE TAPERED SECTION OF THE R	OD. THE CLAMP CANNOT BE PROPERLY TIGHTENED DUE TO THE ANGLE IN THE ROD AND EVENTUALLY BECOMES LOOSE. WHEN THE CLAMP IS F	REE TO MOVE ALONG THE ROD, IN CERTAIN CONDITIONS,  THE CLAMP CAN INTERFERE WITH CONTROL COLUMN MOVEMENT. MFG HAS CORRECT	ED THE PROBLEM ON OTHER AC, NOT ON THIS AC, THUS A MODIFICATION IS REQUIRED. (TC NR 20071029002)		2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2008013100068	20080131	00068	NE  	2008	1	31	CA071029003      	2	20071019	G	8530	399357	CYLINDER        			AYRES 	S2    	S2RHGT65    	0970110	SO  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	23D	23D40       	NE  	NR 7	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			910  	910  							(CAN) PILOT REPORTED FAILURE OF ENGINE TO MAINTAIN FULL POWER AT THE TAKEOFF SETTING. AIRCRAFT RETURNED TO THE RAMP. COM	PRESSION TEST REVEALED CYLINDER NR 7, WAS LOW ON COMPRESSION AND LEAKING VIA A CRACK IN THE EXHAUST PORT AREA OF THE CYL	INDER. THE OFFENDING CYLINDER WAS REMOVED AND AN OVERHAULED CYLINDER WAS INSTALLED. AIRCRAFT RETURNED TO FLIGHT STATUS. 	(TC NR 20071029003)			1	L	7	1 	3T	3	R	NC	        	5E2	6	C	P719	 
2008013100069	20080131	00069	SW  	2008	1	31	CA071029004      	1	20070809	G	6320		HOUSING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					M/R TRANSMISSION	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						BMC00040					(CAN) OIL FOUND ON TRANSMISSION DECK AFTER BRIEF DAILY INSPECTION, OIL LEAK FOUND FROM THE BOTTOM OF THE TRANSMISSION.  	UPON FURTHER INVESTIGATION TRANSMISSION REMOVED AND BOTTOM CASING FOUND TO BE CRACKED AT LOWER MAST SUPPORT BRG. (TC NR 	20071029004)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008013100070	20080131	00070	CE  	2008	1	31	CA071029005      	1	20071027	G	3240	10310300	BOLT            	CLEVELAND   		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	TORQUE PLATE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			337  								(CAN) DURING MAINTENANCE ON AIRCRAFT, NR 4 MAIN TIRE WORN TO LIMITS.  DURING NR 4 MAIN WHEEL AND TIRE CHANGE, FOUND 3 OU	T OF 6 BRAKE TORQUE PLATE ATTACH BOLTS MISSING AND REMAINING ATTACH BOLTS LOOSE. A LOOSE BOLT WAS FOUND LODGED IN WHEEL 	BETWEEN A WHEEL HALF TIE BOLT HEAD AND THE BRAKE DISC.  3 NEW BOLTS WERE INSTALLED AND ALL 6 BOLTS WERE INSTALLED AND TO	RQUED TO MFG SPECS. OTHER 3 BRAKE INSTALLATIONS AND 4 BRAKE INSTALLATIONS VISUALLY VERIFIED NO BOLTS MISSING.  HAVE CONT	ACTED MFG TO PURSUE THE USE OF DRILLED AND LOCKWIRED BOLTS. (TC NR 20071029005)		1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008012900120	20080129	00120		2008	1	29	CA071029006      	4	20071025	G	3197	MS2524475	CIRCUIT BREAKER 			BELL  	205   	205B        	       	SW  	LYC   	T53   	T5317BLYC   	41616	NE  						ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) SMOKE AND ODOR IN CABIN. LANDED BACK AT PAD. (TC NR 20071029006)						1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008012900121	20080129	00121	EA  	2008	1	29	CA071029007      	1	20071029	G	5544	DAT4864A	BEARING         			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RUDDER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			421  								(CAN) RUDDER BEARING FOUND DAMAGED ON  C-CHECK. THE BEARING WAS INCORPORATED BY SB ON WINTER WORK 2005-2006 AND CUMULATE	 421 HOURS SINCE INSTALLATION.  A/C HOURS 2141 CYCLES 1316 DROPS 11678 (TC NR 20071029007)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008012900122	20080129	00122	EU  	2008	1	29	CA071029008      	1	20071026	G	5320	120A6050	FRAME           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  	HARTZL	HCC3Y	HCC3YR      	GL  	OIL COOLER	DAMAGED         	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA			659  								(CAN) FLIGHT DEPARTED AT 1344 FOR AT TRAINING FLIGHT TO THE WEST PRACTICE AREA. APPROXIMATELY 5 MINUTES OUT WHILE CRUISI	NG AT 4000 FT AND 120 KTS THE INSTRUCTOR OBSERVED (ALT OFF) ANNUNCIATION. A SCAN OF INTEGRATED ENGINE DISPLAY REVEALED (	AMPS) TO BE READING -24A AND VOLTAGE READING 24.7V. THE INSTRUCTOR THEN OBSERVED (VOLT) ANNUNCIATION. THE INSTRUCTOR FOL	LOWED EMERGENCY CHECKLIST AND SELECTED (ALTERNATOR) SWITCH OFF AND REMOVED NON-ESSENTIAL ELECTRICAL LOADS. THIS RESULTED	 IN A REDUCED NEGATIVE LOAD OF -9A. INSTRUCTOR THEN BRIEFLY CONFIRMED FAULT BY RETRYING (ALTERNATOR) SWITCH ON - LOAD WE	NT BACK TO -24A , (ALTERNATOR) SWITCH WAS IMMEDIATELY SELECTED OFF AGAIN. THE INSTRUCTOR MADE (PAN) CALL AND RETURNED . 	1	L	7	1 	3O	3	O	RT	A49CE   	1E4	5	C	P25EA	 
2008012900123	20080129	00123	NM  	2008	1	29	CA071029009      	1	20071027	G	3220	273A45141	SHAFT           			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					NLG	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			6885 								(CAN) THE FLIGHT CREW REPORTED THAT AFTER TAKEOFF, (THE NOSE GEAR INDICATES DOWN IN THE UP POSITION. WHEN GEAR HANDLE PU	T IN THE OFF POSITION, THE NOSE GEAR CAME DOWN.) THE FLIGHT RETURNED TO BASE AND MADE AN UNEVENTFUL LANDING.  MANUAL EXT	ENSION ARM FOUND IN THE EXTEND POSITION AND WOULD NOT RELEASE. PAINT FOUND ON THE P/N 273A4514-1 SHAFT. PAINT REMOVED, M	ICARTA BUSHINGS CLEANED AND SHAFT REINSTALLED IAW OHM 32-35-05 AND SOPM 20-50-01. NOSE GEAR RETRACT TEST C/W IAW AMM 32-	33-00 WITH NO FAULT FOUND.  HAVE ADVISED MFG OF THE EVENT AND THE REPORT OF PAINT FOUND ON THE SHAFT ASSEMBLY. (TC NR 20	071029009)	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2008012900124	20080129	00124	EA  	2008	1	29	CA071029010      	1	20071028	G	2821	63E951	HOUSING         	GRIMES      		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					FUEL FILTER	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA						GWD16759					(CAN) JUST BEFORE PUSHBACK, THE RAMP CREW OBSERVED A FUEL LEAK COMING FROM THE APU AREA. CAPTAIN PERFORMED RAPID PASSENG	ER DEPLANEMENT WITH EMERGENCY CREWS ON STAND-BY.  MAINTENANCE FOUND THE FUEL LEAK COMING FROM THE NR 2 ENGINE- FUEL FILT	ER HOUSING, BY THE FUEL FILTER IMPENDING BYPASS PLUG. IN THIS AREA, THE FUEL FILTER HOUSING AND THE SQUARE PLUG WERE FOU	ND GROOVED AND THE SQUARE PLUG SEAL WAS FOUND DAMAGED AS WELL. MAINTENANCE REPLACED THE ALL FUEL FILTER ASSY. (TC NR 200	71029010)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008012900125	20080129	00125	CE  	2008	1	29	CA071029011      	1	20071027	G	2710		CONTROL CABLE   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AILERONS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GRINDING NOISE UNDER PILOT FLOOR WHEN AILERONS ARE MOVED. CONTROL CABLE FOUND CHAFING ON STEEL BRAIDED NITROGEN LI	NE. APPROX 3 INCH DEFLECTION OF CONTROL CABLE CAUSED, DUE TO INCORRECT ROUTING OF NITROGEN LINE. NITROGEN PRESSURE LINE 	REROUTED.  AILERON CABLE HAS 1 BROKEN STRAND WITHIN ACCEPTABLE LIMITS IAW AMM CH20-04-00-201 (TC NR 20071029011).				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008012900127	20080129	00127	SW  	2008	1	29	CA071030001      	1	20071024	G	2915	204076437003	CHECK VALVE     			BELL  	412   	412EP       	1182205	SW  										HYD SYSTEM	OBSTRUCTED      	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			4    								(CAN) DURING GROUND RUN, FIRST START OF THE DAY, BOTH HYDRAULIC SYSTEMS NR 1 AND NR 2 INDICATED GOOD PRESSURE AND BOTH H	YDRAULIC CAUTIONS WERE EXTINGUISHED. THE FORCE TO DISPLACE PEDALS WAS NOTED TO BE ABNORMALLY HIGH. TO CONFIRM SYSTEM NR 	1 WAS FUNCTIONING CORRECTLY, SYSTEM NR 2 WAS SELECTED OFF. A TOTAL LOSS OF HYDRAULICS WAS ENCOUNTERED TO BOTH CYCLIC AND	 COLLECTIVE. THE AIRCRAFT WAS IMMEDIATELY SHUTDOWN.   DURING INVESTIGATION, FOD WAS FOUND OBSTRUCTING THE CHECK VALVE, O	RIGIN OF FOD IS UNKNOWN AND UNDER INVESTIGATION. (TC NR 20071030001)		1	G	7	2 	4U				H4SW    					 
2008012900128	20080129	00128	CE  	2008	1	29	CA071030002      	1	20071025	G	5753	501600183	FLAP TRACK      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26566								(CAN) ON MAINTENANCE WALKAROUND THE RT OB FLAP HAD MORE PLAY THAN USUAL. FLAP WAS REMOVE AND THE OB FLAP TRACK WAS FOUND	 TO BE CRACKED ON THE REAR TIP. TRACK REPLACED AND AIRCRAFT RETURNED TO SERVICE.  (TC NR 20071030002)					1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2008012900130	20080129	00130	GL  	2008	1	29	CA071030004      	2	20071029	G	7261	6898607	CARBON SEAL     	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1	DAMAGED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA			36   			CAC39586					(CAN) DURING AN OIL LEAK WAS DISCOVERED BY THE BLEED VALVE.  NR 1 BEARING CARBON SEAL FOUND DAMAGED, THE BEARING WAS REM	OVED AND UPON INSPECTION FOUND UNSERVICEABLE. THE BEARING WHEN TURNED HAD A ROUGH, COURSE FEELING TO IT. (TC NR 20071030	004)				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900131	20080129	00131		2008	1	29	CA071030005      	4	20071016	G	3418		CONNECTOR       			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					STALL WARNING	TRANSPOSED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING A 300HR INSPECTION THE STALL WARNING ACCELEROMETER CHECK WAS DUE ( IAW AD 82-01-05). WHEN CHECK WAS CARRIED	 OUT, THE STALL WARNING SYSTEM FAILED. WHEN SYSTEM WAS TROUBLESHOT, IT WAS DISCOVERED THAT CONNECTORS BNC 3 AND BNC 4 (F	ORM PIN D AND PIN F RESPECTIVELY) WERE FOUND REVERSED. CONNECTORS SWITCHED BACK AND STALL WARNING SYSTEM FUNCTIONED CHEC	KED SERVICEABLE. SYSTEM LAST CHECKED AT A MFG SERVICE CENTER. (TC NR 20071030005)			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2008012900132	20080129	00132	NM  	2008	1	29	CA071030006      	1	20071030	G	5730	112A41029	SKIN PANEL      			BOEING	737   	737790      	13844CN	NM  										LWS 260 & 240	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WING LWR SKIN PANEL CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING BLADE SEAL APPROX WSTA 260, 240	 REPAIRED IAW EA 5720-01337. (TC NR 20071030006)					2	L	7	2 	4F			RT	A16WE   					 
2008012900134	20080129	00134	NM  	2008	1	29	CA071030007      	1	20071030	G	5730	112A410210	SKIN PANEL      			BOEING	737   	737790      	13844CN	NM  										RWS 240,260	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING LWR WING SKIN PANEL CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING BLADE SEAL APPROX WSTA 240	,262 REPAIRED IAW EA 5720-01338. (TC 20071030007)					2	L	7	2 	4F			RT	A16WE   					 
2008012900135	20080129	00135	SO  	2008	1	29	CA071030008      	1	20071025	G	7720	41506	INDICATOR       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	OIL TEMP	ERRATIC         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING RUN-UP, OIL TEMP INDICATOR DROPPED OFF SCALE. THEN WENT BACK TO NORMAL INDICATION. THE ERATIC OPERATION COU	LD BE INDUCED BY ENERGIZING DIFFERENT ELECTRICAL EQUIPMENT.  HOURS IN USE, NONE AT THIS TIME.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008012900136	20080129	00136	NE  	2008	1	29	CA071030009      	2	20071029	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1460 								(CAN) DURING AN INSPECTION, THE ENGINEER NOTED THAT THE ENGINE DRIVEN FUEL PUMP HAD EVIDENCE OF OIL LEAKAGE AROUND THE S	EAL AREA (BODY). PUMP WAS REMOVED, REPLACED AND NO FURTHER ISSUES WERE NOTED. THERE HAS BEEN MANY OF THE THESE PUMPS LAT	ELY WITH VARIOUS HRS OF FAILURE. (TC NR 20071030009)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008012900138	20080129	00138	SW  	2008	1	29	CA071030010      	1	20071030	G	7920	6899246	HOUSING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					OIL FILTER	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								CAG34008			(CAN) DUE TO A INTERNAL CASTING DEFECT INSIDE THE OIL FILTER HOUSING, THE PRESSURE REGULATING POPPET CANNOT FULLY BOTTOM	 OUT WHEN INSTALLED. THIS THEN GIVES A FALSE INDICATION OF PROPER POSITION OF THE POPPET WHEN (BACKED OUT) 5.5 TURNS FOR	 INITIAL ADJUSTMENT FOLLOWING OVERHAUL. THE MFG WAS ADVISED AND RECOMMENDS THAT AN APPROVED FACILITY MACHINE THE INTERNA	L SURFACE OF THE HOUSING TO REMOVE THE DEFECT. (TC NR 20071030010)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008012900139	20080129	00139	NE  	2008	1	29	CA071030011      	2	20071008	G	7314		DIAPHRAGM       	LYC         		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			797  			4105					(CAN) DURING INSPECTION, ENGINEER DISCOVERED OIL LEAKAGE FROM VENT. SUSPECT DAMAGED DIAPHRAGM. (TC NR 20071030011)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008012400333	20080124	00333	GL  	2008	1	24	CA071031002      	1	20070417	G	7160	6552241	INTAKE PIPE     			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	ENGINE	DETERIORATED    	W				K				NONE                    				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			394  								(CAN) INTAKE PIPE FLANGE DETERIORATED AND AIR LEAK OCCURRED. ENGINE IDLE INCREASED AND ENGINE RUNS SLIGHTLY ROUGH. INSTA	LLED NEW INTAKE PIPE P/N 655224-1 AND GASKET 554227 (NR 3 CYLINDER) (TC NR 20071031002)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2008013100092	20080131	00092	SO  	2008	1	31	CA071031004      	2	20070621	G	8530	6552241	TUBE            			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	CYLINDER INTAKE	DETERIORATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			470  								(CAN) INTAKE TUBE AT FLANGE TO CYLINDER DETERIORATED. NEW INTAKE PIPE 655224-1 AND GASKET 554227 INSTALLED (NR 3 CYLINDE	R). (TC NR 20071031004)					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2008013100095	20080131	00095	SO  	2008	1	31	CA071031005      	2	20071023	G	8530	50339001	TUBE            			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	CYLINDER INTAKE	DAMAGED         	W				K				NONE                    				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			623  					360074			(CAN) INTAKE PIPE ON NR 1 CYLINDER FLANGE DAMAGED. (TC NR 20071031005)						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2008013100098	20080131	00098	EA  	2008	1	31	CA071031006      	1	20071030	G	5350	600330061	RADOME          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					FUSELAGE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) FLIGHT ON CLIMB OUT THE CREW HEARD A LOUD BANG IN THE NOSE AND SAW A BIRD TRAVEL PAST THE COCKPIT WINDOW. ALL FLIG	HT SYSTEMS WERE NORMAL AND FLIGHT CONTINUED. UPON ARRIVAL MAINTENANCE MET THE AIRCRAFT AND FOUND A HOLE IN THE RADOME AS	 WELL AS A DAMAGE TO THE LT FUSELAGE AFT OF PITOT HEAD. DAMAGE ASSESSMENT IS UNDER WAY AND IT WILL BE UPDATED AS SOON AS	 MORE INFOMATION IS AVAILABLE. (TC NR 20071031006)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100101	20080131	00101	NE  	2008	1	31	CA071031007      	2	20071029	G	8530		CYLINDER HEAD   			DOUG  	DC4   	C54EDC      	3021528	WP  	PWA   	R2000 	R20007M2    	52023	NE  	HAMSTD	23E	23E50       	NE  	FUSELAGE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CRACK DISCOVERED AT SPARK PLUG HOLE, RETURNED TO BASE AND REPLACED CYLINDER AND A/C RETURNED TO SERVICE. (TC NR 20	071031007)					2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
2008013100112	20080131	00112	CE  	2008	1	31	CA071031008      	1	20071030	G	3246	950476	BEARING         	BEECH       		BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MAIN WHEEL	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF THE CREW NOTED THAT THEY FELT A SLIGHT VIBRATION, BUT FELT THAT IT WAS LIKELY THE RAISED RUNWAY LIGHTS.	 AFTER TAKEOFF THEY WERE ADVISED THAT THEY HAD LOST A TIRE. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. MAINTENANCE FOUND 	THAT ONE OR BOTH WHEEL BEARINGS HAD FAILED. THIS ALLOWED THE WHEEL TO DEPART FROM THE AXLE. INSPECTION SHOWED NO DAMAGE 	TO ANY OTHER PART OF THE AIRCRAFT, INCLUDING AXLE AND BRAKE. THE WHEEL ASSY. INCLUDING BEARINGS WERE REPLACED AND THE AI	RCRAFT WAS RELEASED TO SERVICE. (TC NR 20071031008)		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2008013100115	20080131	00115		2008	1	31	CA071031009      	4	20071021	G	2397	EH19565	WIRE HARNESS    			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					CABIN	BROKEN          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) AN APPARENT NOTICEABLE ELECTRICAL ODOR WAS DETECTED IN VICINITY OF SEATS 19 DEF BY IN FLIGHT CREW AND PASSENGER. O	DOR PERSISTED FOR APPROX 5 MIN AND STOPPED AT THE TIME WHEN INFLT VIDEO SYSTEM WAS SHUTDOWN.  FOUND BROKEN WIRE IN THE H	ARNESS THAT RUNS FROM UNDER SEATS 18 DEF TO UNDER THE FLOOR.  BROKEN WIRE CAPPED AND STOWED INSIDE HARNESS CONNECTOR. TH	IS APPEARS TO BE AN INSTALLATION ERROR.  THE WHITE WIRE APPEARS TO HAVE BEEN INSTALLED UNDER TOO MUCH TENSION, AND WAS P	ULLED FROM THE BACK OF THE CONNECTOR. (TC NR 20071031009)		2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2008020400155	20080204	00155	CE  	2008	2	4	CA071101001      	1	20071019	G	3260	MS21090348	SQUAT SWITCH    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH APPROXIMATELY 3 MILES FROM TOUCH DOWN, THE LT THRUST REVERSER (T/R) ARM AND UNLOCK LIGHTS ILLUMI	NATED BRIEFLY. AT APPROXIMATELY 1.5 FROM TOUCH DOWN THE LT T/R ARM, UNLOCK AND DEPLOY LIGHTS ILLUMINATED AND THE LT POWE	R LEVER AUTOMATICALLY MOVED TO IDLE. ALL (3) LIGHTS EXTINGUISHED BEFORE EITHER OF THE PILOTS COULD TAKE ACTION TO EMERGE	NCY STOW THE T/R. THE FACT THAT THE MECHANICAL T/R POWER LEVER INTERCONNECT CAUSED THE POWER LEVER TO RETARD TO IDLE IND	ICATES THAT THE T/R DID ACTUALLY DEPLOY AND THAT THIS WAS NOT AN ERRONEOUS ANUNNCIATOR. THE LANDING GEAR SQUAT SWITCHES 	SHOULD HAVE PREVENTED INADVERTENT T/R DEPLOYMENT, WITH ONLY THE T/R ARM LIGHT ILLUMINATING EVEN IN THE EVENT OF A COMMAN	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008013100118	20080131	00118	EA  	2008	1	31	CA071101002      	2	20071031	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  		POWER LOSS      	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0268			(CAN) DURING FLIGHT, A LOUD NOISE WAS HEARD FOLLOWED BY A LOSS OF POWER RESULTING IN AN INFLIGHT SHUTDOWN OF THE ENGINE.	 POST FLIGHT EXAMINATION REVEALED SEVERE INTERNAL DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE 	ESTABLISHED (TC NR 20071101002)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008031900165	20080319	00165	EU  	2008	3	19	CA071101003      	1	20071029	G	3246		BEARING         			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E5A1  	30022	NE  					NR 4 WHEEL	SEIZED          	W				D				RETURN TO BLOCK         				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			786  								(CAN) THE A/C LANDED NORMALLY, TAXIED TO THE GATE AND STOPPED SHORT OF ITS FINAL POSITION.  THE CREW REPORTED 60 PERCENT	 N1 REQUIRED (SINGLE ENG TAXI) TO MOVE THE AC FROM A HOLD SHORT OF THE GATE. THE GROUND CREW ARRIVING THE AC HEARD A LOT	 OF NOISE FROM THE RT GEAR AS IT MOVED TO THE GATE. NO OTHER FAULT INDICATIONS IN THE COCKPIT.   UPON INSP OF THE RT LAN	DING GEAR IT WAS IDENTIFIED THAT THE (NR 4 WHEEL WAS DRAGGING AND INTERFERING WITH BRAKE CARRIER).  FURTHER INSP FOUND T	HE WHEEL BRG SEIZED ON THE GEAR AXLE, WITH  NR 4 TIRE AND THE BRAKE DAMAGED.  DECOLONIZATION OF THE AXLE WAS NOTED DUE T	O EXCESSIVE HEAT BUILD UP.  THE RT LANDING GEAR ASSY, BRAKE AND TIRE WAS REPLACED IAW AMM.  INVESTIGATION CONTINUES TO I	2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008013100120	20080131	00120	GL  	2008	1	31	CA071101005      	2	20071029	G	7210	78023061	MAGNETIC SEAL   			CESSNA	206   	U206G       	2073356	CE  	ALLSN 	250C  	250C20      	03013	GL  	HARTZL	HCC3Y	HCC3YN      	GL  	PROP RGB	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			22   	22   		074					(CAN) ONE OF THE PILOTS NOTICED A SMALL ENGINE OIL LEAK ON BOTTOM OF ENGINE COWLING. REMOVED THE ENGINE COWLING AND FOUN	D LEAK ON PROP REDUCTION GEARBOX INPUT SEAL AREA. REMOVED PROP REDUCTION GEARBOX, INPUT QUILL ASSY AND REPLACED MAGNETIC	 SEAL. UNDER 10X MAGNIFYING GLASS, A SCRATCH AT 90 DEGREE ACROSS THE CARBON SEALING SURFACE WAS FOUND. AIRCRAFT GROUND R	UN, NO LEAKS, RETURN TO SERVICE. DEFECTIVE MAGNETIC SEAL RETURN TO MFG. (TC NR 20071101005)			1	H	7	1 	3O	3	U		A4CE    	E4CE	5	C	P25EA	 
2008013100122	20080131	00122	EA  	2008	1	31	CA071102001      	1	20071029	G	2752	852D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		AP	APPROACH       	1			CA			7986 	7986 							(CAN) DURING APPROACH, THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE WHEN THE FLAPS WERE SELECTED FROM 0 TO 8 DEGREES. T	HE EICAS FLIGHT CONTROL PAGE WAS INDICATING 0 DEGREE ON BOTH SIDES. THE CREW CONTINUED THE APPROACH AND COMPLETED A FLAP	LESS LANDING WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED.  THE SYSTEM WAS RESET, THE FLAPS SET TO 8 DEGREES AND THE AC W	AS FERRIED FOR MAINTENANCE.  ALL FLAP ACTUATORS WERE REMOVED AND SENT TO THE SHOP. THE LT NR1 FLAP ACTUATOR FAILED THE -	60 DEGREES TORQUE CHECK. DECISION WAS MADE TO REPLACE ALL FLAP ACTUATORS. FLAP ACTUATORS WERE REPLACED, ADJUSTED, TESTED	 AND THE AIRCRAFT WAS RELEASED. A SUCCESSFUL TEST FLIGHT WAS CONDUCTED AND THE AIRCRAFT RETURNED INTO SERVICE. (TC NR 20	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100123	20080131	00123	CE  	2008	1	31	CA071102002      	1	20071031	G	2497	CM358930	SWITCH          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AVIONICS 2	OVERHEATED      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			4804 								(CAN) SHORTLY AFTER DEPARTURE THE PILOT BECAME AWARE OF A BURNING ODOR. HE NOTICED THAT THE AVIONICS 2 SWITCH WAS HOT TO	 TOUCH. THE PILOT RETURNED TO BASE. INVESTIGATION FOUND THAT THE AVIONICS 2 SWITCH HAD OVERHEATED TO THE POINT OF FAILUR	E. A NEW SWITCH P/N 7270-5-30 WAS INSTALLED. ( REF CAB97-8 ) (TC NR 20071102002)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008013100124	20080131	00124	SW  	2008	1	31	CA071102003      	1	20071029	G	6510	206040272101	BOOT            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					DRIVE SHAFT	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21   			A2000807					(CAN) DRIVE SHAFT WAS RECENTLY INSPECTED, GREASED AS REQUIRED AT MFG.   OLD BOOTS WERE SERVICEABLE, BUT AGE WAS NOT KNOW	N SO REPLACEMENT WAS ELECTED AS A SAFETY PRECAUTION.  NEW BOOTS INSTALLED AND DRIVE SHAFT SERVICED.   21.1 HOURS AFTER R	EPACK GREASE LEAK WAS DETECTED BY PILOT AND DRIVE SHAFT REMOVED.   AS A SERVICEABLE DRIVE SHAFT WAS AVAILABLE THE LEAKIN	G ONE IN QUESTION WAS (RED TAGGED).  UNSERVICEABLE DRIVE SHAFT DISASSEMBLED AND BOOT FOUND DETERIORATED, ALMOST TO A DIS	SOLVED STATE, RUBBER SEEMS MORE LIKE A PLASMA THEN RUBBER STATE.  BOOT INFO SKF BO201 SKF BCO-BO-7206 MFG 1/19/07. (TC N	R 20071102003)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008013100125	20080131	00125	GL  	2008	1	31	CA071102004      	1	20071031	G	3245	30200530001110	TUBE            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					MLG TIRE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3    								(CAN) DURING A SPECIAL INSPECT TO THE MAIN AND NOSE WHEEL ASSEMBLIES, DEFECTS WERE NOTED IN THE TIRE-TUBES INSTALLED INT	O BOTH MAIN AND THE NOSE WHEELS. REPORTS HAVE BEEN MADE OF TIRE-TUBES FAILING WITH VERY LOW TIME. AFTER RECEIVING THESE 	REPORTS AN INSPECTION WAS PERFORMED ON ALL 3 WHEEL ASSEMBLIES ON 2 AIRCRAFT ALL TIRE-TUBES INSPECTED WERE DEFECTIVE, SHO	WING THE SAME DEFECTS AS REPORTED. PHOTOGRAPHS OF THE REPORTED TIRE-TUBES FAILURES ARE ATTACHED TO THIS SDR. THE TUBES I	NSPECTED ARE IDENTICAL IN APPEARANCE. SEVERAL TUBES P/N 5.00-5 TR 67 AND 30200530001110 HAVE BEEN FOUND WITH SIMILAR DIS	CREPANCIES (TC NR 20071102004)	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2008013100126	20080131	00126	EA  	2008	1	31	CA071102005      	2	20071026	G	8530	LW167035C	ROCKER BOSS     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CYLINDER HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				145  				L2371415			(CAN) ON CYLINDER NR 3 THE ROCKER SHAFT RT BOSS HAS BEEN FOUND BROKEN (SPLIT) IN THE MIDDLE SECTION. THE BROKEN PART/ALL	 AND REST JUST BESIDE THE EXHAUST VALVE. (TC NR 20071102005)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2008013100127	20080131	00127	CE  	2008	1	31	CA071102006      	1	20071031	G	3260	1CH25	DOWNLOCK SWITCH 			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) UNABLE TO GET NLG (GREEN LIGHT) ON APPROACH. RECYCLED 3 TIMES AND GREEN LIGHT OBTAINED.  NLG DRAG LINK DOWN AND LO	CK SWITCH REPLACED. GEAR SWINGS COMPLETED. NO FURTHER FAULTS AT THIS TIME. (TC NR 20071102006)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008013100129	20080131	00129	SO  	2008	1	31	CA071102008      	1	20071031	G	5210		DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  		DEPARTED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) UPPER DOOR ASSEMBLY DEPARTED THE AIRCRAFT WHILE IN FLIGHT, UPPER DOOR REPLACED AND DAMAGED STRUCTURE REPAIRED. THI	NK THE PROBLEM AROSE WITH THE FACTORY PIPER SLIDING LOCK. WE SUSPECT THAT IT WAS WORN THOUGH THERE WAS NO PRIOR INDICATI	ON. (TC NR 20071102008)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008013100130	20080131	00130	EA  	2008	1	31	CA071102009      	1	20071030	G	2761	601R107022	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					SPOILERON	FRACTURED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA						SBRJ75					(CAN) DURING SHORT FINAL, THE FLAPS WERE SELECTED TO 45 DEGREES AND THE AIRCRAFT ROLLED TO THE RT.  FULL AILERON TRIM AN	D A LITTLE BIT OF AILERON WAS REQUIRED TO KEEP THE AIRCRAFT LEVEL. THE EICAS FLIGHT CONTROL PAGE WAS REVIEWED AND THE RT	 SPOILERON WAS SHOWING UP. THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE DISCOVERED THAT THE RT SPOILERON OB ACTUAT	OR ATTACHMENT HAS FRACTURED. THE RT SPOILERON ASSY AND BOTH ACTUATORS WERE REPLACED, ADJUSTED AND THE SYSTEM TESTED SERV	ICEABLE. THE AIRCRAFT WAS RELEASED AND RETURNED INTO SERVICE. (TC NR 20071102009)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100131	20080131	00131	NM  	2008	1	31	CA071102010      	1	20071017	G	5230		SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	CARGO DOOR	FALSE INDICATION	W				B				EMER. DESCENT           				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS ALREADY UNDER MEL 52-10-05 DUE FORWARD BAGGAGE DOOR GIVES A FALSE (OPEN) INDICATION IN THE COCKPIT.  	AIRCRAFT COULD FLY PRESSURIZED BUT PRESSURIZATION SYSTEM MUST BE CONTROL IN MANUAL MODE.  AIRCRAFT SUFFERED A DEPRESSURI	ZATION AT 20,000 FT.  ALL SYSTEM CHECK AND NO FAULT WAS FOUND IN MANUAL AND AFTER DOOR SENSOR WAS REPAIR SYSTEM WORK ALS	O IN AUTO MODE.  STILL UNDER INVESTIGATION. (TC NR 20071102010)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008013100132	20080131	00132	EA  	2008	1	31	CA071102011      	2	20071031	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LEFT	NOISY           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			2047 					PCEFA0268			(CAN) AROUND 20000 FT, AFTER HEARING A STRANGE SOUND THAT SEEM TO COME FROM THE LT ENGINE, PILOT NOTICED THAT THE LT ENG	INE SUDDENLY STOPPED BY ITSELF. PILOT WAS ABLE TO FEATHER THE PROP. EMERGENCY WAS DECLARED. A/C LANDED WITHOUT OTHER PRO	BLEM. NO ONE INJURED.  UNDER INVESTIGATION (TC 20071102011)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008013100133	20080131	00133	CE  	2008	1	31	CA071102012      	1	20071102	G	3211	05412024	BUSHING         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	MLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4792 	4792 							(CAN) THE MAIN GEAR LEG BUSHINGS ARE A STEEL OUTER TUBE, WITH A THICK INNER URETHANE CENTER. DURING PROGRESSIVE CARE OPE	RATION  NR 4, INSPECTION OF THE LT MAIN GEAR LEG REVEALED THAT THAT THE URETHANE INNER BUSHING MATERIAL HAD DEPARTED FRO	M THE OUTER STEEL BUSHING (P/N 0541202-4). IT HAD MOVED LOOSELY ALONG THE TUBULAR GEAR LEG TOWARDS THE CENTER OF THE AIR	CRAFT. 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. (TC NR 2007	1102012)	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2008013100137	20080131	00137	SW  	2008	1	31	CA071102013      	1	20071101	G	6320	476206283	BEARING CAGE    	BELL        		BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1E    	41516	EA  					M/R TRANSMISSION	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				100  		B125159					(CAN) DURING ROUTINE INSPECTION, SMALL AMOUNT OF BRASS WAS FOUND IN OIL SCREEN, THE TRANSMISSION WAS DISASSEMBLED TO LOC	ATE THE FAILED ITEM AND IT WAS FOUND TO BE ONE OF THE BEARING CAGES IN THE DUPLEX BEARING THAT THE UPPER SUN GEAR GOES T	HROUGH, THIS IS THE NEW AND IMPROVED BEARING INSTALLED IAW TB 47-75-4 (TC NR 20071102013)				1	G	7	1 	3O	3	O		H1      	E279				 
2008013100143	20080131	00143	EA  	2008	1	31	CA071103001      	1	20071101	G	4970	21188002	ECU             	HONEYWELL   		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					APU	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			18983	6143 							(CAN) FLIGHT RETURNED DUE TO APU OIL PRESSURE MESSAGE CAUSING THE APU TO FAIL. AIRCRAFT WAS ALREADY OPERATING WITH 1 IDG	 GENERATOR UNSERVICEABLE. MAINTENANCE CHECKED THE SYSTEM AND FOUND AN ECU FAULT MESSAGE. THE APU ECU WAS REPLACED AND TH	E A/C WAS CHECKED SERVICEABLE.  NR 1 IDG WAS ALSO REPLACED AT THIS TIME AND CHECKED SERVICEABLE CLEARING THE MEL. CYCLES	 SINCE OVERHAUL:4860 (TC NR 20071103001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100144	20080131	00144	NE  	2008	1	31	CA071105001      	2	20071101	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								114284			(CAN) CREW OBSERVED LOW OIL PRESSURE WARNING, FOLLOWED BY SMOKE IN THE CABIN. ELECTION WAS MADE TO PERFORM AN INFLIGHT E	NGINE SHUTDOWN.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.   FULL ENGINE SN GAS GENERATO	R MODULE: 114283 POWER SECTION MODULE: 114135 (TC NR 20071105001)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2008013100146	20080131	00146	EU  	2008	1	31	CA071105002      	1	20071102	G	2910	9433772104	HOSE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT MAIN GEAR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN TRYING TO INSTALL THE NEW LINE IT WOULD BIND UP HALF WAY ON,   HAD 2 NEW HOSES AND WHEN WE TRIED THE OTHER HO	SE IT WENT ON WITH NO PROBLEMS, SUSPECT THREADS ON  B-NUT FITTING ON NEW HOSE. (TC NR 20071105002)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008013100149	20080131	00149	NE  	2008	1	31	CA071105003      	2	20071024	G	7200		TRANSDUCER      			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					ECU	DEFECTIVE       	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								125146			(CAN) TAKEOFF WAS ABORTED DUE TO UNCOMMANDED POWER CHANGES OBSERVED ON GAUGES IN CONCERT WITH AIRCRAFT YAWING MOTION.  T	ROUBLESHOOTING DETERMINED THAT THE PT TRANSDUCER IN THE ELECTRONIC CONTROL WAS DEFECTIVE. PN AND SN TO BE SUPPLIED IN DU	E COURSE. (TC NR 20071105003)				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2008013100152	20080131	00152	EA  	2008	1	31	CA071105004      	1	20071030	G	5610	601R3303312	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	BROKEN          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA			12170								(CAN) OUTBOUND THE FOS SIDE WINDOW BROKE GOING THROUGH 20,000 FT.  MX REPLACED SIDE WINDOW (TC NR 20071105004)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100157	20080131	00157	NE  	2008	1	31	CA071105005      	2	20071026	G	7200	601R6000267	ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 1	FAILED          	W				O				OTHER                   				C	E		F.O.D.                    	VIBRATION/BUFFET          		CL	CLIMB          	1			CA			4404 					872911			(CAN) AFTER TAKEOFF, THE CREW SENT ACARS INDICATING THAT THE LT ENGINE HAD A HIGH VIB.  AFTER FOLLOWING THE QRH. THEY RE	DUCED POWER TO ACCOMMODATE THE VIB IN THE GREEN. IN SEPARATE ACARS, THEY HAD ANTI SKID MESSAGE. THEY CONTINUED AND ONCE 	ON THE GROUND DISCOVERED THAT THE NR 2 MAIN TIRE HAD SHREDDED AND PART OF THE DEBRI WENT INTO THE NR 1 ENGINE. 2 FAN BLA	DES WERE BENT AND 2 STATORS WERE CRACKED. THE NOSE COWL HAS A DENT THAT IS OUT OF LIMITS. THE REMAINING MAIN WHEEL TIRE 	PRESSURES WERE ALL ABOVE 200 PSI.  PARTS REPLACED:  STATOR SPACER PN 5128T05G01 NSN,  FAN BLADE C-25 PN 6018T30P06 SN KL	AJ6586  FAN BLADE L-11 PN 6018T30P06 SN KGAR3406 FAN BLADE C-22 PN 6018T30P14 SN KGACR870 FAN BLADE L-8 PN 6018T30P14 SN	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100160	20080131	00160	NM  	2008	1	31	CA071106001      	1	20071017	G	5610	NP17820110	WINDSHIELD      			GULSTM	200   	200         	4500308	NM  										COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			830  								(CAN) PILOT REPORTED RT WINDSHIELD CRACKED ON RETURN. C/O INSPECTION ON RT WINDSHIELD AND COULD NOT FAULT THE WINDSHIELD	. THE AIRCRAFT WAS RELEASE FOR RETURN TO SERVICE. THE AIRCRAFT MADE (3) OTHER TRIPS. THE PILOTS REPORTED THE SAME CRACK 	ON THE RT WINDSHIELD. AGAIN C/O THE INSPECTION ON THE RT WINDSHIELD AND COULD NOT FAULT. PILOTS REPORTED THEY COULD ONLY	 SEE THE CRACK WHEN THE AIRCRAFT IS AT ALTITUDE. SPOKE TO MFG AND DECIDED TO REPLACE THE WINDSHIELD. THE UNIT REMOVED WI	LL BE SENT BACK TO MFG AND THEY WILL REPORT ON THE FAILURE OF THE WINDSHIELD. THE NEW RT WINDSHIELD WAS INSTALLED AND TH	E AIRCRAFT HAD SEVERAL FLIGHTS WITH NO FURTHER REPORTS. (TC NR 20071106001)	2	L	7	2 	4F			RT	A53NM   					 
2008013100161	20080131	00161	CE  	2008	1	31	CA071106002      	1	20071105	G	3244	226K084	TIRE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			412  								(CAN) DURING AN INSPECTION, A BULGE WAS NOTICED ON THE NR 2 TIRE. THIS BULGE WAS NOTICED IN 3 SPOTS ON THE TIRE, EACH EX	TENDING FOR ABOUT 3 INCHES. THE BULGE STARTED AT THE CORNER OF THE TREAD AND EXTENDED TO THE SIDEWALL AND. THE TIRE WAS 	REPLACED. (TC NR 20071106002)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008013100164	20080131	00164	NM  	2008	1	31	CA071106003      	1	20071106	G	5330	146A323110	SKIN            			BOEING	737   	737990      	       	NM  										BS 777-830 RBL26	SCRATCHED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SCRATCHES ON FUSELAGE SKIN BELOW AFT CARGO PIT LOWER SILL BS 777 TO BS 830, RBL 26 REPAIRED IAW CUSTOMER EA. (TC N	R 20071106003)					2	L	7	4 	4F			RT	A16WE   					 
2008013100167	20080131	00167	NM  	2008	1	31	CA071106004      	1	20071106	G	5730	112A4102209	SKIN            			BOEING	737   	737990      	       	NM  										LWS 240	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WING LOWER SKIN PANEL CHAFFING AT WSTA 240, IB OF BLADE SEAL. REPAIRED IAW CUSTOMER EA (TC NR 20071106004)						2	L	7	4 	4F			RT	A16WE   					 
2008013100170	20080131	00170	NM  	2008	1	31	CA071106005      	1	20071106	G	5730	112A4102209	SKIN            			BOEING	737   	737990      	       	NM  										LWS 260	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WING LOWER SKIN PANEL CHAFFING DAMAGE AT WSTA 260, OB OF BLADE SEAL FAIRING. REPAIRED IAW CUSTOMER EA (TC NR 20	071106005)					2	L	7	4 	4F			RT	A16WE   					 
2008013100172	20080131	00172	NM  	2008	1	31	CA071106006      	1	20071106	G	5730	112A4102210	SKIN            			BOEING	737   	737990      	       	NM  										RWS 240	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING LOWER SKIN CHAFING DAMAGE AT WSTA 240, IB OF FAIRING SEAL REPAIRED IAW CUSTOMER EA (TC NR 20071106006)						2	L	7	4 	4F			RT	A16WE   					 
2008013100176	20080131	00176	CE  	2008	1	31	CA071106007      	1	20071106	G	2931	9536830	INDICATOR       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WE HAD A PRESSURE GAUGE THAT HAD A SMALL LEAK SO WE PURCHASED A NEW GAUGE FROM MFG AND INSTALLED IT ON THE AIRCRAF	T. WHEN SYSTEM WAS BROUGHT UP TO THE PROPER PRESSURE THE NEW GAUGE LEAKED WORSE THAN THE ORIGINAL GAUGE. THE GAUGE WAS S	ENT BACK TO BEECH AND WE ARE WAITING FOR A REPLACEMENT. THIS IS A QUALITY CONTROL ISSUE. (TC NR 20071106007)				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008013100179	20080131	00179	NE  	2008	1	31	CA071106008      	3	20071025	G	6110	31025731	RETAINER        			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROP SHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P44738			(CAN) WHILE ENGINE WAS BEING REPLACED MAINTENANCE NOTICED FATIQUE CRACKS EMINATING FROM THE (PROP SHAFT) RETAINING BOLT 	AREA. (TC NR 20071106008)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2008013100182	20080131	00182	SW  	2008	1	31	CA071106009      	1	20071026	G	3220	2752530001	ARM             			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG CENTER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROLLER BEARING OUTER CASE FOUND CRACKED COMPLETLY THROUGH. REPLACED AND RETURNED TO SERVICE (TC NR 20071106009)						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2008013100186	20080131	00186	WP  	2008	1	31	CA071106010      	2	20071030	G	7313	31032359	FUEL NOZZLE     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL NOTICED IN ENGINE COWL DURING INSPECTION. NOZZLE IN NR 3 POSITION FOUND CRACKED WHERE PRIMARY/SECONDARY LINES	 HOOK UP TO NOZZLE. CRACK WAS 95 PERCENT THROUGH CIRCUMFERENCE. (TC NR 20071106010)					2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
2008013100187	20080131	00187	EU  	2008	1	31	CA071106011      	1	20071025	G	2820	30733341	TUBE            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A PREFLIGHT INSPECTION, MAINTENANCE DISCOVERED THE FIRE DETECTOR (P/N 3001-31-900-400-17) AGAINST THE FUEL TUBE	 ASSEMBLY (P/N P-84417). UPON REPOSITIONING THE FIRE DETECTOR INTO POSITION, A CHAFED MARK ON THE NR 1 ENGINE FUEL TUBE 	ASSEMBLY WAS DISCOVERED. THE FUEL TUBE ASSEMBLY WAS ORDERED AND REPLACED. AN ENGINE RUN WAS CARRIED OUT FOR A LEAK CHECK	 INSPECTION. (TC NR 20071106011)			2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2008013100188	20080131	00188		2008	1	31	CA071106012      	4	20071104	G	2210	BACC18AE35	CIRCUIT BREAKER 			BOEING	737   	737*        	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  						FAILED          	W				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CR	CRUISE         	1			CA											(CAN) ENROUTE AT FL300, THE CREW EXPERIENCED AN AUTO PILOT DISENGAGEMENT AS WELL AS THE LOSS OF THE FOLLOWING, YAW DAMPE	R, MACH TRIM, CAPTS. PITOT STATIC, NR 1 ENG ANTI ICE, RADAR ALTIMETER, NO 2 EGT AND SEVERAL OTHERS.   THE CREW ATTEMPTED	 A RESET OF THE NR 1 NORMAL TRANSFER BUS CIRCUIT BREAKER, WHICH FAILED. THE AIRCRAFT WAS DIVERTED AND LANDED WITHOUT FUR	THER INCIDENT. MAINTENANCE REPLACED THE CIRCUIT BREAKER AND THE AIRCRAFT HAS RETURNED TO SERVICE WITHOUT FURTHER PROBLEM	. (TC NR 20071106012)		2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2008013100190	20080131	00190	EA  	2008	1	31	CA071107001      	2	20071103	G	7200		ENGINE          			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCE50661			(CAN) PILOTS HAD TO SHUTDOWN RT ENGINE. MAINTENANCE INSPECTION FOUND PROP WOULDN`T TURN, EXPECT POWER SECTION FAILURE. (	TC NR 20071107001)					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008013100193	20080131	00193	EA  	2008	1	31	CA071107002      	2	20071105	G	7230		BLADES          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COMPRESSOR	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA								PCE85202			(CAN) PILOTS OBSERVED SPARKS COMING OUT RT ENGINE EXHAUST ON LANDING. MAINTENANCE INSPECTION FOUND COMPRESSOR BLADES LAY	ING IN THE ENGINE BAY. (TC NR 20071107002)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008013100197	20080131	00197	CE  	2008	1	31	CA071107003      	1	20071107	G	2731	55657544	LEVER           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TRIM INDICATOR	WORN            	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			6834 								(CAN) PILOT ABORTED TAKEOFF DUE TO NO RESPONSE TO CONTROL COLUMN INPUT. UPON INSPECTION FOUND ELEVATOR TRIM TAB WAS ALMO	ST ON FULL NOSE DOWN POSITION AND TRIM INDICATION IN COCKPIT WAS AT TAKEOFF. FOUND INDICATOR LEVER AND CONTROL WHEEL WOR	N, INDICATOR LEVER HAD JUMPED ON CONTROL WHEEL TO GIVE WRONG INDICATION. TRIM CONTROL WHEEL AND INDICATOR LEVER REPLACED	 AND INDICATION SYSTEM RIGGED IAW AMM AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071107003)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008013100200	20080131	00200	EU  	2008	1	31	CA071107004      	1	20071107	G	5320	MS24693C273	SCREW           			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E5A1  	30022	NE  					P-ACE RACK	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4104 								(CAN) RETAINING SCREW FOR THE P-ACE (PRIMARY- ACTUATOR CONTROL ELECTRONICS) LT AND RT RACKS WERE THE WRONG SIZE (DIAMETE	R AND LENGTH TOO SMALL). THE RT P-ACE AND RACK WERE FREE FLOATING IN THE SLOT. THE LT P-ACE AND RACK WERE SECURED WITH T	HE WRONG HARDWARE. THE CORRECT P/N OF THE RETAINING SCREW IS MS24693C273.  (TC NR  20071107004)				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008013100202	20080131	00202	EA  	2008	1	31	CA071107005      	1	20071012	G	2730	TBC6CF11461	CABLE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATORS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1532 								(CAN) WHILE INSPECTING THE CONTROL CABLES IAW TRANSPORT,  ALERT (SDA) AL-2007-03, THE ELEVATOR CABLE WAS FOUND CHAFED AT	 THE PULLEYS AT STA 262.0.  THE LOCATION OF THE WEAR ON THE CABLE, IS DIRECTLY OVER THE PULLEYS WHEN THE CONTROL LOCKS A	RE IN. (TC NR 20071107005)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008013100209	20080131	00209	SW  	2008	1	31	CA071108001      	1	20071105	G	2400		ELECTRICAL SYS  			SWRNGN	SA227 	SA227AC     	8780603	SW  											FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA							AC739B				(CAN) A/C ENROUTE AT 6000 FT, EXPERIENCED TURBULENCE AND ST.ELMO`S FIRE. AFTER SOME TIME, LIGHTNING APPEARED AS A BLUE L	IGHT (AS REPORTED BY PASSENGER. IMMEDIATELY AFTER, ALL ELECTRICAL POWER (BOTH BATTERIES AND GENERATORS) WAS LOST. AIRCRE	W RESET THE BATTERIES AFTER ESTABLISHING A SAFE FLIGHT ATTITUDE WITH THEIR PERSONAL FLASH LIGHTS. POWER WAS RESTORED AS 	SOON AS BATTERY RESET WAS ATTEMPTED. FLIGHT CONTINUED. MAINTENANCE WAS CONTACTED. AS THERE WAS NO OBVIOUS DAMAGE, ENTRIE	S WERE MADE IN THE JOURNEY LOG AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071108001)		2	L	7	2 	4T			RT	A8SW    					 
2008013100212	20080131	00212	GL  	2008	1	31	CA071108003      	1	20071102	G	5740		ATTACH FITTING  	DHAV        		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	LIFT STRUTS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9690 			0140					(CAN) WHILE ACCOMPLISHING THE REQUIREMENTS OF SB 2/55, CRACKS WERE DETECTED ON THE LOWER LUGS OF BOTH WING LIFT STRUTS. 	IN BOTH CASES THE CRACKS WERE LOCATED ON THE IB FACE OF THE LUG AND WERE .7500 INCH LONG LT STRUT P/N C2W1103A, S/N 0140	 WAS CRACKED ON THE AFT FACE OF THE FWD LUG RT STRUT P/N C2W1104A S/N 0113 WAS CRACKED ON THE FWD FACE OF THE AFT LUG. S	. B. 2/41 WAS COMPLETED 1 YEAR AGO WITH NO FAULTS FOUND AT THAT TIME. THE AC OPERATES EXCLUSIVELY ON FLOATS IN A CORROSI	VE ENVIRONMENT. BOTH STRUTS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. TAT 18060.1 (TC NR 20071108003)		1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2008013100216	20080131	00216	NE  	2008	1	31	CA071108004      	2	20071025	G	7320	8228224004	EEC             			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					ENGINE	DEFECTIVE       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CG0214			(CAN) DURING FLIGHT, THE CREW RECIEVED A YELLOW, HIGH TEMPERATURE, (WARNING LIGHT). THE POWER WAS REDUCED AND THE FLIGHT	 WAS DIVERTED. TROUBLESHOOTING REVEALED A DEFECTIVE ELECTRONIC ENGINE CONTROL. (TC NR 20071108004)					2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
2008013100218	20080131	00218	NM  	2008	1	31	CA071108005      	1	20071105	G	2820	LJ35801	LINE            			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					NR 1 ENGINE	CHAFED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW NOTICED THAT NR1 ENGINE PARAMETERS WERE NOT AS SCHEDULED. AIRCRAFT RETURNED TO THE AIRPORT.	 WITH DECREASING ALTITUDE THE NR1 ENGINE PARAMETERS IMPROVED AND A NORMAL LANDING WAS PERFORMED. FOUND P1 LINE CHAFED TH	ROUGH. LINE REPLACED. TEST FLIGHT CONDUCTED. ALL PARAMETERS NORMAL. AIRCRAFT RETURNED TO SERVICE. (TC NR 20071108005)				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2008020400154	20080204	00154	NM  	2008	2	4	CA071108006      	1	20071107	G	3233	2630000004	ACTUATOR        			GULSTM	200   	200         	4500308	NM  										MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			855  								(CAN) AFTER TAKEOFF THE CREW REPORTED THAT THE GEAR WAS SELECTED UP AND THE NOSE AND RT MAIN GEAR RETRACTED WITH NO FAUL	T, THE LT GEAR DID NOT RETRACT.  THE CREW REPORTED THEY CYCLED THE GEAR DOWN AND THE (3) GREEN LIGHTS WAS ON EICAS INDIC	ATING DOWN AND LOCK.  ANOTHER ATTEMPT WAS MADE TO CYCLE THE GEAR UP, AGAIN ONLY THE NOSE AND THE RT MAIN RETRACTED. THE 	LT UNSAFE INDICATION WAS INDICATED ON EICAS.  THE CREW ELECTED TO CYCLE THE GEAR DOWN AGAIN AND WAS COMPLETED SUCCESSFUL	LY, (3) GREENS ON EICAS.THE AIRCRAFT WAS RETURNED TO POINT OF DEPARTURE AND LANDED NO PROBLEMS. MAINTENANCE WAS CALLED A	ND THE AIRCRAFT WAS PLACED ON JACKS C/O GEAR SWINGS. TROUBLESHOOTING REVEALED THAT THE LT GEAR ACTUATOR INTERNAL LOCKING	2	L	7	2 	4F			RT	A53NM   					 
2008013100222	20080131	00222	EU  	2008	1	31	CA071108007      	1	20071107	G	3210	200915254	LINK            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			32356	8282 							(CAN) IT HAS BEEN DISCOVERED DURING INSPECTION OF THE ABOVE MENTIONED PART THAT IT IS IN AN UNSERVICEABLE CONDITION. WHI	LE ON JACKS THE COMPONENT WAS INSPECTED AND MOVEMENT COULD BE FELT BETWEEN THE ROD ASSY AND EYE END. THE EYE END IS THRE	ADED INTO THE ROD FOLLOWED BY A JAMB NUT AND SAFETY ASSY. NO MOVEMENT IS PERMITTED. THERE IS EVIDENCE OF CORROSION DEPOS	ITS LEACHING THROUGH THE SEALANT. THIS IS THE SUSPECTED CAUSE. (TC NR 20071108007)			2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2008013100223	20080131	00223	NM  	2008	1	31	CA071109001      	1	20071105	G	2432	4011769	BATTERY         			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MASTER	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			16205	176  							(CAN) DURING ENGINE NR 2 START UP, THE NR STALLED AT 20 NR AND THE ITT INDICATOR REACHED 800 DEGREES CELSIUS. THE ENGINE	 START WAS ABORTED FOLLOWING BY A LOUD BANG FROM THE NOSE COMPARTMENT.  MAINTENANCE WAS CALLED IN AND THEY FOUND THE MAI	N BATTERY TOP COVER POPPED OUT. NO STRUCTURAL DAMAGE WAS OBSERVED. THE MAIN AND AUXILIARY BATTERIES WERE REPLACED. THE A	IRCRAFT WAS RELEASE AND RETURNED INTO SERVICE. (TC NR 20071109001)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008013100224	20080131	00224	CE  	2008	1	31	CA071109002      	1	20071107	G	2731	55657544	LEVER           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TRIM WHEEL	INOPERATIVE     	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			6834 								(CAN) PILOT ABORTED TAKEOFF. UPON INSPECTION FOUND ELEVATOR TRIM TAB WAS ALMOST ON FULL NOSE DOWN TRIM POSITION. TRIM IN	DICATION IN THE COCKPIT WAS AT TAKEOFF. FOUND THAT THE INDICATOR LEVER HAD JUMPED ON THE CONTROL WHEEL TO GIVE THE WRONG	 INDICATION. TRIM CONTROL WHEEL AND INDICATOR LEVER REPLACED AND INDICATION SYSTEM RIGGED IAW AMM. (TC NR 20071109002)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008013100225	20080131	00225	EU  	2008	1	31	CA071109003      	1	20071109	G	7820	L24266710000	BAFFLE          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	EXHAUST SILENCER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION, ONE INTERNAL BAFFLE OF THE PRIMARY EXHAUST SILENCER WAS FOUND TO BE CRACKED 25 PERCE	NT OF THE ATTACHING WELD. SILENCER WAS SUBSEQUENTLY REPLACED. (TC NR 20071109003)					1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2008013100226	20080131	00226	NE  	2008	1	31	CA071109004      	2	20071005	G	8520	16475	CRANKCASE       			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1141 				21739			(CAN) DURING RUNUP AFTER INSPECTION, INVESTIGATION OF A MINOR OIL LEAK REVEALED THAT THE ENGINE CRANKCASE WAS CRACKED NE	AR AN ENGINE THROUGHBOLT AT THE BASE OF NR 2 CYLINDER, BETWEEN CYLS NR 2 AND NR 3. THE ENGINE WAS REPLACED. (TC NR 20071	109004)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2008020400153	20080204	00153	NE  	2008	2	4	CA071109005      	2	20071108	G	7321	7898435010	ECU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2  ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA								PCE120178			(CAN) AC EXPERIENCED AN IN FLIGHT ENGINE SHUTDOWN OF THE NR 2 ENG ON DESCENT ABOUT 20 MILES FROM DESTINATION. CREW REPOR	TED NO DISCREPANCIES PRIOR TO THE INCIDENT. THE CREW DID NOT ATTEMPT A RESTART BUT DECIDED TO LAND AS CONFIGURED. THE EC	U FAULT LIGHT DID NOT ILLUMINATE AFTER ENGINE SHUTDOWN. THE RT UP-TRIM LIGHT ILLUMINATED AFTER THE ENGINE QUIT IN FLIGHT	 AS REPORTED BY THE PILOTS. MAINT VISUALLY INSPECTED THE ENGINE FOR OBVIOUS DEFECTS, NONE NOTED. THE ENGINE DRIVEN FUEL 	PUMP AND HMU WERE REMOVED TO CHECK FOR FUEL PUMP CONDITION. NO FAULTS NOTED. FUEL FILTERS AND ENGINE OIL FILTERS WERE IN	SPECTED OK. NO BYPASS OR FUEL CLOG ANNUNCIATIONS NOTED. THE ENGINE WAS DRY MOTORED TO LISTEN FOR UNUSUAL NOISES (TOWER S	2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008013100244	20080131	00244	SW  	2008	1	31	CA071109006      	1	20071108	G	7720	850568503	INDICATOR       			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ITT	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA							11192				(CAN) DURING CRUISE THE NR2 ENGINE ITT INDICATION BECAME ERRATIC, THEN CLIMBED THROUGH THE RED LINE. THE FLIGHT CREW SHU	TDOWN THE ENGINE AND FEATHERED THE PROP. THE AIRCRAFT RETURNED TO AIRPORT. MAINTENANCE TESTED THE ITT SYSTEM AND FOUND T	HE INDICATOR TO BE AT FAULT. THE ITT INDICATOR WILL BE REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT WILL BE RETURNE	D TO SERVICE. (TC NR 20071109006)			1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P15EA	 
2008013100246	20080131	00246	CE  	2008	1	31	CA071109007      	1	20071013	G	2750	C1450046	GEAR            	CESSNA      		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	TRANSMISSION	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			2880 								(CAN) THE PILOT WAS ON DECENT AND WENT TO SELECT FLAPS AND THE CIRCUIT BREAKER POPPED AFTER THE FLAPS WERE AT ABOUT 10 D	EGREES. HE THEN LANDED THE AIRCRAFT NORMALLY. MAINTENANCE FOUND THE FLAP TRANSMISSION TO BE MAKING NOISE OUT OF THE NORM	. THE INTERNAL GEAR THAT DRIVES THE TRANSMISSION JACK SCREW WAS FOUND TO HAVE CHIPS OUT OF A FEW TEETH. THE TRANSMISSION	 WAS REPLACED AND SYSTEM FUNCTIONED NORMAL. (TC NR 20071109007)			1	H	7	1 	3T	3	T		A37CE   	E4EA	6	C	P15EA	 
2008013100248	20080131	00248	NE  	2008	1	31	CA071109008      	2	20071103	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1859 	407  							(CAN) ENGINE DRIVEN PUMP FOUND TO BE WEAK WILL NOT SUSTAIN ENGINE IDLE ON IT`S OWN. (TC NR 20071109008)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100250	20080131	00250	WP  	2008	1	31	CA071109009      	1	20071103	G	2822	D7431	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			902  	902  							(CAN) ELECTRIC AUX FUEL PUMP WEAK, MOTOR SOUNDED LIKE IT WAS OVERWORKING. (TC NR 20071109009)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100252	20080131	00252	NE  	2008	1	31	CA071109010      	2	20071103	G	7322	25766304	FUEL CONTROL    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1859 	1859 							(CAN) DURING MAINTENANCE GROUND RUN, THE ENGINE WAS HESITATING AT 70 PERCENT AND THEN DROOPS TO 65 PERCENT OR LESS. FUEL	 CONTROL NOT RESPONDING TO THROTTLE INPUT CORRECTLY. (TC NR 20071109010)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008013100254	20080131	00254	EA  	2008	1	31	CA071109011      	2	20071108	G	8530	LW13870	CYLINDER        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				438  							(CAN) DURING A 50 HOUR INSPECTION, BOTTOM SPARK PLUG ON CYLINDER NR 5 REVEALED UNUSUAL AMOUNT OF OIL. A COMPRESSION TEST	 WAS CARRIED OUT AND CYLINDER NR 5 WAS NOTED TO HAVE 18 OVER 80 PSI COMPRESSION.  TSO WILL HAVE TO BE VERIFIED. (TC NR 2	0071109011)				1	G	7	1 	3O	3	O		H11NM   	E295				 
2008013100255	20080131	00255	NM  	2008	1	31	CA071112001      	1	20071111	G	3297	473901	WIRE HARNESS    			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, NOSE GEAR UNSAFE ILLUMINATED. CREW PERFORMED NORMAL EXTENSION AND THE NLG DOORS DID NOT OPEN. ALSO,	 NLG NOT SHOWING DOWN AND LOCKED. SECOND ATTEMPT FOR EXTENSION, NOSE DOOR AMBER LIGHT ILLUMINATED. CREW PERFORMED ALTERN	ATE EXTENSION AND LANDED WITHOUT FURTHER INCIDENTS.   MAINTENENCE DISCOVERED PSEU REPORTED FAULT, NLG LOCK PROX 1. NOSE 	LOCK SENSOR REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20071112001)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008013100256	20080131	00256	WP  	2008	1	31	CA071112002      	1	20071026	G	2720	369A75058	BRACKET         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					RUDDER PEDELS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15663								(CAN) RUDDER PEDALS WERE FOUND TO BE LOOSE IN MOUNTS ON FURTHER INVESTIGATION IT WAS FOUND THE BRACKET THAT THE RUDDER P	EDALS MOUNT IN WAS BROKEN ON (3) OF THE (4) MOUNTING BOLT EARS. (TC NR 20071112002)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2008013100258	20080131	00258	EU  	2008	1	31	CA071112003      	1	20071109	G	2612		FIRE LOOP       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 1 NACELLE	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, ENGINE NR 1 FIRE-WARNING ALARM WENT OFF. THE FLIGHT CREW INFORMED TOWER AND RETURNED TO AIRPORT.  A	 HOLE WAS FOUND IN THE FLEXIBLE DUCT AT THE SUPERCHARGER OUTLET.  ALSO, (2) FIRE DETECTION LOOPS WERE REPLACED BECAUSE T	HEY FAILED THE RESISTANCE CHECK LIMITS FOUND IN THE HS 748 MM. (TC NR 20071112003)				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
2008013100259	20080131	00259	NM  	2008	1	31	CA071113001      	1	20071110	G	6120	699018002	CONTROLLER      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLER	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING FLIGHT, CREW REPORTED A NR 2 PEC CAUTION LIGHT ILLUMINATED FOLLOWED BY THE NR 2 ENGINE NP SURGE. THE QRH CO	NSULTED AND THE NR 2 ENGINE WAS SHUTDOWN.  EMU DOWNLOAD C/O, FAULT ISOLATION C/O FOR CODES 236 AND 260 IAW TASK 61-20-05	-810-822, 61-20-06-810-818. SERVO VALVE CONNECTORS RT J26 AND J27 CLEANED AND TREATED WITH STABILANT. PEC CONNECTORS 20 	AND 21 CLEANED AND TREATED WITH STABILANT. AUTO FEATHER AND UP TRIM CHECKED SERVICEABLE FOR RETURN TO SERVICE IAW TASK 6	1-20-00-710-801. FURTHER FAULT CODE 131 DISPLAYED IN CDS.  RT PEC REPLACED IAW AMM 61-20-36 AND C/O IAW AMM 71-00-00, NI	L FAULTS EVIDENT. (TC NR 20071113001)	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008013100260	20080131	00260	NE  	2008	1	31	CA071113003      	2	20071106	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA								PC1078			(CAN) SHORTLY AFTER TAKEOFF WHILE PERFORMING A LOW LEVEL TURN, THE ENGINE REPORTEDLY LOST POWER. EMERGENCY POWER LEVER W	AS ACTIVATED WITH NO RESPONSE. AIRCRAFT LANDED ON A STREET, NO FATALITIES. INITIAL INVESTIGATION REVEALED NO EVIDENCE OF	 PRE-IMPACT ANOMALIES. FUEL SYSTEM COMPONENTS WILL BE INVESTIGATED.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVIS	E OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071113003)			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008013100261	20080131	00261	NE  	2008	1	31	CA071113005      	2	20071106	G	7321	32448809	FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA								JC0359			(CAN) DURING APPROACH, ENGINE SPEED DESCENDED TO SUBNORMAL VALUE. NO/SLOW RESPONSE FROM THRUST LEVER. CONDITION WAS REPE	ATABLE ON GROUND FOLLOWING THE INCIDENT. FUEL CONTROL CHANGED AS PART OF TROUBLESHOOTING. (TC NR 20071113005)					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2008020400152	20080204	00152	EA  	2008	2	4	CA071113006      	1	20071112	G	3340	BJ10021003	CAMLOCK         	BRUCE       	BJ10021003  	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					LIGHT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0075					(CAN) DURING AN OVERNIGHT MAINTENANCE INSPECTION IT WAS DISCOVERED THAT THE LT WING INSPECTION LIGHT LENS WAS MISSING TO	GETHER WITH THE BULB HOLDER LEAVING THE WIRES EXPOSED. WHEN THE FAIRING WAS REMOVED TO REPLACE THE ASSEMBLY IT WAS NOTIC	ED THAT A CAMLOC NUT HAD BEEN STRETCHED CAUSING THE FASTENER TO BE LOOSE. FORTUNATELY THE MISSING PARTS DID NOT DAMAGE T	HE AIRCRAFT OR THE ENGINE. (TC NR20071113006)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008020400151	20080204	00151	EU  	2008	2	4	CA071113007      	1	20071108	G	2510	5PC41301001	DOUBLER         	ISRAEL      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	SEAT PAN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2763 			386					(CAN) DOUBLER INSTALLED ON CRACKED SEAT PAN WEB IAW SB 5PC41000-MOD1, FOUND CRACKED. NEW DOUBLER PN 5PC41301-001 INSTALL	ED. (TC NR 20071113007)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008020400150	20080204	00150	EA  	2008	2	4	CA071113008      	1	20071106	G	5610	NP13932111	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     	30049	NE  					COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			11455								(CAN) CREW REPORT THAT AT 360 THE CAPTS FWD WINDOW SHATTERED AND THEY DIVERTED WINDOW REPLACED (TC NR 20071113008)						2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008020400149	20080204	00149	NE  	2008	2	4	CA071113009      	2	20071108	G	7261		CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					ACTUATOR	DEFECTIVE       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			17457								(CAN) AFTER TAKEOFF, CREW GOT A (SMOKE TOILET CAUTION MESSAGE). CABIN WAS FILLED WITH SMOKE. AFTER QRH WAS COMPLETED RET	URNED TO FIELD AND MESSAGE WAS GONE A SHORT WHILE AFTER.   MX FOUND OIL LEAKING FROM ENGINE VARIABLE GUIDE VANE (VG) ACT	UATOR STRUTS AND LEAKING INTO THE BLEEDS. SUSPECT NR 3 CARBON SEAL. SLC REPLACED THE RT ENGINE. (TC NR 20071113009)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008020400148	20080204	00148	NE  	2008	2	4	CA071113010      	2	20071105	G	7261		CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 3	LEAKING         	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) JUST AFTER TAKEOFF, THE CABIN STARTED TO FILL WITH SMOKE AND THE LAV SMOKE DETECTOR WENT OFF. THEY DECLARED EMERGE	NCY AND RETURNED TO THE FIELD. NO EVACUATION, SMOKE CLEARED ON LANDING. MX FOUND THE RT ENGINE NR3 CARBON SEAL TO BE FAU	LTY.  MX REPLACED RT ENGINE (TC NR 20071113010)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008020400147	20080204	00147	SO  	2008	2	4	CA071114001      	1	20071022	G	2435		HOUSING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			112  			FN2407123					(CAN) MOTOR ATTACH BOLT PULLING OUT OF HOUSING. NOT AN INFLIGHT SAFETY CONCERN. (TC NR 20071114001)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008020400146	20080204	00146	SO  	2008	2	4	CA071114002      	1	20071109	G	2435		CASE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50   			FNR510603					(CAN) MOTOR ATTACH BOLT PULLING OUT OF HOUSING. (TC NR 20071114002)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008020400145	20080204	00145	CE  	2008	2	4	CA071114003      	1	20070924	G	3246	31607	WHEEL           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2114 								(CAN) RIM WAS EDDY CURRENT INSPECTED FOR CRACKS IAW MM AND CORROSION PITS WERE FOUND ON RIMS (IB AND OB) WHERE TIRE MAKE	S AIR SEAL.  THE CORROSION PITS WERE MORE THAN 0.010 INCH ALLOWED AND WHEEL WAS SCRAPPED. (TC NR 20071114003)					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2008020400144	20080204	00144	WP  	2008	2	4	CA071114004      	1	20071005	G	2140	C16932	SHROUD          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HEATER	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			1288 								(CAN) THE PILOT SMELLED EXHAUST FUMES IN THE CABIN WHILE IN CRUISE FLIGHT. THE PILOT THEN CLOSED THE HEATER CONTROL AND 	OPENED THE VENTS FOR FRESH AIR. THE PILOT THEN FLEW  BACK TO THE BASE FOR THE ENGINEER TO INSPECT.  THE ENGINEER FOUND A	 CRACK IN THE EXHAUST SYSTEM INSIDE THE HEAT SHROUD AT THE ELBOW WHERE THE EXHAUST EXITS THE MUFFLER. THE EXHAUST SYSTEM	 WAS THEN REPLACED WITH A NEW PART. (TC NR 20071114004)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008020400143	20080204	00143		2008	2	4	CA071114005      	4	20071109	G	3418		TRANSMITTER     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AOA	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1873 			0321					(CAN) DURING ROUTINE 150 HR INSP , LT AOA VANE HEAT WAS FOUND INOPERATIVE. PROBE AND PLATE HEAT WERE FUNCTIONING NORMAL.	 COMPLETE ASSY REPLACED. (TC NR 20071114005)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008020400142	20080204	00142	CE  	2008	2	4	CA071114006      	1	20070928	G	2435	300SGL129Q2	STARTER GEN     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  						FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA				671  							(CAN) AC INFLIGHT HAD RT GENERATOR OUTPUT FLUCTUATING. CHECKED ON GENERATOR IAW MM WAS FOUND OK. BUT INFLIGHT FLUCTUATIN	G, REPLACED GENERATOR AND PROBLEM WENT AWAY. (TC NR 20071114006)					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2008020400141	20080204	00141	EU  	2008	2	4	CA071114007      	1	20071012	G	6320	BM1021	CHIP DETECTOR   	UROCOP      		UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					M/R GEARBOX	SHORTED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			33   			M672					(CAN) MAIN GEARBOX MAGNETIC CHIP PLUG SHORTED INTERNALLY. (TC NR 20071114007)						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008020400140	20080204	00140	CE  	2008	2	4	CA071114008      	1	20071102	G	3297		WIRE HARNESS    			CESSNA	525   	525         	2076601	CE  										BRAKES	SHORTED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE EMERGENCY BRAKE HAD TO BE USED UPON LANDING AS IT WAS DISCOVERED THAT THE ANTI-SKID WIRING HARNESS HAD A SMALL	 AMOUNT OF SLACK BETWEEN THE TRAILING LINK AND THE TRUNNION. THIS ALLOWED IT TO RUB AGAINST THE TIRE, WEARING OFF THE CO	ATING AND UPON LANDING ON A WET SURFACE CAUSED SHORTING. (TC NR 20071114008)				1	L	7	2 	4F			RT	A1WI    					 
2008020400139	20080204	00139	CE  	2008	2	4	CA071114009      	1	20070913	G	3211	998100287	BRACE           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	MLG TORQUE LINK	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				6269 							(CAN) FLIGHT CREW CONDUCTED A CROSSWIND LANDING, SHUTDOWN, AND PASSENGERS DEPLANED ON REMOTE RAMP LOCATION. UPON TAXIING	 TO THE TERMINAL FOR THE NEXT FLIGHT, CREW NOTICED THE AIRCRAFT FELT DIFFERENT. MAINTENANCE WAS CALLED, AND A VISUAL INS	PECTION FOUND THAT THE LT MLG TRUNNION BOSS ASSY HAD BROKEN AWAY. FURTHER INVESTIGATION REVEALED THE RT MLG WAS CRACKED 	IN THE SAME AREA. A HARD-LANDING INSPECTION WAS COMPLETED IAW CARS 625 APP G, AND  AMM 5-50-00 AS A PRECAUTIONARY MEASUR	E. MAIN LANDING GEAR ASSEMBLIES WERE REPLACED, SERVICED, AND GEAR SWINGS CONDUCTED IAW AMM. (TC NR 20071114009)		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
2008020400138	20080204	00138	CE  	2008	2	4	CA071114010      	1	20071114	G	5751	0523809	RIB             			CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	LT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9500 	9500 							(CAN) AILERON CENTER RIB P/N 0523809 FOUND CRACKED MULTIPLE LOCATIONS ON FWD VERTICAL ANGLE COMMON TO CONTROL ROD ATTACH	 BRACKET.  IN ADDITION THE CONTROL ROD ATTACH BRACKET P/N 0760011-2 WAS ALSO CRACKED IN 2 LOCATIONS COMMON TO AILERON SP	AR. (TC NR 20071114010)				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2008020400137	20080204	00137	EU  	2008	2	4	CA071115001      	1	20071110	G	5343	S53578400000	FITTING         			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	MLG ACTUATOR	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			29987								(CAN) DURING THE APPROACH, THE CREW HEARD A LOUD BANG WHEN THE LANDING GEAR WAS SELECTED DOWN. THE CREW DID NOT OBSERVE 	ANY OTHER WARNING INDICATIONS AND A NORMAL LANDING WAS COMPLETED. THE CREW CONDUCTED A POST LANDING CHECK AND FOUND THE 	LT MLG EXTENTION/RETRACTION ACTUATOR SEPARATED FROM THE AIRCRAFT. THE FUSELAGE MOUNTING FITTING HAD FAILED. THE AIRCRAFT	 MOVED FOR MAINTENANCE ACTION. THE COMPANY HAS INITIATED A FLEET CAMPAIGN TO INSPECT ALL ACTUATOR FITTINGS. (TC NR 20071	115001)		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008020400136	20080204	00136	EA  	2008	2	4	CA071115002      	1	20071024	G	3246	L814749	BEARING         			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	WHEEL ASSY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING THE LT OB MAIN WHEEL HUBCAP WAS DISCOVERED MISSING. FURTHER INVESTIGATION FOUND THE INNER BEARING WA	S BLOWN APART, THE WHEEL AND BRAKE ASSY HAD EXTENSIVE DAMAGE FROM THE WHEEL RUBBING ON THE BRAKE ASSY. THE AXLE WAS INSP	ECTED, NO DAMAGE WAS FOUND. DUE TO ALL THE RAIN IN THE AREA, THIS AIRCRAFT IS OPERATING IN A EXTREMELY MUDDY ENVIRONMENT	, WE SUSPECT THAT MUD AND WATER MAY HAVE ENTERED THE BEARING AREA CAUSING PREMATURE FAILURE OF BEARING. THIS BEARING HAD	 144 LANDINGS SINCE NEW.  CURRENTLY, THE BEARINGS ARE INSPECTED AND RE-LUBRICATED AT THE (A) CHECK (150 HOURS). THIS INS	PECTION ALONG WITH THE LUBRICATION OF THE LANDING GEAR WILL BE REDUCED TO 50 HOURS FOR THE DURATION OF THE OPERATION IN 	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2008020400135	20080204	00135	GL  	2008	2	4	CA071115003      	2	20071115	G	7230	6871259	BOLT            	ALLSN       							ALLSN 	250C  	250C20J     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3486 					CAC43118			(CAN) COMPRESSOR TIEBOLT S/N KU506716 FOUND CRACKED AXIALLY UPON REWORK AT MPI AFTER REMOVAL OF SILVER PLATING ON EXTERI	OR OF PART. PART SCRAPPED.  CRACK WAS NOT DISCOVERED UPON INITIAL MPI, MOST LIKELY BECAUSE OF THE SILVER PLATE BRIDGING 	THE CRACK SURFACE.   SEM EVALUATION OF CRACK INDICATED A DEPTH OF APPROXIMATELY 600 MICRO METERS RADIALLY . EDS EVALUATI	ON OF THE CRACK INDICATED THAT THE CRACK WAS FULL TO EXTREMITIES WITH IRON OXIDE. THIS APPEARS TO BE A MANUFACTURING DEF	ECT. NO ASSOCIATED DAMAGE OR SERVICE ISSUES NOTED ON REMAINDER OF COMPRESSOR ASSEMBLY. HARDNESS OF MATERIAL WAS WITHIN S	PECIFICATIONS. FAILURE OF BOLT WOULD BE CATASTROPHIC. (TC NR 20071115003)						3	U			E4CE				 
2008020400134	20080204	00134	EA  	2008	2	4	CA071115004      	1	20071115	G	7120	CSP28229	BOLT            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE MOUNT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1739 								(CAN) ENGINE MOUNT BOLTS THAT DAMAGED THE THREADS UPON REMOVAL. BOLTS WHERE INSTALLED ON 12/22/2005. (2) OF THE (4) TOP 	MOUNT BOLTS HAVE DAMAGED THREADS AND ARE NOT RE-USABLE. THREADS IN ENGINE CASE REQUIRE CLEAN-UP. (TC 20071115004)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008020400133	20080204	00133	EU  	2008	2	4	CA071115005      	1	20071115	G	6400	355A12004008	TAIL ROTOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  						OUT OF BALANCE  	W				K				NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			CA											(CAN) UNABLE TO BALANCE T/R WITH OUT LARGE AMOUNTS OF BALANCE WEIGHT. T/R WOULD GO OUT OF BALANCE EVERY 3 TO 4 DAYS. SEN	DING T/R TO MFG FOR EVALUATION. (TC NR 20071115005)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008020400132	20080204	00132	EA  	2008	2	4	CA071115006      	1	20071115	G	2497		BUSS BAR        			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	DAMAGED	SPARKS          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							1968				(CAN) CPB1 CENTER BUS BAR LINK W57PD SPARKING UNDER LOOSED SCREW.  BUS BAR W57PD AND W440PD REPLACED.  10029 DROPS (TC N	R 20071115006)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008020400131	20080204	00131	NE  	2008	2	4	CA071115007      	1	20071114	G	6320	SB2151107	BEARING         			SKRSKY	S76   	S76C        	8143008	NE  										M/R GEARBOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2969 			A23100240					(CAN) MGB REMOVED DUE TO MAKING METAL, THE ABOVE BEARING WAS FOUND TO BE SPALLED (TC NR 20071115007)						1	G	7	2 	3U			NC	H1NE    					 
2008013100262	20080131	00262	GL  	2008	1	31	CA071115008      	1	20071031	G	7602	HF3M	BEARING         	DIAMON      		DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ROD END	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			244  								(CAN) PILOT REPORTED MIXTURE STICKING DIFFICULT TO MOVE. INSPECTION REVEALED MIXTURE CONTROL ROD END AT MECHANICAL FUEL 	PUMP SEIZED. ROD END WAS REPLACED WITH NEW UNIT. THIS ROD END IS OF THE SAME PN WHICH SEIZED ON ANOTHER AIRCRAFT`S THROT	TLE CONTROL WHICH RESULTED IN AN OFF AIRPORT LANDING AND DAMAGE TO THE AIRCRAFT BACK IN FEB. 2005. HOPING TO HAVE THE BE	ARING ANALYZED BY A LAB. (TC NR 20071115008)			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2008013100263	20080131	00263	EU  	2008	1	31	CA071115009      	1	20071115	G	6410	355A12004008	TAIL ROTOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  						UNBALANCED      	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			1067 								(CAN) EXCESSIVE AMOUNT OF TIP BALANCE WEIGHT TO BALANCE TAIL ROTOR. (TC NR 20071115009)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008013100264	20080131	00264	EA  	2008	1	31	CA071115010      	1	20071112	G	5312	C6W11509	RIB             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29229								(CAN) RIB FLANGE FOUND CRACKED ON IB SIDE WHERE IT IS RIVETED TO THE TOP SKIN CORRUGATIONS. CRACKING FOUND WHEN INSPECTI	NG RIBS 8-22 IAW MFG STRUCTURAL LIFE LIMITS. (TC NR 20071115010)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008013100265	20080131	00265	EA  	2008	1	31	CA071115011      	1	20071114	G	5532	C6TFM102527	PLATE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			31743								(CAN) CRACK INDICATION FOUND IN A CORROSION PIT IN THE AFT ATTACH PLATE WHEN INSPECTING IT IAW SB 454. (TC NR 2007111501	1)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008013100266	20080131	00266	SW  	2008	1	31	CA071116001      	1	20071114	G	3040		SENSOR          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	WINDSHIELD TEMP	OVERHEATED      	W				O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		AP	APPROACH       	1			CA			4805 			87H0829830					(CAN) THE FOLLOWING WAS REPORTED BY THE FLIGHT CREW FOLLOWING THE CO-PILOTS HEATED WINDSHIELD FAILURE: (WHILE ON THE ILS	 FO MENTIONED A BURNING SMELL, AND NOTICED IT AS WELL.) TOOK MY FLASHLIGHT OUT BUT COULD NOT NOTICE ANY DETECTABLE SMOKE	 IN THE CABIN OR COCKPIT. CONTINUED THE APPROACH WITH BLEED HEAT OFF AND FRESH AIR FAN RUNNING. BY THE TIME WE LANDED, T	HE SMELL WAS STRONGER BUT COULD NOT SEE ANY SMOKE. ON THE GROUND WE SHUTDOWN THE ELECTRONICS AS SOON AS POSSIBLE AND THE	N SHUT DOWN THE AIRCRAFT. PASSENGERS NOTICED THE SMELL IN THE BACK AS WELL. IT WAS OBVIOUS THAT IT WAS AN ELECTRICAL SME	LL, AND THERE WAS SMOKE EVIDENT WHEN WE TOOK OUT OUR FLASHLIGHTS AGAIN ON THE GROUND.  UPON INSPECTION BY MAINTENANCE IT	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2008013100267	20080131	00267	CE  	2008	1	31	CA071116002      	1	20071115	G	3610	1013800273	REGULATOR VALVE 			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	PNEUMATIC PRESS	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				210  							(CAN) WHILE IN CRUISE FLIGHT AT FL230 THE FLIGHT CREW OBSERVED THE PNEUMATIC PRESSURE GUAGE RAPIDLY FLUCTUATING BETWEEN 	18 AND 23 PSI. THERE WAS AN ASSOCIATED CHATTERING HEARD IN THE AIRFRAME, IN CONJUNCTION WITH THE FLUCTUATING INDICATOR. 	FLIGHT CREW DECIDED TO RETURN TO BASE AND PNEUMATIC INDICATIONS RETURNED TO NORMAL DESCENDING THROUGH 15,000 FEET AND RE	MAINED THAT WAY TO LANDING. MAINTENANCE REPLACED PNEUMATIC PRESSURE VALVE/REGULATOR PN 101-380027-3 (PN 1H75-12). (TC NR	 20071116002)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008013100269	20080131	00269	EA  	2008	1	31	CA071118001      	1	20071115	G	2730	510009	ROD END         	MENASCO     	510009      	CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C5     	30050	NE  					PCU	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						MAL2449					(CAN) REPORT FROM AIR ONE:  REF /A/ - AIPC 27-33-01, FIG 1  WHILE PERFORMING TASK CARD 000-27-220-010 - OPERATIONAL TEST	 OF THE ELEVATOR PCUS, AIR ONE FOUND THAT WITH HYD 1 ONLY, THE ELEVATOR WOULD NOT MOVE.  AFTER INSPECTION, THEY FOUND TH	AT PCU 1 ROD END (ON THE ELEVATOR ATTACHING LUG) WAS BROKEN IN (2) PIECES AT THE PCU PISTON THREADS.  PRIOR REMOVING ANY	THING, IT WAS NOTICED THAT THE ROD END SEEMED JAMMED (UNABLE TO TURN THE ROD END AROUND THE BOLT) ON ITS ATTACHING BOLT 	(REF /A/ ITEM 275)  WHILE ATTEMPTING TO REMOVE THE BROKEN ROD END, THE ATTACHING NUT (REF /A/, ITEM 295) WAS EASILY REMO	VABLE. HOWEVER, IT WAS NOT POSSIBLE TO TURN OR REMOVE THE BOLT (REF /A/, ITEM 275) FROM THE ELEVATOR PCU FITTING (REF SR	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008013100270	20080131	00270	EA  	2008	1	31	CA071118002      	1	20071108	G	5610	NP13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5B1   	30052	NE  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN FLIGHT LT WINDSHIELD CRACKED, AIRCRAFT CONTINUED TO DESTINATION. NO FURTHER REPORTED DETAILS. (TC NR 2007111800	2)					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008013100271	20080131	00271		2008	1	31	CA071119001      	4	20071106	G	2210	065008617	CONTROL MODULE  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EADI	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) (ALT) LAMP DID NOT ILLUMINATE ON MODE CONTROL. ALTITUDE CAPTURE WAS NORMAL WITH ALT CAPTIONS (ON) AS DISPLAYED ON 	BOTH EADI SCREENS. (TC NR20071119001)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008013100272	20080131	00272		2008	1	31	CA071119002      	4	20071115	G	3497		CONNECTOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	OAT INDICATOR	DAMAGED         	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			7326 								(CAN) OAT INDICATION ON EIS ERRACTIC. ONE OF THE PINS IN OAT CONNECTOR FOUND LOOSE. NEW CONNECTOR INSTALLED WITH 2 NEW P	INS. SYSTEM NORMAL.  (TC NR 20071119002)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008013100273	20080131	00273	EU  	2008	1	31	CA071119003      	1	20071115	G	3110	0660312525	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EADI	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT`S EADI DISPLAY REPORTED TO GO (FUZZY) AND INTERMITTENTLY GOING BLANK. ED462 REPLACED WITH SERVICEABLE UNIT. 	(TC NR 20071119003)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008022100004	20080221	00004	NM  	2008	2	21	CA071120001      	1	20071115	G	2910	82970010149	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			20516								(CAN) AIRCRAFT WAS RETURNING TO BASE WHEN THE HYDRAULIC LOW PRESSURE LIGHT ILLUMINATED. UPON SELECTION OF GEAR DOWN A LO	UD (BANGING) NOISE WAS HEARD. GEAR EXTENDED NORMALLY, ALTHOUGH THE LOW PRESSURE LIGHTS WERE FLICKERING IN CONJUNCTION WI	TH THE (BANGING) NOISE. AC WAS PLACED IN HANGER AND HYDRAULIC SYSTEM INSPECTED. THE RESERVOIR WAS FOUND TO BE LOW. RESER	VOIR WAS REFILLED AND HYDRAULIC SYSTEM BLED, IT WAS AT THIS TIME THAT FLUID WAS OBSERVED TO BE LEAKING FROM ABOVE THE NR	 2 ENGINE EXHAUST PIPE.  UPON FURTHER INSPECTION THE PRESSURE LINE (82970010-149, PRE-MOD 8/670) WAS FOUND TO BE SEVEREL	Y CHAFED. IT APPEARS TO HAVE BEEN CHAFED BY SPIRAL WRAP APPLIED TO THE SUCTION LINE, THE LINE WAS ALSO CLAMPED, BUT IMPR	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022100005	20080221	00005	NE  	2008	2	21	CA071120002      	2	20071115	G	7230		COMPRESSOR      			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	ENGINE	STALLED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			25972	4926 				GEE785555			(CAN) TAKEOFF ROLL HAD NO PROBLEMS, BUT WHEN CHANGING THROTTLE SETTING FROM CLIMB POWER TO CRUISE POWER THE LT ENGINE EX	PERIENCED A COMPRESSOR STALL. THEN THE A/C YAWED, THEN ANOTHER COMPRESSOR STALL OCCURRED AND THE (ENGINE) OVER TEMP`D.  	 LITE FOR THE ITT CAME ON, THE PILOTS THEN SHUT THE LT ENGINE DOWN AND RETURNED TO AIRPORT ON THE RT ENGINE. (TC NR 2007	1120002)			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2008022100006	20080221	00006	SW  	2008	2	21	CA071120004      	1	20071116	G	6420	476411731	SHIM            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R HUB	INOPERATIVE     	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA						A3402					(CAN) T/R VIBRATION DISCOVERED AND SUBSEQUENT STROBING WAS NOT EFFECTIVE AT REMOVING THE VIBRATION. DURING INSPECTION OF	 THE T/R HUB ASSEMBLY WAS FOUND TO HAVE BOTH PRE AND POST (TB: 206-91-139) METHODS OF TRUNNION CENTERING PERFORMED. SHIM	 120-006C15-0 AND THRUST PLUG 47-641-173-1 USED ON ONE SIDE AND SHIM 206-011-861-101 AND THRUST PLUG 206-011-862-101 USE	D ON THE OTHER. TAIL ROTOR HUB ASSEMBLY WAS REPAIRED. (TC NR 20071120004)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008020400130	20080204	00130		2008	2	4	CA071120005      	4	20071119	G	3160	066031252500	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LT EHSI WENT BLANK AND BACK ON TWICE DURING FLIGHT. DEFECT WAS CONFIRMED IN THE HANGAR AS THE DISPL	AY WENT BLANK APPROX. 3 MINUTES AFTER POWER UP. (TC NR 20071120005)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008020400129	20080204	00129	EU  	2008	2	4	CA071120006      	1	20071106	G	2140	704A34402034	HOSE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					HEATER	BURST           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HEATER LINE FROM ENGINE FOUND BURST AND NOT SUPPLYING ALL THE HEAT TO THE CABIN. (TC NR 20071120006)						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022100007	20080221	00007	EU  	2008	2	21	CA071120007      	1	20071110	G	7921	350A5310520351	BLOWER MOTOR    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					OIL COOLER	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) HEARD NOISE AFTER LANDING AND SHUT THE AIRCRAFT DOWN. UPON INSPECTION FOUND THE BLOWER ROTOR COMPLETELY GONE. REPL	ACED THE ROTOR, DUCT AND MOTOR TO GET THE AIRCRAFT SERVICEABLE. (TC NR 20071120007)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022100008	20080221	00008	GL  	2008	2	21	CA071121001      	3	20071118	G	6111		BUSHING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROP HUB	WORN            	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			3729 						962459		(CAN) THE PILOTS FELT A VIBRATION ON CLIMB. THEY REDUCED THE POWER BUT THE VIBRATION REMAINED. THEY RETURNED TO THE AIRP	ORT WHERE THE AME INSPECTED THE ENGINE AND PROPELLER. NO DISCREPANCIES WERE NOTED ON THE ENGINE. ONE BLADE OF THE PROP W	AS ABLE TO BE TWISTED BY HAND APPOX 3-5 DEGS. WE SUSPECT A FAILURE OF A BUSHING IN THE HUB AND HAVE SENT A REPLACEMENT P	ROP BEFORE FURTHER FLIGHT. (TC NR20071121001)			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008022100009	20080221	00009	SW  	2008	2	21	CA071121003      	1	20071115	G	2497	AN3230	SWITCH          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	BUSS TIE	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED STRANGE SMELL COMING FROM LT BLEED IN COCKPIT. AFTER TROUBLESHOOTING BY MAINTENANCE IT WAS FOUND TH	AT LT ESSENTIAL BUS TIE SWITCH WAS CRACKED AND THE WIRE CONNECTORS GOING TO THE LT CB PANEL HAD BECOME OVERHEATED AND ME	LTED THE HEAT SHRINK AND THE RUBBER PROTECTIVE BOOT AT THE TERMINALS. BUS TIE SWITCH REPLACED AND BOTH CONNECTORS REPAIR	ED. (TC NR 20071121003)			2	L	7	2 	4T	3	T	RT	A8SW    	E2WE	6	C	3PNE	 
2008022100010	20080221	00010	NM  	2008	2	21	CA071121004      	1	20071120	G	2150		TURBINE         			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	A/C PACK	SEIZED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			350  								(CAN) AIRCRAFT DEVELOPED WHITE SMOKE IN CABIN WHILE TAXING FOR TAKEOFF. PILOTS NOTICED A CAS LT PACK FAIL LIGHT AND AN A	FT LAV SMOKE DETECT CAS MESSAGE. AIRCRAFT RETURNED TO BLOCKS AND PASSENGERS DEBOARDED. CAUSE OF SMOKE WAS TURBINE SEIZED	 CAUSING A LT PACK OVERHEAT. ENVIROMENTAL CONTROL UNIT (ECU) REPLACED. (TC NR 20071121004)				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2008022100011	20080221	00011	EU  	2008	2	21	CA071122001      	1	20071116	G	3234	F10A793	CONTROL HANDLE  			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG EMER EXTEND	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			5874 								(CAN) DURING THE CLIMB, THE LT MAIN LANDING GEAR INTRANSIT STAYED ON DURING GEAR RETRACTION. THE CREW FLEW BACK TO DEPAR	TURE WITH THE GEAR DOWN. AFTER THEY LANDED AT DEPARTURE AIRPORT. WE INSPECTED THE GEAR IAW THE MM AND CAR 605.88. IT WAS	 FOUND THAT THE MANUAL EMERGENCY HANDLE WAS OFF SET SLIGHTLY CAUSING THE GEAR NOT TO FULLY LOCK IN THE UP POSITION. THE 	EMERGENCY CONTROL SYS WAS RESET IAW THE MM. SATISFACTORY GEAR SWINGS WERE CARRIED OUT.  CALLED FOR A TEST FLIGHT, THE TE	ST FLIGHT WAS CARRIED OUT WITH NO FAULTS. (TC NR 20071122001)		2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2008022100012	20080221	00012	CE  	2008	2	21	CA071122002      	1	20071121	G	3210	508103237	TORQUE LINK     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SPECIAL LPI INSP (SELF IMPOSED INSPECTION DUE TO BROKEN LINK SEE SDR NR 2007024010) OF THE UPPER AND LOWE	R TORQUE LINKS ON (2) OF OUR AC, (3) TORQUE LINKS WERE FOUND CRACKED IN THE RADIUS AREA.  ONE LINK HAS 2 CRACKS SIDE BY 	SIDE THE OTHER HAD ONE SMALLER CRACK. THE CRACK IN THE THIRD LINK WAS VERY SMALL AND DID NOT SHOW IN THE PHOTOS. (TC NR 	20071122002)			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2008022100016	20080221	00016	NM  	2008	2	21	CA071122003      	1	20071122	G	3246	296852629	BEARING         			BOMBDR	DHC8  	DHC8400     	       	NM  										NR 4 WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1584 	70   							(CAN) WHILE SERVICING THE MAINT OBSERVED SWARF AND GREASE AROUND THE HUBCAP OF NR 4 MAIN WHEEL ASSY. IB BEARING HAD FAIL	ED. (TC NR 20071122003)					2	H	7	2 	4T			RT	A13NM   					 
2008022100017	20080221	00017	SW  	2008	2	21	CA071122004      	1	20071123	G	2810	71494R	TANK            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FUEL SYS	CRACKED         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			3206 								(CAN) AIRCRAFT WAS IN FOR A 50 HR INSPECTION. AFTER ENGINE RUN UP, MECHANIC DETECTED GAS FUMES AND LOOKED ON THE RT SIDE	 ON THE AC WINGS NEAR TRAILING EDGE NOTICE FUEL STAINING. RT OB TANK WAS REMOVED AND 1 INCH CRACK WAS FOUND ON THE RADIU	S OF THE LATERAL RE-ENFORCEMENT INDENT OF TANK. (TC NR 20071122004)				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2008022100018	20080221	00018	NM  	2008	2	21	CA071122006      	1	20071109	G	3230	656021132	ACCESSORY UNIT  			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) THE CREW DISCOVERED THAT THE LANDING GEAR HANDLE WOULD NOT MOVE PAST THE (OFF) POSITION WITHOUT THE USE OF THE OVE	RRIDE TRIGGER. AT THE TERMINATING STATION, MAINTENANCE REPLACED THE LANDING GEAR ACCY UNIT AND RETURNED THE AIRCRAFT TO 	SERVICE. (TC NR 20071122006)				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008022100019	20080221	00019	NE  	2008	2	21	CA071122007      	2	20071121	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1242 	1242 							(CAN) ENGINE START ATTEMPTED, RT MAGNETO FAILED TO OPERATE. (TC NR 20071122007)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100020	20080221	00020	SO  	2008	2	21	CA071123001      	1	20071120	G	8120		BEARING         	GARRTT      		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			357  	357  		JJR00638					(CAN) DURING A RT ENGINE INSPECTION AN EXHAUST STAIN WAS WAS NOTICED IN THE AREA OF THE TURBOCHARGER.  UPON CLOSER INVES	TIGATION, IT WAS DISCOVERED THAT THE TURBOCHAGERS EXHAUST BEARING SEAL BETWEEN THE COMPRESSOR AND TURBINE HAD FAILED. TH	E TURBO WAS REPLACED AND AC RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20071123001)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008022100021	20080221	00021	EU  	2008	2	21	CA071123002      	1	20071123	G	7700		ENGINE          		ARRIEL2B    	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  						MALFUNCTIONED   	W				R				AUTOROTATION            				J			WARNING INDICATION        			CR	CRUISE         	1			CA								22360			(CAN) PILOT IN CRUISE FLIGHT, APPROX 2000 FEET, EXPERIENCED ENGINE PROBLEMS WITH ANNUNCIATOR INDICATIONS . PROCEEDED WIT	H SUCCESSFUL AUTOROTATION LANDING IN FIELD.  REST IS UNDER INVESTIGATION (TC NR 20071123002)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008022100022	20080221	00022	CE  	2008	2	21	CA071123003      	1	20071122	G	7120	595104814	MOUNT           			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6126 								(CAN) WHILE PERFORMING MFG 100 HR ENGINE INSPECTION ON THE RT ENGINE, THE OB ENGINE MOUNT WAS FOUND CRACKED. THE MOUNT W	AS REPLACED WITH A NEW UNIT. (TC NR 20071123003)					1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
2008022100023	20080221	00023	EA  	2008	2	21	CA071123004      	1	20071116	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT SIDE WINDOW CRACKED ON FLIGHT. AC RETURNED.  NO FURTHER INFORMATION REPORTED BY CREW.  RT SIDE WINDOW CHANGED A	ND AC RETURNED TO SERVICE. (TC NR 20071123004)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022100024	20080221	00024	WP  	2008	2	21	CA071123005      	2	20071122	G	7210		REDUCTION GB    			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R333	R333482F12  	GL  	LT ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			18925	4525 				P63283			(CAN) WHILE IN CRUISE AT 16000 FT,  A THUMP WAS FELT AND HEARD FROM THE LT ENGINE.  A LARGE POWER DROP WAS NOTICED THEN 	A SECOND THUMP FROM THE LT ENGINE WHICH WAS FOLLOWED BY THE OIL CAP ANNUNCIATION ILLUMINATION.  IMMEDIATELY TURNED BACK 	AND SHUT THE ENG DOWN. ATC, COMPANY, AND PASSENGERS WERE ADVISED AND REQUESTED THE EMERGENCY VEHICLES BE ON STANDBY, THE	 REMAINDER OF THE FLIGHT AND LANDING WERE UNEVENTFUL.  MAINT INSP OF LT ENGINE REVEALED LIMITED ENGINE ROTATION WHEN TUR	NING THE PROP, INDICATING RGB INTERNAL COMPONENT/S FAILURE. LT ENGINE CHIP DETECTOR AND OIL FILTER WERE REMOVED AND META	L CONTAMINATION WAS OBSERVED IN BOTH AREAS. THE ENGINE WAS REMOVED FOR SHIPMENT TO A REPAIR FACILITY FOR TEAR DOWN DAMAG	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2008022100025	20080221	00025	NE  	2008	2	21	CA071126001      	2	20071123	G	7310	87620102007015	CONTROL ROD     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUEL SYS	SEPARATED       	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL, THE NR 1 ENG PROPELLER RPM ONLY REACHED 900 RPM (NORMAL 1200RPM) AND THE TORQUE INDICATION REACHE	D 115 PERCENT FOR APPROX  2 SECONDS. POWER LEVERS WERE RETARDED TO FLIGHT IDLE AND THE TAKEOFF ABORTED, AC RETURNED TO T	HE GATE. THE PROPELLER WOULD NOT FEATHER NORMALLY SO MANUAL FEATHER WAS SELECTED TO FEATHER AND WHEN THE FUEL CONDITION 	WAS SET TO SHUTOFF, THE ENGINE DID NOT SHUTDOWN AND THE FIRE T-HANDLE HAD TO BE PULLED TO SHUTDOWN.  MAINT INVESTIGATED 	AND IT WAS FOUND THAT THE FUEL CONDITION CONTROL ROD HAD SEPARATED, THEREFORE THERE WAS NO FUEL SHUTOFF CONTROL.  THE FU	EL CONDITION CONTROL ROD WAS REPLACED (PN 87620134-003 INSTALLED, 72-20-00-05-150) AND THE AC RETURNED TO SERVICE. (TC N	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022100026	20080221	00026	GL  	2008	2	21	CA071126002      	3	20071110	G	6110	1192	DIAPHRAGM       			NAVION	STC   	STCNAVION   	       	    	CONT  	E225  	E2254       	17015	SO  	HARTZL	HC12X	HC12X207    	GL  	PROPELLER	SPLIT           	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA									NAV4779		(CAN) RUBBER ON DIAPHRAM WAS FOUND SPLIT AT INNER SECTION. UNCERTAIN AS TO WHY THE RUBBER APPEARED STIFFER THAN THE PREV	IOUS DIAPHRAM. THE DIAPHRAM IS BEING RETURNED TO MFG FOR INSP.  WILL UPDATE WHEN RECEIVE THE INFORMATION BACK FROM THE M	FG. (TC NR 20071126002)				1	L	7	1 	3O	3	O		A782    	E267	5	C	P845	 
2008022100027	20080221	00027	EA  	2008	2	21	CA071126003      	1	20071123	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAP	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			2    	2    							(CAN) FLAP FAIL CAUTION MESSAGE ILLUMINATED WHILE IN CRUISE AND FLAPS WERE AT 0 DEG. FLAPLESS LANDING C/O AND A/C LANDED	 SAFELY. MAINT RANG OUT WIRES AND COULD NOT FIND ANY FAULTS. THE FECU AND THE RT BPSU WERE REPLACED. A TEST FLIGHT WAS C	/O TO COLD SOAK TEMPERATURES FOR (2) HOURS AND THE A/C TESTED SERVICEABLE. THERE HAS NOT BEEN A REOCCURRENCE AT THIS TIM	E.  (TC NR 20071126003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022100028	20080221	00028	CE  	2008	2	21	CA071126006      	1	20071106	G	8011	35016R	GEAR            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	STARTER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				360  				814153R			(CAN) STARTER DRIVE ENGAGES ON TEETH ON GEAR. STARTER WAS SLIPPING, TOOK APART TO EXAMINE AND FOUND 3 BROKEN TEETH. STAR	TER IS LIGHT WEIGHT. REPLACE STARTER SOLENOID 19 HOURS EARLIER AND BELIEVE FAULTY SOLENOID CAUSE OF PROBLEM. (TC NR 2007	1126006)				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2008022100029	20080221	00029	WP  	2008	2	21	CA071126007      	2	20071108	G	7200	21190108000	COMPUTER        			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					DEEC	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			7    								(CAN) ENGINES FRESH, NEW INSTALLATION OF DEECS ON AC. DEEC PROBLEMS OCCURRED.  THE PROBLEM ENCOUNTERED WITH DIGITAL ENGI	NE COMPUTERS (DEEC). (TC NR 20071126007)					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2008022100030	20080221	00030	EA  	2008	2	21	CA071126008      	1	20071122	G	2420	766283C	GCU             			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C5     	30050	NE  					NR 2	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) ACCORDING TO THE CREW WRITE UP: NR1- HYD 3A FAILED ( HYP PUMP 3A CAUTION MSG POSTED) ELECTRICALLY POWERED BY AC BU	S NR2 - (GEN2 FAILED) WE DID NOT GET A AMBER GEN FAIL INDICATION OR WARNING. AC BUS 2 FAILED AGAIN, NO WARNING. TRU 2 AN	D ESS TRU FAILED, NO WARNING. GEN AND IDG PINK ON SYNOPTIC PAGE AND PURPLE DASH LINES FOR KVA, V, HZ. GEN1 DID NOT PIC	K UP AC BUS 2.  MAINTENANCE RAN THE ENGINES, CYCLED THE IDG SW (AUTO/OFF/RESET), COULD NOT DUPLICATE.  PLACED A GCU ON O	RDER. BASED ON THE MDC INFORMATION.  GCU  NR 2 REPLACED. (TC NR 20071126008)		2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022100031	20080221	00031	EA  	2008	2	21	CA071126009      	1	20071123	G	7110	2285000808	COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NACELLE	BROKEN          	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) UPON LANDING, DURING THE OPERATION OF NR1 THRUST REVERSER THE NR 1 ENGINE UPPER FAN COWL DEPARTED THE AC.  THE PIL	OTS DID NOT NOTICE THAT THE COWLING WAS MISSING UNTIL THEY DID THEIR POST FLIGHT WALK-AROUND. THE COWLING WAS LATER FOUN	D BY AIRPORT OPERATIONS ON THE AIRFIELD OFF THE SIDE OF THE RUNWAY. THE COWLING WAS FOUND TO BE BROKEN IN HALF WHEN IT W	AS RECOVERED. THE FAA STILL HAS POSSESSION OF THE COWING AT THIS TIME. (WILL ADD COWL SN WHEN THEY ARE MADE AVAILABLE) (	TC NR  20071126009)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022100032	20080221	00032	NE  	2008	2	21	CA071126010      	1	20071122	G	6320	S613566300	GEARBOX         			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			30833	961  							(CAN) INTERMEDIATE GEAR BOX CHIP LIGHT ILLUMINATED IN FLIGHT. AFTER LANDING CHIP PLUG INSPECTION CONFIRMED METAL CONTAMI	NATION, AS WELL AS PAINT DISCOLORATION WAS NOTED IN THE INPUT BRG AREA.  ASSY WILL BE SENT TO OH SHOP FOR INVESTIGATION.	 (TC NR 20071126010)				2	G	7	2 	4U	4	U		1H15    	1E3				 
2008022100033	20080221	00033	SW  	2008	2	21	CA071126011      	1	20071113	G	6320	212030154101	FITTING         	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					LIFT BEAM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE INSPECTION OF THE LIFT LINK AREA, A CRACK WAS NOTED ON THE LIFT LINK FITTING. UPON FURTHER INVESTIGATIO	N THE AFT EAR WAS COMPLETLY BROKEN FROM THE FITTING. THE BOLT SECURING THE LIFT LINK TO THE FITTING WAS INCORRECT FOR TH	AT PN OF FITTING. THE BOLT DID FIT THE AFT EAR HOWEVER THERE WAS A .030 INCH GAP BETWEEN THE BOLT AND BUSHING IN THE FWD	 EAR ALLOWING THE BOLT TO ROCK UP AND DOWN IN THE FITTING. THIS ROCKING MOTION OCCURRED EVERY TIME IT WAS UNDER LOAD, AN	D STRESSED THE AFT EAR SUBSEQUENTLY CAUSING IT TO CRACK. THE TRANSMISSION WAS INSTALLED IN 2001. ALL ENGINEERS MUST BE C	ERTAIN WHEN INSTALLING FASTERNERS OR COMPONENTS THAT CORRECT PARTS ARE BEING USED ESPECIALLY WHEN DISASSEMBLY WHEN OFTEN	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008022100034	20080221	00034	SW  	2008	2	21	CA071126012      	1	20071121	G	5302	206030446001	BULKHEAD        	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BCJN07214					(CAN) LT AFT MOUNTING HOLE FOR T/R GEARBOX FOUND CRACKED. (TC NR 20071126012)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008022100035	20080221	00035	EU  	2008	2	21	CA071127001      	1	20071120	G	2913	3508806	PUMP            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					HYD SYSTEM	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				180  							(CAN) DURING CRUISE, THE YELLOW HYD SYS OVERHEAT ECAM MESSAGE CAME ON. LATER THE HYD RESERVOIR (LO LEVEL) WARNING CAME O	N THE ECAM. NORMAL QRH PROCEDURE WAS PERFORMED. DURING INVESTIGATION, MAINT FOUND YELLOW HYD PUMP LEAKING. HYD PUMP CASI	NG WAS CRACKED. PUMP AND FILTERS WERE REPLACED AND AC RETURN TO SERVICE. UNSERVICEABLE PUMP WAS ROUTED TO REPAIR SHOP FO	R INVESTIGATION. (TC NR 20071127001)			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2008022100036	20080221	00036	EU  	2008	2	21	CA071127002      	1	20071121	G	2530	HE62190	COFFEEMAKER     			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					GALLEY	SPARKS          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			20783	1782 							(CAN) DURING FLIGHT, THE F/A REPORTED THE FWD COFFEE MAKER/WATER BOILER OVERHEATING AND NOTICED SOME SPARK COMING FROM T	HE UNIT. THE UNIT WAS DEACTIVATED. THE UNIT WAS REPLACED BY MAINTENANCE AND ROUTED TO THE REPAIR SHOP FOR INVESTIGATION.	 (TC NR 20071127002)				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2008022100037	20080221	00037	WP  	2008	2	21	CA071127003      	1	20071126	G	6210	C1591	BEARING         	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					M/R BLADE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			652  			5470A					(CAN) WHILE CONDUCTING A DI, THE M/R BLADE BOOT WAS FOUND DISTORTED. THE BOOT WAS REPLACED AND A CHECK OF THE SPINDLE BE	ARINGS WERE FOUND TO BE ROUGH. FURTHER INVESTIGATION REVEALED THE NR 6 BEARING INNER RACE WAS FOUND SPALLING. BEARING RE	PLACED AND ASSY REINSTALLED. (TC NR 20071127003)				1	G	7	1 	3O	3	O		H11NM   	E295				 
2008022100038	20080221	00038	WP  	2008	2	21	CA071127004      	1	20071120	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1848 								(CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION THE FWD LT SERVO WAS FOUND LEAKING. THE SERVO WAS CHANGED, GROUND RUN AND	 LEAK CHECK CARRIED OUT WITH OUT FURTHER INCIDENT. (TC NR 20071127004)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100039	20080221	00039	NE  	2008	2	21	CA071127005      	2	20071125	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	FAILED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA			355  								(CAN) WHEN PILOT TRIED TO PULL THE AC UP IN A HOVER, THE ENGINE DECELERATED (BOGGED DOWN) UNTIL THE COLLECTIVE WAS LOWER	ED. THIS WAS TRIED SEVERAL TIMES WITH NO SUCCESS. ALL INDICATIONS WERE NORMAL, TEMPS, PRESSURES, MAG DROPS, ETC.  WHILE 	WAITING FOR THE ENGINEER TO ARRIVE ON SITE, THE PILOT GROUND RAN THE AC FOR 40 MIN TO WARM IT UP AND TRIED TO PULL POWER	 AGAIN. THIS TIME THE AC LIFTED UP NORMALLY WITH NO SYMPTOMS WHATSOEVER. WHEN THE ENGINEER ARRIVED THE AC WAS INSPECTED 	AND NO DEFECTS WERE FOUND. A 5 MIN TEST FLIGHT WAS COMPLETED WITH NO ABNORMAL SYMPTOMS. THE AC WAS SHUTDOWN AND REFUELED	 TO BE REPOSITIONED TO ANOTHER LOCATION.  AFTER RE-STARTING AND WHILE TRANSITIONING FROM A HOVER TO FWD FLIGHT, THE ENGI	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100040	20080221	00040	SW  	2008	2	21	CA071127006      	1	20071122	G	5302		BULKHEAD        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAILBOOM	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFT BULKHEAD P/N 206-030-446-001F CRACKED AT RT GEARBOX MOUNTING HOLE. (TC NR 20071127006)						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008022100041	20080221	00041	SO  	2008	2	21	CA071127007      	1	20071122	G	8120	LW12778	BUTTERFLY VALVE 	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	WARPED          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				1487 		RL145668A					(CAN) THE AC WOULD NOT GET FULL POWER ON THE RT ENGINE. AFTER A RUNUP ALL PARAMETERS WERE NORMAL AND THE TAKEOFF RESUMED	. MAINT INSPECTED THE ENGINE AND FOUND THE BUTTERFLY VALVE TUBE THAT GOES OVER THE SHAFT WAS WARPED AND SPLIT. THIS WAS 	PROBABLY CAUSING AN INTERMITTENT STICKINESS IN THE BUTTERFLY. THE WASTEGATE WAS REPLACED WITH NO FURTHER ISSUES. (TC NR 	20071127007)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008022100042	20080221	00042	EA  	2008	2	21	CA071127008      	1	20071121	G	5610	NP13932114	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) F/O WINDSHIELD SHATTERED OUTSIDE LAYERS AT FL340. (TC NR 20071127008)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022100043	20080221	00043	EA  	2008	2	21	CA071127009      	1	20071120	G	5610	13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGH 32,400 ON OUR WAY TO 34,000 WE HEARD A POP AND SAW THE PILOTS WINDSHIELD CRACK/ SPLINTER. FOLLOWE	D QRH AND CONTINUED TO DESTINATION.  (TC NR 20071127009)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022100044	20080221	00044	NM  	2008	2	21	CA071127010      	1	20071123	G	3297		CONNECTOR       			GULSTM	200   	200         	4500308	NM  										NLG STEERING SYS	CONTAMINATED    	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			878  								(CAN) AIRCRAFT LANDED, PILOT REPORTED NO NOSE WHEEL STEERING. PARKED AIRCRAFT AT FBO. LATER A/C WAS TAKEN TO MFG. THE NO	SE WHEELING SYSTEM WAS INSPECTED AND MOISTURE WAS FOUND IN THE FEEDBACK POTENTIOMETER CONNECTOR PLUG. CLEANED AND RECONN	ECTED CONNECTOR PLUG, APPLY SEALANT TO THE CONNECTOR PLUG AND THE COVER FOR THE FEEDBACK POTENTIOMETER.  C/O FUNCTION CH	ECKS ON SYSTEM OK.   AIRCRAFT RELEASE FOR RETURN TO SERVICE. (TC NR 20071127010)			2	L	7	2 	4F			RT	A53NM   					 
2008022100045	20080221	00045	SW  	2008	2	21	CA071127011      	1	20071105	G	6320	2120400545	FITTING         	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				785  		ABT301					(CAN) ON ROUTINE INSPECTION, A CRACK WAS NOTED IN THE LIFT LINK FITTING. TRANSMISSION WAS REMOVED AND SENT FOR REPAIR. T	HE TSO FOR THE COMPLETE TRANSMISSION WAS AT 785.1 AND TT 19803.1. NO AVAILABLE INFORMATION FOR TT ON THE SUMP ASSY CASE.	 (TC NR 20071127011)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008022100046	20080221	00046	EU  	2008	2	21	CA071128001      	1	20071106	G	6130		PROP BRAKE      			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					PROPELLER	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								127023			(CAN) SHORTLY AFTER ENGINE START, CREW OBSERVED A PROP BRAKE WARNING LIGHT FOLLOWED BY A FIRE WARNING. ENGINE WAS SECURE	D AND THE AIRCRAFT EVACUATED.  INITIAL INVESTIGATION REVEALED A SEVERELY DAMAGED PROPELLER BRAKE ASSY.  MFG WILL CONTINU	E INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071128001)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2008022100047	20080221	00047	NE  	2008	2	21	CA071128002      	2	20071108	G	7532	31J285704	TORQUE MOTOR    			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					BLEED VALVE	DEFECTIVE       	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA								DD0396			(CAN) DURING DESCENT, CREW NOTED ENGINE NOISE, FOLLOWED BY A REVERSION OF THE EEC TO MANUAL. ENGINE POWER LEVEL REMAINED	 AT FLIGHT IDLE.  INVESTIGATION REVEALED A DEFECTIVE BLEED VALVE TORQUE MOTOR. (TC NR 20071128002)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008022100048	20080221	00048	NE  	2008	2	21	CA071128003      	2	20071108	G	7200		HMU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA								120178			(CAN) OPERATOR REPORTED UNCOMMANDED ENGINE SHUTDOWN AND EEC REVERSION DURING CLIMB. EEC WAS LATER REPLACED ON GROUND AND	 OPERATION WAS NORMAL. HMU WAS ALSO REPLACED AS A PRECAUTION. BOTH UNITS WILL BE RETURNED TO MFG FOR INVESTIGATION AND F	OLLOW UP. (TC NR 20071128003)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008022100049	20080221	00049	NE  	2008	2	21	CA071128004      	2	20071112	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  						SEIZED          	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								93211			(CAN) CREW REPORT FLASH OF LIGHT FOLLOWED BY SPARKS FROM ENGINE, AND ELECTED TO PERFORM AN INFLIGHT SHUTDOWN. AFTER LAND	ING AND DURING INITIAL INVESTIGATION, THE PROPELLER COULD NOT BE ROTATED.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND	 ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR20071128004)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008030600204	20080306	00204	NM  	2008	3	6	CA071128005      	1	20071020	G	4920		TURBINE BLADES  	PWC         		BOEING	747   	747400      	13848AT	NM  										APU ENGINE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						900663					(CAN) DURING AC B-CHECK, AIRFRAME APU COMPARTMENT IMPACT DAMAGE WAS OBSERVED CAUSED BY APPARENT TURBINE BLADE LIBERATION	 AND CASE FLANGE SEPARATION.  THE APU HAD BEEN DECLARED INOPERATIVE BY THE OPERATOR SINCE OCTOBER 20 2007.  MFG WILL CON	TINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071128005)				2	L	7	4 	4F			RT	A20WE   					 
2008022100050	20080221	00050	EA  	2008	2	21	CA071128006      	2	20071103	G	7200		ENGINE          			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		SURGES          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								40865			(CAN) DURING CRUISE, THE CREW OBSERVED ENGINE (SURGES) AND PERFORMED AN INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION REVEAL	ED A SEIZED PROPELLER SHAFT AND POWER TURBINE BLADE DISTRESS.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF R	OOT CAUSE ONCE ESTABLISHED (TC NR 20071128006)				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008022100051	20080221	00051	WP  	2008	2	21	CA071128007      	1	20071024	G	5311	C04621	FRAME           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUSELAGE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1314 								(CAN) THE HELICOPTER WAS IN FOR A SCHEDULED 100 HOUR INSPECTION AND THE BROKEN FRAME WAS DISCOVERED BY THE AME. THE AIRC	RAFT WAS GROUNDED AND A NEW PART WAS ORDERED AND INSTALLED. (TC NR 20071128007)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100052	20080221	00052	CE  	2008	2	21	CA071128008      	1	20071128	G	2435		BRUSHES         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	STARTER GEN	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				670  		12527					(CAN) WHILE ON FINAL THE PILOT NOTICED THAT THE LT GENERATOR HAD FAILED. UPON LANDING, AN INSPECTION WAS CARRIED OUT ON 	THE GENERATOR. IT WAS NOTICED THAT THE BRUSHES WERE ALL BROKEN WHICH WOULD INDICATE AN INTERNAL FAILURE. (TC NR 20071128	008)				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008022100053	20080221	00053	NE  	2008	2	21	CA071128009      	2	20071116	G	7261	AS3209014	O-RING          			BRAERO	1000  	BAE1251000A 	1500104	EU  	PWA   	305   	PW305B      	52128	NE  					NR 4 BEARING	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								305025			(CAN) CREW REPORTED OIL PRESSURE FLUCTUATIONS AND ILLUMINATION OF THE LOW OIL PRESSURE WARNING INDICATOR. THE ENGINE WAS	 SHUTDOWN AND THE FLIGHT DIVERTED.  INVESTIGATION REVEALED DEFECTIVE O-RINGS ON THE  NR4 BEARING TRANSFER TUBES (TC NR 2	0071128009)				2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
2008022100054	20080221	00054	CE  	2008	2	21	CA071128010      	1	20071116	G	5344	051218712	BULKHEAD        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	DOOR FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4714 								(CAN) WHILE CARRYING OUT THE SEB 97-1 AFT DOORPOST INSPECTION, CRACKS WERE NOTED AT THE SUBJECT AREAS ON BOTH DOORPOSTS 	(IPC "CHANNEL-BULKHEAD"). SUBMITTER SUSPECTS THAT TAXIING OVER ROUGH SURFACES, OR POSSIBLY HARD OR CRABBED LANDINGS, CON	TRIBUTES TO THE FLEXING OF THE BULKHEAD THAT RESULTS IN THE CRACKING.  CRACKS ARE FOUND BY LOOKING WITH LIGHT AND MIRROR	 FORWARD NEAR THE AILERON CABLE PULLEY AT THE BOTTOM OF THE AFT DOORPOSTS. THE CRACK RADIATES FROM THE RELIEF CUTOUT WHE	RE THE INSIDE FLANGE OF THE BULKHEAD CHANGES FROM VERTICAL TO HORIZONTAL.  (TC NR 20071128010)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2008022100055	20080221	00055	NE  	2008	2	21	CA071128011      	2	20071031	G	7321		FUEL CONTROL    			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	INOPERATIVE     	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								JG0033			(CAN) DURING CRUISE, ENGINE POWER GRADUALLY REDUCED FROM 102 PERCENT N1 INDICATION TO 74 PERCENT. NO RESPONSE TO THROTTL	E LEVER MOVEMENT. FLIGHT WAS DIVERTED AND AIRCRAFT LANDED WITH BOTH ENGINES RUNNING.  THE ENGINE FUEL CONTROL WAS REPLAC	ED AND AIRCRAFT RETURNED TO SERVICE.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE	D. (TC NR 20071128011)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2008032000004	20080320	00004	GL  	2008	3	20	CA071128012      	1	20071123	G	2432	GE50C	BATTERY         			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	12D	12D40       	NE  	MASTER	SHORTED         	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA			253  								(CAN) AC SUFFERED ALMOST AN ENTIRE ELECTRICAL FAILURE DURING CLIMBOUT. AFTER SUBSEQUENT UNSCHEDULED LANDING, IT WAS DETE	RMINED THAT THE BATTERY HAD ACQUIRED AN INTERNAL SHORT, WHICH DEPLETED THE GENERATOR OUTPUT AND CAUSED THE AVIONICS TO M	ALFUNCTION.  BATTERY REPLACED WITH A SERVICEABLE SPARE, AND AC ELECTRICAL SYS CONFIRMED OPERATIONAL. (TC NR 20071128012)				1	L	7	1 	3R	3	R		EXPA1L71	5E2	5	C	P257	 
2008022100056	20080221	00056	NE  	2008	2	21	CA071128013      	2	20071109	G	7321		FUEL CONTROL    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FAILED          	W				O				OTHER                   				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA								PC0509			(CAN) ENGINE POWER LOSS AND SUBSEQUENT INFLIGHT SHUTDOWN REPORTED.  MFG IS ATTEMPTING TO RECOVER THE FUEL CONTROL UNIT F	OR INVESTIGATION AND WILL ADVISE. (TC NR 20071128013)					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008022100057	20080221	00057	NE  	2008	2	21	CA071128014      	2	20071123	G	7261		FILTER          			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE OIL	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA								120189			(CAN) DURING CLIMB, THE CREW OBSERVED ERRATIC OIL PRESSURE INDICATIONS AND ELECTED TO RETURN TO POINT OF DEPARTURE. THE 	ENGINE OIL PRESSURE CONTINUED TO REDUCE AND THE CREW PERFORMED AN INFLIGHT SHUTDOWN. INVESTIGATION REVEALED A FAULTY MAI	N OIL PRESSURE FILTER WITH A REPORTED COLLAPSED INTERNAL ELEMENT.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE 	OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071128014)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022100058	20080221	00058	NM  	2008	2	21	CA071128015      	1	20071126	G	3240	ZMV811A	VALVE           			GULSTM	200   	200         	4500308	NM  	PWC   	PW306 	PW306A      	52165	NE  					PARKING BRAKE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			878  								(CAN) PILOT REPORTED PARK BRAKE SET AND INDICATED ON EICAS. STARTED RT ENGINE WITH THE CHOCKS REMOVED, READY FOR DEPARTU	RE. THE AIRCRAFT ROLL FWD AFTER THE ENGINE WAS STARTED. PILOT CHECKED THE INDICATION ON EICAS AND THE INDICATION WAS STI	LL ON EICAS PARK BRAKE ON.  PILOT HAD TO USE NORMAL BRAKE TO STOP AIRCRAFT.  MAINT WAS CALLED AND TROUBLESHOOTING REVEAL	ED THAT THE PARK BRAKE VALVE FAILED IN THE CLOSED POSITION. REPLACED PARK BRAKE VALVE AND C/O F/C ON PARK BRAKE SYS AND 	AC BRAKING SYS ALL FUNCTIONS OK.  AC RELEASED FOR RETURN FOR SERVICE. (TC 20071128015)		2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
2008022100059	20080221	00059	WP  	2008	2	21	CA071128017      	1	20071126	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				857  							(CAN) WHILE CARRYING OUT A 100 HOUR INSP THE FWD LT HYDR SERVO WAS DISCOVERED LEAKING. SERVO WAS REPLACED, GROUND RUN AN	D LEAK CHECK CARRIED OUT SERVICEABLE (TC NR 20071128017)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100060	20080221	00060	CE  	2008	2	21	CA071128018      	1	20071128	G	2510	505590401	CABLE           	AMSAFE      	505590401   	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					SEAT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2    								(CAN) COMPLIED WITH SB07-5 PILOT SECONDARY SEAT STOP INSTALLATION. THE AIRCRAFT LEFT OUR SHOP SERVICABLE AND IN COMPLIAN	CE WITH THE SB.  BROUGHT IT IN THE NEXT DAY TO DO UNSCHEDULED MAINT.  LOOKING OVER THE JOB FOR A SECOND TIME FOUND THE T	HREADED PLASTIC END OF THE CABLE BROKEN IN HALF AND THE PRODUCT NO LONGER FUNCTIONING CORRECTLY. BELIEVE A POSSIBILITY O	F THE PART BRAKING TO BE COOL WEATHER AND THE FACT THAT THE PART IS PLASTIC. (TC NR 20071128018)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2008022100061	20080221	00061	WP  	2008	2	21	CA071128019      	1	20071006	G	7810	C16932	TAILPIPE        			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED ODOR OF EXHAUST IN CABIN. INSPECTION OF EXHAUST COMPLIED WITH AND FOUND BURNED OUT AREA AT TAILPIPE	 JUNCTION. CF90-03R2 COMPLIED WITH 72.8 HRS PREVIOUS WITH NO DEFECTS FOUND AT THAT TIME. EXHAUST REPLACED. (TC NR 200711	28019)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100062	20080221	00062		2008	2	21	CA071129001      	2	20071122	G	7261	AS121670	CLEVIS PIN      		PN3004073   	DHAV  	DHC6  	DHC6300     	2802606	EA  						HARTZL	HCB3T	HCB3TN3     	GL  	OIL TANK DRAIN	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				22   							(CAN) THIS RT ENGINE S/NPCE-50013, WAS IDENTIFIED TO HAVE THE OIL TANK DRAIN PLUG P/N 3004073, MISSING THE LOCKING PIN P	/N AS121670. THIS COULD HAD LEAD TO THE COMPLETE LOSS OF ENGINE OIL, RESULTING OF ENGINE SHUTDOWN, IF THE PLUG HAD LOOSE	N AND FALLEN AWAY FROM THE ENGINE. (TC NR 20071129001)				1	H	7	2 	3T			RT	A9EA    		6	C	P15EA	 
2008022100063	20080221	00063	CE  	2008	2	21	CA071129002      	1	20071122	G	5753	3516505030	BRACKET         	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	FLAP BRACKET	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7336 			BB1610					(CAN) DURING PHASE 1 INSPECTION, LT FLAPS WERE REMOVED TO INSPECT SUPECTED AREA AS RT OB FLAP HAD FAILED IN THE SAME ARE	A A FEW HOURS PRIOR AND WAS REPORTED UNDER A SEPARATE SDR. WHEN RT OB FLAP BRACKET FAILED, THE FLIGHT CONTROLS WERE AFFE	CTED. THE CAUSE OF THE WEAR ON THE BRACKET IS FROM BEARING PN BC56985 WEARING OUT CHAFING INTO BRACKET. (TC NR 200711290	02)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008022100064	20080221	00064	NM  	2008	2	21	CA071130001      	1	20071110	G	3350	32145410	POWER SUPPLY    			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A3    	 	NE  					EMERGENCY LIGHTS	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) IN PROCESS OF DOING AB EMERGENCY LIGHTING TEST, AFTER THE COMPLETION OF THE IN-FLIGHT ENTERTAINMENT MAKEOVER, IT W	AS DISCOVERED THAT THE AFT EMERGENCY LIGHTING WAS NOT TESTING. A STRONG BURNING SMELL WAS DETECTED AFTER OPENING A PANEL	 TO ACCESS THE AFT EMERGENCY POWER SUPPLY UNIT. ONE CORNER OF THE BATTERY UNIT WAS MELTED THROUGH THE CASE AND THE POSIT	IVE TERMINAL CONNECTION AND CIRCUIT BOARD ON THE ESPU HAD SIGNS OF SEVERE OVERHEATING. THE ESPU AND BATTERY WERE SENT TO	 THE SHOP FOR EVALUATION.  THE SUSPECTED CAUSE WAS LIQUID INGESTION BUT COULD NOT BE SUBSTANTIATED. (TC NR 20071130001)		2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2008022100065	20080221	00065	GL  	2008	2	21	CA071130002      	1	20071129	G	2422	GC53100043	INVERTER        			BOMBDR	BD100 	BD1001A10   	1390044	GL  	RROYCE	BR700 	BR700710A220	09500	NE  						OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			257  								(CAN) DURING MAINT AND AFTER THE AC HAD BEEN POWERED WITH EXTERNAL GROUND POWER FOR APPROX 4 HOURS, THE CREW NOTICED A B	URNING SMELL AROUND THE AC. NO ABNORMAL INDICATIONS WERE DISPLAYED ON THE CREW ALERTING SYS (CAS) MESSAGE AND THE ELECTR	ICAL MGMT SYS CONTROL AND DISPLAY UNITS (EMSCDU). THE POWER WAS REMOVED FROM THE AC.  THE INVESTIGATION INDICATES THAT T	HE INTEGRAL LIGHTING INVERTER A179 SHOWN SIGN OF INTERNAL OVERHEATING. THIS RESULTED IN DEPOSITING SOOT TO THE ADJACENT 	INTEGRAL LIGHTING POWER SUPPLY A176 AND WIRES. BOTH UNITS WERE REMOVED, REPLACE AND SENT TO THE VENDOR TO IDENTIFY THE R	OOT CAUSE OF THE FAILURE. THE AC IS BACK IN SERVICE. (TC NR 20071130002)	2	L	7	2 	4F	4	F	RT	T00005NY	E00061EN				 
2008022100066	20080221	00066	CE  	2008	2	21	CA071130003      	1	20071128	G	5610	10138402522	WINDSHIELD      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) COPILOTS WINDSHIELD INNER PANE SHATTERED DURING NORMAL CRUISE FLIGHT. WINDSHIELD REPLACED UPON RETURN TO MAINTENAN	CE BASE. (TC NR 20071130003)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008022100067	20080221	00067	EU  	2008	2	21	CA071130004      	1	20071128	G	2497		WIRE HARNESS    			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	CONTROL PANEL	SHORTED         	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) STANDBY HORIZON CB POPPED. MODERATED ELECTRICAL SMELL/SMOKE.  WIRE BUNDLE UNDER COPILOTS SIDE PANEL ASSY (PNS25110	49800300) FOUND CHAFED AND SHORTING TO PANEL. (PANEL IS BELIEVED TO BE MADE OF CARBON FIBER WHICH WILL CONDUCT ELECTRICI	TY). PANEL ASSY INSPECTED WITH BURNED SPOTS AT WIRE BUNDLE LOCATION AS WELL AS AFT EDGE WHICH WAS CHAFING ON (2) SCREWS.	 DAMAGED WIRING BUNDLE REPAIRED. PANEL REPAIRED AND REINSTALLED. (TC NR 20071130004)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008022100068	20080221	00068	WP  	2008	2	21	CA071130006      	1	20071123	G	2435	14924HTH	STARTER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			155  								(CAN) A PILOT ATTEMPTING A START THE AC AND FAILED TO TURN OVER. FURTHER INVESTIAGTION REVEALED STARTER WAS DEFECTIVE. S	TARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071130006)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022100069	20080221	00069	NM  	2008	2	21	CA071130007      	1	20071130	G	5315	146A75031	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										CARGO BAY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+6 LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA, LEVEL 2 CORROSION. (TC N	R 20071130007)					2	L	7	2 	4F			RT	A16WE   					 
2008013100275	20080131	00275	NM  	2008	1	31	CA071130008      	1	20071130	G	5315	146A75035	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOORBEAM RAIL CORRODED AT BS 767+6 LBL 8 AND REPAIRED IAW CUSTOMER EA LEVEL 2 CORROSION (TC NR 2007	1130008)					2	L	7	2 	4F			RT	A16WE   					 
2008013100276	20080131	00276	NM  	2008	1	31	CA071130009      	1	20071130	G	5315	147A55047	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS 947	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CABIN FLOOR SUPPORT BEAM AT BS 947 LBL 53 CORRODED AND REPAIRED IAW CUSTOMER EA  LEVEL 2 CORROSION (TC NR 2007	1130009)					2	L	7	2 	4F			RT	A16WE   					 
2008013100277	20080131	00277	NM  	2008	1	31	CA071130010      	1	20071130	G	5730	112A410210	SKIN            			BOEING	737   	737790      	13844CN	NM  										RWS 240	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING LWR SKIN AT AFT EDGE CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING INBD BLADE SEAL AT APPROX	. WS 240 REPAIRED IAW CUSTOMER EA (TC NR 20071130010)					2	L	7	2 	4F			RT	A16WE   					 
2008013100278	20080131	00278	NM  	2008	1	31	CA071130011      	1	20071130	G	5730	112A41029	SKIN            			BOEING	737   	737790      	13844CN	NM  										LWS 260	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WING LWR SKIN CHAFFING DAMAGE FOUND FROM CONTACT WITH NACELLE STRUT AFT FAIRING OB BLADE SEAL AT APPROX WS 260 	 REPAIRED IAW CUSTOMER EA (TC NR 20071130011)					2	L	7	2 	4F			RT	A16WE   					 
2008013100279	20080131	00279	EU  	2008	1	31	CA071130012      	1	20071130	G	6321	C762C1004103	BRAKE           			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1730 								(CAN) MECHANICAL DAMAGE TO ROTOR BRAKE GRID ASSEMBLY, DUE TO IMPROPER OPERATION.  TRIGGER WAS NOT DEPRESSED PRIOR TO ENG	AGING ROTOR BRAKE HANDLE CAUSING MECHANICAL DAMAGE TO GRID ASSEMBLY.  NEW GRID ASSEMBLY INSTALLED (TC NR 20071130012)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008013100280	20080131	00280	NM  	2008	1	31	CA071130013      	1	20071130	G	5730	112A410210	SKIN            			BOEING	737   	737790      	13844CN	NM  										RWS 260	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING LWR SKIN CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING OB BLADE SEAL AT APPROX WS 260 REPAIR	ED IAW EA.(TC NR 20071130013)					2	L	7	2 	4F			RT	A16WE   					 
2008020400128	20080204	00128		2008	2	4	CA071130014      	1	20071126	G	3411	3001T60P03	SEAL            								GE    	CT58  	CT581401    	30011	NE  						DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								295291			(CAN) STATIC DISCHARGE SEAL DEBONDED WHILE ENGINE (SN 295-291) WAS BEING RUN. OUR INTERNAL SQID REPORT NR 07-06724 REFER	S. (TC NR 20071130014)										4	U			1E3				 
2008020400127	20080204	00127		2008	2	4	CA071130015      	4	20071130	G	3197		WIRE            			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  		BURNED          	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			393  								(CAN) AFTER STARTING ENGINE FOR GROUND RUN, AVIONICS SWITCH WAS SELECTED ON. IMMEDIATELY SMOKE STARTED COMING FROM RT CB	 PANEL. ENGINES WERE IMMEDIATELY SHUTDOWN AND POWER WAS REMOVED FROM A/C. INVESTIGATION REVEALED THAT A FACE PLATE MOUNT	ING SCREW HAD SHORTED TO AN AVIONICS FEEDER WIRE P72A10 DUE TO POOR ROUTING OF THE WIRE AT MFG.  (2) 10GAUGE WIRES ARE A	TTACHED TO ONE TERMINAL OF CB120 (TCAS), ONE COMING FROM CB92 (AVIONICS POWER LT GEN BUS) WHICH IS A 30AMP BREAKER. ONE 	OF THE WIRES WAS MOUNTED ALONG THE BACK OF THE PANEL AND HAD BEEN IN HARD CONTACT WITH THE AFT MIDDLE FACE PLATE MOUNTIN	G SCREW. WIRE REPLACED IAW AC43.13-1B PARA 11-98, ROUTED TO AVIOD CONTACT WITH MOUNTING HARDWARE. (TC NR 20071130015)	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008020400126	20080204	00126	CE  	2008	2	4	CA071202001      	1	20071201	G	5312		BULKHEAD        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPLIANCE WITH SEB 93-5 INSP OF LOWER DOOR POST, THE BULKHEAD WAS FOUND CRACKED ON THE LT SIDE, UPPER PART	 OF LOWER BULKHEAD, JUST IB OF THE WING STRUT ATTACHMENT FITTING. RT SIDE WAS TO BE FREE OF CRACKS AT THIS TIME. MFG SER	VICE KIT SK260-42C WAS INCORPORATED TO THE LT LOWER DOOR POST. AC RETURNED TO SERVICE.  THIS INSP IS ALSO CALLED UP IN T	HE CONTINUED AIRWORTHINESS PROGRAM  INSP NR 53-40-01 INITIAL INSPECTION TO BE DONE AT 12000 HOURS AND REPEAT INSPECTIONS	 EACH 3000 HOURS THERE AFTER. SEB 95-3R1 CALL FOR THIS INSPECTION AT 4000 HOURS TT AND REPEAT INSPECTIONS EACH 1000 HOUR	S THERE AFTER.  NOT ALL OPERATORS OF THESE AC ARE IN COMPLIANCE WITH THE C.A.P MANUALS. (TC NR 20071202001)	1	H	7	1 	3O	3	O		A4CE    	E3SO	5	C	P36EA	 
2008013100281	20080131	00281	NM  	2008	1	31	CA071202002      	1	20071201	G	5730	112A4101209	SKIN            			BOEING	737   	737990      	       	NM  										RWS 260	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19198								(CAN) A/C UNDERGOING C-CHECK,HEAVY MAINTENANCE. RT WING, LOWER SKIN PANEL CHAFING DAMAGE FOUND FROM CONTACT WITH NACELLE	 STRUT AFT FAIRING OB BLADE SEAL AT APPROX WS 260. REPAIRED IAW EA 5720-01345. (TC NR 20071202002)					2	L	7	4 	4F			RT	A16WE   					 
2008013100282	20080131	00282	NM  	2008	1	31	CA071202003      	1	20071201	G	5730	112A4101209	SKIN            			BOEING	737   	737990      	       	NM  										LWS 240	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19198								(CAN) A/C UNDERGOING C-CHECK HEAVY MAINTENANCE. LT WING LOWER SKIN PANEL CHAFING DAMAGE FOUND DUE TO CONTACT WITH NACELL	E STRUT AFT FAIRING IB BLADE SEAL AT APPROX WS 240. REPAIRED IAW EA 5720-01345. (TC NR 20071202003)					2	L	7	4 	4F			RT	A16WE   					 
2008022100070	20080221	00070	NM  	2008	2	21	CA071202004      	1	20071201	G	5730	112A4101209	SKIN PANEL      			BOEING	737   	737990      	       	NM  										WS 260	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19198								(CAN) A/C UNDERGOING C-CHECK HEAVY MAINT. LT WING LOWER SKIN PANEL CHAFING DAMAGE FOUND DUE TO CONTACT WITH NACELLE STRU	T AFT FAIRING OB BLADE SEAL AT APPROX WS 260. REPAIRED IAW EA 5720-01346. (TC NR 20071202004)					2	L	7	4 	4F			RT	A16WE   					 
2008022100071	20080221	00071	SO  	2008	2	21	CA071203001      	1	20071202	G	3710		VANE            	RAPCO       	441CC7      	PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	AIR PUMP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				771  		125777					(CAN) DURING A PRE-MAINTENANCE GROUND RUN, IT WAS NOTED THAT THE RT AIR PUMP WAS INDICATING INOPERATIVE DURING INSPECTIO	N. THE DRIVESHAFT WAS FOUND TO BE SHEARED DUE TO THE CARBON VANES BREAKING AND JAMMING THE PUMP. (TC NR 20071203001)					1	L	7	1 	3O	3	O	RT	A20SO   	E14EA	5	C	P33EA	 
2008022500010	20080225	00010	SO  	2008	2	25	CA071203002      	1	20071202	G	5340		STRUCTURE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17329	17329							(CAN) DURING AN EVENT 1 INSP ON THE AC, ENGINEER NOTICED WHAT HE THOUGHT THERE WAS A CRACK ON THE EXTRUSION (LOCATED ABO	VE THE NLG WHEEL WELL, JUST AFT OF HYD POWERPACK), TO WHICH THE NOSE LANDING GEAR RETRACTION ACTUATOR ATTACHES TO. AFTER	 PERFORMING A LIQUID PENETRANT INSP, THE PRESENCE OF A CRACK WAS CONFIRMED. THE EXTRUSION WAS REMOVED FROM THE AIRCRAFT,	 AT THIS TIME IT WAS ALSO NOTED THAT THE ATTACH POINT (BOLT HOLE) WAS ALSO CRACKED. A NEW EXTRUSION IS BEING INSTALLED. 	THIS EXTRUSION HAS BEEN INSTALLED SINCE THE AIRFRAME WAS MFG (17328.9 TSN). (TC NR 20071203002)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008022500011	20080225	00011	NE  	2008	2	25	CA071203003      	2	20071203	G	7314	D7341	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) THE AUXILIARY FUEL PUMP LIGHT CAME, AND WOULD NOT EXTINQUISH. TROUBLESHOOTING REVEALED THAT THE PUMP WAS NO LONGER	 PUMPING FUEL. THE PUMP WAS CHANGED, LEAK, AND FUNCTION CHECKED SERVICEABLE. (TC 20071203003)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500012	20080225	00012	SW  	2008	2	25	CA071203004      	1	20071101	G	5514	400928	SPRING          			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	TAIL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			858  								(CAN) CRACK FOUND ON TAIL SPRING BEGINNING FROM FWD ATTACH HOLE EXTENDING ALONG SIDE OF SPRING. CRACK THEN EXTENDS TO TO	P OF SPRING. LENGTH OF CRACK TOTALS APPROX 6 INCHES. (TC NR 20071203004)					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008022500013	20080225	00013	EU  	2008	2	25	CA071203005      	1	20071203	G	6720	11731822A	PITCH LINK      			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TAIL ROTOR	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR PITCH LINKS P/N 117.31822A.  REPLACED ON 31 OCT/2007, DUE TO BEARING WEAR. ON DEC 3/2007 THE LINKS WERE	 INSPECTED PRIOR TO BEARING REPLACEMENT AND WERE FOUND TO HAVE AN INCORRECT P/N STAMPED ON THEM. THE NR WAS MISSING THE 	NR 1. THE STAMP INDICATED P/N 117.3822A. THIS NUMBER IS NOT IN THE IPC MANUAL. THE LINKS ARE THEREFORE SUSPECT. (TC NR 2	0071203005)			1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2008022500014	20080225	00014	SW  	2008	2	25	CA071203006      	1	20071203	G	7120	205060105001	MOUNT           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7609 								(CAN) LT ENGINE TRIPOD AFT TUBING MOUNT FOUND CRACKED DURING 100 HRS INSPECTION JUST BELOW ENGINE MOUNTING PLATE AFT TUB	E JUNCTION.  NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071203006)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008031900166	20080319	00166	NE  	2008	3	19	CA071203007      	2	20071201	G	7321	01645487201	FCU             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	LEAKING         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) THE PILOT WAS DESCENDING WHEN ALL OF A SUDDEN THE CABIN AREA FILLED UP WITH A MIST ORIGINATING FROM THE THE DEFROS	T VENTS. THE MIST WAS SO STRONG THAT THE PILOT HELD HIS BREATH AND OPENED THE FUSELAGE DOOR SO THE MIST COULD EXIT THE A	C.  AFTER A FEW SECONDS THE MIST DISSIPATED SO THE PILOT COULD BREATH NORMALLY. THE PILOT LANDED AT STAGING SITE AND THE	 AC WAS GROUNDED. THE ENGINEER WAS CALLED TO TROUBLESHOOT THE PROBLEM.  WE BELIEVE IT IS THE FUEL CONTROL THAT CAUSED TH	IS FUEL MIST IN THE CABIN. THE FUEL CONTROL HAS ABOUT 1400 HOURS SINCE LAST OVERHAUL THE TECH. (3000 HOUR O/H BY MFG) (T	C NR 20071203007)	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022500015	20080225	00015	SW  	2008	2	25	CA071203008      	1	20071126	G	3210		BUTTON          	FRCHLD      		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	SHORT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AC714					(CAN) UPON DISASSEMBLY OF A MLG FOR OVERHAUL AND SERVICING IT WAS NOTICED THE CYLINDER PISTON TEFLON BUTTONS WERE UNDER 	FLUSH WITH THE PISTON. THE TEFLON BUTTONS AND PINS ALLOW THE PISTON TO SLIDE INSIDE THE CYLINDER WITHOUT SCORING AND WIT	HOUT ALLOWING FLUID BLOWBY. UPON INSPECTION OF THE PISTON IT WAS NOTICED THE HOLES WERE TOO DEEP FOR THE TEFLON BUTTONS 	AND PINS AND ALLOWED FOR SCORING OF THE CYLINDER WALLS. WHEN COMPARED TO A KNOWN CERTIFIED PART, IT DID NOT MEET THE SAM	E MEASUREMENTS. ACTUAL ENGINEERING DRAWINGS WITH SPECIFIC MEASURMENTS WERE NOT AVAILABLE TO CONFIRM PISTON MEASURMENTS. 	LIKELY THIS PART IS SUBSTANDARD BUT THE POSSIBILITY OF BEING AN UNAPPROVED PART EXISTS. TOTAL TIME ON THE PISTON IS UNKN	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2008022500016	20080225	00016	GL  	2008	2	25	CA071204001      	2	20071129	G	7323	23076061	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	INOPERATIVE     	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				456  							(CAN) WHILE CARRYING OUT A START, THE ENGINE WAS SLOW TO REACH IDLE, WITH THE N2 INDICATOR STICKING ON START. ONCE DESNA	GGED IT WAS DISCOVERED THE GOVENOR WAS THE CAUSE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008022500017	20080225	00017	SW  	2008	2	25	CA071204002      	1	20071101	G	2450	PDLM120	CIRCUIT BREAKER 			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	CB BODY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5676 	5676 							(CAN) CB CRACKED.  (TC NR 20071204002)						1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008022500018	20080225	00018	SW  	2008	2	25	CA071204003      	1	20071101	G	5320		NUT             		EISRVAC     	AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	VACUUM SWITCH	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5676 	5676 							(CAN) THE VACUUM SWITCH WAS SUPPLIED BY MFG. PLASTIC ADJUSTING NUT SPLIT, PREVENTING THE VACUUM SWITCH FROM INDICATING A	 LOW FUEL PRESSURE WARNING. (TC NR 20071204003)					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008022500019	20080225	00019	NM  	2008	2	25	CA071204004      	1	20071204	G	3230	656021132	ACCESSORY UNIT  			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LANDING GEAR	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			9451 	7879 							(CAN) SHORTLY AFTER TAKEOFF WHEN GEAR WAS BEING RETRACTED, CREW NOTICED THAT THE RT MAIN GEAR RED LIGHT WAS STILL ILLUMI	NATED. CREW CYCLED THE LANDING GEAR (3) TIMES WITH THE SAME RESULTS. THE CREW ADVISED THAT AIR NOISE COULD BE HEARD. GEA	R WAS SELECTED DOWN WITH (3) GREEN AND RETURNED TO THE RAMP. EXTENSIVE TROUBLESHOOTING AND GEAR SWINGS REVEALED LANDING 	GEAR ASSY UNIT IS AT FAULT. SERVICEABLE UNIT INSTALLED AND GEAR FUNCTION TESTED SERVICEABLE. THE AC HAS FLOWN 4 LEGS SIN	CE THE REPAIR WITH NO FURTHER PROBLEMS.		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008022500020	20080225	00020	NE  	2008	2	25	CA071204006      	2	20071202	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			1013 								(CAN) THE AIRCRAFT WAS FLOWN FOR AN HOUR AND THEN SHUTDOWN TO WAIT FOR CUSTOMERS. THE AC WAS RE-STARTED A HALF HOUR LATE	R AND THE PILOT TRIED TO LIFT OFF, WHEN THE ENGINE LOST PARTIAL POWER AND THE MANIFOLD PRESSURE ROSE ABNORMALLY.  THE PO	WER SETTINGS CAME BACK TO NORMAL WHEN THE COLLECTIVE WAS LOWERED BUT WOULD DETERIORATE EVERY TIME THE COLLECTIVE WAS RAI	SED. AFTER SHUTTING DOWN THE ENGINE, FUEL WAS SEEN FLOWING OUT OF THE ENGINE DRIVEN FUEL PUMP DRAIN. THE OAT WAS -30 CEL	CIUS AND THE ENGINE WAS PRE-HEATED. (TC NR 20071204006)		1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500021	20080225	00021	SW  	2008	2	25	CA071204007      	1	20071204	G	6410	212010710001	BALANCE WEIGHT  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					T/R BLADE	INCORRECT       	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) INCORRECT WEIGHT FOR PN CAUSED IMBALANCE IN TAIL ROTOR WHICH COULD NOT BE CORRECTED WITHIN BALANCE LIMITS. (TC NR 	20071204007)					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2008022500022	20080225	00022	NE  	2008	2	25	CA071204008      	1	20071129	G	6520		BEARING         		S613566300  	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					GEARBOX	OVERHEATED      	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA				14   		A151024					(CAN) ON FIRST FLIGHT OF THE DAY, AIRCRAFT WAS GROUND TAXIING TO TAKE OFF AREA WHEN GROUND CREW NOTICED SMOKE FROM TAIL 	ROTOR DRIVE INTERMEDIATE GEAR BOX AREA. AIRCRAFT WAS SHUT DOWN, AND INSPECTION REVEALED OVERHEATING IN THE INPUT BEARING	 AREA. SIKORSKY AND OVERHAUL SHOPS ADVISED, AND ARE INVESTIGATING CAUSE. THIS IS A REOCCURANCE OF PREVIOUS FAILURE. IN B	OTH CASES GEAR BOX OIL LEVEL WAS FOUND TO BE SATISFACTORY. (TC# 20071204008)			2	G	7	2 	4U	4	U		1H15    	1E3				 
2008022500023	20080225	00023	GL  	2008	2	25	CA071204009      	1	20071130	G	5551	C2TP160A	BRACKET         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING THE REQUIREMENTS OF CF 91-42R1 IAW SB 2/47 REV (E), THE RT FWD STABILIZER ATTACH BRACKET WAS FOUN	D TO BE CRACKED. THE CRACK EXTENDED FROM THE TOP OF THE IB EAR OF THE BRACKET, THROUGH THE LOCKWIRE HOLE AND CONTINUED A	PPROX 75 PERCENT OF THE WAY DOWN THE BRACKET. THIS AIRCRAFT OPERATES EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT.				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2008022500024	20080225	00024	NE  	2008	2	25	CA071204010      	2	20071123	G	7261	1111065	OIL FILTER      			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	RESTRICTED      	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				600  							(CAN) INFLIGHT SHUTDOWN AS A PRECAUTION, OIL PRESSURE INDICATION FLUCTUATING IN FLIGHT.  OIL FILTER APPEARED CLEAN BUT W	AS RESTRICTING FLOW AS TO WHERE IT WAS CAUSING OIL BYPASS IN THE FILTER HOUSING, WHICH CAUSED THE ERRONEOUS INDICATIONS.	 (TC NR 20071204010)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500025	20080225	00025	GL  	2008	2	25	CA071204011      	1	20071123	G	5343		ATTACH FITTING  			TCRAFT	BC    	BC12D       	8850316	GL  	CONT  	A65   	A658        	17003	SO  	UNIVAC	72	72A         	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSTALLING NEW STRUTS IAW APPLICABLE STC, THE LT REAR ATTACH FITTING SEPERATED (BROKE IN HALF) AS VERY SLIGH	T DOWNWARD PRESSURE WAS APPLIED TO THE LIFT STRUT.  INSPECTION OF THE FAILED PART SHOWED A PRE EXISTING CRACK UNDER THE 	LOCKNUT. (TC NR 20071204011)				1	H	7	1 	3O	3	O		A696    	E205	5	N	802	 
2008022500026	20080225	00026	EA  	2008	2	25	CA071205001      	1	20071205	G	2820	215T640836	FITTING         			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	TANK DRAIN	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) MAJOR FUEL LEAK BY THE BROKEN NR 3 COLLECTOR TANK DRAIN FITTING, SOLENOID SIDE. PIPE DRAIN 215T64083-6 REPLACED.  	 (TC NR 20071205001)					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2008022500027	20080225	00027	EU  	2008	2	25	CA071205002      	1	20071203	G	5610	3501262334	WINDSHIELD      			SNIAS 	350   	AS350*      	       	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							2295				(CAN) DURING PREFILGHT INSP, CRACKS WERE DISCOVERED ON LT WINDSHIELD TECH TOOLS PLASTICS P/N 350126231 AND RT WINDSHIELD	 TECH TOOLS PLASTICS P/N 3501-2623-1. BOTH LT AND RT WINDSHIELDS WERE CRACKED 4.5 TO 5 INCHES LONG ON BOTTOM EDGE. THE A	IRCRAFT HAND FLOWN THE PREVIOUS DAY IN TEMPERATURES OF -30 DEGREES C AND HAD BEEN HANGERED OVERNIGHT. (TC NR 20071205002	)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022500028	20080225	00028	EA  	2008	2	25	CA071205003      	2	20071205	G	7322	62226	STOP PIN        			AMTR  	ELITE 	ELITE532    	13027GG	GL  	LYC   	O360  	O360A2F     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	AIR METERING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				105  							(CAN) AN INTERMITTENT, MINOR ROUGHNESS IN THE ENGINE WAS OBSERVED TO TAKE PLACE JUST BEFORE LANDING. NOTHING OUT OF THE 	ORDINARY WAS OBSERVED DURING LANDING, TAXI AND SHUTDOWN (I.E. NO ABNORMAL CHT, EGT OR RPM). INSP OF ENGINE REVEALED NOTH	ING, EXTERNALLY.   CARB WAS REMOVED FROM ENGINE AND SENT IN TO INSTALL AN OPTIONAL ENRICHMENT KIT TO CONVERT THE P/N 10-	3878 CARB TO A P/N 10-3878M FOR IMPROVED PERFORMANCE AND BETTER COLD WEATHER OPS. WHEN DISASSEMBLED, IT WAS DISCOVERED T	HAT THE CARB AIR METERING STOP PIN HAD VIBRATED LOOSE AND HAD FALLEN OUT. ALLOWING SPRING LOADED AIRBLEED NEEDLE TO POP 	OUT AND FALL INSIDE CARB, JAMMING THE THROTTLE. PILOT DID NOT DETECT ANY JAMMING OF THROTTLE OR MALFUNCTION OF MECHANICA	1	G	7	1 	3I	3	O	NT	EXPA1G71	E286	5	N	P4EA	 
2008022500031	20080225	00031	NE  	2008	2	25	CA071205004      	2	20071128	G	7300		UNKNOWN         			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  						UNKNOWN         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE EEC REVERTED TO MANUAL WITH LOSS OF THRUST LEVER, RESPONSE NOTED. THRUST DECREASED INITIALLY TO 	54 PERCENT AND LATER TO 25 PERCENT. FLIGHT WAS DIVERTED AND AN UNSCHEDULED LANDING PERFORMED. AFTER TROUBLESHOOTING, AC 	WAS CLEARED TO RETURN TO BASE. ADDITIONAL TROUBLESHOOTING FOCUSED ON FUEL SYS COMPONENTS.  AC HAS RETURNED TO SERVICE AF	TER REPLACEMENT OF SUSPECT COMPONENTS.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS	HED (TC NR 20071205004)		2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008022500035	20080225	00035	EU  	2008	2	25	CA071205005      	1	20071202	G	7110		COWLING         			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					ENGINE	BURNED          	W				E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START, AN ENGINE COMPARTMENT FIRE WAS NOTED. DAMAGE IS EVIDENT TO COWLING, ENGINE AND ENGINE COMPARTMENT.  	MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071205005)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2008022500037	20080225	00037	NE  	2008	2	25	CA071205006      	2	20071130	G	7261		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  						OIL CONSUMPTION 	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								AE0084			(CAN) OIL MIST WAS NOTED IN THE CABIN AFTER LANDING. INITIAL TROUBLESHOOTING REVEALED THAT 2 LITRES OF OIL WERE CONSUMED	 DURING THE PREVIOUS FLIGHT. ENGINE WAS REMOVED FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE	 OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071205006)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008022500039	20080225	00039	EA  	2008	2	25	CA071205007      	2	20071130	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T6       	52045	EA  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								72459			(CAN) CREW HEARD A METALLIC BANG FROM THE ENGINE AREA, FOLLOWED BY CAUTION LIGHTS. ENGINE WAS SHUTDOWN AND AIRCRAFT LAND	ED. SUBSEQUENT INITIAL INSPECTION REVEALED DEBRIS ON THE OIL FILTER. ENGINE IS BEING REMOVED FOR INVESTIGATION. P&WC WIL	L CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071205007)				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2008022500041	20080225	00041	NE  	2008	2	25	CA071205008      	2	20071128	G	7314		PUMP            			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					FUEL SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE CREW REPORTED THAT ENGINE TORQUE WAS (UNSTABLE).   POST FLIGHT INVESTIGATION REVEALED THAT ENGI	NE POWER WAS LIMITED TO 86 PERCENT VS. 90 PERCENT TARGET. FUEL PUMP AND FUEL CONTROL WERE REPLACED. FUEL PUMP IS SUSPECT	 AND WILL BE SENT FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE	D (TC NR 20071205008)			2	H	7	2 	4T	4	T	RT	        	E20NE				 
2008022500068	20080225	00068	EA  	2008	2	25	CA071205009      	2	20071130	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						FOD             	W				O				OTHER                   				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA						FA0279					(CAN) ENGINE (FLAMED OUT) AND AUTO RECOVERED WITHIN TEN SECONDS TIME FRAME WITH NO CREW INTERVENTION.  FADEC DATA INDICA	TES POSSIBLE WATER/ICE INGESTION. (TC NR 20071205009)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2008022500069	20080225	00069	EU  	2008	2	25	CA071205010      	1	20071126	G	2160	342B030000AMDTA	THERMOSTAT      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					TEMP CONTROL	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			5970 								(CAN) WHILE IN CRUISE AT FL 390, THE CREW HAD A BLEED AIR SUPPLY NR 2 FAILURE, AND DURING A DESCENT WHILE REFERING TO TH	E QRH, ALSO HAD NR 1 BLEED FAIL. CREW LOST BOTH PACKS, AND INITIATED EMERGENCY DESCENT TO 10,000 FT. FLT DIVERTED TO NEA	RBY AIRPORT.  TEMP CONTROL THERMOSTAT (TCT) AND FAN AIR VALVE WERE CHANGED. IT IS TO BE NOTED THAT THE TCT IS POST MOD T	O ENABLE IT TO OPERATE UNDER SINGLE BLEED CONDITIONS. (TC NR 20071205010)			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2008022500071	20080225	00071	CE  	2008	2	25	CA071206001      	1	20071205	G	3230	508103237	TORQUE LINK     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	MLG	CRACKED         	W				L				ABORTED APPROACH        				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SPECIAL LPI INSPECTION OF THE MLG TORQUE LINKS DUE TO THE FAILURE OF A LINK ON ANOTHER AIRCRAFT (SDR 2007	1024010 AND 20071122002), 3 OF THE 4 LINKS WERE FOUND CRACKED.  THE LINKS FROM 3 ADDITIONAL AIRCRAFT WERE REPLACED IN OR	DER TO COMPLETE THE LPI OFF AIRCRAFT, THE LPI WAS COMPLETED AND 4 OF THE 12 LINKS WERE FOUND TO HAVE VERY SMALL CRACKS, 	ALL THE CRACKS ARE IN THE SAME RADIUS AREA,  (TC# 20071206001)			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
2008022500073	20080225	00073	CE  	2008	2	25	CA071206003      	1	20071203	G	3510	1183840093	CONTROL CABLE   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	OXYGEN MASK	STIFF           	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			10075								(CAN) WHILE PERFORMING AN INTERIOR PREFLIGHT CHECK THE F/O PULLED THE CONTROL KNOB FOR THE OXYGEN SYS. THE KNOB WAS DIFF	ICULT TO PULL BUT THE PILOT CONFIRMED THAT THERE WAS FLOW AT THE MASKS. DURING THE FLIGHT THE PILOT AND CO-PILOT DONNED 	THE OXYGEN MASKS AND FOUND THERE WAS NO OXYGEN FLOW.  UPON RETURN TO BASE MAINT CHECKED THE SYS AND FOUND IT SERVICEABLE	. DURING THE NEXT FLIGHT THE PILOTS FOUND THE SAME PROBLEM WITH THE CONTROL KNOB. DURING TROUBLESHOOTING THE AC WAS COLD	-SOAKED AND THE KNOB FOUND DIFFICULT TO PULL. THE CONTROL CABLE ASSY WAS REMOVED AND REPLACED. (TC NR 20071206003)		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008022500075	20080225	00075	CE  	2008	2	25	CA071206004      	1	20071205	G	3260	MS25237327	BULB            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG ANNUNCIATOR	BURNED OUT      	W				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) PILOTS REPORT, ON FINAL TO LANDING RUNWAY, SELECTED THE GEAR DOWN HOWEVER THE RT MAIN GEAR GREEN LIGHT FAILED TO I	LLUMINATE. THE RED (GEAR UNLOCKED) LIGHT WAS EXTINGUISHED. ADVISED TOWER AND CONDUCTED A MISSED APPROACH WITH REQUEST FO	R VECTORS TO REMAIN IN AREA. WE COULD VISUALLY SEE THE WHEEL DOWN, AND THE GEAR HORN WOULD NOT SOUND WITH FULL FLAPS HOW	EVER EXECUTED THE MANUAL EXTENSION PROCEDURE REGARDLESS, ASKED FOR THE EMERGENCY VEHICLES TO BE STANDING BY ON LANDING A	S A PRECAUTION. BRIEFED OURONLY PASSENGERS AND LANDED WITH OUT FURTHER INCIDENT. CLEARED THE RUNWAY, ASKED FOR EMERGENCY	 CREWS TO VIEW OUR RT WHEEL FOR ANY OBVIOUS DAMAGED. THEY REPORT NOTHING APPARENT TO THEM AND SINCE THE AC LANDED, ROLLE	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008022500078	20080225	00078	CE  	2008	2	25	CA071206005      	1	20071203	G	2120		UNKNOWN         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA							UE63				(CAN) UPON REACHING LEVEL FLIGHT BOTH THE CAPT AND F/O SMELLED SMOKE IN THE COCKPIT, WHICH SHORTLY AFTER COULD ALSO BE S	EEN IN THE COCKPIT. AFTER LESS THAN A MINUTE THE SMOKE DISSIPATED AND THE CAPTAIN MADE THE DECISION TO RETURN TO THE DEP	ARTURE POINT. AFTER CONTACT WITH ATC THE SMOKE AND SMELL HAD COMPLETELY DISAPPEARED. MAINT PERFORMED GROUND RUNS AND COU	LD NOT DUPLICATE THE DEFECT. SYS TESTED AND INSPECTED, FWD NOSE AVIONICS, INSTRUMENT PANEL WIRING, COOLING FANS, CABIN A	ND COCKPIT LIGHTING, CIRCUIT BREAKERS, PC BOARDS, INVERTER AND DC BUS CHECKS, ENVIRONMENTAL SYSTEM, ACM, LT AND RT ENGIN	ES, AND WINDSHIELD HEAT ALL CHECKED SERVICEABLE WITH NO FAULT FOUND. (TC NR 20071206005)	1	L	7	2 	4T	4	T		A24CE   	E26NE	5	C	P10NE	 
2008022500079	20080225	00079	NM  	2008	2	25	CA071206006      	1	20071126	G	2710	82700518001	CONTROL CABLE   			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	AILERON	WORN            	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) PILOTS REPORTED THAT THE AILERON CONTROLS WERE STIFF (OAT -20C). INSPECTION OF THE AIRCRAFT WAS CARRIED OUT AND TH	E AILERON CABLE WAS FOUND TO BE WORN WHERE IT CROSSED A ROLLER FAIRLEAD AT APPROX STN YW189.00. THE ROLLER FAIRLEAD WAS 	NEARLY SEIZED. THE OB AILERON QUADRANT BEARINGS WERE ALSO FOUND TO BE STIFF WHEN COLD. THE CABLES IN BOTH WINGS WERE REP	LACED AS WELL AS THE ROLLER FAIRLEAD. THE BEARINGS WERE REPLACED IN THE AILERON QUADRANTS AND THE AIRCRAFT WAS RETURNED 	TO SERVICE WITH NO FURTHER DEFECTS. (TC NR 20071206006)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500083	20080225	00083	NM  	2008	2	25	CA071206007      	1	20071203	G	2797		WIRE HARNESS    	LUCAS       		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AILERON ACTUATOR	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			18550	18550		0084					(CAN) AFTER ROTATION, HEAVY LT AILERON INPUT NEEDED IN FLIGHT. AILERON TRIM WAS CENTERED BUT HAD NO EFFECT. FLIGHT RETUR	NED TO DEPARTURE AIRPORT SAFELY WITH NO NEED TO DECLARE AN EMERGENCY. MAINT TROUBLESHOOTING, FOUND WIRE HARNESS ON AILER	ON TRIM ACTUATOR WORN WHERE WIRES ENTER BODY OF ACTUATOR CAUSING CIRCUIT BREAKER TO POP WHEN TRIM IMPUT WAS SELECTED. AI	LERON TRIM ACTUATOR REPLACED AND SYSTEM TESTED SERVICEABLE. (TC NR 20071206007)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008031900167	20080319	00167	NE  	2008	3	19	CA071206008      	2	20071129	G	7320	70BM032010	MODULE          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					ENGINE FUEL	DAMAGED         	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA			2975 								(CAN) IN A CRUISE FLIGHT OR CLIMB POWER, THE AC ENGINE WOULD SURGE. THE AC WAS REMOVED FROM SERVICE FOR INSP.  A CLOSE I	NSPECTION OF THE COVER THAT IS LOCATED OVER THE COMPRESSOR IMPELLOR, REVEALED A HOLE APPX. 4-5MM IN DIAMETER. THE MODULE	 3 WAS REMOVED AND REPLACED WITH A DIFFERENT MODULE AND THE AIRCRAFT WAS RE CERTIFIED.				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008022500085	20080225	00085	SO  	2008	2	25	CA071207002      	1	20071120	G	3231	40327000	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							317552130				(CAN) DURING INSPECTION, A CRACK WAS FOUND IN THE RT UPPER TRUNNION, MOVING FROM THE BOTTOM OF THE TRUNNION UPWARDS TOWA	RD THE ATTACHMENT POINT, THE GEAR DOOR ROD.  THIS IS THE SECOND ONE THIS YEAR. (TC NR 20071207002)					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
2008022500086	20080225	00086	NM  	2008	2	25	CA071207003      	1	20071104	G	3230	483023	SOLENOID VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UPON TAKEOFF AND GEAR RETRACTION RT MLG DOOR REMAINED OPEN WITH RT GEAR DOOR UNSAFE INDICATION.  MAINT REPLACED RT	 MLG SOLENOID SEQUENCE VALVE. (TC NR 20071207003)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008031900168	20080319	00168	EA  	2008	3	19	CA071207004      	2	20071130	G	8500		ENGINE          			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540B1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  		POWER LOSS      	W				B				EMER. DESCENT           				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AFTER 45 MINUTE FLIGHT BOTH ENGINES BEGAN LOSING PWR WITH NO FUEL FLOW INDICATIONS OR FUEL PRESSURE INDICATIONS. E	NGINES WOULD ONLY DEVELOP IDLE PWR. PILOT MADE A FORCED LANDING WITH MINOR INJURIES. FOLLOW UP INVESTIGATION TO FOLLOW. 	FOLLOW UP REPORT ON FINDING TO FOLLOW. (TC NR 20071207004)				1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P25EA	 
2008031900169	20080319	00169	NE  	2008	3	19	CA071208001      	2	20071205	G	7320	01644448430	FCU             			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	SURGES          	W				K				NONE                    				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			CA											(CAN) FCU WAS SURGING DURING A GROUND RUN LEAK CHECK, BLEED VALVE TACH BOX HAD BEEN CHANGED FOR TROUBLESHOOTING, SURGING	 CONTINUED. FCU CHANGED OUT AND SURGING PROBLEM WAS RESOLVED.  AC RETURN TO SERVICE. (TC NR 20071208001)					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2008022500087	20080225	00087	NM  	2008	2	25	CA071210001      	1	20071206	G	2133	20224806	ACTUATOR        			BOEING	767   	7673Y0      	       	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					OUTFLOW VALVE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE FLIGHT, LOST BOTH AUTO PRESSURIZATION SYS. FLIGHT CLIMBED TO FL190, AND RETURNED TO AIRPORT. CABIN PR	ESS WAS APPROX 2000 FT. THE STATUS MESSAGES RECEIVED: CABIN ALT AUTO 1 AND CABIN ALT AUTO 2. QRH CARRIED OUT, AND FLIGHT	 RETURNED TO DEPARTURE. NO FAULT FOUND, SYSTEM RESET, BUT THE VALVE ACTUATOR IS SUSPECTED,  (TC NR 20071210001)				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2008032400421	20080324	00421	EU  	2008	3	24	CA071210003      	1	20071206	G	3250	AIR860020	SELECTOR VALVE  			BAG   	JETSTM	JETSTM3212  	1500217	EU  										NLG STEERING	UNSERVICEABLE   	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						BADL48					(CAN) ON TAXI, PILOT FOUND THAT HE HAD REDUCED STEERING CONTROL OF THE AC USING THE NOSE WHEEL STEERING SYS. PILOT RETUR	NED TO BLOCKS, UNABLE TO CONTINUE HIS FLIGHT. UPON TROUBLESHOOTING, IT WAS FOUND THAT THE STEERING SELECTOR WAS NOT OPER	ATING PROPERLY, CAUSING A STEERING SYS FAILURE. THE STEERING SELECTOR WAS INSTALLED 03/10/2007 AND HAS ACCUMULATED 513 C	YCLES SINCE O/H AND 38.2 WEEKS IN SERVICE. THE O/H INTERVAL FOR THIS PART IS 10 000 CYCLES OR 72 MONTHS. THE STEERING SE	LECTOR WAS REMOVED AND AN O/H UNIT WAS INSTALLED AND THE NOSE WHEEL STEERING SYS FUNCTION CHECKED WITH NO FAULTS FOUND. 	AC RETURNED TO SERVICE. THIS STEERING SELECTOR WAS PURCHASED THROUGH TURBINE ENGINE CONSULTANTS INCORPORATED AFTER HAVIN	2	L	7	2 	4T			RT	BA15CAA 					 
2008022500089	20080225	00089	CE  	2008	2	25	CA071210004      	1	20071209	G	5753	351650503031	HINGE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9534 								(CAN) LT AND RT OB FLAPS IB HINGES WORN DUE TO ROLLER DIGGING INTO OB BRACKETS P/N 35-165050-30 AND 35-165050-31. THE AF	T BEARINGS/ROLLERS HAVE TO BE REMOVED TO GET A GOOD INSPECTION OF THIS AREA. IT SHOULD NOT BE DONE (IN-SITU). THIS IS TH	E 3RD AIRCRAFT IN THIS COMPANY FLEET THAT HAS HAD WEAR IN THIS AREA. IF LET GO TOO FAR, A FLIGHT CONTROL ISSUE MAY BE EN	COUNTERED. (TC NR 20071210004)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008022500090	20080225	00090	WP  	2008	2	25	CA071210005      	1	20071204	G	6310	369A53515	HOUSING         	DOUG        		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					CLUTCH	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1758 							(CAN) CLUTCH HOUSING RECEIVED FOR OVERHAUL AFTER PAINT STRIPPING HOUSING SENT OUT FOR NDT INSPECTION AND CAME BACK FOUND	 CRACKED ON ENGINE SIDE OF HOUSING. (TC NR 20071210005)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2008022500091	20080225	00091	EU  	2008	2	25	CA071210006      	1	20071207	G	2917	RPR2B	CONTROLLER      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					HYD ACCUMULATOR	MALFUNCTIONED   	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			8813 								(CAN) DURING FIRST GROUND RUN FOLLOWING A MAJOR 12 YEAR INSP, THERE WAS SIGNIFICANT HYDR FLUID LOSS IN THE AREA OF THE M	AIN ROTOR ACCUMULATORS. THE HELICOPTER HAD BEEN AT 70 PERCENT GROUND IDLE FOR APPROX 3-4 MINUTES. THE HELICOPTER WAS SHU	TDOWN IMMEDIATELY AND INSPECTED. ALL (3) ACCUMULATORS UNDERWENT VARYING DEGREES OF DEFORMATION (EXPANSION) DUE EXCESSIVE	 HYDR PRESSURE. HYDR FLUID LOSS WAS ISOLATED TO THE AREA OF THE COLLECTOR ASSEMBLIES MOUNTED ON THE SIDES OF THE SERVOS,	 SPECIFICALLY AT THE ACCUMULATOR AND ELECTRO VALVE JOINTS. IT IS SUSPECTED THE PRESSURE REGULATING VALVE OF THE HYDR MAN	IFOLD STUCK, PREVENTING FLUID FROM RETURNING TO TANK. THIS ALLOWED PRESSURE TO BUILD BEYOND REGULATED PRESSURE. FURTHER 	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022500092	20080225	00092	NM  	2008	2	25	CA071211001      	1	20071108	G	2731	82760174005	JACKSCREW       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR TRIM	CONTAMINATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			7816 								(CAN) ADVISORY MESSAGE DISPLAY INDICATED (MISTRIM NOSE DN) WITH AUTOPILOT ENGAGED. DISENGAGED AUTOPILOT - FWD CONTROL CO	LUMN FORCE REQUIRED TO MAINTAIN LEVEL FLIGHT, ATTEMPTED TO TRIM FWD BUT TRIM WHEEL WAS JAMMED WITH TRIM INDICATOR AT FWD	 OF THE TAKEOFF RANGE. TRIM MOVED REARWARDS OF THAT POSITION BUT NOT FWD OF IT. PAN DECLARED AND SERVICES REQUESTED, NOR	MAL APPROACH AND LANDING COMPLETED. FUNCTIONAL CHECK OF THE ELEVATOR TRIM SYS CARRIED OUT ON THE GROUND.  UNABLE TO REPL	ICATE REPORTED CONDITION. BOTH THE LT AND RT HAND SCREW JACK ASSEMBLIES, ELEVATOR TRIM WERE INSPECTED AND FOUND TO HAVE 	SUFFICIENT GREASE LUBRICATION, BUT THE GREASE WAS DETERMINED TO BE WATER CONTAMINATED DUE TO THE DISCOLORATION OF THE GR	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500093	20080225	00093	EU  	2008	2	25	CA071211002      	1	20071210	G	2750	Z4243130000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			404  								(CAN) THE FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE. (TC NR 20071211002)						1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2008022500094	20080225	00094		2008	2	25	CA071211003      	4	20071208	G	3417	8220372497	ADC             			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF348C5     	30050	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA			616  	616  							(CAN) THE FO REPORTED AN AIRSPEED OVER-SPEED TAPE ILLUMINATED AND COVERED THE ENTIRE SPEED TAPE ON THE AIRSPEED INDICATO	R. AN AMBER (STALL FAIL) EICAS MESSAGE AND STICK SHAKER ENSUED. THE STALL PTCT SWITCH WAS SELECTED OFF HOWEVER THE STICK	 SHAKER CONTINUED. QRH PROCEDURE C/O, REVERTED TO NR1 ADC AND SHAKER STOPPED, ALTHOUGH STALL FAIL, SPOILER FAIL AND MANY	 OTHER EICAS MESSAGES DISPLAYED. OPERATED SINGLE ADC AND ELECTED TO TURN BACK TO DEPARTURE. MDC FAULT HISTORY DISPLAYED 	ADC 2 NR OUT PUT MESSAGE B1-005863, STALL FAIL B1-008073 AND LABEL 350 BIT 27 SET INCONSISTENT ADC DATA. NR2 ADC AND NR2	 AOA SENSOR AT FAULT. NR2 ADC AND NR2 AOA SENSOR REPLACED AND FUNCTION TEST OF ADC-OVERSPEED WARNING AND ALTIMETER SCALE	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022500095	20080225	00095	EA  	2008	2	25	CA071211004      	1	20071205	G	2750	865D1007	PDU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			7610 	7610 							(CAN) AFTER LANDING WITH FLAPS AT 45 DEGREES, FLAPS SELECTED TO 0 DEGREES. CREW RECEIVED A FLAP FAIL AMBER MESSAGE AT FL	APS 41 DEGREES. MAINTENANCE TROUBLESHOOTING REVEILED FECU FAULT CODES FOR ASYMMETRY, BINDNG AND FLAPS NOT IN POSITION LE	ADING TO REPLACEMENT OF THE FLAP POWER DRIVE UNIT IAW AMM 27-52-01-400.  WILL UPDATE WHEN TEAR DOWN RESULTS BECOME AVAIL	ABLE. (TC NR 20071211004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500096	20080225	00096	EA  	2008	2	25	CA071211005      	1	20071205	G	2750	1104SD10020	FLEX DRIVE      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	TWISTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING WITH FLAPS AT 45 DEGREES, FLAPS SELECTED TO 0 DEGREES. CREW RECEIVED A FLAP FAIL AMBER MESSAGE AT FL	APS 41 DEGREES. DURING MAINTENANCE TROUBLESHOOTING OF FLAPS THE NR 2 RT FLEX DRIVE SHAFT ASSY WAS FOUND TWISTED. UPON RE	MOVAL PART LENGHTH WAS DISCOVERED TO BE 40 INCHES INSTEAD OF 39 INCHES IAW MFG SPECIFICATIONS. NO RECORD OF PREVIOUS REP	LACEMENT SINCE AC NEW. IPC 27-53-00 FIG 1, ITEM 10B.  (TC NR 20071211005)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500097	20080225	00097	NE  	2008	2	25	CA071211006      	2	20071130	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENG FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				746  							(CAN) DURING A 50 HOUR INSPECTION THE ENGINE DRIVE FUEL PUMP WAS FOUND LEAKING FROM SEAL.  (INNER DIAPHRAM) (TC NR 20071	211006)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500098	20080225	00098	NE  	2008	2	25	CA071211007      	2	20071211	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENG FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			822  								(CAN) DURING GROUND RUN, PUMP WAS FOUND LEAKING FROM DRAIN. PUMP REPLACED, NO FURTHER DEFECT. (TC NR 20071211007)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500099	20080225	00099	EU  	2008	2	25	CA071211008      	1	20071210	G	2820		WYE PIPE        			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE AC WAS BEING REFUELED OUT SIDE WHEN FUEL STARTED POURING ON THE GROUND FROM SOMEWHERE IN THE FUEL TANK AREA. F	URTHER INVESTIGATION REVEALED THE (Y) CONNECTION OF THE FUEL SUPPLY LINE FROM THE 2 BOOST PUMPS HAD SIMPLY FALLEN OUT OF	 THE FUEL LINE GOING UP TO THE FUEL FILTER ON THE TRANSMISSION DECK. THE 2 GEAR CLAMPS THAT SECURE THE HOSE TO THE (Y) F	ITTING WERE SECURED TIGHT ENOUGH THAT THE CLAMPS FELT TIGHT AND COULD NOT BE ROTATED ON THE HOSE BUT WHEN CHECKED WITH A	 SCREWDRIVER, THEY COULD BE TIGHTENED BY A FEW TURNS.  DUE THE NATURE OF THE ROUTING AND CLAMPING OF THE HOSE, THERE WAS	 A NATURAL TENDENCY FOR THE Y FITTING TO PULL DOWN ON THE UPPER HOSE. THE HOSE WAS REPOSITIONED AND CLAMPED PROPERLY TO 	1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2008022500101	20080225	00101	CE  	2008	2	25	CA071212002      	1	20070921	G	5711	95B55	SPAR            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9896 								(CAN) DURING ANNUAL INSPECTION, VISUAL INSPECTION OF AREA REVEALED A SUSPECTED CRACK. NOT OF DYE PENETRANT AND EDDY CURR	ENT CONFIRMED. MFG SERVICE KIT TO INSTALLED. PART LAST NDT INSPECTED 22.1 HRS PREVIOUS AND NO INDICATIONS. (TC NR 200712	12002)				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920	 
2008022500102	20080225	00102		2008	2	25	CA071212003      	4	20070510	G	3416	152734	RING            			ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE7313A    	01518	WP  					STBY ALTMETER	INCORRECT       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						8091					(CAN) MODIFICATION OF LOCKING PIN SLOT OF ITEM (PN 152734). RING SUPPORT FOUND ON THIS STBY ALTIMETER (TC NR 20071212003	).					2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2008022500103	20080225	00103	GL  	2008	2	25	CA071212004      	3	20071110	G	6114	B1192	DIAPHRAGM       			NAVION	STC   	STCNAVION   	       	    	CONT  	E185  	E1853       	17014	SO  	HARTZL	HC12V	HC12V20*    	GL  	PROP HUB	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			34   								(CAN) OIL LEAK AROUND PROP HUB AND SPRAYED ONTO WINDSHIELD.  PROP REMOVED. JACK PLATE ASSY REMOVED. DIAPHRAGM REMOVED. I	NNER SURFACE AROUND CENTER ATTACH RING ALMOST TOTALLY SPLIT AROUND CIRCUMFERENCE. THE DIAPHRAGM WAS INSTALLED JUNE 15, 2	007 AND FAILED IMMEDIATELY.  (TC NR 20071212004)				1	L	7	1 	3O	3	O		A782    	E246	5	C	P46GL	 
2008022500105	20080225	00105	CE  	2008	2	25	CA071212005      	1	20071127	G	5344	051701912	HINGE PIN       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	DOOR HINGE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DOOR HINGE PINS APPEAR TO BE WELDING RODS OR STEEL PINS CUT LONG AND BENT OVER TO SERVE FROM FALLING OUT. REPLACED	 WITH PROPER PARTS. CAUSED DISSIMILAR METAL CORROSION TO HINGE MATERIAL AS BOGUS PINS RUSTED.  THE ENTIRE FLEET HAS THES	E SAME BOGUS PINS (10 AIRCRAFT IN TOTAL). INSTALLED BY PREVIOUS MAINTAINER, AMO 73-03. (TC NR 20071212005)				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2008022500106	20080225	00106	EA  	2008	2	25	CA071212006      	3	20071127	G	6111		BLADE           	SNSNCH      		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			265  			AG1827			AG1827		(CAN) LONGITUDINAL CRACK AT BLADE TIP NR 1 BLADE.  CRACK APPROX 1.5 INCH LONG AT APPROX .75 CHORD.  FOUND DURING INSPECT	ION (ROUTINE). APPEARS TO BE CAUSED BY IMPACT DAMAGE FROM FOD. (TC NR 20071212006)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2008022500108	20080225	00108	EA  	2008	2	25	CA071212007      	3	20071127	G	6111		BLADE           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	PROPELLER	CRACKED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			330  			AG3920			AG3920		(CAN) LONGITUDINAL CRACK AT BLADE TIP, NR 1 BLADE.  CRACK APPROX 0.75 INCH LONG AT .25 CHORD.  FOUND DURING INSPECTION (	ROUTINE). NO APPARENT CAUSE, NO IMPACT DAMAGE FROM FOD. (TC NR 20071212007)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2008022500110	20080225	00110	NE  	2008	2	25	CA071212009      	2	20071114	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  						CONTAMINATED    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								123216			(CAN) CREW RECEIVED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUTDOWN THE ENGINE. INITIAL POST FLIGHT INVESTIGATION REV	EALS CONTAMINATION OF THE CHIP DETECTORS AND OIL FILTERS. THE ENGINE WILL BE SENT FOR INVESTIGATION.  MFG WILL CONTINUE 	INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071212009)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008022500111	20080225	00111	NE  	2008	2	25	CA071212010      	2	20070613	G	7250		TURBINE         			AEROSP	ATR72 	ATR72201    	8680943	EU  	PWA   	PW120 	PW124B      	 	NE  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								124515			(CAN) REPORTED TO MFG ON DEC 07 2007.  ENGINE REPORTED TO HAVE SUFFERED AN INFLIGHT SHUTDOWN DURING TAKEOFF/CLIMB. NO OT	HER DETAILS PROVIDED. POST FLIGHT INSPECTION INDICATES SEVERE DAMAGE TO THE TURBINE SECTION.   MFG WILL CONTINUE INVESTI	GATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071212010)				2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2008022500113	20080225	00113	NE  	2008	2	25	CA071212011      	2	20071021	G	7261		TUBE            			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  					ENGINE OIL	FRACTURED       	W				F	E	A		ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         	UNSCHED LANDING         		K	A	J	FLUID LOSS                	FLAME/FIRE                	WARNING INDICATION        	CR	CRUISE         	1			CA								120746			(CAN) FIRE WARNING DURING CRUISE. CREW ACTIVATED THE FIRE SUPPRESSION SYSTEM AND SECURED THE ENGINE. POST FLIGHT INITIAL	 INSPECTION REVEALED A FRACTURED NR 6 AND NR 7 BEARING OIL TRANSFER TUBE. SOME FIRE DAMAGE WAS OBSERVED ON THE AFT PORTI	ON OF THE ENGINE. THE ENGINE HAS BEEN REMOVED AND FORWARDED FOR FUTHER INVESTIGATION.   MFG WILL CONTINUE INVESTIGATING 	THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071212011)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2008022500114	20080225	00114	CE  	2008	2	25	CA071212012      	1	20071211	G	2720	MS35206228	SCREW           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RUDDER PEDAL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SL 550-27-14 FOUND 2 SCREWS, P/N MS350206-228, MISSING FROM PILOTS LT RUDDER SUPPORT BRACKET AND 2 LOOSE SCREWS P/	N MS 350206-228 ON THE CO-PILOTS RT RUDDER SUPPORT BRACKET.CARRY OUT ACCOMPLISHMENT INSTRUCTIONS PARAGRAPH 1THRU 4. (TC 	NR 20071212012)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008022500115	20080225	00115	EU  	2008	2	25	CA071212014      	1	20071211	G	2922	704A34629013	STRAINER        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STRAINER WAS INSPECTED AND FOUND CONTAMINATED WITH PARTICLES FOREIGN MATTER AND SLIVERS OF MATERIAL FROM THE O-RIN	G, P/N MS28775-016, WHICH WAS HARD AND BRITTLE.  THE MFG MM REQUIRES INSPECTION AND CLEANING OF THE STRAINER ONLY WHEN T	HE MANIFOLD IS REPLACED DURING A HYDRAULIC PUMP REPLACEMENT, THERE IS NO SCHEDULED INTERVAL FOR CLEANING.  ALL AC IN THE	 COMPANY FLEET WILL BE INSPECTED ON OR BEFORE THE NEXT 100 HOUR INSPECTION AND THIS TASK WILL BE ADDED TO 500 HOUR T-INS	PECTION.  THE MFG TECH REP HAS BEEN INFORMED OF THE FINDINGS OF THIS INSPECTION. (TC NR 20071212014)		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2008022500118	20080225	00118	EA  	2008	2	25	CA071212024      	1	20071026	G	7810	3009090	EXHAUST DUCT    			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5861 								(CAN) WHILE INSPECTING THE POWER SECTION FOR REASSEMBLY AFTER HSI, CIRCUMFERENTIAL CRACKS WERE DISCOVERED ALONG THE WELD	S OF THE EXHAUST DUCT JUST FWD OF THE PT VANE MOUNTING FLANGE. (4) CRACKS RANGED IN LENGTH FROM .75 INCH TO 4.75 INCH. T	HE POWER SECTION WAS REPLACED. (TC NR 20071212024)				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008022500119	20080225	00119	GL  	2008	2	25	CA071212025      	3	20071212	G	6114	87292	HUB             	MCAULY      		CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1481 			022853			022853		(CAN) AT OVERHAUL PROPELLER HUB WAS STRIPPED OF PAINT FINISH. ENTIRE OUTER SURFACE OF HUB AND BLADE O-RING GROOVES WERE 	CORRODED BEYOND LIMITS. HUB WAS RETURNED TO MFG FOR EVALUATION. (TC NR 20071212025)					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
2008022500122	20080225	00122	GL  	2008	2	25	CA071212026      	3	20071211	G	6110		FLANGE          	MCAULY      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1516 		SR773463			SR773463		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION IAW AD 2003-12-05. A SMALL CRACK WAS LOCATED RADIALLY AT THE EDGE OF O	NE MOUNTING BOLT HOLE.  TIME SINCE LAST INSPECTED FOR AD 2003-12-05 WAS 409.2 HOURS. (TC NR 20071212026)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2008022500123	20080225	00123	CE  	2008	2	25	CA071212027      	1	20071207	G	3244	TU29110010	TIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	FLAT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) TIRE WENT FLAT. (TC NR 20071212027)						1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008022500124	20080225	00124	CE  	2008	2	25	CA071212028      	1	20071128	G	3244	TU29110010	TIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	FLAT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			920  								(CAN) TIRE WENT FLAT. (TC NR 20071212028)						1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008022500126	20080225	00126	NE  	2008	2	25	CA071213001      	2	20071212	G	7261	6087T04P09	SCAVENGE PUMP   	GE          		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			29540	367  		807240		807240			(CAN) DURING CRUISE FLIGHT, THE CREW RECEIVED RED NR 2 ENG LOW OIL PRESS MESSAGE AND GAUGE INDICATION FOR NR 2 ENGINE SH	OWED (0) PSI, CREW ELECTED TO SHUTDOWN ENGINE AND RETURN TO DEPARTURE AIRPORT, NORMAL LANDING. MAINTENANCE FOUND NR 2 EN	GINE, OIL LUBE/SCAVENGE PUMP ROTATES FREELY WITH NO PRESSURE OUTPUT.  PUMP TO BE SENT OUT TO VENDOR FOR INVESTIGATION.  	OIL PUMP INFORMATION: MFG CO P/N 99207SOCN6087T04P09, CODE IDENT 86329, REF 4406-9 S/N NMAAD498 TSN 29540HR / 24208CY , 	TSO 367HR / 309CY.(TC NR 20071213001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500127	20080225	00127	CE  	2008	2	25	CA071213002      	1	20071212	G	2121		BRUSHES         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BLOWER MOTOR	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				1357 							(CAN) CREW DECLARED EMERGENCY DUE TO SMOKE IN COCKPIT AND LANDED SAFELY. REPAIR PARTY LT FROM ANOTHER BASE. FOUND CAUSE 	WAS CABIN VENT BLOWER. DISABLED SYSTEM. AIRCRAFT FERRIED TO AIRPORT.  MAINTENANCE WILL REPLACE VENT BLOWER. (TC NR 20071	213002)				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2008022500128	20080225	00128	NM  	2008	2	25	CA071213003      	1	20071213	G	5321	CMKD8400FP540	FLOOR PANEL     			BOMBDR	DHC8  	DHC8400     	       	NM  										CABIN	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2595 								(CAN) FORWARD CABIN FLOOR PANEL WHERE PURSER STANDS TO GIVE PRE-FLIGHT BRIEFING STARTING TO DELAMINATE. MATERIAL IS COMP	 28 WHICH IS BUILT TO STAND STRESS OF 75 LB/FT SQUARED. (TC NR 20071213003)					2	H	7	2 	4T			RT	A13NM   					 
	20080520		CE  	2008	5	20	CA071213004      	1	20070725	G	2720	07600323	SHAFT           			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	RUDDER PEDALS	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			14983								(CAN) RUDDER BAR ASSY CRACKED AT SPIGOT ATTACH POINT WHERE RUDDER PEDAL STUB SHAFT (PN 0411307) CONNECTS TO RUDDER BAR A	SSY.  PILOTS REPORTED A SOFT PEDAL ON WATER OPERATIONS, INVESTIGATION REVEALED A SPHERICAL CRACK ON THE RUDDER PEDAL TOR	QUE TUBE. (TC NR 20071213004)				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
2008022500129	20080225	00129	CE  	2008	2	25	CA071214001      	1	20071204	G	5220		HANDLE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	EMERGENCY EXIT	JAMMED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			200  								(CAN) DURING THE INITIAL PHASE ONE INSPECTION THE EMERGENCY EXIT COULD NOT BE OPENED FROM THE OUTSIDE AND THE EXIT COULD	 NOT BE LOCKED FROM THE INSIDE. (TC NR 20071214001)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008022500130	20080225	00130	GL  	2008	2	25	CA071214002      	1	20071214	G	5751	C2WA126A	HINGE BRACKET   	DHAV        		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985*       	52008	NE  					AILERON	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA						SA721					(CAN) FAILURE NOTICED DURING WALK AROUND BY MECHANIC. THE SPIGOT (INTEGRAL PART OF THE HINGE BRACKET) HAD FAILED COMPLET	ELY, JUST BELOW THE UPPER EDGE OF THE BALANCE WEIGHT ARM. JUDGING BY THE SURFACES THE SPIGOT HAD BEEN BROKEN FOR SOME TI	ME. EXTREMELY DANGEROUS SITUATION. NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 20071214002)				1	H	7	1 	3R	3	R	RC	A806    	5E1				 
2008013100283	20080131	00283	EA  	2008	1	31	CA071214003      	1	20071214	G	2823	C2CE523A	CABLE           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985*       	52008	NE  					FUEL SELECTOR	CORRODED        	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) FUEL SELECTOR CABLE VERY BADLY CORRODED, CABLE FAILED WHEN REMOVED.  NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 200	71214003)					1	H	7	1 	3R	3	R		A806    	5E1				 
2008013100284	20080131	00284	EA  	2008	1	31	CA071214004      	1	20071213	G	2752	852D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) FLAP FAIL ON DESCENT, WHEN FLAP SELECTED FROM 0 DEG TO 8 DEG. FLAPLESS LANDING CARRIED OUT WITHOUT FURTHER INCIDEN	T. TROUBLESHOOTING IN PROGRESS. WILL UPDATE WHEN MORE INFORMATION IS AVAILABLE (TC NR 20071214004)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008013100285	20080131	00285	GL  	2008	1	31	CA071214005      	1	20071004	G	5344	C2FS1253A	HINGE BRACKET   			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11888								(CAN) TOP HINGE BRACKET CRACKED ON FWD FACE OF HINGE.  (TC NR 20071214005)						1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2008013100287	20080131	00287		2008	1	31	CA071214006      	4	20071212	G	6122	3011847	LINE            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								PCE51194			(CAN) AFTER DEPARTURE DURING CLIMB, THE PILOT NOTICED SLIGHT POWER LOSS ON THE LT ENGINE WHICH SLOWLY DECAYED UNTIL TORQ	UE WAS AT 100LBS AT WHICH TIME THE PROP WAS FEATHERED. THE CREW ELECTED TO LEAVE THE ENGINE RUNNING AS ALL OTHER INDICAT	IONS WERE GREEN AND THEY WANTED THE GENERATOR RUNNING AS ICING CONDITIONS WERE FORECAST.  UPON INSPECTION BY MAINTENANCE	, IT WAS DISCOVERED THE PY LINE FROM THE PROP GOVERNOR TO THE FCU WAS CRACKED. THE LINE WAS REPLACED GROUND RUNS CARRIED	 OUT AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071214006)		1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2008020400125	20080204	00125	EU  	2008	2	4	CA071214007      	1	20071210	G	3411	257SF2099	PITOT TUBE      			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  						CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6664 								(CAN) FOLLOWING A FAILED PITOT STATIC TEST, AN INSPECTION OF THE PITOT STATIC TUBING WAS CARRIED OUT AND MAINT FOUND THA	T ONE OF THE TUBES (P/N 25-7SF209-9) HAD A PIN HOLE, WHICH APPEARS TO HAVE BEEN CAUSED BY INTERGRANULAR CORROSION. THE L	INE WAS REPAIRED AND THE PITOT STATIC SYSTEM TESTED SERVICEABLE.  REFERENCE:  PARTS CATALOG 34-10-00-22 ITEM 24 (P/N 25-	7SF209-9), PIPE ASSY-STATIC 5 FEED, TEE-PIECE TO TEE-PIECE, 3/8 INS O/D, L56, 22 SWG (MOD252870) (TC NR 20071214007)			2	L	7	2 	4F	4	F		A3EU    	E6WE				 
	20080520		CE  	2008	5	20	CA071214008      	1	20071213	G	3230	CAC99126259	VALVE           			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			585  								(CAN) AT LANDING GEAR SELECTION, THE LANDING GEAR DID NOT COME DOWN AND NONE OF THE FOLLOWING INDICATIONS WERE OBSERVED:	  HYD PUMP OPERATION GEAR MOVEMENT / NOISE GEAR DOWN LIGHTS INDICATION ON THE CONTROLLER,  NOTE: ALL OTHER HYD CONSUMERS	 WERE OPERATIONAL THE GEAR WAS RECYCLED WITH NO SUCCESS. A GO-AROUND WAS INITIATED THEN THE ABNORMAL/EMERGENCY CHECKLIST	 WAS REVIEWED AND CARRIED OUT, GEAR CAME DOWN AND LOCKED . VALVE REPLACED GEAR SYS, OK (TC NR 20071214008)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008020400124	20080204	00124	SW  	2008	2	4	CA071214009      	1	20071210	G	7120	205060106001	MOUNT           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9047 								(CAN) RT ENGINE BIPOD INSPECTED FOR SUSPICIOUS CRACK IN FRONT TUBING DURING 100 HRS INSPECTION. NDT REVEALED CRACK MOUNT	 AT WELDED JOINT.  NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071214009)					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008020400123	20080204	00123	WP  	2008	2	4	CA071214010      	1	20071214	G	7603	A9333	ROD END         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					THROTTLE CONTROL	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE HAD HIGH IDLE, TRYED TO ADJUST AND WAS UNABLE TO BRING IDLE BELOW 64 PERCENT ENG RPM. INSPECTED THROTTLE LI	NKAGE AND FOUND ROD END BRG OUTER HOUSING SEPARATED FROM STAKED IN SPHERICAL BEARING. POSSIBLE LOST OF ENGINE CONTROL UN	DER QUICK POWER CHANGES. REPLACED ROD END AND RECTIFIED DEFECT. (TC NR 20071214010)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008020400122	20080204	00122	CE  	2008	2	4	CA071214011      	1	20071214	G	5280	16911003421	BOLT            	BEECH       		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	MLG DOOR	MISSING         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT NOTICED ON PRE-FLIGHT, ABNORMAL ANGLE OF GEAR DOOR. IT WAS DISCOVERED THAT THE BOLT SECURING THE DOOR WAS MI	SSING. THIS STRESSED THE AFT BRACKET TO THE POINT OF CRACKING WHICH ALSO CAUSED THE DOOR TO CRACK ALONG THE BOLT HOLES. 	(TC NR 20071214011)				1	L	7	2 	3O	3	O		A29CE   	E286	5	C	P43GL	 
2008020400121	20080204	00121	NE  	2008	2	4	CA071217001      	2	20071205	G	7230		FAN BLADE       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					RT ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				C	E		F.O.D.                    	VIBRATION/BUFFET          		CR	CRUISE         	1			CA								807658			(CAN) CREW REPORTED N2 VIB ICON (RT ENG) POSTED DURING CRUISE AT FL320. CREW FOLLOWED QRH AND COULD NOT CONTROL VIB IFSD	 AND DIVERTED.  MAINTENANCE OBSERVED FOD DAMAGE TO FAN BLADES. ENGINE REMOVED AND REPLACED (TC NR 20071217001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008020400120	20080204	00120	NM  	2008	2	4	CA071217003      	1	20071205	G	2910	DSC252B40124	FLEX LINE       			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) TOTAL FAILURE OF NR 2 HYD SYS OCCURRED AFTER GEAR EXTENSION (NORMAL). LOSS OF PRESSURE WITH ASSOCIATED CAUTION LIG	HTS QUICKLY FOLLOWED BY TOTAL LOSS OF ALL NR 2 HYD QUANTITY (FLUID). UPGRADED CALL TO PAN WITH REQUEST FOR LOCAL SERVICE	S ON STANDBY. AFTER ALTERNATE GEAR EXTENSION, THE NR 2 HYD PRESSURE ROSE TO NORMAL AT 3000 PSI. AFTER LANDING WITH NORMA	L HYD PRESSURE, AC TAXIED CLEAR OF RUNWAY.   ENGINEERING INVESTIGATION REVEALED A FAILURE OF THE NLG DRAG BRACE ACTUATOR	 (DOWN) FLEXIBLE HOSE. HOSE REPLACED AND FOLLOWING APPROPRIATE CHECKS IAW THE MM.  THE AIRCRAFT WAS RELEASED BACK TO SER	VICE WITHOUT FURTHER INCIDENT.   THIS IS A KNOWN ISSUE PREVIOUS SDR 20031030005. (TC NR 20071217003)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500136	20080225	00136	EA  	2008	2	25	CA071217004      	1	20071212	G	7600	3052970	CONTROL CABLE   			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	CONDITION LEVER	DISCONNECTED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) AFTER FLIGHT, THE NR 2 CONDITION LEVER WOULD NOT MOVE TO FEATHER OR CUTOFF, THE ENGINE HAD TO BE SHUTDOWN USING TH	E T-HANDLE.  FURTHER INVESTIGATION REVEALED THAT THE NR 2 TELEFLEX CABLE HAD BECOME UNSCREWED NEAR THE BEARING.  WE WERE	 UNAWARE THAT THE CABLE COULD BE UNSCREWED AT THIS LOCATION, WHEN THE CABLE IS ASSEMBLED THERE IS NO VISUAL INDICATION T	HAT THE CABLE CAN BE DISASSEMBLED. THERE ARE NO PROVISIONS FOR THE CABLE TO BE LOCK WIRED AT THIS LOCATION. TIME SINCE N	EW UNKNOWN.  FURTHER INVESTIGATION FOUND ONE OTHER UNSCREWED CABLE ON THE AIRCRAFT. WE WILL BE INSPECTING OUR FLEET TO A	SSURE NO OTHER CABLES ARE LOOSE. (TC NR 20071217004)	2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2008022500137	20080225	00137	EA  	2008	2	25	CA071217005      	1	20071214	G	2752	852D100	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FROZEN          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) FLAP FAIL DURING DESCENT. FLAPS WOULD NOT EXTEND WHEN SELECTED, FLAP 0 APPROACH AND LANDING CONDUCTED. AIRCRAFT LA	NDED WITHOUT FURTHER INCIDENT.  FAULT CODES SENT TO TECH OPS, AIRCRAFT WILL BE FERRIED WHEN CREW AVAILABLE. FAULT CODES 	ARE AS FOLLOWS: EVENT 1 FLIGHT LEG 4555  JAM/ LT BPSU/ PDU DIFFERENTIAL/ 5 1B/ 5 2B/ 9 1A/ 9 2A/ 17 1A/ 17 2A/ 25 BC. EV	ENT 2 FLIGHT LEG 4555 JAM/ ADC SIGNALS/ LH BPSU FAIL/ 5 2B. FAULT INDICATION IS POINTING A FREEZE EVENT. MORE INFORMATIO	N WILL BE ADDED AS SOON AS BECOME AVAILABLE. (TC NR 20071217005)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500138	20080225	00138	WP  	2008	2	25	CA071217006      	2	20071214	G	7321	NAS1351C3LL6	BOLT            	WOODWARD    		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	FUEL CONTROL	BACKED OUT      	W				A				UNSCHED LANDING         				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		CL	CLIMB          	1			CA						2137501					(CAN) ON CLIMB OUT, THE PILOT REPORTS NR 1 ENG RPM DROPPED TO 97 PERCENT AND HE WAS NOT ABLE TO RESTORE THE ENG TO 100 P	ERCENT RPM.  PROCEEDED TO MAKE AN UNSCHEDULED LANDING AT DEPARTURE AIRFIELD. UPON INVESTIGATION IT WAS FOUND THAT THE BO	LT ATTACHING THE SPEED LEVER TELEFLEX CABLE TO SPEED INPUT SHAFT OF THE FCU HAD BACKED OUT COMPLETELY AND THE CABLE HAD 	SEPARATED FROM THE INPUT ROD. THE BOLT IN QUESTION WAS RE-USED ON AN ENGINE CHANGE THAT TOOK PLACE 33.6 HOURS PRIOR TO T	HIS EVENT, ON 11/28/2007. AT THAT TIME THE BOLT MET THE RUN-DOWN TORQUE REQUIREMENTS FOR SELF LOCKING HARDWARE IAW MM ST	ANDARD PRACTICES. THE BOLT WAS REPLACED, THE ENGINE RE-RIGGED WITH NO FAULTS FOUND AND THE AC RETURNED TO SERVICE. (TC N	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2008022500140	20080225	00140	NE  	2008	2	25	CA071217007      	2	20071217	G	7314	D7431	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX FUEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1564 								(CAN) PILOT ATTEMPTED TO START AIRCRAFT, BUT FAILED. FURTHER INVESTIGATION REVEALED THE AUX FUEL PUMP DID NOT SUPPLY FUE	L TO START AIRCRAFT.  PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071217007)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500141	20080225	00141	EA  	2008	2	25	CA071217008      	1	20071212	G	2750	5275200	DRIVE ASSY      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			9151 	9145 							(CAN) FLAPS FAILED AT 30 DEG WHEN 45 DEG SELECTED.  FLAP ACTUATORS, PDU AND FECU REPLACED TEST FLIGHT CARRIED OUT CHECKE	D SUSPECT POWER FLAP DRIVE AT FAULT DUE TO HISTORY. (TC NR 20071217008)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500142	20080225	00142	EA  	2008	2	25	CA071217009      	1	20071214	G	2752	854D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAP	MALFUNCTIONED   	W				L				ABORTED APPROACH        				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		AP	APPROACH       	1			CA			7255 								(CAN) ON APPROACH THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE AFTER SELECTING THE FLAP LEVER TO 8 DEGREES. THE EICAS F	LIGHT CONTROL PAGE WAS SHOWING THE FLAP POSITION AT 2 DEGREES. THE CREW REQUESTED EMERGENCY SERVICES AND LANDED WITHOUT 	FURTHER INCIDENT.   AC WAS INSPECTED AND FERRIED. ADCF 2007-10 AND SB601R-27-150 WERE COMPLETED. THE LT NR4 AND RT NR3 F	LAP ACTUATORS FAILED THE -60 DEGREES CELSIUS TORQUE CHECK AT A VALUE OF 35 AND 30 INCHES/POUND RESPECTIVELY.   LT NR4, P	/N 854D100-19, S/N 2312, TSN 7255:58, CSN 5839, TSR 1971:52 RT NR3, P/N 853D100-20, S/N 3377, TSN 8268:20, CSN 6104, TSR	 1971:52  BOTH ACTUATORS WERE REPLACED. THE LT NR3, RT NR1 AND NR4 FLAP ACTUATORS WERE FOUND NEAR SERVICE LIMIT AND WERE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500143	20080225	00143	EA  	2008	2	25	CA071217010      	1	20071213	G	2750		FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAULTED         	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLAP FAIL ON APPROACH WHEN FLAPS SELECTED TO 20 FROM 8.  SYS RESET AND CHECKED SERVICEABLE, MAINT EMPLOYEE ON SITE	 GOT FAULT CODES FROM FECU.  SKEW BITE RESET AND FLAP CONTROL AND POWER DRIVE UNIT RESETS CARRIED OUT.  FLAP FAULT CLEAR	ED. FLAPS CYCLED SEVERAL TIMES NO FAULTS NOTED. SYSTEM FUNCTION CHECKED SERVICEABLE FOR FLIGHT. (TC NR 20071217010)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500145	20080225	00145	EU  	2008	2	25	CA071218001      	2	20071208	G	7261	FC3401B01B01B029	HOSE            			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	ENGINE OIL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			2000 								(CAN) PILOT LANDED NORMALLY AND SHUTDOWN AFTER NOTICING FALLING OIL PRESSURE INDICATION. THIS WAS ON INITIAL TEST FLIGHT	 OF A NEW ENGINE INSTALLATION, ON INSPECTION THE OIL PRESSURE HOSE FITTING AT THE OIL PUMP WAS FOUND TO BE LEAKING, THIS	 WAS TIGHTENED AND AN INSPECTOR OF THE ENGINE COMPLETED. A SEPARATE MECHANIC VERIFIED THE OIL LINE FITTING AND FOUND IT 	TO BE LOOSENED OFF AGAIN. A TWIST IN THE HOSE AND A WEAK THREAD ENGAGEMENT WERE SUSPECTED. A NEW HOSE WAS INSTALLED AND 	THE ENGINE TEST RUN AND CHECKED WITH NO PROBLEMS NOTED, A TEST FLIGHT WAS COMPLETED AND ANOTHER INSPECTION OF THE ENGINE	 REVEALED NO PROBLEMS. THE AC WAS RETURNED TO SERVICE. (TC NR 20071218001)	1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO	 
2008022500147	20080225	00147	CE  	2008	2	25	CA071218002      	1	20071214	G	7110	10191011947	VANE            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RT INTAKE DUCT	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			744  								(CAN) ON THE RT ENGINE COWLING INTAKE DUCT THERE IS A VANE ASSY TO REDIRECT INTAKE AIRFOW. THE VANE ASSY WAS FOUND TO HA	VE DEBONDED ITSELF FROM THE ATTACH BRACKETS. THE VANE WAS ALSO CRACKED COMPLETELY ALONG THE TRAILING EDGE AND A 4 INCH C	RACK LOCATED ON THE LT SIDE LEADING EDGE OF THE VANE. IT LOOKS LIKE POOR WELDING AND BONDING WERE THE CAUSE OF FAILURE. 	(TC NR 20071218002)			2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2008022500149	20080225	00149	NE  	2008	2	25	CA071218003      	2	20071217	G	7320	78639110	HMU             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA				26832				120644			(CAN) NR2 ENGINE EXPERIENCED AN IN FLIGHT SHUTDOWN, SHORT FINAL (500FT AGL) AND WAS IN ECU MODE. CREW DID NOT HAVE THE T	IME TO TRY MANUAL MODE. AS THEY WERE FEATHERING THE ENGINE (PROPELLER), THEY NOTICED THE TORQUE INCREASING, AS IT HIT AR	OUND 90 PERCENT AND THE CREW SHUT THE ENGINE DOWN.  FDR WAS REMOVED AND YYC AVIONICS SHOP HAS BEEN RESERVED TO READ THE 	FDR.  ANALYSIS OF THE FDR INDICATES THAT THERE IS AN UNCOMMANDED INPUT OF FUEL TO NR2 ENGINE. THERE IS NO INDICATION THA	T THE PROPELLER IS OVER TORQUED AND IS THEREFORE SERVICEABLE FOR FURTHER USE. THE FOLLOWING MAINTENANCE ACTIONS WERE CAR	RIED OUT: NR2 HMU CHANGED. NR2 ENGINE RIGGING CHECK CARRIED OUT FROM THE COCKPIT OUT TO THE ENGINE.  NR 2 SPRING STRUT I	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500151	20080225	00151	CE  	2008	2	25	CA071218004      	1	20071217	G	3246		WHEEL           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PILOTS WALK AROUND THEY FOUND METAL AROUND NOSE WHEEL TIRE. AIRCRAFT WAS TOWED INTO A HEATED HANGER AND PILOT P	HONED MAINTENANCE . ENGINEER JACKED NOSE WHEEL AND INSPECTED NOSE WHEEL SPIN-UP KIT AND FOUND LT TURBINE AND LT SPIN-UP 	COVER WERE DAMAGED. REMOVED NOSE WHEEL SPIN-UP KIT AND INSTALLED ANOTHER TIRE/WHEEL ASSY AND RETURNED AIRCRAFT TO SERVIC	E (TC NR 20071218004)			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008022500152	20080225	00152	NE  	2008	2	25	CA071218005      	2	20071216	G	7261		SEAL            			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	NR 1 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								PCE120670			(CAN) AFTER DEPARTURE AND ENROUTE TO DESTINATION, THE CREW OBSERVED A LOW OIL PRESSURE WARNING LIGHT AND NOTED FLUCTUATI	NG OIL PRESSURE ON THE NR 1 ENGINE. THE ENGINE WAS SHUTDOWN AND RESTARTED IAW THE OPERATING PROCEDURES MANUAL, THE OIL P	RESSURE WAS NOTED TO BE NEAR ZERO. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. NO EMERGENCY	 WAS DECLARED. MAINTENANCE DETERMINED THAT THE NR 1 GENERATOR SEAL FAILED RESULTING IN THE LOSS OF OIL FROM THE NR 1 ENG	INE. (TC NR 20071218005)		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008022500153	20080225	00153	SW  	2008	2	25	CA071218006      	1	20071214	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			4884 								(CAN) UPON ENGINE START AND TAXI THE F/O HEATED WINDSCREEN CRACKED. THE GLASS CRACKED FROM THE BOTTOM UP. THE CREW TURNE	D AROUND AND SHUTDOWN. MAINT REMOVED AND REPLACED THE WINDOW. OUR COMPANY CONTINUES TO HAVE PROBLEMS WITH THESE HEATED W	INDSHIELDS AND IN SPEAKING WITH OTHER OPERATORS IN THE RECENT PAST THEY HAVE HAD SIMILAR FAILURES OF THESE WINDSHIELDS. 	MOST OF THE FAILURES ARE IN FLIGHT FAILURES. THE TOTAL TIME ON THE WINDSHIELD WAS DETERMINED TO BE 4884.1 BUT MAY BE SLI	GHTLY HIGHER AS THIS WINDSHEILD WAS INSTALLED ON THE AC PRIOR TO PURCHASE. REGARDLESS OF TOTAL TIME THE FAILURE MODE OF 	THESE WINDOWS IS A SAFFTY CONCERN. (TC NR 20071218006)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2008022500155	20080225	00155	EA  	2008	2	25	CA071218007      	1	20071214	G	5320	CA447	SHROUD          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					BS 559	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29474								(CAN) DURING HEAVY CHECK INSP, THE FUEL DISTRIBUTION PRESSURE BOX ASSY, P/N 601R62676-5 WAS FOUND CRACKED AND BOTH THE F	UEL SHROUD AND FUEL LINES HAVE CHAFFING DAMAGE BEYOND LIMITS. THESE COMPONENTS ARE LOCATED AT FUSELAGE STATION FS559.  P	ARTS ARE ON ORDER AND DAMAGED FUEL SHROUD AND THE FUEL BOX WILL BE REPLACED BEFORE AIRCRAFT IS RELEASED FROM HEAVY CHECK	. NOTE:- PLEASE REFER TO PREVIOUS SDR NR 20071005001 (TC NR20071218007)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500156	20080225	00156	EU  	2008	2	25	CA071218008      	1	20071213	G	2560	22719TK060052X	PIN             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					SEAT BELT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE PROCESS OF AN ICC FOLLOWING HEAVY MAINT, THE ENGINEER NOTICED THAT THE RETAINING PIN P/N 22719TK060052X	 FOR THE PILOT`S SEAT BELT OB FITTING WAS LOOSE OR ABOUT TO FALL OUT OF THE FLOOR SUPPORT. UPON INVESTIGATION IT WAS FOU	ND THAT THE RIVET THAT NORMALLY HOLDS THE SEAT BELT PIN IN PLACE HAD BEEN REPLACED, POSSIBLE DURING A VERTICAL REFERRENC	E WINDOW INSTALLATION. THE RIVET WAS REPLACED WAS BUCKED TO THE NORMAL SIZE IAW STANDARD PRACTICES AND DID NOT PROTRUDE 	LONG ENOUGH TO HOLD THE PIN IN PLACE. UPON NOTICING THIS OCCURANCE WE CHECKED (4) OTHER AIRCRAFT ON SITE AND FOUND 2 MOR	E WITH THE SAME PROBLEM.  IN THE IPC 53.10.20.000 (04-06) PAGE 02.00 FIGURE 1 SHOWS THE PIN AS DRILLED AT THE END MAYBE 	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022500157	20080225	00157	NM  	2008	2	25	CA071219001      	1	20071216	G	3234	6131001001	SELECTOR VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR SELECTOR LEVER SELECTED UP, BOTH LT AND RT MAIN GEAR DOOR CAUTION LIGHTS ILLUMINATED, 	BOTH MAIN GEARS FAILED TO RETRACT BUT NOSE GEAR HAD RETRACTED.  AC RETURNED TO BASE FOR FURTHER INVESTIGATION. FLIGHT SN	AG COULD BE DUPLICATED ON GROUND. DURING TROUBLESHOOTING AND REMOVAL OF THE MLG SELECTOR VALVE, IT WAS NOTICED THAT FILT	ER HAD SEPARATED IN VALVE CAUSING BLOCKAGE. (TC NR 20071219001)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022500159	20080225	00159	NE  	2008	2	25	CA071219002      	2	20071218	G	7230	BRH20419	BLADE           	RROYCE      		BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					HP COMPRESSOR	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA			1744 			M33121					(CAN) ENGINE SURGE ON LANDING. ENGINE RETURNED TO SHOP FOR SUSPECTED HPC STG 1 BLADES DAMAGE. DURING ENGINE DISSASEMBLY 	HPC ROTOR WAS FOUND WITH HEAVY DAMAGE, SUSPECT DAMAGE CAUSED BY A BLADE FAILURE AT PLATFORM. ALL FAILED PARTS WILL BE RE	TURNED TO THE OEM FOR INVESTIGATION. (TC NR 20071219002)				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2008022500160	20080225	00160	NE  	2008	2	25	CA071219003      	2	20071219	G	7250	FW35594	TURBINE BLADES  			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			8994 								(CAN) ENGINE WILL BE INDUCTED IN JANUARY, 2008 FOR INVESTIGATION FOR HPT STG 1 BLADE FAILURE.  BLADES WERE FITTED NEW AT	 LAST SHOP VISIT AT 14773 CYCLES. SUSPECT FAILURE SIMILAR TO PREVIOUS SDR SUBMITTED 20070911004, 20071001001. FURTHER DE	TAILS WILL BE SUBMITTED AT ENGINE DISASSEMBLY. (TC NR 20071219003)				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2008022500161	20080225	00161	NE  	2008	2	25	CA071219004      	2	20071219	G	7250	FW35544	TURBINE BLADES  			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			7723 								(CAN) ENGINE CURRENTLY IN SHOP FOR REPAIR DUE TO HP 1 TURBINE BLADE FAILURE, ENGINE DISASSEMBLY REVEALED FAILURE OF BLAD	E AT PLATFORM. FAILED PART WILL RETURNED TO THE OEM FOR INVESTIGATION. PREVIOUS SDR RAISED FOR SAME EVENT 2007091104, 20	071001001,20071219003. ENGINES SHOP VISITS DOCUMENTATIONS HAS BEEN REQUESTED BY THE OEM FOR ALL SIMILAR EVENT FOR THE IN	VESTIGATION (TC NR 20071219004)			2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2008022500162	20080225	00162	NE  	2008	2	25	CA071219005      	2	20070905	G	8530	127599	SCREW           			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	INTAKE ROCKER	SEVERED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				869  							(CAN) DURING AN UNRELATED INSPECTION, THE INTAKE VALVE ROCKER ARM ADJUSTMENT SCREW (127599) WAS FOUND SEVERED INSIDE THE	 LOCKING JAM NUT.  POSSIBLE METAL FATIGUE.  (TC NR 20071219005)					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2008022500164	20080225	00164	EA  	2008	2	25	CA071219006      	1	20071217	G	5414		SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29474								(CAN) BOTH THE LT AND RT REPAIR DOUBLERS THAT ARE IDENTIFIED AS ITEM -1 ON THE ATTACHED REO601R-53-61-358, REVISION A, W	ERE FOUND CRACKED DURING AN INSPECTION OF THE ENGINE SUPPORT BEAMS AT A HEAVY CHECK VISIT.  THIS AC CAME INTO OUR AIRLIN	E OPERATION AT APPROX 20859 CYCLES. WE ARE UNABLE TO CONFIRM THE EXACT TIME THIS REPAIR WOULD HAVE BEEN INCORPORATED ON 	THIS AC.  WE HAVE CONTACTED THE MFG TECHNICAL HELP DESK WITH OUR FINDING AND ARE AWAITING FURTHER REPAIR INSTRUCTIONS FR	OM THEM. (TC NR 20071219006)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080520		CE  	2008	5	20	CA071219008      	1	20071213	G	2497	AAPA4CHAFED	WIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	NR 2 BUS BAR	CHAFED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT ALL (3) BUS, NR 2 CIRCUIT BREAKERS POPPED AND THE STANDBY POWER CIRCUIT BREAKER ON BUS, NR 2 	POPPED. THE AC LANDED WITHOUT FURTHER INCIDENT. UPON ARRIVAL MAINT PERSONNEL INSPECTED THE WIRING ON THE DISTRIBUTION PA	NEL AND FOUND WIRE AAPA4 CHAFED TO THE NR 2 BUS BAR. THE CHAFED WIRE WAS REPAIRED IAW STANDARD PRACTICES AND THE AC WAS 	GROUND RUN AND CHECKED SERVICEABLE. (TC NR 20071219008)			1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008022500167	20080225	00167	NM  	2008	2	25	CA071219009      	1	20071218	G	3230	535201	SEQUENCE VALVE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			28240	925  							(CAN) THE GEAR WAS SELECTED UP, IT RETRACTED NORMALLY. THROUGH 2000 FT THUMPING NOISE IN NOSE WAS HEARD FOLLOWED BY AN A	MBER LIGHT IN THE SELECTOR KNOB FLASHING ON.  OCCASIONALLY A RED NOSE GEAR LIGHT CAME ON. MAINT REPLACED NLG DOOR WARN P	ROX SWITCH AND SWAPPED THE NOSE GEAR SEQ VALVE RELAY WITH THE RT MLG DOOR SEQ VALVE. AFTER FURTHER T/S IT WAS SUSPECTED 	THAT MLG SELECTOR HANDLE WAS AT FAULT. AT THIS TIME THE MLG SELECTOR HANDLE WAS REPLACED FOR T/S AND WILL UPDATE FURTHER	 WHEN AVAILABLE. GEAR SWINGS WERE C/O WITH THE NEW SELECTOR HANDLE AND THE A/C WAS CHECKED SERVICEABLE.  (TC NR 20071219	009)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500169	20080225	00169	WP  	2008	2	25	CA071219010      	2	20071214	G	7261	31081331	TUBE            			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE OIL	CHAFED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								P63333			(CAN) DURING A SCHEDULED FLIGHT BETWEEN, A WARNING INDICATION OF OIL PRESSURE LOSS ON THE NR 1 ENGINE APPEARED ON THE AN	NUNCIATOR PANEL. THE CREW VERIFIED THE WARNING BY OBSERVING THE OIL PRESSURE GAUGE. THE ENGINE WAS SHUTDOWN AND AN EMERG	ENCY WAS DECLARED. THE CREW LANDED THE AC WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT THE STEEL TUBE BETWEEN THE	 PROPELLER GOVERNOR AND A T-FITTING WAS LEAKING FROM THE FLARED END WHERE IT ATTACHED TO THE T-FITTING. THE TUBE WAS REP	LACED WITH A NEW ONE AND HIGH POWER GROUND RUNS WERE PERFORMED. NO LEAKS WERE PRESENT. THE OIL WAS CLEANED FROM THE ENGI	NE COMPARTMENT AND THE AC RETURNED TO BASE. DURING REPLACEMENT OF THE TUBE IT WAS NOTED THAT IT HAD BEEN CHAFFING ON AN 	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2008022500170	20080225	00170	NM  	2008	2	25	CA071220001      	1	20071219	G	3297		GROUND STUD     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	MLG	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			39432	39432							(CAN) AFTER SELECTING GEAR UP, LT AND RT MAIN GEAR DOOR AMBER WARNING AND NLG RED WARNING. GEAR SELECTED DOWN AND NORMAL	 EXTENSION, AFTER GEAR DOWN (AMBER) NLG LIGHT REMAINED ILLUMINATED. MAINT INSPECTION/ TROUBLE SHOOTING REPLACED LANDING 	GEAR SELECTOR VALVE AND NLG DOOR SEQUENCE VALVE, DURING GEAR SWINGS GEAR FAILED TO RETRACT AFTER SECOND CYCLING . FURTHE	R INVESTIGATION FOUND NLG DOOR SEQUENCE VALVE GROUND STUD (WIRE DIAGRAM 32-30-00 SHEET 4 OF 4 PAGE 1 WIRE IDENTIFIER 93A	22N , STUD IDENTIFIER 3251-GS-1) LOOSE. STUD LOCATED ON BULKHEAD FWD OF FWD PRESSURE BULKHEAD. STUD TIGHTENED, GEAR SWIN	GS COMPLETED SUCCESSFULLY. AC RETURNED TO SERVICE. (TC NR 20071220001)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008031900170	20080319	00170	EU  	2008	3	19	CA071220002      	2	20071108	G	7320	057610E000201	ECU             	THIELT      		DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12502114 		EU  					FADEC	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA			608  			3544					(CAN) DURING FLIGHT TRAINING MANEUVERS, SIMULATED SINGLE ENG OPS AT 5000 FT ASL, THE LT ENGINE WAS THROTTLED BACK TO FLI	GHT IDLE (5 PERCENT PWR, THROTTLE RETARDED).  UPON RETURN TO NORMAL PWR OPS THE LT ENG BEGAN TO SURGE FROM 20-100 PERCEN	T PWR, REGARDLESS OF THROTTLE POSITION, ENG WAS UNCONTROLLABLE.  THE LT ENGINE FADEC WAS SELECTED FROM ECU A TO ECU B AN	D CONTROL OF LT ENGINE WAS REGAINED. THE AC RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT.  MAINT ACTIONS:  	DISCREPANCY COULD NOT BE DUPLICATED DURING GROUND TESTS. LT ENGINE OPERATED NORMALLY ON BOTH ECU A AND ECU B OF THE LT F	ADEC.  LT HAD FADEC REPLACED AND AC RELEASED FOR TEST FLIGHT. NO FURTHER ENG SURGING NOTED. (TC NR 20071220002)	1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
	20080520		CE  	2008	5	20	CA071220004      	1	20071215	G	2910	AE2463531G0460	HOSE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HYDRAULIC PUMP	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ALL GEARS DOWN AND LOCK WITH (3) GREEN LIGHTS.  WHEN PILOT SELECTED FLAPS DOWN, LT HYD FLOW LIGHT COMES ON AND FOL	LOW THE RT SIDE. FINALLY, HYD FLUID LEVEL LIGHT COMES ON.  AC LANDED SAFELY WITH NO HYD SYS AVAILABLE. FOUND LT ENG HYD 	PRESSURE HOSE CRACKED. BOTH HYD PRESSURE HOSE REPLACED WITH AE2463531G0460 ON LT SIDE AND AE2463531G0226 ON RT AND BOTH 	ENG DRIVEN HYD PUMP REPLACED WITH 9912062-4. HYD FILTER INSPECTED AND REPLACED WITH NEW FILTER KIT CPDPHF-1. FUNCTIONAL 	CHECK C/O AND AC RETURN TO SERVICE. (TC NR 20071220004)		2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2008022500172	20080225	00172	EU  	2008	2	25	CA071221001      	1	20071219	G	2997		WIRE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					HYD CONTROL	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA							2076				(CAN) DURING AN AC CONVERSION IAW SB 01.00.50 THE HYD CONTROL WIRE WAS FOUND NOT CRIMPED PROPERLY IN SPLICE CONNECTOR.  	WIRE DH5E PULLED OUT OF SPLICE DURING HANDLING.  WIRE CONNECTOR SHOW NO SIGN OF PROPER CRIMP.  THE INSTALLATION OF THIS 	SPLICE IS MANDATED BY EASA AD F-2004-089 (ASB 29.00.07).  WIRE CONNECTION FAILURE RENDERS THE PILOT UNABLE TO PERFORM EM	ERGENCY PROCEDURES LISTED IN THE FLIGHT MANUAL SECTION 3.3  (HYD FAILURE) AND SECTION 3.1 PARA 5 (TAIL ROTOR CONTROL FAI	LURE) THE LACK OF PROPER CRIMPING WAS ALSO FOUND ON AC.  (TC NR 20071221001)		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2008022500174	20080225	00174	NE  	2008	2	25	CA071221002      	2	20071209	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						SEIZED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								17384			(CAN) SHORTLY AFTER TAKEOFF, CREW FELT VIBRATION FOLLOWED BY AN INDICATION OF LOW OIL PRESSURE.  AC LANDED IN A FIELD AW	AY FROM THE DEPARTURE POINT AND CREW SHUTDOWN ENGINE.  POST FLIGHT INSP REVEALED THAT NEITHER ENGINE ROTOR COULD BE TURN	ED AND THE OIL FILTER AND CHIP DETECTORS WERE CONTAMINATED BY DEBRIS.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADV	ISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071221002)			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008022500175	20080225	00175	NE  	2008	2	25	CA071221003      	2	20071212	G	7532	31J285704	MOTOR           			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					BLEED VALVE	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				E	F	J	VIBRATION/BUFFET          	FLT CONT AFFECTED         	WARNING INDICATION        	DE	DESCENT        	1			CA								DD0323			(CAN) VIBRATION, (RUMBLE) AND EEC REVERSION WAS EXPERIENCED DURING DESCENT. THE CREW ELECTED TO PERFORM AN INFLIGHT SHUT	DOWN OF THE ENGINE AND CONTINUE TO DESTINATION. TROUBLESHOOTING REVEALED A DEFECTIVE BLEED VALVE TORQUE MOTOR CAUSING TH	E COMPRESSOR SURGES/STALLS. THE UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC 20071221003)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008022500176	20080225	00176	EU  	2008	2	25	CA071221004      	1	20071212	G	7930		OIL SYSTEM      			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								127176			(CAN) DURING CRUISE, THE CREW OBSERVED FLUCTUATIONS IN THE OIL PRESSURE, FOLLOWED BY A DROP TO ZERO. THE ENGINE WAS SHUT	DOWN ACCORDINGLY.  TROUBLESHOOTING IS ONGOING, MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE E	STABLISHED (TC NR 20071221004)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
2008022500177	20080225	00177	NE  	2008	2	25	CA071221005      	2	20071214	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA								1140211142			(CAN) DURING FINAL APPROACH, THE LOW OIL PRESSURE WARNING ACTIVATED. THE CREW SHUTDOWN THE ENGINE. POST FLIGHT INVESTIGA	TION REVEALED THAT THE ENGINE ROTORS WERE DIFFICULT TO TURN AND THAT METAL SHAVINGS WERE DEPOSITED ON THE OIL FILTER. TH	E ENGINE IS BEING SENT FOR INVESTIGATION.  MFG  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTA	BLISHED (TC NR 20071221005)			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2008022500181	20080225	00181	NE  	2008	2	25	CA071221006      	2	20071217	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  						SEIZED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								123019			(CAN) OPERATOR REPORTED THAT THERE WAS AN INFLIGHT SHUTDOWN OF THE ENGINE AND THAT POST FLIGHT INSPECTION REVEALED THAT 	THE POWER TURBINE ASSY COULD NOT BE ROTATED. NO OTHER DETAILS PROVIDED AT THIS TIME.  MFG WILL CONTINUE INVESTIGATING TH	E EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071221006)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008022500182	20080225	00182	NE  	2008	2	25	CA071221007      	2	20071202	G	7250		TURBINE BLADES  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	DISTRESSED      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA								PC503			(CAN) OPERATOR REPORTED (TECHNICAL PROBLEMS) WHICH RESULTED IN A FORCED LANDING ON A PUBLIC MOTORWAY. INITIAL INVESTIGAT	ION REVEALED COMPRESSOR TURBINE BLADE DISTRESS. THE ENGINE IN BEING RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE P	ROVIDED WHEN AVAILABLE. (TC NR 20071221007)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008022500183	20080225	00183	NE  	2008	2	25	CA071221008      	2	20071216	G	7261		ENGINE          			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  		LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								120670			(CAN) DURING CLIMB, THE OIL PRESSURE STARTED TO FLUCTUATE AND THE LOW OIL PRESSURE WARNING WAS ACTIVATED. THE CREW SHUT 	THE ENGINE DOWN AND RETURNED TO THE POINT OF ORIGIN. 5 MIN PRIOR TO LANDING, THE ENGINE WAS RE-STARTED AND ALL PARAMETER	S WERE NORMAL EXCEPT THAT THERE WAS NO OIL PRESSURE INDICATION AND THE LOW OIL PRESSURE WARNING.  THEY KEPT THE ENGINE R	UNNING TILL LANDING. POST FLIGHT INSP REVEALED THAT THE OIL TANK WAS EMPTY AND A SIGNIFICANT OIL LEAK WAS OBSERVED AT TH	E STARTER GENERATOR PAD.   THE ENGINE WILL BE REMOVED AND SENT FOR REPAIRS.  MFG WILL CONTINUE INVESTIGATING THE EVENT A	ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071221008)	2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008022500184	20080225	00184	EA  	2008	2	25	CA071221009      	2	20071129	G	7261		FITTING         			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	ENGINE OIL	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								FA0302			(CAN) DURING CRUISE, THE OIL PRESSURE WAS OBSERVED TO DECREASE AND AND A WARNING SOUNDED. THE ENGINE WAS SHUTDOWN AND TH	E AC RETURNED TO BASE. INITIAL INVESTIGATION REVEALED AN AIRFRAME SUPPLIED OIL COOLER HOSE FITTING HAD PULLED FREE OF TH	E ENGINE AND CAUSED A MASSIVE LEAKAGE. THE ENGINE HAS BEEN REMOVED AND WILL BE SENT FOR INVESTIGATION.  MFG WILL CONTINU	E INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071221009)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022500185	20080225	00185	NE  	2008	2	25	CA071221010      	2	20071129	G	7250		TURBINE BLADES  			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								38152			(CAN) DURING CRUISE A LOUD BANG WAS HEARD AND ENGINE OPERATION CEASED WITHOUT CREW INVOLVEMENT.  POST FLIGHT INPECTION D	ISPLAYED COMPRESSOR AND POWER TURBINE BLADE DAMAGE. THE COMPRESSOR ROTOR IS SEIZED THE ENGINE WILL BE REMOVED AND FORWAR	DED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED WHEN AVAILABLE. (TC NR 20071221010)				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2008022500186	20080225	00186	NM  	2008	2	25	CA071221011      	1	20071215	G	7712		SIGNAL COND UNIT			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW123D      	52152	NE  					ENGINE TORQUE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								AG0044			(CAN) TAKEOFF WAS ABORTED DUE TO NOISES SIMILAR TO ENGINE SURGE OR PROPELLER MALFUNCTION. INSPECTION REVEALED THAT THE E	NGINE HAD REACHED 136 PERCENT TORQUE FOR A PERIOD LESS THAN 20 SECONDS. THE PROPELLER, TORQUE PROBE AND TORQUE SIGNAL CO	NDITIONER WERE REPLACED. ROOT CAUSE HAS NOT BEEN ESTABLISHED. UPDATES WILL BE PROVIDED WHEN AVAILABLE. (TC NR 2007122101	1)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008022500187	20080225	00187	NE  	2008	2	25	CA071221012      	2	20070820	G	7250		TURBINE BLADES  								PWA   	PW120 	PW127       	 	NE  					ENGINE	CLOGGED         	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THIS SDR IS BEING RAISED TO ADVISE OF A QUALITY ESCAPE REPORTED. DUE TO THE USE IMPROPER MATERIALS AND PROCEDURES,	 THE COOLING PASSAGES OF SOME HP TURBINE BLADES WERE INADVERTANTLY BLOCKED BY BLASTING MEDIA DURING THE CLEANING PROCESS	 AT SHOP VISIT. THESE BLADES WERE THEN INSTALLED ON A NR OF ENGINES AND RELEASED TO THE FIELD FOR SERVICE.  THERE HAVE B	EEN (2) CASES OF THESE BLADES SUBSEQUENTLY FRACTURING IN SERVICE DUE TO OVERHEATING, ENGINES AV0063 AND 120308.   HAVE A	CKNOWLEGED THE QUALITY ESCAPE AND TAKING REMEDIAL ACTION TO ADDRESS OTHER AFFECTED ENGINES.  WILL BE ADVISED OF FURTHER 	OCCURANCES IN THE FIELD. (TC NR 20071221012)						4	T			E20NE				 
2008022500188	20080225	00188	NM  	2008	2	25	CA071222001      	1	20071222	G	5315	146A75032	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS 767	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+5 RBL 3 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REPAI	RED IAW CUSTOMER E.A. (TC NR 20071222001)					2	L	7	2 	4F			RT	A16WE   					 
2008022500189	20080225	00189	NM  	2008	2	25	CA071222002      	1	20071222	G	5315	146A75031	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS767	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+14, LBL 3 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REP	AIRED IAW CUSTOMER EA. (TC NR 20071222002)					2	L	7	2 	4F			RT	A16WE   					 
2008022500190	20080225	00190	NM  	2008	2	25	CA071222003      	1	20071222	G	5320	146A75035	FLOOR SUPPORT   			BOEING	737   	737790      	13844CN	NM  										BS767	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+5, LBL8 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REPAI	RED IAW CUSTOMER EA. (TC NR 20071222003)					2	L	7	2 	4F			RT	A16WE   					 
2008022500191	20080225	00191	NM  	2008	2	25	CA071222004      	1	20071222	G	5315	141A550519	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS 344	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PASSENGER CABIN FLOORBEAM AT BS 344, RBL4 TO LBL56 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REPAI	RED IAW CUSTOMER EA. (TC NR 20071222004)					2	L	7	2 	4F			RT	A16WE   					 
2008022500193	20080225	00193	NM  	2008	2	25	CA071222005      	1	20071222	G	5315	147A55048	FLOORBEAM       			BOEING	737   	737790      	13844CN	NM  										BS 947	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CABIN FLOORBEAM AT BS 947, LBL53 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION FOUND. REPAIRED IAW 	CUSTOMER EA. (TC NR 20071222005)					2	L	7	2 	4F			RT	A16WE   					 
2008022500194	20080225	00194	WP  	2008	2	25	CA071224001      	1	20071223	G	2897	WIRE1544	WIRE HARNESS    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX FUEL PUMP	CHAFED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) AC HAD AN INTERMITTENT PROBLEM WITH ITS FUEL PUMP WARNING LIGHT. INTERMITTENTLY THE AUX FUEL PUMP WARNING LIGHT WO	ULD FLICKER ON AND OFF AT APPROX. 60 PERCENT BRIGHTNESS DURING A LONG FLIGHT. AN ENGINEER CHANGED THE AUX FUEL PUMP AND 	THE FUEL PRESSURE SWITCH. THE PROBLEM DID NOT REOCCUR DURING TESTING. HOWEVER, THE AC WAS BROUGHT BACK TO BASE TO ENSURE	 THERE WAS NO OTHER PROBLEM. UPON FURTHER INSPECTION, FOUND ONE OF THE WIRES FOR THE FUEL PUMP WAS CHAFING ON A VENT TUB	E NEAR THE FIREWALL. REPLACED A SECTION OF WIRE AND COVERED IT IN SPIRAL WRAP, TO PREVENT CHAFING IN THE FUTURE. (TC NR 	20071224001)	1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500195	20080225	00195	EU  	2008	2	25	CA071224002      	1	20071213	G	2710		AILERON         			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  						ICED            	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			9523 								(CAN) PILOTS REPORTED ON APPROACH INTO AIRPORT, COULD NOT GET ANY ROLL ON AC CONTROLS. IT APPEARED THAT AILERONS WERE F	ROZEN. SHORTLY BEFORE TOUCHDOWN THEY WERE ABLE TO GAIN CONTROL OF THE AILERON MOVEMENT. THE AC LANDED WITHOUT INCIDENT. 	MAINT WAS CALLED AND ON INSPECTION OF THE AC FOUND ICE BUILD UP ON LT AND RT AILERON HORNS, LT AND RT WINGS AND WING TIP	S. SOME AREAS OF THE LEADING EDGE HAD SOME ICE BUILD UP. CHECKED AC CONTROLS AND VERIFIED CORRECT MOVEMENT. AILERON CONT	ROLS OPERATED WITHOUT ANY BINDING. CONTACTED MFG AND REPORTED INCIDENT. FURTHER TROUBLESHOOTING WILL BE CARRIED OUT ON T	HE AC AILERONS TO AS CERTAIN THE CAUSE OF THE AILERON FREEZING UP. (TC NR 20071224002)	2	L	7	2 	4F	4	F		A3EU    	E6WE				 
2008022500225	20080225	00225	NE  	2008	2	25	CA071224003      	2	20071220	G	7314	D74311	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			828  								(CAN) WHILE ATTEMPTING TO START THE AIRCRAFT, THE AUX FUEL PUMP FAILED TO RUN. FURTHER INVESTIGATION REVEALED THE PUMP A	ND AUX FUEL PUMP PRESSURE SWITCH (P/N B426-6) HAD FAILED. PUMP AND SWITCH WERE REPLACED AND NO FURTHER DEFECTS WERE NOTE	D. (TC NR 20071224003)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500226	20080225	00226	NM  	2008	2	25	CA071224004      	1	20071219	G	7920	305726501	ADAPTER         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LP COMPRESSOR	LOOSE           	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			2628 								(CAN) WHILE INVESTIGATING AN OIL LEAK, DISCOVERED THAT WHEN REMOVING THE OIL COOLER LINE FROM THE LP COMPRESSOR CASE, AF	TER CUTTING THE LOCKWIRE FROM 1 OF THE 3 BOLTS, THE REMAINING 2 BOLTS CAME OUT WITH THE LOCKWIRE STILL ATTACHED. BOLTS S	ECURE THE OIL COOLER LINE AND ADAPTOR OIL TUBE TO THE LP COMPRESSOR. (TC NR 20071224004)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2008022500227	20080225	00227	EA  	2008	2	25	CA071226001      	1	20071222	G	3020	300013000003	ANTI-ICE VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					LT NACELLE	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			7709 	7709 							(CAN) WHILE ENROUTE, AC DEVELOPED A COWL ANTI ICE SNAG. THE AC RETURNED TO FOR REPAIRS. MAINTENANCE FOUND THE COWL ANTI 	ICE VALVE TO BE AT FAULT ONCE REPLACED OPERATIONAL CHECKS WERE C/O SERVICEABLE. A/C WAS RETURNED TO SERVICE.  (TC NR 200	71226001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500228	20080225	00228	EA  	2008	2	25	CA071227001      	1	20071224	G	2752	854D1001921	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, CREW WERE UNABLE TO RETRACT FLAPS, STUCK AT 41 DEGREES. FLT CANCELLED AS A RESULT. EXPECT TO FERRY 	AC. CODES RETRIEVED: 1)FECU/BPSU 2)ETHER BPSU 3)WIRING,  AC RETRIEVED CODES, FORWARDED TO TECH. CARRIED OUT ACTION PLAN 	168 AND ALL WIRING RANG OUT OK. FLAPS WERE CYCLED 5 TIMES IN HANGAR WITH NO FAULTS NOTED.  PERFORMED A LOW TEMP TORQUE C	HECK OF THE ACTUATORS AND REPORT FAILED UNITS. TAIL 168 FLAP ACTUATOR FREEZE TORQUE CHECK COMPLETED AND RESULTS AS FOLLO	WS: LT IB FLAP, IB ACT FAILED, C NR 5275305  LT IB FLAP, OB ACT PASSED  LT OB FLAP, IB ACT FAILED, C NR 5275306 LT OB FL	AP, OB ACT FAILED, C NR 5275308  RT IB FLAP, IB ACT PASSED RT IB FLAP, OB ACT FAILED, C NR 5275305 RT OB FLAP, IB ACT FA	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500229	20080225	00229	NE  	2008	2	25	CA071227002      	2	20071223	G	7230	355924400	SENSING ELEMENT 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					14TH STAGE DUCT	CHAFED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) RT 14TH STAGE DUCT MESSAGE DURING CLIMBOUT. FLIGHT RETURNED TO AIRFIELD.  MAINTENANCE INSPECTION DISCOVERED 14TH S	TAGE COWL DUCT INSULATION BROKEN AND CHAFING ON SENSING LOOP. BOTH SENSING LOOP AND DUCT WERE REPLACED AND ENGINE RUNS 	WERE C/O AND THE AC WAS CHECKED SERVICEABLE.  (TC NR 20071227002)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080520		CE  	2008	5	20	CA071227003      	1	20071015	G	3220	NAS464P5A42	BOLT            			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	D3A36	D3A36C410   	GL  	NLG DRAG STRUT	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			8203 								(CAN) WHILE TAXING ON BUSH STRIP, NOSE GEAR AFT DRAG STRUT BOLT BROKE AND WORKED OUT CAUSING NOSE GEAR TO FOLD FWD. (TC 	NR 20071227003)					1	H	7	1 	3O	3	O		3A21    	3E1	5	C	P47GL	 
	20080520		CE  	2008	5	20	CA071227004      	1	20070909	G	5312	12128582	BULKHEAD        			CESSNA	206   	TU206A      	2073318	CE  	CONT  	O520  	TSIO520C    	17040	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5803 								(CAN) CRACK IN REAR BULKHEAD PIN DURING MANDATORY NDT INSPECTION OF THE ARGA. (TC NR 20071227004)						1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P25EA	 
2008022500230	20080225	00230	EA  	2008	2	25	CA071227006      	1	20071213	G	2421	M2750010SP3U00	WIRE HARNESS    			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348E5A1   	30062	NE  					RAT	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15541								(CAN) DURING INCORPORATION OF SB601-0591 (SPECIAL CHECK/MODIFICATION  AIR-DRIVEN GENERATOR SYS REPLACEMENT OF CHAFING AD	G POWER FEED WIRE) FOUND THE WIRING CHAFED BARE AND CLAMPS BURNED AFT OF THE FWD PRESSURE BULKHEAD AT THE FIRST STANDOFF	 AFT OF THE FEED THROUGH AT APPROX  FS 210. WIRES HAVE BEEN REPLACED IAW SB601-0591 INSTRUCTIONS. (TC NR 20071227006)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022500232	20080225	00232	GL  	2008	2	25	CA071227007      	2	20071218	G	7261	6793065	CAP             	ALLSN       	23035102    	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					OIL PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						SER26317					(CAN) DURING ROUTINE INSPECTION AND FILTER CHANGE, A CRACK AROUND THE EAR OF THE CAP WAS NOTED. THE STUD WAS ALSO STRIPP	ED. MFG COVERED THIS TOPIC IN THEIR CSL-1251. TORQUEING IS THE POSSIBLE CAUSE FOR THIS DEFECT, THE LETTER RECOMMENDS 30-	40 LBS-IN. IT IS IMPORTANT TO FOLLOW MFG PROCEDURES IN ASSEMBLY AND REPAIR. (TC NR  20071227007)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2008022500233	20080225	00233	EA  	2008	2	25	CA071227008      	1	20071220	G	3260	895304	PSEU            			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			2275 								(CAN) A/C EXPERIENCED A PROX SYS FAULT DURING CLIMB OUT MESSAGE BECAME INTERMITTENT AFTER 8-10 MINUTES. FLIGHT RETURNED 	AND LANDED WITHOUT FURTHER INCIDENT. MAINT REPLACED THE PSEU AND CHECKED THE SYS THROUGH THE MFG SERVICEABLE. GEAR SWING	S C/O, NFF. A/C RETURNED TO SERVICE. (TC NR 20071227008)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022500235	20080225	00235	EU  	2008	2	25	CA071228001      	1	20071224	G	7603	7898435010	ECU             			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	POWER LEVER	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) POWER LEVER SPLIT AT HIGH POWER SETTINGS. FAULT ISOLATED TO FAULTY LT ENGINE ECU. ECU REPLACED. TESTED SERVICEABLE	. (TC NR 20071228001)					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008022500237	20080225	00237	EA  	2008	2	25	CA071228002      	1	20071227	G	2421	720845E	IDG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					NR 2	DAMAGED         	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			3922 	3922 		4258					(CAN) AT ALTITUDE CREW RECEIVED AN IDG CAUTION MESSAGE. THE NR 2 IDG WAS DEFERRED UNTIL MAINT COULD BE ACCOMPLISHED. AC 	WAS BROUGHT TO THE HANGER TO HAVE REPAIRS C/O, REMOVAL OF THE IDG REVEALED THAT THE INTERNAL SHAFT OF THE IDG PUNCHED TH	ROUGH THE OUTER CASING AND METAL SHAVINGS COLLECTED AT BOTTOM OF IDG/AGB MATING FLANGE PLUGGING DRAIN HOLE. ALL METAL DE	BRIS WAS CLEANED FROM THE FLANGE AND DRAIN AND NEW CARBON SEAL AND IDG INSTALLED AND CHECKED SERVICEABLE. (TC NR 2007122	8002)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500238	20080225	00238		2008	2	25	CA071228003      	4	20071227	G	8300	3008779	COLLAR          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ACCESSORY G/B	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE40510			(CAN) DURING AN ENGINE NR 2 SCHEDULE OIL CHANGE WHILE REMOVING OIL AT THE ACCESSORY GB DRAIN PLUG PORT HOLE, A METALLIC 	COLLAR HALF (P/N 3008779) FELL OUT. SUSPECTED THAT THIS COLLAR HALF HAD FALLEN OFF THE SCAVENGE OIL PUMP DRIVESHAFT.  EN	GINE REMOVED FROM AIRCRAFT AND SENT TO MFG FOR INVESTIGATION. (TC NR 20071228003)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008022500239	20080225	00239	EA  	2008	2	25	CA071231001      	1	20071228	G	2750	855D10011	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) FLAP FAIL ON APPROACH. FLAP ZERO APPROACH AND LANDING CARRIED OUT. FLIGHT LANDED WITHOUT FURTHER INCIDENT. RT FLAP	 BRAKE SENSOR UNIT, SKEW DETECTION UNIT AND RT OB FLEX DRIVE SHAFT REPLACED. FLAP SYS FUNCTION CHECKED SERVICEABLE. (TC 	NR 20071231001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500240	20080225	00240	SO  	2008	2	25	CA071231002      	1	20071228	G	3397	2067081	CONNECTOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					CONTROL PANEL	BURNED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) STROBE CB POPPED AND WILL NOT RESET. FAULT T/S TO DAMAGED WIRE IN RT WING. WIRE (L161FF) REPLACED IAW AC43-13-1B A	ND SECURED. WIRES FOR AILERON TRIM, STALL WARNING, POSITION LIGHTS AND FUEL QUANTITY SENDERS DISTURBED. ALL CONNECTIONS 	OF THESE SYSTEMS WERE RETERMINATED AND OPERATION CHECKED OK. DURING T/S CONNECTOR E312(TAXI AND LANDING LIGHTS) IN THE O	VERHEAD PANEL WAS NOTED DAMAGE. (SEVERAL BURNED PINS) INSULATION TEST OF THE SYS CARRIED OUT AND ADDITIONAL DAMAGE FOUND	 AT CONNECTOR E302. BOTH CONNECTORS REPLACED AS REQUIRED. TAXI AND LANDING LIGHT LINES MEGGERED OUT WITH NO FURTHER FAUL	TS INDICATED. SYSTEM OPN TESTED SERVICEABLE. (TC NR 20071231002)	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2008022500253	20080225	00253	NM  	2008	2	25	CA080102004      	1	20071227	G	3310		LAMP            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT LIGHTS	BURNED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) SIDEWALL LAMP HOLDER AT SEAT AREA 3DF FOUND BURNED WHILE TROUBLESHOOTING SAME POSITION. DEFECT FOUND DURING LAND S	ERVICE CHECK. LAMP HOLDER/BALLAST ASSY REPLACED. (TC NR 20080102004)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500254	20080225	00254	CE  	2008	2	25	CA080102005      	1	20071231	G	5420	10191001641	COVER           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND EXHAUST SOOT IN COWLS. CLOSER INSPECTION FOUND THE BUTTERFIELD STC COVER PLATE LEAKING AND THE HEATED INLET 	CRACKED IN MULTIPLE LOCATIONS ON BOTH COWLS. (TC NR 20080102005)					1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2008022500257	20080225	00257	EA  	2008	2	25	CA080102007      	1	20071230	G	2150		A/C PACK        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					RIGHT	SMOKE           	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) (AC RETURNED TO THE FIELD DUE TO SMOKE TOILET WARNING. THERE WAS A HAZE IN THE CABIN. THEY DECLARED AN EMERGENCY) 	 FOUND THAT THE RT PACK WAS SMOKING UP THE CABIN.  DEFERRED THE RT PACK.  ADDITIONAL INFORMATION REQUESTED TO THE FSR, A	C STILL UNDER MMEL (TC NR 20080102007)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080522		SW  	2008	5	22	CA080102008      	1	20071227	G	2612	3219027001	MODULE          	FRCHLD      	2782797001  	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FIRE EXTINGUISH	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA			5472 								(CAN) DURING CLIMB-OUT THE PILOTS NOTICED THE ENGINE FIRE DETECTION INDICATION LIGHT CAME ON. THE ENGINE WAS SHUTDOWN AN	D THE ENGINE FIRE EXTINGUISHING BOTTLE WAS ACTIVATED. THE PILOTS DECLARED AN EMERGENCY, LANDED SAFELY AT THE AIRPORT OF 	ORIGIN AND EVACUATED THE AIRCRAFT. NO ENGINE FIRE WAS OBSERVED. MAINTENANCE INSPECTED THE FIRE EXTINGUISHING SYSTEM AND 	FOUND THAT THE FIRE LOGIC CONTROL BOX HAD HEAT DAMAGE AT AN ELECTRICAL CONNNECTOR. (TC NR 20080102008)			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2008022500258	20080225	00258	NE  	2008	2	25	CA080103001      	2	20071224	G	7414	E06KA245	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			224  								(CAN) AFTER ROUTINE START ENGINE RPM AND OR GOVENOR BEGAN TO HUNT. PROBLEM PERSISTED EVEN AFTER ENGINE WARMED UP. ENGINE	 SHUTDOWN AND RT MAGNETO REPLACED. GROUND RUN CARRIED AND NO DEFECTS FOUND WITH NEW MAGNETO. (TC NR 20080103001)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500259	20080225	00259	WP  	2008	2	25	CA080103004      	1	20071223	G	2910	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA			1213 								(CAN) DURING A POST FLIGHT INSPECTION THE HYDRUALIC SERVO WAS FOUND LEAKING AT THE PILOT VALVE. SERVO CHANGED AND LEAK C	ARRIED OUT SERVICEABLE. (TC NR 20080103004)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022500261	20080225	00261	CE  	2008	2	25	CA080103005      	1	20071228	G	7797	8975294	WIRE HARNESS    	GARRTT      	TPE3316252  	BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			1000 			P27038		P27038			(CAN) AFTER A STOPOVER THE AIRCREW WENT TO START THE NR 2 ENGINE, AT THIS TIME IT WAS NOTED THAT THE ITT GAUGE WAS NOT W	ORKING. MAINTENANCE PERSONNEL FLEW TO THE AIRCRAFT LOCATION AND THROUGH TROUBLESHOOTING DETERMINED THAT THE ITT HARNESS 	HAD FAILED. A FERRY PERMIT WAS USED TO RETURN THE AIRCRAFT BACK TO THE MAIN BASE. ENGINE WAS REMOVED AND A NEW HARNESS I	NSTALLED. (TC NR 20080103005)			1	L	7	2 	3T	4	T		A14CE   	E2WE	6	C	P40EA	 
2008022500262	20080225	00262	EA  	2008	2	25	CA080103006      	2	20071227	G	7414	BL6006163	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				961  							(CAN) ENGINE WOULD NOT START.  LT MAGNETO FOUND UNSERVICEABLE.  MAGNETO CHANGED, GROUND RUN AND FUNCTIONAL CHECKS CARRIE	D OUT SERVICEABLE. (TC NR 20080103006)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2008022500264	20080225	00264	WP  	2008	2	25	CA080103008      	1	20071222	G	8011		COVER           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			173  								(CAN) DURING A 50/100 HOUR INSPECTION, THE STARTER COOLING COVER WAS FOUND LOOSE. THE 3 SCREWS HOLDING IT IN PLACE HAD L	OOSENED OFF. THE STARTER WAS REPLACED, GROUND RUN CHECKED SERVICEABLE. (TC NR 20080103008)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080520		CE  	2008	5	20	CA080104002      	1	20071229	G	7603	SL60112SL6011	KNOB            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	POWER LEVER	SEPARATED       	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			6101 	6101 							(CAN) (2) KNOBS ON EITHER SIDE OF THE POWER LEVER ARE USED TO RAISE A GATE TO ALLOW REVERSE THRUST. THE KNOBS ARE SCREWE	D TOGETHER. DURING FLIGHT THE KNOBS SEPARATED (UNSCREWED) AND FELL OFF. THIS ALLOWED THE GATE TO PIVOT IF THE POWER LEVE	R WAS RETARDED ALLOWING THE ENGINE/PROP TO ENTER THE REVERSE MODE OF OPERATION. (TC NR 20080104002)				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008022500266	20080225	00266	EU  	2008	2	25	CA080104003      	1	20071231	G	6410	355A12003114	TRIM TAB        			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3104 								(CAN) WHILE PERFORMING A BRIDGING INSPECTION ON AN A/C PREVIOUSLY LEASED TO A DIFFERENT COMPANY, AD 2007-0138-E WAS BEIN	G C/O. SECTION OF MISSING PAINT NOTED ON AREA REQUIRING INSPECTION IAW ASB 05-00.40( IB ATTACHMENT POINT OF T/E TAB). A 	CRACK WAS NOTED THROUGH VISUAL INSP, AND THE T/R ASSY REMOVED FROM A/C FOR FURTHER EVALUATION. AD HAD BEEN SIGNED OUT BY	 PIC PRIOR TO PERFORMING FERRY FLIGHT TO OUR BASE. T/R ASSY WAS INSTALLED ON THIS AIRCRAFT 19.7 HRS PRIOR TO DISCOVERY O	F DEFECT. BLADE ASSY SENT TO MFG FOR FURTHER EVALUATION (TC NR 20080104003)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008031900172	20080319	00172	EA  	2008	3	19	CA080105001      	1	20071224	G	2497	VS643	RELAY           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					ELECTRICAL PWR	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON ARRIVAL, GROUND PWR APPLIED TO AC BUT SHUTOFF IMMEDIATELY. GROUND PWR RESTARTED AND AFTER ABOUT A MINUTE CREW	 NOTED NUMEROUS CIRCUIT BREAKERS POPPED, HEARD A LOUD BANG FROM THE NOSE SECTION AND A LIGHT SMELL OF SMOKE IN THE COCKP	IT. CIRCUIT BREAKERS POPPED INCLUDED CENT TRU 1, NAV LIGHTS, TRU 1, TRU2, STCU, TRU SERVICE, SENSOR TOILET, CEILING LIGH	TS, SIDEWALL LIGHTS AND STAB CHAN HSTCU. MAINT TROUBLESHOOTING, TRACED FAULT TO AN AC SERVICE BUS FAULT. PWR SENSE RELAY	 K5XD ( P/N VS-643) IN JB6 REPLACED (SHORTED WIRING ALSO REPAIRED). NUMEROUS OTHER PARTS REPLACED DUE TO DOWN LINE FAILU	RES. ( HSTCU P/N 7060-10, S/N 213.)  LT AND RT WINDSHIELD HEAT CONTROLLERS P/N 601R59006-5, S/NS 5131 & 3475(SOME BURNE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900174	20080319	00174		2008	3	19	CA080106002      	4	20071228	G	3418	501177003	ACTUATOR        			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C5B1   	30052	NE  					STICK PUSHER	FOD             	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) THE CABLE RUNS HAVE BEEN INSPECTED IN THE FWD ELECTRONICS BAY AND THE FWD QUADRANTS HAVE BEEN INSPECTED AND NO DEF	ECTS NOTED. THE FWD PULLEYS AND CABLES WERE LUBED AND AC SENT FOR A TEST FLIGHT. IN ALL OTHER MODES OF FLIGHT THE AC OPE	RATES NORMALLY. ONLY ON LANDING WHEN THE PILOTS HAVE FLARED THE NOSE UP AND THE MLG HITS THE GROUND DOES IT SEEM TO LOCK	 UP PREVENTING THE PILOTS FROM PRESSING THE NOSE DOWN TO LAND.         WITH THE AC ON THE GROUND AND THE PITCH DISCONNEC	TED YOU CAN FEEL WHAT IS DESCRIBED AS A ROUGH SPOT IN THE FOS YOKE AS YOU MOVE HALF WAY FROM FULLY AFT TO CTR AND HALF 	WAY FROM CENTER POSITION TO FULLY FWD POSITION.  PROBLEM WAS SOLVED BY REPLACING THE STICK PUSHER ASSY. STICK PUSHER WAS	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008032000005	20080320	00005	NE  	2008	3	20	CA080108001      	2	20071218	G	7261		SUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 1 ENGINE	LEAKING         	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN)  SMOKE CARGO MESSAGE SHORTLY AFTER T/O AND ODOR OF SMOKE ON FLIGHT DECK. LANDED, & TAXI TO PARKING AND DEBARKING O	F PAX, CABIN INSPECTED BY FIRE BRIGADE. CABIN CREW REPORTED NO SMOKE IN CABIN AND TOILET DURING FLT AND TAXI BACK. DURIN	G TROUBLESHOOTING, FOUND A-SUMP OIL LEAK ON ENGINE NR 1. A-SUMP CARBON SEAL NR 1 AND NR 3 ON ENGINE NR 1 ON WING ACC. SE	I 756 SPECIAL PROCEDURE 41 REPLACED. INSP AND ENGINE RUNS SATISFACTORY. NO MORE SMOKE OBSERVED. REF OS WO 5524048. AIRCR	AFT RELEASED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080520		CE  	2008	5	20	CA080108008      	1	20071217	G	3230	55275042	VALVE SEAT      	CESSNA      	55275042    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					UPLOCK ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6025 								(CAN) WHEN PRESSURE IS APPLIED TO THE UPLOCK ACTUATOR THE ACTUATOR MUST TRAVEL FULL STROKE BEFORE ALLOWING FLUID TO THE 	GEAR ACTUATOR. IN THIS ACTUATOR THE DAMAGED SEAT ALLOWED FLUID TO THE GEAR ACTUATOR BEFORE THE UPLOCK HAD RELEASED THE G	EAR.  WE HAVE HAD A COUPLE INCIDENTS WHERE THE GEAR WOULD NOT EXTEND WHEN THE GEAR ACTUATOR APPLIED DOWN FORCE TO THE GE	AR BEFORE THE UPLOCK COULD RELEASE AND THE UPLOCK COULD NOT OVERCOME THE FORCE. UPLOCK ACTUATOR WAS REPLACED. (TC NR 200	80108008)		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20080520		NE  	2008	5	20	CA080109007      	2	20071227	G	7261	MS955610	BOLT            			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					PUMP	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AC WAS ON MONITOR FOR LOW OIL QTY SNAGS SINCE THE 21ST OF DEC. TODAY (27TH) ALL OF THE EDP MIDDLE CASING BOLTS WER	E FOUND LOOSE.  CMM 29-12-10, ITEM 300: BOLT P/N MS9556-10 AND ITEM 305: WASHER NAS620C10L. (TC NR 20080109007)					2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008022500274	20080225	00274	NM  	2008	2	25	CA080110004      	1	20070831	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  										HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1497 								(CAN) MFG HAD ISSUED SB 84-29-15A/ SB 66173-29-349 DUE TO LEAKING OF THE ENGINE DRIVEN HYD PUMP. THE SB WAS CARRIED OUT 	ON THE ABOVE MENTIONED COMPONENT AT TSN: 834.0 AND CSN OF 874. COMPONENT REMOVED DUE TO LEAKAGE IN THE FLANGE AREA THAT 	HAD BEEN RETORQUED IAW THE SB. HAVE ADDED THE RETORQUING OF THIS COMPONENT IAW THE ABOVE MENTIONED SB INTO THE AC MAINT 	PROGRAM. (TC NR 20080110004)			2	H	7	2 	4T			RT	A13NM   					 
2008022500275	20080225	00275	CE  	2008	2	25	CA080110005      	1	20070108	G	7110	10191001651	COWLING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	MCAULY	3G34C7	3GFR34C701  	GL  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BACK WALL OF HEATED LIP ASSY FOUND CRACKED.  DEFECT INTRODUCES HOT EXHAUST GASES INTO COWL ASSY, CONTAMINATING ENG	INE INTAKE, CABIN PRESSURIZATION, ENGINE CONTROL, AIR.  DEFECT CAUSES INCREASED CORROSION OF COWL ASSY.  DEFECT IS DIFFI	CULT TO SEE UPON INSP DUE TO LOCATION. (TC NR 20080110005)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P60GL	 
2008032000008	20080320	00008	EU  	2008	3	20	CA080114004      	1	20071212	G	2497		WIRE            			GROB  	120   	G120A       	1660208	EU  										ALTERNATOR	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			632  								(CAN) ALTERNATOR CB POPPED IN FLIGHT WITH MINOR SMELL OF SMOKE.  AC RETURNED TO BASE WITHOUT FURTHER INCIDENT. MAINT FOU	ND THE ALTERNATOR PWR WIRE HAD CHAFED THROUGH THE OIL COOLER HSG AND GROUNDING CONTACT WAS MADE THROUGH CARBON FIBER LOW	ER COWLING AND HARDWARE ATTACH POINTS SEVERING THE GROUND CABLE FROM THE ALTERNATOR. THIS WAS THE THIRD INCIDENT (FOR FL	EET) INVOLVING THE ALTERNATOR WIRES MAKING CONTACT WITH THE OIL COOLER SHROUD. MFG ADDRESSED THE PROBLEM BY ISSUING SB 1	121-093, WHERE THE ALTERNATOR WIRES WERE SHORTENED AND SECURED AWAY FROM THE OIL COOLER SHROUD. (TC NR 20080114004)		1	L	7	1 	3O			RT	A49CE   					 
2008030600220	20080306	00220	EA  	2008	3	6	CA080115011      	1	20071217	G	2910	AE4186G0210000	LINE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30068	NE  					HYDRAULIC SYS	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA			4495 								(CAN) PRESSURE LINE ON NR 3A PUMP RUPTURED AND SYS FLUID WAS LOST. GEAR WAS ALTERNATELY EXTENDED AND LANDED WITHOUT INCI	DENT. THE HOSE WAS REPLACED AND THE AC WAS FERRIED. THE GEAR WAS SWUNG AND THE HYDRAULICS BLED, TESTED SERVICEABLE. THER	E ARE CURRENTLY NO LIFE LIMIT ON THESE LINES. (TC NR 20080115011)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600222	20080306	00222	NE  	2008	3	6	CA080116004      	2	20071220	G	7200		ENGINE          			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								AM0076			(CAN) VIBRATION WAS FELT ACCOMPANIED BY 3 LOUD NOISES AND FIRE WARNING. ENGINE WAS SHUTDOWN AND AC RETURNED TO POINT OF 	DEPARTURE. POST FLIGHT INSPECTION REVEALED NO EVIDENCE OF FIRE, HOWEVER PROPELLER COULD NOT BE ROTATED AND THE TURBOMACH	INE CHIP DETECTOR WAS FOUND TO BE HEAVILY CONTAMINATED WITH METALIC DEBRIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AN	D ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080116004)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2008030600223	20080306	00223	NE  	2008	3	6	CA080116005      	2	20071212	G	7200		ENGINE          			AEROSP	ATR42 	ATR42500    	8680948	EU  	PWA   	PW120 	PW127       	 	NE  						SHUTDOWN        	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								AM0110			(CAN) CREW ELECTED TO SHUTDOWN ENGINE DURING FLIGHT DUE TO LOW/NO OIL PRESSURE INDICATION.  ENGINE WAS SUBMITTED TO REPA	IR SHOP FOR INVESTIGATION AND REPAIR.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH	ED (TC NR 20080116005)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2008030600225	20080306	00225	NE  	2008	3	6	CA080116008      	2	20071220	G	7200		FITTING         			AGUSTA	A109  	A109E       	0260119	EU  	PWC   	PW206C	PW206C      		NE  					P3	CONTAMINATED    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								BC0503			(CAN) DURING CRUISE, THE ENGINE POWER DECREASED UNCOMMANDED TO IDLE SETTING, FOLLOWED BY LOSS OF OIL PRESSURE. THE CREW 	ELECTED TO SHUTDOWN THE ENGINE AND RETURN TO BASE. INVESTIGATION FOUND THE P3 FITTING TO BE CONTAMINATED WITH FOREIGN DE	BRIS. FITTING AND SYS WAS CLEANED AND THE AC RETURNED TO SERVICE. (TC NR 20080116008)				1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
2008030600227	20080306	00227	NE  	2008	3	6	CA080116010      	2	20071221	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J	B		WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA								114478114162			(CAN) DURING CRUISE, THE MASTER CAUTION ILLUMINATED AND ENGINE SURGES WERE NOTED FOLLOWED BY LOSS OF POWER AND OIL HAZE 	IN THE CABIN. THE CREW ELECTED TO SHUT THE ENGINE DOWN. THE ENGINE IS TO BE RETURNED TO MFG FOR INVESTIGATION, UPDATES T	O FOLLOW. (TC NR 20080116010)				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2008030600228	20080306	00228	NE  	2008	3	6	CA080116011      	2	20071226	G	7320		FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	INOPERATIVE     	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA								JC0550			(CAN) DURING APPROACH, THE ENGINE DID NOT RESPOND TO THRUST LEVER INPUTS AND REMAINED AT IDLE. AFTER LANDING GROUND TEST	S INDICATED THAT THE ENGINE WOULD NOT ACCELERATE ABOVE 46 PERCENT, N2. THE FUEL CONTROL WAS REPLACED AND AIRCRAFT RETURN	ED TO SERVICE. (TC NR 20080116011)				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2008030600229	20080306	00229	NE  	2008	3	6	CA080116012      	2	20071231	G	7320		FUEL CONTROL    			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA								DB0324			(CAN) DURING APPROACH AT 3000 FEET, THE LOW FUEL FLOW WARNING CAME ON, FOLLOWED BY ENGINE SHUTDOWN. THE FUEL CONTROL HAS	 BEEN REMOVED AND SUBMITTED FOR INVESTIGATION. UPDATES WILL BE PROVIDED WHEN AVAILABLE. (TC NR 20080116012)					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008030600230	20080306	00230	EU  	2008	3	6	CA080116013      	1	20071230	G	7931		OIL SYSTEM      			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								EB0078			(CAN) DURING CRUISE, THE ENGINE OIL PRESSURE FLUCTUATED INTERMITTENTLY, THEN DROPPED DURING DESCENT. THE CREW ELECTED TO	 SHUTDOWN THE ENGINE.  ENGINE IS TO BE INVESTIGATED BY MFG, UPDATES TO FOLLOW. (TC NR 20080116013)					2	H	7	2 	4T	4	T	RT	        	E20NE				 
2008030600233	20080306	00233	EA  	2008	3	6	CA080116016      	2	20071126	G	7250		TURBINE BLADES  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	FRACTURED       	W				C	E	D		ABORTED TAKEOFF         	ENGINE SHUTDOWN         	RETURN TO BLOCK         		R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PG0179			(CAN) DURING TAKEOFF ROLL, THE ENGINE LOST POWER. TAKEOFF WAS ABORTED AND AC RETURNED TO THE RAMP. INVESTIGATION BY MFG 	REVEALED FRACTURED COMPRESSOR TURBINE BLADES AND A FRACTURED FUEL BYPASS LINE. (TC NR 20080116016)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2008030600235	20080306	00235	NM  	2008	3	6	CA080116018      	1	20071225	G	4920		STARTER         	PWC         		BOEING	747   	747400      	13848AT	NM  										APU ACC G/B	FAILED          	W				F				ACTIVATE FIRE EXT.      				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						900077					(CAN) WHILE DEPLANING PASSENGERS, AN OIL SMELL WAS NOTED IN THE CABIN ACCOMPANIED BY A FIRE WARNING. THE FIRE BOTTLES WE	RE DISCHARGED. THE ENGINE WAS REMOVED AND SENT FOR INVESTIGATION. INITIAL INSP INDICATES A MALFUNCTION OF THE STARTER MO	TOR LEADING TO ACCESSORY GEARBOX DISTRESS.  UPDATES WILL BE PROVIDED AS AVAILABLE. (TC NR 20080116018)				2	L	7	4 	4F			RT	A20WE   					 
2008032400427	20080324	00427	GL  	2008	3	24	CA080116019      	2	20071230	G	7230	23064613	IMPELLER        	ALLSN       		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	SATURATED       	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			5708 			CAC44047					(CAN) AFTER UNEVENTFUL AND NORMAL SHUTDOWN, PILOT NOTICED A POOL OF OIL UNDER THE AC AND OIL ALL OVER THE ENGINE COWLS A	S WELL AS SOAKING THE IB .2500 OF THE MAIN ROTOR BLADES. THERE WERE NO OIL TEMP OR PRESSURE CAUTION WARNINGS OR ENGINE C	HIP LIGHT INDICATIONS. TO THE PILOT SHUTDOWN WAS NORMAL AND PLANNED, EXCEPT FOR A NOTICEABLE ODOR IN THE COCKPIT.  SUBSE	QUENT INSP SHOWED OIL EMANATING FROM COMPRESSOR FRONT SUPPORT AREA WITH OIL DISCHARGING FROM BLEED VALVE (VENTED INTO EX	HAUST COLLECTOR) AND COMPRESSOR VENT. INITIALLY SUSPECTED NR1 BEARING OIL SEAL FAILURE OR CRACK IN THE COMPRESSOR FRONT 	SUPPORT OIL PRESSURE/RETURN STRUT. ENGINE SERVICE TECH WAS CALLED IN TO DISASSEMBLE AND REPLACE THE FRONT SUPPORT OR SEA	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20081104		CE  	2008	11	4	CA080121006      	1	20071218	G	3222	0543011	CAP             			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					NLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3346 								(CAN) DURING ANNUAL INSP OF THE NOSE GEAR ASSY AND OLEO, THE OLEO CAP WAS FOUND TO BE CRACKED. THE CRACK WAS LOCATED .18	75 IN FROM THE RADIUS OF THE END FLANGE. THE CAP WAS FOUND TO BE BROKEN THROUGH AND WAS REMOVED IN 2 PIECES. REVIEW OF T	HE TECHNICAL RECORDS INDICATED THAT THE ACFT HAD BEEN SUBJECT TO SIGNIFICANT DAMAGE LATE IN 1979 AT 2479.9 HRS TTAF. (TC	 NR 20080121006)			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
	20081105		    	2008	11	5	CA080122006      	1	20071107	G	7810	PN2031	COLLECTOR       			NAVION	STC   	STCNAVION   	       	    	CONT  	E185  	E1853       	17014	SO  	HARTZL	HC12V	HC12V20*    	GL  	EXHAUST	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND WHEN CF90-03R2 WAS DONE. THERE WERE NO VISIBLE SIGNS OF EXHAUST LEAKS. WHEN PRESSURE TESTED WITH AIR AND SOA	PY WATER, 4 LEAKS WERE EVIDENT. IT HAS BEEN STANDARD PRACTICE IN THIS AMO TO DO SOAPY WATER TESTS ONLY. OVER THE LAST 8 	TO 10 YEARS WE HAVE FOUND 4 OR 5 EXHAUST UNITS THAT SHOW NO VISIBLE SIGNS OF LEAKS, BUT FAIL THE SOAPY WATER TEST. ALL W	ERE LEAKS AROUND EXISTING WELDS. ONE CRACK THAT STARTED MY POLICY OF SOAPY WATER ONLY TESTING, WAS ALONG THE EDGE OF A W	ELDED PIPE. THAT CRACK WAS ABOUT .6250 INCH LONG. THERE WERE NO SIGNS OF LEAKS. IT WAS THE RATHER SURPRISED RESPONSE FRO	M MY TC. THAT PROMPTED THIS REPORT. THE QUESTION IS, HOW MANY OTHERS ARE OUT THERE THAT PASS THE VISUAL TEST, BUT FAIL T	1	L	7	1 	3O	3	O		A782    	E246	5	C	P46GL	 
2008022000037	20080220	00037	CE  	2008	2	20	CA080122011      	1	20071225	G	2497		WIRE            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	DC GENERATOR	CHAFED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) MAINT HAD TROUBLESHOT A GENERATOR PROBLEM. THE GENERATOR WOULD GO OFF LINE OCCASIONALLY.  REPLACED PC CARD, REPLAC	ED THE GENERATOR. THE PROBLEM WAS GONE FOR 3 WEEKS. IT RETURNED, MAINT REPLACED THE PC CARD, WITH A HARD FAULT. TESTED S	ERVICEABLE. NEXT MORNING ON TAXI THE GENERATOR FAILED AGAIN. DISCOVERED A WIRE FROM THE PC CARD TO THE GENERATOR BUS TIE	 RELAY CHAFED IN THE NACELLE. THE BUNDLE WAS PROPERLY SECURED AND PROTECTED, HOWEVER, THE ONE WIRE WAS ON THE EDGE OF TH	E BUNDLE AND CHAFED ON A RIVET HEAD. REROUTED THE BUNDLE, SPLICED THE WIRE AND RETURNED THE AC TO SERVICE. (TC NR 200801	22011)	2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2008022000038	20080220	00038	CE  	2008	2	20	CA080122012      	1	20071128	G	3610	13182E40600	TUBE            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	BLEED AIR	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CREW REPORTED A BLEED AIR FAIL ANNUCIATOR IN FLIGHT. TROUBLESHOOT AND FOUND A PIN HOLE IN THE BLEED AIR WARNING LI	NE. HOLE WAS NOT CAUSED BY A BLEED AIR LEAK, NOR BY MECHANICAL DAMAGE. LINE WAS ADEQUATELY SUPPORTED AND NO CHAFING WAS 	EVIDENT. SPLICED IN REPAIR SECTION IAW MFG SIRM AND TESTED SERVICEABLE. SECOND AC TO HAVE A FALSE FAILURE RECENTLY. (TC 	NR 20080122012)			2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
2008022000041	20080220	00041	EU  	2008	2	20	CA080123004      	1	20071009	G	6220	704A33633208	SPHERICAL STOP  			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5209 								(CAN) PROTRUDING RUBBER FOUND COMING OUT, IN THE MIDDLE OF STOP. (TC NR 20080123004)						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008022000042	20080220	00042	EU  	2008	2	20	CA080123005      	1	20071009	G	6220	350431182703	FREQ ADAPTER    			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					MAIN ROTOR HEAD	BLISTERED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5208 								(CAN) ON INSP OF MAIN ROTOR HEAD AT THE END OF THE DAY ENGINEER FOUND BLISTERS ON THE SIDE OF ONE FREQUENCY ADAPTER. BLI	STERS WHERE FOUND TO BE BEYOND LIMITS:  REPLACED ALL (3) ADAPTERS. (TC NR 20080123005)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008022000076	20080220	00076	SO  	2008	2	20	CA080128003      	1	20070527	G	2912	460635	FILTER          			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			10144								(CAN) DURING APPROACH TO LANDING, FLIGHT CREW EXPERIENCED DIFFICULTY EXTENDING THE LANDING GEAR VIA NORMAL MEANS AND SUB	SEQUENTLY MANUALLY LOWERED THE GEAR. INVESTIGATION SHOWED SUBSTANTIAL HYD FLUID LOSS THROUGH CRACKED THREADS OF THE LT E	NG HYDR FILTER BOWL. MAINT TO REPLACE THE DAMAGED BOWL WITH NEW, AND TO OVERHAUL THE HYDR PUMPS AND FLUSH THE HYD SYS PR	IOR TO FURTHER FLIGHT. (TC NR 20080128003)			1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
2008022000077	20080220	00077	SW  	2008	2	20	CA080128006      	1	20071215	G	6320	214040118001	BEARING         	BELL        	205040001101	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					TRANSMISSION	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						ABT00760					(CAN) TSO OF THE TRANSMISSION ASSY 1186.6 HOURS.  THE AC HAD TAKEN OFF AND WAS IN CRUISE WHEN A TRANSMISSION METAL DETEC	TOR LIGHT ILLUMINATED. THE PILOT LANDED AC BACK AT CAMP FOR THE ENGINEER TO INVESTIGATE THE DEFECT.  THE BEARING IS AN O	N CONDITION BEARING.  THE MAST ASSY AND TRANSMISSION ASSY WERE REMOVED.  THE COMPONENT SHOP FOUND THAT THE TRANSMISSION 	INPUT TRIPLEX BEARING, P/N 214-040-118-001, WAS THE FERROUS METAL MAKER.  THE MAST BEARING WAS ALSO INSPECTED AND NO DEF	ECT WAS FOUND. (TC NR 20080128006)		1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008031900183	20080319	00183	SW  	2008	3	19	CA080204006      	1	20070614	G	2497		WIRE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					COCKPIT	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED SPARKS AND A SMALL AMOUNT OF SMOKE FROM THE OVERHEAD CONSOL. UPON INVESTIGATION IT WAS FOUND THAT T	HE LT OVERHEAD CONSOL PANEL HAD CHAFED THROUGH SEVERAL WIRES COMING UP THE CENTER POST OF THE WINDSHIELD CAUSING THE WIR	ES TO SHORT TO GROUND.   AFFECTED WIRES REPLACED AND THE WIRING BUNDLE REPOSITIONED. (TC NR 20080204006)				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008031900192	20080319	00192	EU  	2008	3	19	CA080206007      	1	20071217	G	6123		PROPELLER       			CASA  	C212  	C212CC      	2410204	EU  	PWA   	PW120 	PW127       	 	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA								AX0043			(CAN) DURING APPROACH, CREW REPORTED TORQUE AND PROP SPEED REDUCTION. THE PROPELLER FEATHERED AND AC LANDED. TROUBLESHOO	TING IS FOCUSING ON AUTOFEATHER UNIT.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH	ED.  INSTALLATION IS CASA 295M. FLEET PRESENTLY GROUNDED AND TROUBLESHOOTING ON HOLD DUE TO CRASH OF SISTER AC. (TC NR 2	0080206007)			2	H	7	2 	4T	4	T		A43EU   	E20NE				 
	20081222		CE  	2008	12	22	CA080207001      	1	20071214	G	2160	IE502	ACTUATOR VALVE  			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					HEAT EXCHANGER	STICKING        	W				C				ABORTED TAKEOFF         				M	J		OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			CA			88   	88   							(CAN) RT BLEED AIR OVERTEMP WARNING LITE CAME ON DURING T/O. TWICE IN 42 T/O. THE HEAT EXCHANGER VALVE WAS STICKING IN C	LOSED POSITION - VALVE ACTUATOR PIN IE50-2 WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081222		CE  	2008	12	22	CA080207002      	1	20071214	G	7830	64ND782047	ACTUATOR        			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					THRUST REVERSER	LEAKING         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			88   	88   							(CAN) LT THRUST REVERSER INBD ACTUATOR. WEEPING HYDRAULIC FLUID. NOTE: THIS ACTUATOR WEEPED FLUID FROM DAY ONE ON 560 S/	N 0648 HAD 2 ACTUATORS I/B LT REPLACED FOR HYDRAULIC FLUID LEAKS OVER APPROX 1800 HRS.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081222		CE  	2008	12	22	CA080207003      	1	20070920	G	2433	RR18	CONVERTER       			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  						INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			69   	69   							(CAN) MFD FAIL TO COME ON WHEN ACFT MASTER SWITCH TURNED ON. DC-DC CONVERTER REPLACED - SAME PROBLEM OCCURED AT 102.6 AI	RFRAME HRS. - 66 AIRFRAME CYLES, AND DC-DC CONVERTER REPLACED AGAIN (33 HRS + 19 CYCLES) MFG IS AWARE OF THE POOR QUALIT	Y OF THE RR18 DC-DC CONVERTERS.				1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
	20081222		CE  	2008	12	22	CA080207004      	1	20071005	G	3246	49290	PLUG            			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					RT WHEEL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			30   	30   							(CAN) TIRE/WHEEL ASSY LOOSING AIR PRESSURE. SL560XL32-19 PROVIDES IMPROVED THERMAC PLUG. PIN 542-7 WHICH WAS TO BE INSTA	LLED IN THIS SERIAL NR ACFT AND WHEEL S/N- THE OLD PIN 49-290 PLUG IS MAGNETIC. THE NEW PIN 542-7 IS NO MAGNETIC. CHECKI	NG OF NEW SPARE WHEEL AND BOTH ACFT MAIN WHEELS FOUND OLD PIN PLUGS INSTALLED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008031900210	20080319	00210	NM  	2008	3	19	CA080208006      	1	20071230	G	7160	658536912	NOSE BULLET     			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) FOLLOWING DEPARTURE, THE CREW REPORTED COMPRESSOR STALLING OF THE NR 1 ENG AT CLIMB PWR. THE ENGINE PWR WAS REDUCE	D AND COMPRESSOR STALLS STOPPED. THE AC RETURNED TO DEPARTURE WITH NO FURTHER INCIDENT. INSP OF THE ENGINE IDENTIFIED TH	AT THE NR 1 ENGINE NOSE DOME HAD SEPARATED FROM THE ENGINE DURING FLIGHT AND MINOR DAMAGE TO THE INTAKE ACOUSTIC LINER A	ND FIRST STAGE COMPRESSOR BLADES. A BOROSCOPE INSP SHOWED NO INTERNAL ENGINE DAMAGE. THE FIRST STAGE COMPRESSOR BLADES W	ERE BLENDED, ENGINE INTAKE WAS REPLACED ALONG WITH THE NOSE DOME AND THE A/C WAS RETURNED TO SERVICE. (TC NR 20080208006	)	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2008031900216	20080319	00216	NM  	2008	3	19	CA080211016      	1	20070224	G	3260	H10101534	DOWNLOCK SWITCH 			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) DURING APPROACH INTO AIRPORT, THE LANDING GEAR WAS EXTENDED AT WHICH TIME THE NOSE GEAR UNSAFE LIGHT REMAINED ILLU	MINATED AND THE DOWN AND LOCKED LIGHT REMAINED EXTINGUISHED. THE GEAR WAS RECYCLED WITH THE SAME RESULT AND SOON AFTERWA	RD, THE UNSAFE LIGHT EXTINGUISHED AND THE DOWN AND LOCKED LIGHT ILLUMINATED AND THE AC LANDED WITHOUT FURTHER INCIDENT. 	THE GEAR UNSAFE AND DOWN AND LOCKED SWITCHES WERE REPLACED AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080211016)			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20080520		SO  	2008	5	20	CA080213009      	1	20071101	G	2752	B5195	WORM DRIVE      	EMB         	D22466      	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLAP ACTUATOR	STRIPPED        	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA				1872 							(CAN) AFTER LANDING, THE WING FLAPS OF AN AC COULD NOT BE RETRACTED. THE ASYMMETRY WARNING SYSTEM HAD BEEN TRIPPED. THE 	LT AND RT FLAP ACTUATORS WERE REPLACED WITH OVERHAULED UNITS AND THE AC WAS DISPATCHED. UPON DISASSEMBLY OF THE ACTUATOR	 AT THE OVERHAUL SHOP THE BRASS WORM WHEEL THAT DRIVES THE SCREW JACK WAS FOUND STRIPPED.  AWD 82-07-04R3 PART 2 HAD BEE	N COMPLETED FEBRUARY 19, 2007. THE PART HAD ONLY 2202 CYCLES AND 1871.8 HOURS SINCE OVERHAUL AND THE ACCOMPLISHMENT OF T	HE AWD. (TC NR 20080213009)		1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
	20080521		EA  	2008	5	21	CA080213011      	1	20070919	G	3250	712761	STUD            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG STEERING	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING TAXI, A SNAP WAS HEARD BY THE FLIGHT CREW AND HYDRAULIC STEERING CONTROL WAS LOST. THE AC WAS TAXIED TO THE	 RAMP USING DIFFERENTIAL PWR AND BRAKING.  THE STUD SECURING THE HYD STEERING ACTUATOR WAS FOUND SHEARED. THE NOSE GEAR 	ASSY WAS REPLACED AND AC WAS RETURNED TO SERVICE. THE CAUSE OF THE BROKEN STUD COULD NOT BE DETERMINED. (TC NR 200802130	11)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20080521		GL  	2008	5	21	CA080214006      	2	20071219	G	7250	6847100	SHAFT           			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	ENGINE	DAMAGED         	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				445  							(CAN) IN CRUISE AT 22,000 FEET, THE CREW OBSERVED A DROP IN RPM FOLLOWED BY A FIRE WARNING IN ENGINE NR1. THE FLIGHT CRE	W PULLED THE (E) HANDLE AND DISCHARGED THE (2) FIRE EXTINGUISHER BOTTLES. THE FLIGHT CREW THEN PROCEEDED, AFTER DECLARIN	G AN EMERGENCY. THE AC LANDED SAFELY AND NO OTHER INCIDENT REPORTED. THE COMPRESSOR AND TURBINE INTERCONNECT SHAFT AND C	OUPLING FOUND DAMAGED CAUSING FREE TURBINE ROTATION. THE QEC WAS REMOVED, SPLIT, INSPECTED AND ALL THE PARTS SENT TO THE	 ENGINE SHOP FOR INVESTIGATION. (TC NR 20080214006)		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
	20081230		CE  	2008	12	30	CA080219003      	1	20070914	G	5551	04320049	ATTACH BRACKET  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12749								(CAN) DURING INSP OF FIN ATTACH BRACKET NUT PLATES IAW AD 80-11-04 CRACKS WERE DISCOVERED RUNNING ALONG THE BEND RADIUS 	OF THE WELDED BRACKET. THE AD ALLOWS FOR REMOVING REPETATIVE INSP REQUIREMENTS IF THE NUT PLATES ARE DRILLED OFF AND REP	LACED WITH FIBERLOCKING NUTS. ALTHOUGH THE AD MAY NO LONGER MAY BE APPLIABLE IN SOME ACFT THE ENTIRE WELDED BRACKET SHOU	LD BE INSPECTED CLOSELY EVERY 100-HRS.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081104		WP  	2008	11	4	CA080221006      	1	20071214	G	6330	369H5105	BOLT            			HUGHES	369   	369A        	4470503	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN ROTOR TRANSMISSION RECEIVED FOR OVERHAUL AFTER NDT INSPECTION 31 OF THE 32 RING GEAR BOLTS P/N 369H5105 WERE 	FOUND CRACKED UNDER THE BOLT HEADS. (TC NR 20080221006)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
200805141    	20080514	1    	EA  	2008	5	14	CA080304008      	2	20070322	G	8530	LW13622	INTAKE VALVE    	LYC         	05K21108    	PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			136  								(CAN) WHILE IN CRUISE, THE PILOT HEARD A BANG AND EXPERIENCED A LOSS IN POWER ON THE LT ENGINE. AS THE ENGINE REMAINED R	UNNING AND THERE WAS NO IMMEDIATE CONCERN FOR SAFETY THE PILOT CHOSE TO LEAVE THE ENGINE RUNNING AND SET DOWN AT THE NEA	REST AIRPORT. UPON EXAMINATION OF THE ENGINE IT WAS DISCOVERED THAT THE NR1 CYLINDER INTAKE VALVE HAD FAILED AT THE TIP 	KEEPER LOCATION. THE DECISION WAS MADE TO REMOVE THE ENTIRE ENGINE ASSY AND RETURN IT TO THE OVERHAUL SHOP DUE TO THE LO	W TIME SINCE OVERHAUL (TSO).   I WOULD LIKE TO MAKE NOTE THAT THE ENGINE PARTS MANUAL IS NOT CLEAR AS TO THE STYLE OF KE	EPER REQUIRED FOR THE INTAKE VALVE POSITION AND, THOUGH IT WAS NOT A CONCERN IN THIS CASE, IT COULD BECOME AN ISSUE FOR 	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20090102		CE  	2009	1	2	CA080305006      	1	20071130	G	2197	OR551	RESISTOR        			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HEATER BLOWER	OVERHEATED      	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) RESISTOR LOCATED UNDER CO-PILOT SEAT(CONTROLS HIGH LOW OPERATION OF HEATER BLOWER MOTOR.  THERE ARE 3 RESISTORS OF	 THE SAME TYPE IN THIS LOCATION, IN THIS CASE HEATER RESISTOR-OR55-1 OVERHEATED CAUSING THE TY-RAP LOCATED ON THE UPPER 	PORTION OF RESISTOR TO MELT AND CATCH FIRE, THERE IS A SMALL SHIELD OF FLAME RESISTANCE MATERIAL ON THIS TERMIAL WHICH T	HE TY-RAP KEEPS IN PLACE.  RECOMMEND THIS AREA BE CHECK TO THE HEAT BUILD UP OF THIS RESISTOR AS THIS WILL INDIACATE THE	 NEED TO BE CHANGED. RESISTOR WAS CHANGED AND THE NEW RESISTOR HL55-08-Z-1-OHM WAS FOUND AFTER A 30 MINUTE RUN THE TEMP 	WAS 123 FDEGREES AND THE OLD RESISTOR WAS 187F DEGRESS IN FREE AIR WITH THE SAME LOAD FACTOR,IN THE ENCLOSED SPACE I ASS	1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
	20080602		NE  	2008	6	2	CA080305014      	2	20071220	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						STOPPED         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											DURING FLIGHT AT 12000 FEET ENGINE POWER WAS LOST.  THE AIRCRAFT WAS FORCED TO DITCH 25 MILES OFF COAST.  CREW WAS RESCU	ED.  INVESTIGATION REVEALED THAT THE ENGINE WAS MAKING NO POWER AT TIME OF IMPACT.  THE FUEL PUMP DRIVE SHAFT REVEALED W	ORN AND FRACTURED DRIVE SPLINES.  INVESTIGATION IS ONGOING, UPDATES WILL BE PROVIDED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20080521		NE  	2008	5	21	CA080305015      	2	20071027	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  						FAILED          	W				A				UNSCHED LANDING         				E	T		VIBRATION/BUFFET          	ENGINE CASE PENETRATION   		AP	APPROACH       	1			CA											(CAN) DURING APPROACH, VIBRATION WAS NOTED BY THE CREW THROUGH THE FLIGHT CONTROLS. LANDING WAS ABORTED AND AC RETURNED 	TO BASE. NEARING BASE, VIBRATION LEVEL INCREASED ABD CREW DECLARED AN EMERGENCY. DURING LANDING FLARE, (2) LOUD NOISES W	ERE HEARD. POST FLIGHT INSP REVEALED NON-CONTAINMENT OF ENGINE POWER TURBINE SECTION HARDWARE WHICH HAD PENETRATED THE A	IRFRAME DECK, COWLING AND BELLY.  MFG WAS NOTIFIED OF THIS BY THE OVERHAUL AGENCY CONDUCTING THE INVESTIGATION. THE DAMA	GED HARDWARE WILL BE RETURNED TO MFG FOR FURTHER ANALYSIS.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT	 CAUSE ONCE ESTABLISHED (TC NR 20080305015)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081104		EU  	2008	11	4	CA080305018      	1	20071017	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					FUEL BOOST	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA				162  							(CAN) PILOT HAD INDICATION OF A FUEL BOOST PUMP FAILURE. ACFT PERFORMED A NORMAL PLANNED LANDING AND THE PUMP WAS SUBSEQ	UENTLY REPLACED, NO FURTHER INCIDENT. (TC NR 20080305018)					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20080521		NE  	2008	5	21	CA080305019      	2	20071010	G	7310	419110003	MANIFOLD        			SNIAS 	350   	AS350B2     	8680813	EU  	LYC   	LTS101	LTS101*     		NE  					FUEL SYSTEM	UNSERVICEABLE   	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING POST MAINT INSP GROUND RUN, A FUEL LEAK WAS DISCOVERED AT THE FUEL MANIFOLD, IT WAS DETERMINED THE MANIFOLD	 WAS THE CAUSE, THE PART WAS REPLACED WITHOUT FURTHER INCIDENT. (TC NR 20080305019)					1	G	7	1 	3U	3	U		H9EU    	E5NE				 
	20081105		EU  	2008	11	5	CA080318005      	1	20071120	G	2916		RESERVOIR       			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3193 								(CAN) THE RESERVOIR SECTION OF THE HYDRAULIC PUMP ASSEMBLY BEGAN TO LEAK HYDRAULIC FLUID. THE LEAK WAS NOTED ON A PREFLI	GHT INSPECTION WHERE THERE WAS A PUDDLE OF HYDRAULIC FLUID ON THE TRANSMISSION DECK OF THE HELICOPTER. THE FLIGHT WAS CA	NCELLED. THE LEAK WAS TRACED TO A LARGE PLUG WHICH IS SWAGED OR STAKED INTO THE BOTTOM OF THE RESERVOIR. THE HYDRAULIC P	UMP ASSEMBLY WAS REMOVED AND IT WAS FOUND THAT THE PLUG WAS LOOSE IN THE BOSS, AND COULD ROTATE FREELY. THERE IS NO REPL	ACEABLE SEAL OR METHOD TO RESEAL THE PLUG. THE HYDRAULIC PUMP ASSEMBLY WAS RETURNED TO THE MANUFACTURER.		1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20081229			2008	12	29	CA080404003      	4	20070807	G	8300	2140402141	LINER           	BELL        		BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					RGB BEARING	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9203 	1345 							(CAN) DURING THE COURSE OF A 100 HR INSP, AME FOUND A LARGE AMOUNT OF NON-FERROUS METAL PARTICLES IN THE REDUCTION GEARB	OX OIL FILTER AND THE OIL DRAINED FROM THE GEARBOX. CHIP PLUG WAS INSPECTED AND FOUND CLEAN. REDUCTION GEARBOX WAS REMOV	ED AND REPLACED WITH A SERVICEABLE GEARBOX. LATER TEARDOWN OF THE GEARBOX FOUND THE INPUT BEARING LINER P/N 214-040-214-	1 HAD SHEARED ITS 3 RETAINING PINS AND SPUN WITHIN THE MAGNESIUM CASE P/N 214-040-211-005.			2	G	7	1 	4U	4	U		H6SW    	E4NE				 
	20081107		NE  	2008	11	7	CA080714002      	2	20070806	G	7250	304915201	TURBINE BLADES  			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	TURBINE SECTION	FRACTURED       	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA			7628 								(CAN) ON AUGUST 6/2007 SHORTLY AFTER TAKEOFF, MX HAD A REPORT FROM THE CREW OF A SMELL OF OIL IN THE CABIN. THIS WAS FOL	LOWED BY A NR 2 ENGINE FIRE WARNING AND THE CREW PROCEEDED TO CARRY OUT THEIR SOP`S AND THE ENGINE WAS SHUT DOWN. THE AC	FT PROCEEDED BACK TO YYT WHERE IT LANDED WITHOUT INCIDENT.  THE ENGINE WAS REMOVED AND SENT FOR EVALUATION. IT WAS DETER	MINED THAT 1 OF THE LOW PRESSURE TURBINE BLADES HAD FRACTURED AT THE BLADE ROOT. THE BLADES WERE SENT TO P&W FOR EVALUAT	ION. IT WAS DETERMINED THAT 1 FRACTURED LPT BLADE AT .050 INCH FROM THE BLADE PLATFORM OCCURRED AS A RESULT OF FATIGUE O	RIGINATING FROM THE TRAILING EDGE. DAMAGE TO THE REMAINING LPT BLADE AIRFOILS WAS CAUSED BY SUBSEQUENT MECHANICAL IMPACT	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081112		EU  	2008	11	12	CA080729005      	1	20070620	G	2913	1259A	MOTOR           			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB4T	HCB4TN5     	GL  	HYD SYSTEM	INTERMITTENT    	W				O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			CA				1153 							(CAN) UPON SELECTED GEAR DOWN NOTHING HAPPENED. PILOT THEN CYCLED THE GEAR DOWN AGAIN ALL FUNCTION NORMALLY, 3 GREEN DOW	N AND LOCKED. ACFT WAS THEN INSPECTED, NO FAULTS FOUND, MAINT CREWS AND EQUIPMENT WERE FLOWN IN AND PUT A/C ON JACKS GEA	R SWUNG NO FAULTS ACFT WAS THEN FLOWN BACK, FOR FURTHER TROUBLESHOOTING. AFTER SEVERAL GEAR SWING HYDR MOTOR WAS FOUND T	O OPERATE INTERMITTENTLY. IT IS ALSO BELIEVED THAT COLD WEATHER POSSIBLY COULD OF HAD A INFLUENCE, BELIEVED TO BE -40.			2	H	7	2 	4T	4	T	RT	A16EU   	E2WE	6	C	P40EA	 
	20081119		EA  	2008	11	19	CA080805004      	1	20070901	G	3070	11020140T	HEAT TAPE       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					WATER HEATER	BURNED          	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA											(CAN) THE AFT WATER SUPPLY HEATER TAPE OVERHEATED AND BURNED. INVESTIGATION REVEALED WATER HEATER WAS RUNNING WITHOUT TE	MP REGULATION.  HEATER WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081112		NM  	2008	11	12	CA080815008      	1	20071224	G	3240		BRAKE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					MLG	STICKING        	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) AS REPORTED BY FLIGHT CREW: ON LANDING IAH BRAKES WORKED WELL. DURING TAXI OFF RUNWAY FELT BRAKES GRABBING. WALKAR	OUND NORMAL, BRAKE TEMP NORMAL. HAD REPORT OF SMOKE FROM RT SIDE. NO EVIDENCE OF DAMAGE. ON TAXI OUT RT OTBD FAILED. BRA	KE WAS REMOVED AND CONFIRMED CARBON FAILURE				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081230			2008	12	30	CA081118009      	4	20071101	G	2300		TRANSPONDER     			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					NAV/COMM	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) LOSS OF COMM/NAV/ TRANSPONDER OCCURRED BACK IN NOV 2007. NOT REPORTED UNTIL 9/11/08 AFTER CUSTOMER HAD HEARD OF A 	SIMILAR OCCURRENCE ON ANOTHER CHALLENGER 300 (20016) THROUGH ADV COMMITTEE CONFERENCE CALL. IN FLIGHT CREW NOTED THAT TR	ANSPONDER CODE CHANGING FREQ.  LT AND RT RADIOS INDICATED YELLOW ON C/P MFD. ALSO ON C/P MFD, HAD AMBER BOXED DCP FLASHI	NG ON AND OFF. IAW RECOMMENDATION FROM REP, THE C/P DCP CHANGED OUT. TECHS UNABLE TO DUPLICATE PROBLEM.			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20081230		GL  	2008	12	30	CA081121008      	1	20071109	G	2910	1005354220N50192	LINE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  										HYDRAULIC SYS	CHAFED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			4000 								(CAN) CREW REPORTED DURING CRUISE FLIGHT THEY LOST ALL RT SIDE HYD FLUID. NUMEROUS CAS MESSAGES. RT SYS SHOWS 2 PERCENT 	QUANTITY AND 0 PSI. TEMP 36 C.  ACFT DIVERTED IN FLIGHT. AFTER LANDING CREW NOTED HYD FLUID RUNNING OUT OF THE LR FUSELA	GE BY THE MAIN WHEEL WELL AREA. FOUND NR 2 ENGINE HYD SUPPLY LINE WITH CLAMP THAT HAD CHAFED INTO THE TUBE ASSY AND WORN	 A HOLE.			2	L	7	2 	4F			RT	T00005NY					 
2008010800361	20080108	00361	EA  	2008	1	8	CHI08CA035       	2	20071101	G	8520		NUT             	LYC         		MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	CONNECTING ROD	BACKED OUT      	G				B	A	H		EMER. DESCENT           	UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS		R	Y	T	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	ENGINE CASE PENETRATION   	CR	CRUISE         	1			GL	11	5912Q	1800 	818  			821	L227651A	CA385		NR 3 PISTON CONNECTING ROD SEPARATED FROM THE CRANKSHAFT. PISTON SHEARED MOUNTING STUDS OF CYLINDER HOUSING AT ENGINE CA	SING. CYLINDER HOUSING SEPARATED FROM ENGINE CASING. ENGINE SHUTDOWN.					1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
2007050400131	20070504	00131	CE  	2007	5	4	CM2R747K         	1	20070501	G	2730	53608014	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  	ALLSN 	250C  	250C28B     	03013	GL  					ELEVATOR	BROKEN          	B			CM2R	O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			SW	15	397R	6383 	127  			0009				BEARING AND BOLT FAILED IN THE ELEVATOR BELLCRANK P/N 5360801-4.  CENTER BEARING THAT SUPPORTS THIS BELLCRANK FAILED.  B	EARING IS P/N MS27640-4.   BOLT P/N AN4-14 WAS SEVERELY WORN AND BROKEN IN TWO.  IF EITHER END OF THE BOLT SLIPPED OUT O	F THIS BELLCRANK, THE A/C WOULD HAVE LOST PRIMARY ELEVATOR CONTROL.  THE ELEVATOR TRIM SYSTEM WOULD STILL FUNCTION.				1	L	7	2 	3O	3	U		3A25    	E1GL				 
2007080800065	20070808	00065	CE  	2007	8	8	CNQ2918C         	1	20070726	G	3010	M1200180244	THERMAL SWITCH  			CESSNA	680   	680CE       	2076811	CE  										ANTI ICE SYSTEM	WARNING MESSAGE 	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	25	350QS	1725 				6800036				IN-FLIGHT AT FL 300, LT IB WING ANTI-ICE MSG ILLUMINATED, FOLLOWED BY ILLUMINATION OF THE LT WING ANTI-ICE COLD CAS MSG 	AND THE LT WING BLEED LEAK CAS MSG. FLIGHT CREW FOLLOWED CHECKLIST PROCEDURES; COULD NOT EXTINGUISH ANY AMBER CAS MSGS. 	 FLIGHT CREW DIVERTED AIRCRAFT FOR MAINTENANCE.  TECHNICIANS FOUND THE (2) ELECTRICAL LEAD WIRES BROKEN AT SL006 SWITCH,	 SOLDER CONNECTIONS.  REPAIRED WIRES AND PERFORMED OPERATIONAL CHECKS; ALL OPERATIONAL CHECKS WERE SATISFACTORY.  AIRCRA	FT RETURNED TO SERVICE 07/19/07.		2	L	7	2 	4F			RC	T00012WI					 
2007082400310	20070824	00310	NM  	2007	8	24	CO1Y200700001    	1	20070818	G	5313	A6A71211	LONGERON        			DOUG  	MD11  	MD11        	3023602	NM  										ZONE 100	CRACKED         	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	702BC					48504				CAC COMPARTMENT AT STA 6-100 ON LONGHERON NR 37LT SIDE FOUND CRACK 1 INCH.						2	L	7	3 	4F			RT	A22WE   					 
2007082400311	20070824	00311	NM  	2007	8	24	CO1Y200700002    	1	20070818	G	5330	AEA75732	DOUBLER         			DOUG  	MD11  	MD11        	3023602	NM  										BS 1321-1341	CORRODED        	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	702BC					48504				MAIN CABIN FROM STA 1321 TO STA 1341 FROM L NR 13 TO L NR 14 RT SIDE ON DOUBLER FOUND CORROSION.						2	L	7	3 	4F			RT	A22WE   					 
2007091700002	20070917	00002	NM  	2007	9	17	CO1Y200700003    	1	20070901	G	5730		SKIN            			DOUG  	MD11  	MD11        	3023602	NM  										LT WING	CORRODED        	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	702BC					48504				LT WING UPPER SURFACE ON SKIN FROM XORS 130 TO XORS 738 FOUND EXFOLIATION CORROSION.						2	L	7	3 	4F			RT	A22WE   					 
2007091700001	20070917	00001	NM  	2007	9	17	CO1Y200700004    	1	20070901	G	5730		SKIN            			DOUG  	MD11  	MD11        	3023602	NM  										RT WING	CORRODED        	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	702BC					48504				RT WING UPPER SURFACE FROM XORS 345 TO XORS 828 FOUND 15EA EXFOLIATION CORROSION POINTS.						2	L	7	3 	4F			RT	A22WE   					 
2007120400104	20071204	00104	NM  	2007	12	4	CO1Y200700009    	1	20071105	G	5330	ACA3108503	SKIN            			DOUG  	MD11  	MD11        	3023602	NM  										BS 535	CRACKED         	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	702BC					48504				AT RT AIR CONDITIONING COMPARTMENT AFT DOOR JAMB FOUND 0.25 INCH CRACK ON EXTERNAL SKIN STA 535 L NR32RH.						2	L	7	3 	4F			RT	A22WE   					 
2007020200015	20070202	00015	SO  	2007	2	2	CWQD200702       	1	20070130	G	3251	1159LM305489	SCISSORS        			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					MLG STEERING	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	411QS	9576 				1311				DURING CHECKLIST FOUND UPPER TORQUE LINK CRACKED P/N 1159LM30548-9 AT CONNECTING LOWER TORQUE LINK P/N 1159LM30553-3.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007013100140	20070131	00140	CE  	2007	1	31	CWQR200701       	1	20070122	G	2730	55653426	PUSHROD         			CESSNA	500   	550         	2076604	CE  										ELEVATOR	MISMANUFACTURED 	B			DXTA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05										DURING THE REPAIR STATION PRELIMINARY INCOMING PARTS INSPECTION, IT WAS OBSERVED THAT ONE OF THE NEW ELEVATOR PUSHROD CL	EVIS ENDS WERE ATTACHED WITH ALUMINUM RIVETS. ANOTHER NEW UNIT AND THE OLD PUSHRODS USED MONEL RIVETS. A CALL TO MFG CON	FIRMED THAT MONEL RIVETS SHOULD BE INSTALLED. THE PART WAS REJECTED, TAGGED AND RETURNED TO MFG.  ASKED MFG TO CHECK THE	IR STOCK FOR THIS CONDITION. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 271980.			1	L	7	2 	4F				A22CE   					 
2007041700134	20070417	00134	CE  	2007	4	17	CWQR200702       	1	20070416	G	5410	65526022	FLANGE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					NACELLE	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	820QS	2627 				5600650				DURING A PHASE 1-4 INSPECTION A 2.5 INCH CRACK WAS FOUND ON THE ENGINE INLET FLANGE, THIS CRACK PASSES THROUGH (2) FASTE	NERS THAT ATTACH THE INLET TO THE FLANGE. AND ARE AT THE 3 O'CLOCK POSITION ON BOTH THE LT AND RT ENGINES.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007071200134	20070712	00134	CE  	2007	7	12	CWQR200703       	1	20070706	G	5340	556560821	ATTACH BRACKET  			CESSNA	500   	560CESSNA   	2076750	CE  										MASTER CYLINDER	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	347QS	7855 				5600357				DURING A PHASE 1-4 INSPECTION, FOUND THE MASTER CYLINDER ATTACH BRACKET MOUNT HOLES GOUGED DURING INSTALLATION AT THE FA	CTORY, UPON FURTHER INSPECTION FOUND A .7500 INCH CRACK IN THE FLANGE ATTACH LEG RADIUS. REPLACED WITH NEW BRACKET ASSY.	 SUBMITTED SCR TO MFR UNDER SCR NR 301844.				2	L	7	2 	4F			RT	A22CE   					 
2007080800045	20070808	00045	CE  	2007	8	8	CWQR200704       	1	20070716	G	5712	66211511	CLOSEOUT PANEL  			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					LEFT WHEEL WELL	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	694QS					5605194				DURING A PHASE 5 INSPECTION, FOUND LT WHEEL WELL AFT SPAR CLOSE OUT PANEL CRACKED.  (3) CRACKS WERE FOUND BEGINNING FROM	 THE LOWER SKIN ATTACH FLANGE AND GOES STRAIGHT UP THE PANEL.  AN SDR HAS BEEN SUBMITTED TO AIRCRAFT UNDER NR 303303.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007080800046	20070808	00046	CE  	2007	8	8	CWQR200705       	1	20070716	G	5712	66211511	CLOSEOUT PANEL  			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					LEFT WHEEL WELL	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	694QS					5605194				DURING A PHASE 5 INSPECTION, FOUND LT WHEEL WELL AFT SPAR CLOSE OUT PANEL CRACKED.  (3) CRACKS WERE FOUND BEGINING FROM 	THE LOWER SKIN ATTACH FLANGE AND GOES STRAIGHT UP THE PANEL.  AN SCR HAS BEEN SUBMITTED TO MFG AIRCRAFT UNDER NR 303303.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007080800101	20070808	00101	CE  	2007	8	8	CWQR200706       	1	20070725	G	5540	663322513	PLATE           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RUDDER	RUSTED          	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	801QS					5600601				DURING A PHASE 1-4 INSPECTION, NOTICED A RUST STAIN COMING FROM THE LOWER RUDDER BEARING PLATE ASSY (LOWEST HINGE POINT)	. UPON DISASSEMBLE, FOUND THE DRAIN HOLE FROM THE RUDDER TORQUE TUBE WAS DRAINING INTO THE LOWER BEARING PLATE ASSY. THI	S IS DUE TO A NEW DESIGN OF THE PLATE ASSY, THE NEW ONE IS BEEFED UP AND HAS A BUILT UP AREA AROUND THE BEARING, THAT DI	RECTS WATER TO THE BEARING, UNLIKE THE PREVIOUS DESIGN THAT WAS A FLAT PLATE AND ALLOWED WATER TO DRAIN AWAY FROM THE BE	ARING.  SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER NR 305034.		2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007082400304	20070824	00304	CE  	2007	8	24	CWQR200707       	1	20070821	G	5540	66331508	BALANCE WEIGHT  			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					RUDDER	MISINSTALLED    	B			DXTA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	698QS					5605653				DURING A PHASE 1-4 INSPECTION, FOUND THE RUDDER BALANCE WEIGHT WAS TRIMMED DOWN AND ATTACHED WITH ONLY (2) BOLTS.THE IPC	 SHOWS (4) BOLTS TO ATTACH THIS WEIGHT. CONTACTED MFG ENGINEERING, THEY STATED THE WEIGHT REQUIRES (4) BOLTS TO MEET THE	 100 (G) STANDARD. APPEARS THE RUDDER BALANCE WEIGHT WAS TRIMMED DOWN AND INSTALLED AT THE FACTORY. REPLACED RUDDER BALA	NCE WEIGHT IAW SRM 51-60-03, RUDDER BALANCING.  SUBMITTED SERVICE CONDITION REPORT TO MFG UNDER NR 310349.			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007082400312	20070824	00312	CE  	2007	8	24	CWQR200708       	1	20070731	G	3110	556560914	SUPPORT CHANNEL 			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					INST PANEL	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	371QS					5600471				DURING MAINTENANCE FOUND THE RUDDER UPPER SUPPORT CHANNEL CRACKED WHERE IT ATTACHES TO THE INSTRUMENT PANEL.  THIS AIRCR	AFT HAD SL560-27-13 COMPLIED WITH 826.6 HOURS PRIOR TO FINDING THE CRACKED CHANNEL. THIS SL UPGRADED THE ATTACHING HARDW	ARE BUT DOES NOT CHANGE THE BRACKET.  REPLACED BRACKET AND HARDWARE WITH NEW.  AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR	 306488.			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007082400313	20070824	00313	CE  	2007	8	24	CWQR200709       	1	20070808	G	5415	65526022	MOUNT           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					NACELLE	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	810QS					5600625				DURING AN INSPECTION FOUND THE ENGINE NACELLE ATTACH FLANGE EARS CRACKED IN (2) LOCATIONS. SENT TO MFG FOR EVALUATION AN	D REPAIR. SUBMITTED SCR TO MFG UNDER NR 308174.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007082400315	20070824	00315	CE  	2007	8	24	CWQR200710       	1	20070808	G	3220	55423002	FORK            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					NLG	LOOSE           	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	804QS					5600610				DURING A MAINTENANCE TAXI CHECK NOTICED SHIMMY FROM NOSE GEAR. UPON DISASSEMBLY FOUND FORK LOOSE ON NOSE GEAR PISTON, TH	IS SHOULD BE A PRESS FIT FROM THE FACTORY.  SENT UNIT RELIABILITY GROUP FOR EVALUATION.   A SCR HAS BEEN SUBMITTED TO MF	G UNDER NR 308107.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007082400316	20070824	00316	CE  	2007	8	24	CWQR200711       	1	20070813	G	7160	65526057	INTAKE DUCT     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					LT ENGINE	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	804QS					5600610				DURING A PHASE INSPECTION FOUND LT ENGINE INLET DUCT ASSY CRACKED. CRACKS WERE FOUND ON THE AFT PORTION OF THE INLET DUC	T ASSY THROAT. THIS UNIT HAD TO BE RETURNED TO THE MFG FOR REPAIR. AN SCR WAS SUBMITTED TO MFG UNDER NR 308858.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007082400317	20070824	00317	CE  	2007	8	24	CWQR200712       	1	20070813	G	7160	65526057	INTAKE DUCT     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					RT ENGINE	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	804QS					5600610				DURING A PHASE INSPECTION FOUND RT ENGINE INLET DUCT ASSY CRACKED. CRACKS WERE FOUND ON THE AFT PORTION OF THE INLET DUC	T ASSY THROAT. THIS UNIT HAD TO BE RETURNED TO THE MFG FOR REPAIR. AN SCR WAS SUBMITTED TO MFG UNDER NR 308873.					2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2007020900101	20070209	00101	CE  	2007	2	9	DEBD624B0207     	1	20070202	G	3246	GYS186C21	BOLT            	GOODYEARAERO		BEECH 	MU300 	400A        	1155402	CE  										MLG WHEEL	BROKEN          	B			DEBD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	624B	1169 			NOV991386	RK369				A WHEEL THRU BOLT BROKE WHILE BEING TORQUED DURING WHEEL REASSEMBLY AFTER A TIRE CHANGE.						2	H	7	2 	4F			RT	A16SW   					 
2007012500140	20070125	00140	CE  	2007	1	25	DELR200700001    	1	20070104	G	7120	2652002	BOLT            			LEAR  	55    	55LEAR      	5170702	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					ZONE 400	SHEARED         	B			DELR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	345RJ	7248 	6267 			078	P85197			AFTER REMOVAL OF SAFTY WIRE TO REMOVE BOLT, THE MOUNT BOLT WAS FOUND SHEARED AT THE NECK OF THE BOLT. THREADED SECTION O	F BOLT WAS REMOVED WITH AN EASYOUT IAW CHAPTER 5 THIS ITEM IS LIFE LIMITED AT 20,000.00 HOURS.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2007050400150	20070504	00150	GL  	2007	5	4	DJS041707        	1	20070417	G	7700	35C155103	SENSOR          			AMTR  	500   	ECLIPSE500  	05614K5	GL  										ENGINE	FAULTY          	C				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	27	110DJ	42   				000007				INFLIGHT SHUTDOWN IAW AFM DUE TO LOSS OF OIL TEMPERATURE. TROUBLESHOT TO A FAULTY MOT/MOP SENSOR.						1	L	7	2 	3F			RT	EXPA1L72					 
2007042500248	20070425	00248	GL  	2007	4	25	DJS110DJ         	1	20070416	G	3244	40440A	TIRE            			AMTR  	500   	ECLIPSE500  	05614K5	GL  										LT MLG	BLOWN           	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	27	110DJ	41   				000007				LT MAIN WHEEL AND TIRE ASSEMBLY BLEW OUT DURING TAXI.						1	L	7	2 	3F			RT	EXPA1L72					 
2007030200035	20070302	00035	NM  	2007	3	2	DU4R2007060      	1	20070227	G	5710		VENT            			DOUG  	MD80  	MD83        	3023681	NM  										LT WING	CORRODED        	B			BWIA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	789BV					49789				S/O 244001 N/R 22938 N/R 22839 CORROSION ON I/B END OF EXISTING REPAIR ON AFT L/H WING VENT BOX REPAIRED BY REMOVING EXI	STING DOUBLER, FLAP PEENED CORROSION IAW BWIA DWG BW-D9-57-A/5120 AND MD-80 MM 20-10-10. FABRICATED AND INSTALLED DOUBLE	R 41.9 X 3.5, FILLER 1.5 X .9 FROM 2024-T3 0.100 IAW BWIA DWG BW-D9-57-A/5120 AND MD-80 SRM 51-30-2 AND 51-30-1.				2	L	7	2 	4F			RT	        					 
2007110100192	20071101	00192	CE  	2007	11	1	EA25070193       	1	20071019	G	3220	3400	LANDING GEAR    			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					FWD RT	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			EA	25	6506M	30   				18263735				AIRCRAFT ALTERED IAW STC SA02031NY INSTALLATION OF 3400 AMPHIBIOUS FLOATS APPROXIMATELY 36 HOURS PRIOR TO OCCURRENCE. ON	 TAKEOFF FROM HARD SURFACE RUNWAY, RT FORWARD WHEEL AND SUPPORT ASSY DEPARTED LANDING GEAR STRUT. WHEEL AND SUPPORT ASSY	 LT GEAR STRUT CLEANLY AND ONLY DAMAGE APPEARED TO BE FROM GROUND IMPACT.  AIRCRAFT MADE SUBSEQUENT WATER LANDING WITHOU	T INCIDENT. INSPECTION OF AIRCRAFT SHOWS THAT WHEEL AND SUPPORT ARE ATTACHED TO GEAR STRUT THROUGH USE OF A SPRING AND P	AWL MECHANISM.  IMPOSSIBLE TO TELL IF SPRING OR PAWL FAILED WITHOUT FURTHER DISASSEMBLY. POSSIBLE THAT ASSEMBLY WAS OVER	-GREASED OR GREASED TOO QUICKLY, AS PLACARD NEAR GREASE FITTING WARNS TO (APPLY GREASE SLOWLY).  WILL FORWARD THIS INFOR	1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2008011000130	20080110	00130	SO  	2008	1	10	EA25200802753    	1	20071218	G	5340	62522000	FITTING         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1031U	9840 				347250012				DURING WINDSHIELD REPLACEMENT, NOTED STEEL FITTINGS AND ATTACHING HARDWARE WERE SUBSTANTIALLY CORRODED. FUNCTION OF FITT	INGS IS ATTACHMENT OF FUSELAGE OVERHEAD (A) PILLAR TO FUSELAGE STRUCTURE PROPER. OTHER THAN SOME RIVETS THROUGH THE SKIN	S, THESE FITTINGS ARE THE MAJOR STRUCTURAL ATTACHMENTS OF THE CABIN OVERHEAD TO THE FUSELAGE STRUCTURE. CAUSE OF CORROSI	ON APPEARS TO BE FOAM INSULATION, HELD IN CONSTANT CONTACT WITH THE FITTINGS, BECOMING AND REMAINING WET THROUGH LEAKING	 WINDSHIELDS. COMPANY MECHANIC RECOMMENDS REMOVING PORTION OF INSULATION IN CONTACT WITH FITTINGS AND INSPECTING THIS AR	EA AT EACH 100 HOUR/ANNUAL INSPECTION. ACCESS IS GAINED THROUGH SIMPLE REMOVAL OF INTERIOR WINDSHIELD PILLAR TRIM PANELS	1	L	7	2 	3O	3	O		A7SO    	1E10				 
2008012200011	20080122	00011	SO  	2008	1	22	EA25200803022    	1	20071218	G	5340	68257000	FITTING         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  						CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1031U	9840 				347250012				DURING WINDSHIELD REPLACEMENT, MECHANIC NOTED STEEL FITTINGS AND ATTACHING HARDWARE WERE SUBSTANTIALLY CORRODED. FUNCTIO	N OF FITTINGS IS ATTACHMENT OF FUSELAGE OVERHEAD A PILLAR TO FUSELAGE STRUCTURE PROPER. OTHER THAN SOME RIVETS THROUGH T	HE SKINS, THESE FITTINGS ARE THE MAJOR STRUCTURAL ATTACHMENTS OF THE CABIN OVERHEAD TO THE FUSELAGE STRUCTURE. CAUSE OF 	CORROSION APPEARS TO BE FOAM INSULATION, HELD IN CONSTANT CONTACT WITH THE FITTINGS, BECOMING AND REMAINING WET THROUGH 	LEAKING WINDSHIELDS. MECHANIC RECOMMENDS REMOVING PORTION OF INSULATION IN CONTACT WITH FITTINGS AND INSPECTING THIS ARE	A AT EACH 100 HOUR/ANNUAL INSPECTION. ACCESS IS GAINED THROUGH SIMPLE REMOVAL OF INTERIOR WINDSHIELD PILLAR TRIM PANELS.	1	L	7	2 	3O	3	O		A7SO    	1E10				 
2007062500004	20070625	00004	EU  	2007	6	25	EBVR200700000    	1	20070609	G	2742	12342	MOTOR           	AMD         		AMD   	FALC10	FALCON10    	2730101	EU  										BRAKE UNIT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	55DG		863  		103	207				FAILED NORMAL MOTOR TRAVEL TIME CHECKS. SUSPECT NORMAL MOTOR BRAKE WAS PREVIOUSLY ASSEMBLED INCORRECTLY CAUSING DAMAGE T	O MOTOR.					2	L	7	2 	4F				A33EU   					 
2007071200126	20070712	00126	NE  	2007	7	12	EWCR070700002    	2	20070703	G	7200		ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LEFT	UNKNOWN         	B			EWCA	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X	Y	T	ENGINE FLAMEOUT           	ENGINE STOPPAGE           	ENGINE CASE PENETRATION   	CL	CLIMB          	1			EA	39	757CK					5600028	108055			FOLLOW UP REPORT AFTER PILOT REPORT TO FSDO OF (LARGE) BIRD STRIKE TO INLET AND INGESTION INTO LT ENGINE.						2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2007082100281	20070821	00281		2007	8	21	EY2R0097613      	3	20070718	G	6110	7826761	BEARING         			EMB   	120   	EMB120      	3260201	SO  										BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										PROPELLER BLADE BEARING CORRODED.						2	L	7	2 	4T			RT	A31SO   					 
2007113000111	20071130	00111	SO  	2007	11	30	FA20071025001    	2	20071025	G	7414	655845	GEAR            	SLICK       	4309        	DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	MAGNETO	BROKEN          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	25	629DC	1134 	490  		99052002	C0129	806243	AE4420		IN CRUISE,  NOTICED DROP IN OIL PRESSURE BELOW YELLOW ARC NOT INDICATED DURING RUN UP & TAKEOFF.  MADE PRECAUTIONARY RET	URN TO HOME BASE & LANDED APPROX 7-8 MINUTES AFTER NOTICING DROP IN OIL PRESSURE.  OIL PRESSURE INDICATED ZERO PSI DURIN	G TAXI BACK TO HANGER.  PRELIMINARY INSP &MAINT PERFORMED.  REMOVED OIL FILTER, CUT OPEN  AND INSPECTION SATISFACTORY, N	O METAL PRESENT.  REPLACED OIL PRESSURE TRANSDUCER WITH NEW AND RAN ENGINE.  LOW OIL PRESSURE STILL INDICATED.  CHECKED 	OIL PRESSURE WITH CALIBRATED SHOP GAGE.  LOW OIL PRESSURE INDICATED.  REMOVED AND CHECKED OIL PRESSURE RELIEF VALVE, FOU	ND FERROUS METAL CHUNK APPROX SIZE .060 DIA AT VALVE SEAT.  RAN ENGINE & OIL PRESSURE IN INDICATED IN THE GREEN ARC.  IN	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2008011100232	20080111	00232	GL  	2008	1	11	FAA010208001     	1	20071130	G	2497		UNKNOWN         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					PFD	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	123DV					1313				PFD AND GPS/NAV1 BOTH REBOOTED AT THE SAME TIME.  RESTARTED WITHOUT GOING THROUGH EITHER ITS STANDARD INITIALIZATION OR 	ITS FAST START ROUTINE.  THE AUTOPILOT SEEMED TO BE STILL ENGAGED BUT THE VS SELECTION, QNH, ALTITUDE PRE-SELECT AND HEA	DING WERE RESET AND THESE RESET VALUES APPEARED TO BE PASSED TO THE AUTOPILOT.  THIS OCCURRED AT LOW LEVEL, IN THE CLIMB	, IN IMC WITH HEADING AND ALTITUDE ACQUIRE SET ON THE AUTOPILOT.  THERE WAS SOME ELECTRICAL ACTIVITY  WITHIN 10 MILES.  	THE AIRCRAFT WAS FLOWN SAFELY BACK TO THE DEPARTURE FIELD USING BACKUP INSTRUMENTS.  ENGINEERS SUSPECT EITHER A SPIKE FR	OM ALTERNATOR 2 OR MFG BELIEVES THIS COULD BE A BONDING ISSUE AND WAS CAUSED BY STATIC.  MFG INCIDENT REF: 871500HQ.  EN	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2008011100233	20080111	00233	CE  	2008	1	11	FAA010208002     	1	20071102	G	3233	MS28775218	O-RING          			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					NLG ACTUATOR	DISINTEGRATED   	B			YN8R	A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			CE	07	1262K					4250234				AN EMERGENCY LANDING MADE, DID NOT GET A GREEN DOWN AND LOCK INDICATION FOR MLG.  MADE SAFE LANDING.  FOUND RT MLG NOT D	OWN AND FULLY LOCKED.  DISCOVERED BLOW DOWN BOTTLE FULLY DISCHARGED,  DISCOVERED HYDRAULIC RESERVOIR EMPTY.  JACKED ACFT	 & ATTEMPTED TO MANUAL EXTEND RT MLG BY HAND.  DISCOVERED THAT RT MLG WAS HYDRO-LOCKED.  BLED OFF HYDRAULIC PRESSURE FRO	M ACTUATOR, ABLE TO ENGAGE DOWNLOCK.  , JACKED ACFT AND TRIED TO CYCLE GEAR SYSTEM.  GEAR WOULD NOT CYCLE UP OR DOWN.  T	ROUBLESHOT AND DISCOVERED NLG ACTUATOR, PISTON O-RINGS HAD COME APART AND WENT THRU THE ENTIRE MLG AND PLUGGED SYSTEM.  	PRIOR TO FLIGHT, FWD SEALS ON ACTUATOR HAD BEEN REPLACED DUE TO EVIDENCE OF HYD LEAK.  AFTER SEALS HAD BEEN REPLACED, PE	1	L	7	2 	3T	4	T	RT	A7CE    	E4EA				 
2008011100235	20080111	00235	SO  	2008	1	11	FAA010208003     	2	20071219	G	8550	SAS6250	VALVE           			BBAVIA	7     	7EC         	2110120	SW  	CONT  	O200  	O200A       	17020	SO  					OIL TANK	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	274AC	1    				10142007	256377			INSTALLED OIL QUICK DRAIN VALVE PN SG250 ON NEW AIRCRAFT/ ENGINE.  AIRCRAFT FLEW APPROX 1 HOUR.  OIL LEAK NOTICED FROM D	RAIN VALVE.  REMOVED VALVE TO FIND VALVE SNAP RING IN OIL DRAINED FROM ENGINE AND VALVE O-RING DAMAGED.  ONE CUT THROUGH	 AND THE OTHER NICKED.  INVESTIGATION REVEALED OIL DRAIN VALVE CONTACTED THE EDGE OF THE OIL PICK-UP TUBE CAUSEING DAMAG	E.  SUBJECT VALVE IS NOT COMPATABLE WITH THE O200A66B ENGINE.  (K)			1	H	7	1 	3O	3	O		A759    	E252				 
2007070300048	20070703	00048	EU  	2007	7	3	FAA070628001     	1	20070628	G	6320	350A32031002	GEARBOX         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					MAIN ROTOR	MAKING METAL    	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	17	808CP	161  				4151	23335			MGB CHIP LIGHT CAME ON IN FLIGHT. REMOVED CHIP PLUGS FROM THE MGB AND THE MAST FOUND PARTICALS ON THE MGB PLUG LESS THAN	 LIMITS CALLED OUT IN AEC AS350B3 SPM 20.08.01.601 NOTHING ON THE MAST PLUG.PERFORMED 10 MIN. HOVER AND RECHECKED CHIP P	LUGS AS PER AEC AS350B3 MWC 05.53.00.608 NO MORE PARTICALS FOUND AND NO RE-ACCURANCE OF THE CHIP LIGHT.				1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008011100144	20080111	00144	EA  	2008	1	11	FAA122707001     	2	20071111	G	8530	AEL65102SN041	CYLINDER HEAD   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	D				B				EMER. DESCENT           				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			SO	19	62281	1083 				17275242	L1236139A			HEAD CAME OFF BARRELL OF CYLINDER P/N AEL65102 SN0.41 S/N 20255-13 1083.3 HOURS ON CYLINDER SINCE INSTRUCTION OF 10/5/04	 (HEAD, BARRELL SEPARATED).					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2008011100222	20080111	00222	CE  	2008	1	11	FAA122808001     	1	20071228	G	3220	AN7520	BOLT            			BEECH 	18    	H18         	1151012	CE  	PWA   	R985  	R985*       	52008	NE  					NLG	SHEARED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	19	117ME					BA638				DURING THE INVESTIGATION.  IT WAS DISCOVERED THAT THE REMAINDER OF THE BOLT FOR NOSE GEAR RETRACT PUSH PULL TUBE TO CANT	ILEVER ARM FOR DRAG BRACE HAD SHEARED ON (2) DIFFERENT OCCASIONS FOR REASONS UNDETERMINED.  THE OPERATOR ALSO OPERATES (	2) OTHER VOLPAR TRICYCLE GEARED AC, A BOLT FROM ONE OF THOSE AC WAS REMOVED TO FIND SCORE MARKS IN THE SHANK OF THE BOLT	 IN THE SAME VICINITY OF THE SHEAR POINTS OF THE INCIDENT AIRCRAFT BOTH AIRCRAFT HAVE SIMILAR AIRFRAME TT.  IT WAS DISCU	SSED WITH THE OPERATOR ON TECHNIQUES AND MISTAKES MADE DURING LANDING AND IT WAS DISCOVERED THAT IF THE AIRCRAFT IS EMPT	Y/LIGHT AND THE PILOT ALLOWS THE NOSE TO SETTLE TOO SOON IF COULD INDUCE A PORPOSING EFFECT THAT COULD PUT LARGE SHEAR L	1	L	7	2 	3R	3	R		A765    	5E1				 
2007070300006	20070703	00006	GL  	2007	7	3	FAA20070618001   	3	20070618	G	6114		HUB             			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2Y*      	GL  	PROPELLER	FAILED          	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	15	15156					347350028				ON JUNE 6,2007 PIPER SENECA N15156 WHILE IN CRUSE ON A TRAINING FLIGHT HAD A CATROSTRIFIC FAILRUE OF THE PROPELLER HUB C	AUSING THE LOSS INFLIGHT OF ONE OF THE PROPELLER BLADES. THE FAILURE OF THE HUB WAS OF THE SAME KIND ADDRESSED IN AD2006	-18-15 EXCEPT THE FAILURE IN THIS CASE PROPAGATED FROM THE AFT HALF OF THE HUB WHICH IS NOT PART OF THE AD'S REQUIRED IN	SPECTION. EDDY CURRENT INSPECTION IN ACCORDANCE WITH THE AD HAD BEEN PREFORMED 17 HOURS PRIOR TO THE FAILURE. INSPECTOR 	FOR HARTZELL PROPS CONFIRMED THIS INFORMATION AFTER INSPECTING THE HUB ALONG WITH FAA AND NTSB INVESTIGATORS ON JUNE 9TH	, 2007.	1	L	7	2 	3O				A7SO    		5	C	P920	 
2008010400239	20080104	00239	SO  	2008	1	4	FAA2007121001    	1	20071210	G	2130	SYLC518361	ACTUATOR        			EMB   	135   	EMB135BJ    	3260306	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					RAM AIR	SHORTED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	11	124LS					14500948				WHILE IN FLIGHT THE AIRCRAFT EXPERIENCED AND NR1 PAC OVLD INDICATION WITH SUBSEQUENT NR1 PAC AUTO SHUTDOWN AS A RESULT T	HE FLIGHT CREW MADE AN IN-FLIGHT DIVERSION AND UNSCHEDULED LANDING.  PERFORMED DOWNLOAD OF THE CENTRAL MAINTENANCE COMPU	TER WHICH REVEALED 1 OCCURRENCE OF NR1 PAC OVERTEMP AND 63 OCCURRENCES OF NR2 PAC OVERTEMP.  TROUBLESHOOTING REVEALED TH	AT THE LT AND RT PAC OVERTEMP SWITCHES FAILED BENCH CHECK.  BOTH SWITCHES WERE REPLACED WITH NEW SWITCHES.  DURING THE P	ERFORMANCE OF THE PAC SYSTEM OPERATIONAL TEST IT WAS DISCOVERED THAT THE RT RAM AIR ACTUATOR HAD AN ELECTRICAL SHORT CAU	SING THE CIRCUIT BREAKER TO (POP).  REPLACED THE RT RAM AIR ACTUATOR AND PERFORMED PAC SYSTEM OPERATIONAL TESTS.  DURING	2	L	7	2 	4F	4	F	RT	        	TE6CH				 
2007012500254	20070125	00254		2007	1	25	FCPR20070001     	4	20070105	G	3416	5934PA1	ALTIMETER       																	COCKPIT	BROKEN          	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										BAROMETRIC SCALE DOES NOT MOVE WITH DIAL INDICATION RESULTING IN INACCURATE READINGS THROUGH OUT THE ENTIRE RANGE.  ALLO	WS GEARS TO DISENGAGE INTERNALLY.  PART IS REMOVED FROM AIRCRAFT AT DISCOVERY.																		 
2007021400143	20070214	00143	SO  	2007	2	14	FCPR20070003     	2	20070131	G	8520	655516	GEAR            			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					CAMSHAFT	BROKEN          	B			FCPR	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			NM	09	18391	200  				E1113	685492			ENGINE FAILED IN FLIGHT.  FOUND 13 TEETH MISSING FROM CAMSHAFT GEAR P/N 655516.						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2008011000057	20080110	00057		2008	1	10	FCPR200700118    	2	20071227	G	7322	10603511	CARBURETOR      																	ENGINE	NO TEST         	B			FCPR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09										CARBURETOR FAILED THE STUMBLE TEST, FOUND TO BE ACCELERATOR CIRCUIT.  PART RETURNED TO MFG FOR FURTHER EVALUATION.  (K)																			 
2008011400085	20080114	00085		2008	1	14	FCPR200700125    	2	20071227	G	7322	10603511	CARBURETOR      																	ENGINE	NO TEST         	B			FCPR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	09										CARBURETOR FAILED THE STUMBLE TEST, FOUND TO BE ACCELERATOR CIRCUIT.  PART RETURNED TO MFG FOR FURTHER EVALUATION.  (K)																			 
2008010800351	20080108	00351	EA  	2008	1	8	FCPR20070110     	2	20071208	G	7314	RB15985	DIAPHRAGM       	ROMEC       	RG179801M   	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					FUEL PUMP	FAILED          	B			FCPR	K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			NM	09			294  		C5518	277754126	L853261A			PUMP VALVE REGULATOR DIAPHRAGM FAILED AT GUIDE PIN, PUMP WOULD NOT FUNCTION.						1	L	7	2 	3O	3	O		1A10    	E14EA				 
2007041200006	20070412	00006	CE  	2007	4	12	FMOR20070001     	1	20070409	G	3230	57412025	UPLOCK HOOK     			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ZONE 700	CRACKED         	B				O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			SO	15	6161Z	7024 				414A0019				PILOT REPORTED THAT THE LANDING GEAR CAME UNHOOKED FROM THE UP POSITION IN FLIGHT.  THE GEAR WAS EXTENDED AND THE AIRCRA	FT LANDED.  THE AIRCRAFT WAS JACKED AND THE GEAR CYCLED TO THE UP POSITION.  WHEN ALL (3) UPLOCK SWITCHES WERE MADE THE 	RT MAIN GEAR FELL FROM THE WHEEL WELL.  A DISTORTED AND CRACKED UPLOCK HOOK WAS FOUND.  THE CRACK WAS FROM THE CENTER OF	 THE HOOK TO THE HOLE FOR THE UPLOCK SWITCH.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007041300111	20070413	00111	CE  	2007	4	13	FMOR20070002     	1	20070410	G	2731	NAS302665170	CONTROL CABLE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					FS 216	FRAYED          	B				O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			SO	15	120TT	5072 				LJ1073				THE ELEVATOR TRIM CABLE BEGAN UNRAVELING JUST FORWARD OF THE CABIN DOOR.  FROM THERE THE CABLE BEGAN BINDING IN A PULLEY	 UNDERNEATH THE PILOT'S SIDE FORWARD FACING PASSENGER CHAIR CAUSING STIFFNESS OF OPERATION BY HAND AND THE MALFUNCTION O	F THE ELECTRIC TRIM SYSTEM LEADING TO THE EVENTUAL INOPERATION OF THE ELEVATOR TRIM.  THE ISSUE MOST LIKELY AROSE DUE TO	 AGE.  WHILE UNDER THE SCHEDULED INSPECTION PROGRAM OUTLINED BY MFG THE INSPECTION OF THESE AREAS OCCURS ONCE EVERY (2) 	YEARS OR 800 HOURS.		1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2007090600082	20070906	00082	CE  	2007	9	6	FMOR20070003     	1	20070828	G	2731	NAS302665170	CONTROL CABLE   			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FS 216	FRAYED          	B			FMOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	725AR	6415 	310  			LJ879				THE ELEVATOR TRIM CABLE WAS FOUND TO HAVE SEVERAL BROKEN STRANDS AND BEGINNING TO UNRAVEL WHERE IT GOES AROUND THE ELEVA	TOR TRIM ACTUATOR CAPSTAND. THIS CONDITION WAS MOST LIKELY CAUSED BY AGE.					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2007042500260	20070425	00260	CE  	2007	4	25	FMOR477K         	1	20070409	G	3230	57412025	UPLOCK HOOK     			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	DISTORTED       	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	6161Z	7024 				414A0019				PILOT REPORTED THAT THE LANDING GEAR CAME UNHOOKED FROM THE UP POSITION IN FLIGHT.  THE GEAR WAS EXTENDED AND THE AIRCRA	FT LANDED.  THE AIRCRAFT WAS JACKED AND THE GEAR CYCLED TO THE UP POSITION.  WHEN ALL (3) UPLOCK SWITCHES WERE MADE THE 	RT MAIN GEAR FELL FROM THE WHEEL WELL.  A DISTORTED AND CRACKED UPLOCK HOOK WAS FOUND.  THE CRACK WAS FROM THE CENTER OF	 THE HOOK TO THE HOLE FOR THE UPLOCK SWITCH.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2008011100134	20080111	00134		2008	1	11	FPFC20070113     	2	20071226	G	7322	10603511	CARBURETOR      																		NO TEST         	B			FCPR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	09										CARBURETOR FAILED THE STUMBLE TEST, FOUND DEFECTIVE ACCELERATOR CIRCUIT. PART RETURNED TO PRECISION FOR FURTHER EVALUATI	ON.																		 
2007082400324	20070824	00324	CE  	2007	8	24	GC4N200700001    	1	20070824	G	3233		ACTUATOR        			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					NLG	FAULTED         	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			GL	07	7088S					RB188				AFTER COMPLAINT FROM THE PILOT OF NOT GETTING A NOSE LANDING GEAR DOWN LIGHT STRAIT AWAY, PLACED THE AIRCRAFT ON JACKS A	ND CARRIED OUT 4 RETRACTIONS WHICH RESULTED IN 100 PERCENT FAILURE OF THE NOSE LANDING GEAR FULLY EXTENDING, AFTER FAULT	 FINDING WE BELIEVE THE NOSE LANDING GEAR ACTUATOR TO BE FAULTY, A PART IS ON ORDER FROM MFG.				1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2008011100284	20080111	00284	SO  	2008	1	11	GW4R200700001    	1	20071210	G	2130	SYLC518361	ACTUATOR        			EMB   	135   	EMB135BJ    	3260306	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					RAM AIR	FAILED          	B			CWQA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	11	124LS					14500948				DURING FLIGHT, AIRCRAFT EXPERIENCED AND NR 1 PACK OVLD INDICATION WITH SUBSEQUENT NR 1 PACK AUTO SHUTDOWN AS A RESULT MA	DE AN IN-FLIGHT DIVERSION AND UNSCHEDULED LANDING.  PERFORMED DOWNLOAD OF THE CENTRAL MAINTENANCE COMPUTER WHICH REVEALE	D 1 OCCURRENCE OF NR 1 PACK OVERTEMP AND 63 OCCURRENCES OF NR 2 PACK OVERTEMP.  TROUBLESHOOTING REVEALED THE LT AND RT P	ACK OVERTEMP SWITCHES FAILED BENCH CHECK.  BOTH SWITCHES WERE REPLACED.  DURING PERFORMANCE OF PACK SYSTEM OPS TEST, IT 	WAS DISCOVERED THAT THE RT RAM AIR ACTUATOR HAD AN ELECTRICAL SHORT CAUSING THE CIRCUIT BREAKER TO TRIP.  REPLACED THE R	T RAM AIR ACTUATOR AND PERFORMED PAC SYSTEM OPS TESTS.  DURING THE ABOVE CENTRAL MAINTENANCE COMPUTER DOWNLOAD, 17 OCCUR	2	L	7	2 	4F	4	F	RT	        	TE6CH				 
2008010800326	20080108	00326	SO  	2008	1	8	GW4R237272       	1	20071129	G	2130	SYLC518361	ACTUATOR        			EMB   	135   	EMB135BJ    	3260306	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					RT RAM AIR	SHORTED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	11	124LS					14500948				WHILE IN FLIGHT THE AC EXPERIENCED AND NR1 PAC OVLD INDICATION WITH SUBSEQUENT NR1 PAC AUTO SHUTDOWN AS A RESULT THE FLI	GHT CREW MADE AN IN-FLIGHT DIVERSION AND UNSCHEDULED LANDING.  DOWNLOAD OF THE COMPUTER REVEALED 1 OCCUR OF NR1 PAC OVER	TEMP AND 63 OF NR2 PAC OVERTEMP.  LT AND RT PAC OVERTEMP SWITCHES FAILED BENCH CHECK.  BOTH SWITCHES WERE REPLACED.  DUR	ING THE PAC SYSTEM OPS TEST, THE RT RAM AIR ACTUATOR HAD AN ELECTRICAL SHORT CAUSING THE CIRCUIT BREAKER TO POP.  REPLAC	ED THE RT RAM AIR ACTUATOR AND PERFORMED PAC SYSTEM OPERATIONAL TESTS.  DURING THE COMPUTER DOWNLOAD, 17 OCCURRENCES OF 	A NR1 PRECOOLER TEMP CONTROL SYSTEM FAIL MESSAGE WAS NOTED.  ACCESSED FAN AIR TEMPERATURE THERMOSTATS FOR TROUBLESHOOTIN	2	L	7	2 	4F	4	F	RT	        	TE6CH				 
2008010800333	20080108	00333	SO  	2008	1	8	GW4R237272NR1    	1	20071129	G	2150	SYLC518361	SWITCH          			EMB   	135   	EMB135BJ    	3260306	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					A/C PACK	FAILED          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			UK	UNKNOWN        	1			SO	11	124LS					14500948				IN FLIGHT AC EXPERIENCED AND NR1 PAC OVLD IND WITH NR1 PAC AUTO SHUTDOWN.  FLT CREW MADE AN IN-FLIGHT DIVERSION AND UNSC	HEDULED LANDING.  DOWNLOAD OF THE COMPUTER REVEALED 1 OCCUR OF NR1 PAC OVERTEMP AND 63 NR2 PAC OVERTEMP.  LT AND RT PAC 	OVERTEMP SWITCHES FAILED BENCHCHECK.  BOTH SWITCHES WERE REPLACED.  DURING THE PAC SYSTEM OPS TEST DISCOVERED THE RT RAM	 AIR ACTUATOR HAD AN ELEC SHORT CAUSING THE CB TO POP.  REPLACED THE RT RAM AIR ACTUATOR AND PAC SYSTEM OPS TESTS.  DURI	NG THE COMPUTER DOWNLOAD, 17 OCCURRENCES OF A NR1 PRECOOLER TEMP CONTROL SYSTEM FAIL MESSAGE WAS NOTED.  ACCESSED FAN AI	R TEMPERATURE THERMOSTATS FOR TROUBLESHOOTING AND UPON REMOVAL IT WAS NOTED THAT THE AMBIENT AIR TEMPERATURE PORTS ON EA	2	L	7	2 	4F	4	F	RT	        	TE6CH				 
2007022700054	20070227	00054	CE  	2007	2	27	HAG07001         	1	20070223	G	5753	2322330177	SUPPORT BRACKET 	GARKENYON   	26044       	LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       	 	NE  					FLAP ACTUATOR	FAILED          	B			H51R	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			NM	03	252FX	5936 			0295	196				DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LT WING RIB SEGMENT.						2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007030900001	20070309	00001	CE  	2007	3	9	HAG07002         	1	20070222	G	5532	4555030001804	PANEL           			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312B    	 	WP  					VERTICAL STAB	CRACKED         	B			H51R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	451WM	5571 				091				DURING INSPECTION, FOUND RT SIDE VERTICAL STABILIZER CENTER BULLET FAIRING PANEL CRACKED IN 5 LOCATIONS.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2007031200058	20070312	00058	CE  	2007	3	12	HAG2007001       	1	20070223	G	5740	2322330177	SUPPORT BRACKET 	GARKENYON   	26044       	LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ZONE 500	FAILED          	B			H51R	O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			NM	03	252FX	5936 			0295	196				DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LT WING RIB SEGMENT.						2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2007022600164	20070226	00164	CE  	2007	2	26	HAGGAN07001      	1	20070223	G	5740	2322330177	SUPPORT BRACKET 	GARKENYON   	26044       	LEAR  	60    	60LEAR      	5170707	CE  										ZONE 500	FAILED          	B			H51R	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			NM	03	252FX	5936 			0295	196				DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LT WING RIB SEGMENT.						2	L	7	2 	4F			RT	A10CE   					 
2007061300171	20070613	00171	NE  	2007	6	13	IG0R200743437    	2	20070508	G	7322	2526385	BELLOWS         	ALIDSG      	DPF2        						PWA   	PT6   	PT6A135     	52043	NE  					FUEL CONTROL	FAILED          	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			NM	03			92   		A59386		PCE92578			THE FUEL CONTROL (FCU) P/N 3244777-4-3-2, S/N A59386 DIRECTED THE ENGINE TO MIN FLOW SHORTLY AFTER LANDING WITHOUT ANY F	URTHER POWER LEVER RESPONSE.  THE CONTROL TSO IS 92.8.  THIS CONTROL WAS LAST SERVICED BY INTERNATIONAL GOVERNOR SERVICE	S (IGS) IN NOV 2006. THE AS RECEIVED TEST REVEALED FUEL FLOWS HAD DROPPED BELOW SCHEDULE AT ALL TEST POINTS EXCLUDING MI	N FLOW AND MAX FLOW (THESE ARE BOTH PHYSICAL HARD STOPS).  FURTHER INVESTIGATION REVEALED THAT THE EVACUATED SECTION OF 	THE BELLOWS (HONEYWELL P/N 2526385) WAS BREACHED (LOST THE VACUUM). THE INSPECTION CRITERIA FOR THE EVACUATED SECTION OF	 THE BELLOWS INVOLVES MEASURING THE BELLOWS HEIGHT AND COMPARING THE READING WITH THAT RECORDED DURING ORIGINAL MANUFACT						4	T			E4EA				 
2007061300203	20070613	00203	EA  	2007	6	13	IG0R200743667    	2	20070509	G	7321	2523973	BEARING         	ALIDSG      	DPF2        						PWA   	PT6   	PT6*        	52043	EA  					FCU	FAILED          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03					C75067		PCEPH0218			ALLIED SIGNAL AEROSPACE (HONEYWELL) FUEL CONTROL UNIT (FCU)P/N 4138008-3, S/N C75067 RECEIVED FOR OVERHAUL AT INTERNATIO	NAL GOVERNOR SERVICES (IGS) CRS IG0R976N EXPERIENCED A SPOOL BEARING (P/N 2523973) FAILURE.  THE FCU WAS REMOVED FROM PT	6A ENGINE S/N PCE-PH0218.  CONTROL APPEARS TO BE FIRST RUN OVERHAUL, HOWEVER, WE ARE UNABLE TO OBTAIN TIME SINCE NEW. IG	S WILL FORWARD THE BEARING TO HONEYWELL FOR REVIEW.  NOTE: THIS IS THE 5TH OR 6TH BEARING WE HAVE SEEN FAIL IN THE PAST 	6 MONTHS OR SO.							3	T			E2NE				 
2007061500172	20070615	00172	EA  	2007	6	15	IG0R200746139    	2	20070518	G	7322	2523629	HOUSING         	HONEYWELL   	DPF2        						PWA   	PT6   	PT6*        	52043	EA  					FUEL CONTROL	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03			2452 		309482					CORROSION ON FLOW BODY METERING VALVE OPERATING LEVER COVER, EXCEEDS LIMITS.											3	T			E2NE				 
2008011000133	20080110	00133	EA  	2008	1	10	IG0R200751070    	2	20071219	G	7321	2523631	BELLOWS         	HNYWL       	DPF2        	BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FCU	DAMAGED         	B				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NM	03			54   		A33630					ENGINE WENT TO IDLE IN FLIGHT. FAILED BELLOWS BENCH TEST. BELLOWS BREACHED. UPON FURTHER INSPECTION THERE WAS NO PHYSICA	L DAMAGE TO THE BELLOWS HOWEVER THERE WAS CORROSION ON THE TOP OF THE BELLOWS AND AT THE FIRST CONVOLUTION. REPLACED BEL	LOWS AND RECALIBRATED FUEL CONTROL UNIT.				1	L	7	2 	3T	4	T		3A20    	E4EA				 
2007120500061	20071205	00061	CE  	2007	12	5	IWP2720085003    	1	20071123	G	3230	608100961	SPRING          	BEECH       		BEECH 	60    	B60         	1153605	CE  										MLG DOWNLOCK	MISINSTALLED    	G				O				OTHER                   				G			MULTIPLE FAILURE          			LD	LANDING        	1			WP	27	408FA					P434				THIS AIRCRAFT EXPERIENCED A BENT /DAMAGED RT MAIN GEAR RETRACT ROD ASSEMBLY P/N 60-810057-617. A CURRENT OVERLOAD OF THE	 LANDING GEAR MOTOR CIRCUIT. THE RT MAIN GEAR FAILED TO EXTEND. THE EMERGENCY GEAR FAILED TO ALSO EXTEND THE RETRACTED M	AIN. AC WAS FORCED TO LAND GEAR UP.  INVESTIGATION REVEALED AN IMPROPERLY INSTALLED TORSION SPRING (IN QUESTIONABLE COND	ITION) ON THE RT MAIN DOWN-LOCK CABLE (JURY STRUT). INVESTIGATION REVEALED THAT THE IMPROPER INSTALLATION OF THIS SPRING	 RESULTED IN THE RT DOWN LOCK CABLE MOVING INTO AND ENTANGLING WITH THE DRAG BRACE KNEE JOINT AND UPLOCK DOWNLOCK PIVOT 	POINT DURING RETRACTION. HOWEVER- IT HAS NOT BEEN PROVEN BY FAA INSPECTORS, THAT THE IMPROPER INSTALLATION OF THIS SPRIN	1	L	7	2 	3O				A12CE   					 
2007031200022	20070312	00022	CE  	2007	3	12	J0UR200700001    	1	20070218	G	2121	EM6039	MOTOR           			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					BLOWER	FAILED          	B			J0UR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	09	1103G					LJ1475				AIR CONDITIONING / VENT BLOWER MOTOR ASSEMBLY FAILED CAUSING SMOKE IN COCKPIT. PILOT DECLARED EMERGENCY AND LANDED AT CL	OSEST AIRPORT WITHOUT FURTHER INCIDENT.					1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2007022600126	20070226	00126		2007	2	26	JZBR710K21907    	2	20070219	G	7322	9867500500	NUT             			SKRSKY	S76   	S76C        	8143008	NE  										FILTER CAP ASSY	MISSING         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	165ML				121B	760471	20026			DURING COMPLIANCE WITH MANDATORY SB 292-73-2824, (REPLACEMENT OF FUEL FILTER DRAIN SCREW ON HMU FILTER BOWL COVER ASSEMB	LY), UPON COVER REMOVAL IT WAS DISCOVERED THAT THE NUT (P/N 9867500500) AND STOP WASHER (P/N 0319910870) WERE NOT INSTAL	LED, MISSING FROM DRAIN SCREW THREADS ON THE INSIDE OF THE COVER ASSEMBLY. FILTER WAS REMOVED FOR FURTHER INSPECTION OF 	FILTER BOWL LOWER RECESSES WITH NO EVIDENCE OF MISSING PARTS INSIDE.			1	G	7	2 	3U			NC	H1NE    					 
2008010800325	20080108	00325	EU  	2008	1	8	LJER12102007     	2	20071206	G	7414	106825515	CONTACTOR       			PIPER 	PA44  	PA44180     	7104402	SO  	ROTAX 	      	ROTAX*      		EU  					MAGNETO	DEBONDED        	B			LJER	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	09	2163	1    								CONTACT POINT MATERIAL DEBONDED, POINTS WILL NOT CLOSE.						1	L	7	2 	3O	3	I		A19S0   	EXPE3I				 
2007091800110	20070918	00110	EA  	2007	9	18	LX5R200700006    	2	20070913	G	7200		ENGINE          			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					RIGHT	MAKING METAL    	B			LX5R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	19	761LL	3685 				760379	PS36144			DURING CRUISE, SHORTLY AFTER T/O NR 2 ENG CHIP LIGHT ILLUMINATED.  APPROPRIATE CB WAS PULLED TO TRY AND (BURN) OFF FUSS,	 BUT LIGHT REMAINED ILLUMINATED. IAW FLIGHT MANUAL, CREW LANDED WITHOUT INCIDENT AT NEAREST AIRPORT TO INVESTIGATE CHIP 	LIGHT. FLIGHT CONDITIONS WERE DAY VFR, NO CLOUDS, UN-RESTRICTED VISABILITY, WIND CALM, 65 DEGREE F, AND CRUISE SPEED WAS	 145KTS.   AFTER LANDING CREW CALLED HOME MAINT BASE. A MECHANIC TALKED TO OUR HOME BASE AND INSPECTED AFFECTED CHIP DET	ECTOR. IT WAS DETERMINED, THE SMALL SLIVERS OF METAL WERE ACCEPTABLE IAW MM. ENG WAS CLOSED UP AND THE CREW PERFORMED A 	GROUND RUN AND CHIP LIGHT DID NOT COME BACK ON. FLGT CONTINUED TO DESTINATION, WITHOUT OTHER INDICATIONS.  (K)	1	G	7	2 	4U	4	U		H1NE    	E4EA				 
2007022600031	20070226	00031	SO  	2007	2	26	M1144            	2	20070208	G	8530		EXHAUST VALVE   			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NR 5 CYLINDER	BROKEN          	B				B				EMER. DESCENT           				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CE	03	540CA	1776 	612  			421C0144				PILOT REPORTED THAT RT ENGINE WAS RUNNING ROUGH IN FLIGHT. HE DID NOT SHUTDOWN ENGINE. FOUND NO COMPRESSION IN NR 5 CYLI	NDER ON RT ENGINE. REMOVED CYLINDER AND FOUND EXHAUST VALVE WAS BROKEN. INSTALLED OVERHAULED CYLINDER ASSEMBLY.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2007040200135	20070402	00135	CE  	2007	4	2	M40675           	1	20070320	G	2740	45AS610023139	ACTUATOR        			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					PITCH TRIM	INOPERATIVE     	C			R71A	O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			WP	05	790SS	1550 				RK363				DIFFICULTY OCCURRED UPON DESCENT. PILOT RECEIVED A WARNING PITCH TRIM WAS NOT SYNCHRONIZED WITH AUTOPILOT SYSTEM AND TO 	PREPARE FOR RESISTANCE WHEN AUTOPILOT IS DISCONNECTED. PITCH TRIM ACTUATOR WAS FOUND INOPERATIVE IN THE EMERGENCY MODE/A	UTOPILOT MODE. REPLACED PITCH TRIM UNIT AND RETURNED AIRCRAFT TO SERVICE. THIS AIRCRAFT WAS LAST INSPECTED ON 11-9-06 AT	 1408.6 TT.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2007050400151	20070504	00151	GL  	2007	5	4	MDR041607        	1	20070416	G	3244		TIRE            			AMTR  	500   	ECLIPSE500  	05614K5	GL  										LT MLG	FAILED          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	27	110DJ	41   				000007				LT MAIN LANDING GEAR WHEEL AND TIRE ASSEMBLY BLEW OUT DURING TAXI. WHEEL HAS BEEN QUARANTINED AND WILL BE FORWARDED TO A	N INDEPENDENT INSPECTION LAB FOR FURTHER REVIEW.					1	L	7	2 	3F			RT	EXPA1L72					 
2007100200029	20071002	00029	SO  	2007	10	2	MINR2007918A     	1	20070918	G	7810	40B19974	EXHAUST PIPE    			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2   	 	EA  					ENGINE	BULGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	498MM	1349 				4636149				THE EXHAUST CROSSOVER EXHAUST PIPE WAS FOUND SEVERELY BULGED IN THE AREA COVERED BY THE HEAT SHROUD. THE DAMAGE WAS TO T	HE POINT, ISSUES WERE FORMING THAT WOULD HAVE LED TO RUPTURE. IF AN EXHAUST LEAK OCCURS IN THIS AREA, THE HEAT WILL AFFE	CT THE MAGNETO, FUEL AND OIL LINES. IT IS HIGHLY RECOMMENDED BY MAINTENANCE PERSONNEL THAT THE HEAT SHROUD BE REMOVED AT	 EACH 100 HOUR INSPECTION FOR AIRCRAFT WITH MORE THAT 500 HOURS.  NR 3 CYLINDER EXHAUST RISER PN 40B19827 WAS ALSO FOUND	 SEVERELY BULGED. THIS CAN BE SEEN WITH THE ENGINE COWLING REMOVED WITHOUT FURTHER DISASSEMBLY.  THE LT EXHAUST TRANSITI	ON PN 47C19848 WAS FOUND BULGED AND CRACKED. THIS CAN BE SEEN WITH A MIRROR AND FLASHLIGHT.  IF ANY DAMAGE IS FOUND ON T	1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2007102300092	20071023	00092	CE  	2007	10	23	N843E12007       	1	20070801	G	2432	9036102331	HED             			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A6       	52043	EA  					BATTERY	FAULTED         	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NE	03	843E	7178 				UE339				CREW LEFT STATION.  TWENTY MINUTES IN FLIGHT "BATT TIE OPEN" ANNUNCIATOR ILLUMINATED.  CREW RETURNED TO STATION WITHOUT 	ISSUE.  REMOVED AND REPLACED BATTERY HED.  OPS CHECK GOOD.					2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2008011400058	20080114	00058	CE  	2008	1	14	ODAA121907001    	1	20071219	G	5510		ACCESS PANEL    			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  						OUT OF ADJUST   	E			ODAA	O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			EA	21	2G					258354				PILOT REPORTED RUDDER PEDALS BINDING FOUND DURING PREFLIGHT, WITH RT PEDAL FORWARD AND LT PEDAL AFT.  AFTER APPLYING PRE	SSURE TO PEDALS WITH FEET, PEDALS BECAME UNBOUND WITH POPPING NOISE HEARD.  INSPECTED RUDDER SYSTEM.  FOUND RUDDER BINDI	NG AT PANEL SCREW FOR LOWER CONTROL COLUMN ACCESS, FORWARD, DUE TO BEND IN PANEL.  REMOVED SCREWS AND ADJUSTED PANEL FOR	 BETTER CLEARANCE.  REPLACED SCREWS WITH SHORTER VERSION OF SAME.  RUDDER SYSTEM OPERATED NORMALLY.  REFERENCE MM, CHAPT	ER 27.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2007121400348	20071214	00348	GL  	2007	12	14	ODAR15DR1        	1	20070411	G	2421	BC4101	ALTERNATOR      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					NR 2	DESTROYED       	B			ODAR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	21	15DR					0394				OWNER REPORTED NR2 ALTERNATOR LIGHT ILLUMINATED.  REMOVED TOP COWLING TO INSPECT NR2 ALTERNATOR.  FOUND NR2 ALTERNATOR B	ROKEN OFF AT MOUNTING PLATE BY (3) STUDS.  ONE STUD STILL ATTACHED WITH NUT, BUT LOOSE.  REMOVED P/N BC410-1, S/N 092140	3.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007041700030	20070417	00030	GL  	2007	4	17	ODAR3            	1	20070411	G	2421	BC4101	ALTERNATOR      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					NR 2	DESTROYED       	B			ODAR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			EA	21	15DR					0394				OWNER REPORTED NR 2 ALTERNATOR LIGHT ILLUMINATED.  REMOVED TOP COWLING TO INSPECT NR 2 ALTERNATOR.  FOUND NR 2 ALTERNATO	R BROKEN OFF AT MOUNTING PLATE BY (3) STUDS.  ONE STUD STILL ATTACHED WITH NUT, BUT LOOSE.  REMOVED P/N BC410-1, S/N 092	1403. PICTURES AVAILABLE AT THIS FACILITY.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2007050100085	20070501	00085	CE  	2007	5	1	OMKR20071        	1	20070331	G	3230	08420003	DRAG LINK       			CESSNA	310   	310C        	2074210	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG	BROKEN          	B			OMKR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	4411					39024				UPON LANDING, THE NOSE LANDING GEAR DRAG LINK ASSEMBLY P/N 0842000-3 BROKE AT THE STRUT ATTACH POINT, ALLOWING THE NOSE 	GEAR TO COLLAPSE REARWARD, CAUSING THE AIRCRAFT TO SLIDE ON ITS NOSE UNTIL IT STOPPED.  THE DRAG LINK ASSEMBLY APPEARS T	O HAVE BROKEN THROUGH THE FORWARD ATTACH HOLE. TOTAL TIME OF THE PART AND TOTAL TIME OF THE AIRCRAFT ARE UNKNOWN AT THIS	 TIME DUE TO ABSENCE OF LOG BOOKS.  CURRENT HOBBS TIME IS 118.4.			1	L	7	2 	3O	3	O		3A10    	E1CE				 
2007120500057	20071205	00057	CE  	2007	12	5	OMKR200711211    	1	20071121	G	2500	443030401	ADJUSTER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  					HARNESS ADJUSTER	IMPROPER PART   	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	9957R					U20606999				AD 2004-19-01C CALLS FOR A SPRING TO BE REMOVED FROM SHOULDER HARNESS ADJUSTER P/N443030-401, THAT WAS INADVERTENTLY INS	TALLED ON A CERTAIN BATCH OF ACCESSORY KITS SHIPPED FROM MFG 1984 THROUGH 1986.  THIS RESULTED IN AD 86-26-04 BEING ISSU	ED.  CURRENTLY HAVE (2) AIRCRAFT IN THE HANGAR WITH THIS PN ADJUSTER WITH SPRINGS INSTALLED.  THEY DO NOT FALL INTO THE 	AFFECTIVITY RANGE OF THE AD OR SB.  CONTACTED THE ENGINEER ON THE BACK OF THE AD, AND HE INSISTS I DO NOT HAVE AN AFFECT	ED ADJUSTER.  HE HAD A MFG REP. WHO WAS FAMILIAR WITH THE AD CONTACT ME AND I FOUND OUT THE AD RESULTS FROM (INCORRECTLY	) INSTALLED SPRINGS.  I SUBMIT THE AD REQUIRES CLARITY AS TO THE DIFFERENCE BETWEEN (INADVERTENTLY INSTALLED) AND (INCOR	1	H	7	1 	3O	3	O		A4CE    	E5CE				 
2007013100171	20070131	00171	SO  	2007	1	31	PAI52007S4448    	2	20070130	G	8520		STUD            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 4 CYLINDER	BROKEN          	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	414CJ		1403 			414A0432	519053			DURING ANNUAL INSPECTION FOUND 5 BROKEN HOLD DOWN STUDS ON NR 4 CYLINDER.  ENGINE WAS MODIFIED IAW RAM STC SE3630SW AND 	SE3631SW AT PREVIOUS OVERHAUL.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2007032600098	20070326	00098	CE  	2007	3	26	PAI52007S4508    	1	20070322	G	7600	10052417717	CONDITION LEVER 			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A6       	52043	EA  					COCKPIT	LOOSE           	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	507EB	4957 				FL81				PILOT NOTED RT ENGINE CONDITION LEVER CONTROL FELT LOOSE AND IDLE N1 SPEED LOW.  UPON INSPECTION, MAINTENANCE FOUND ALL 	SCREWS ATTACHING CONDITION LEVER TO QUADRANT LOOSE TO THE POINT OF ALMOST FALLING OUT.					2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2007061400142	20070614	00142	CE  	2007	6	14	PAI52007S4573    	1	20070515	G	5730	00011013333	SKIN            			BEECH 	B300  	B300        	1159232	CE  										WING	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	507EB	5010 	196  			FL81				WHILE PERFORMING PHASE 2 INSPECTION NOTED AN 8 INCH LONG SPANWISE CRACK ON LOWER SURFACE OF WING LEADING EDGE SKIN P/N 0	00-110133-33.  ALSO FOUND CHANNEL P/N 101-910119-147 INSIDE THE ABOVE MENTIONED SKIN BROKEN IN TWO.  REPLACED BOTH PARTS	 WITH NEW PARTS FROM BEECH.				2	L	7	2 	4T			RT	A24CE   					 
2007100300016	20071003	00016	EU  	2007	10	3	PAI52007S4724    	1	20070926	G	3010	80232118401	DUCT            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6*        	52043	EA  					WING LE	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	145SL	2994 				1093				DURING 3000 HOUR D-CHECK FOUND 3 OF 4 WING OB LEADING EDGE PANELS WITH CRACKED HEATING DUCTS.						1	H	7	2 	3O	3	T	RT	A59EU   	E2NE				 
2007110500004	20071105	00004	SW  	2007	11	5	PAI52007S4751    	1	20071024	G	2910	T610488109	LINE            			GULSTM	690TP 	690B        	7630516	SW  										HYD SYSTEM	RUPTURED        	B			PAI5	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SO	05	91CT					11428				HYDRAULIC PRESSURE FLEX LINE AT RT ENGINE DRIVEN HYDRAULIC PUMP RUPTURED IN FLIGHT CAUSING LOSS OF HYDRAULIC FLUID.						1	H	7	2 	3T				2A4     					 
2007050100117	20070501	00117	CE  	2007	5	1	PAZR200700001    	1	20070416	G	5551	663110215	ATTACH FITTING  			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ZONE 300	CRACKED         	B			PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	186XL	2179 				5605186				DURING A SCHEDULED INSPECTION, A 1.5 INCH CRACK WAS FOUND IN THE LOWER RADIUS OF THE HORIZONTAL STABILIZER AFT ATTACH FI	TTING.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2007020600050	20070206	00050		2007	2	6	QKPR07001        	1	20070202	G	4930	38828406	FCU             	HONEYWELL   	GTCP36150RR 															APU	LEAKING         	B			QKPR	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SO	05										THERE IS A PIN HOLE IN THE FCU HOUSING. IN THIS CASE THERE WAS 4 STREAMS OF FUEL AND HEAVY MISTING.																			 
2007041000068	20070410	00068	NM  	2007	4	10	QXEANM09402      	1	20070315	G	4920	164161100	DRAIN VALVE     	SUNDSTRANDEM		BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					APU	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	402QX					4032				BALL ON WRONG SIDE OF SPRING, WHICH ALLOWS IT TO REST IN CLOSED POSITION, NOT ALLOWING PROPER DRAINAGE.						2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007040900125	20070409	00125	NM  	2007	4	9	QXEANM09417      	1	20070314	G	4920	164161100	DRAIN VALVE     			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					APU	PLUGGED         	G			QXEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	417QX					4086				BALL ON WRONG SIDE OF SPRING ALLOWING IMPROPER DRAINAGE.						2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2007013100185	20070131	00185	NE  	2007	1	31	R021692          	3	20070117	G	6111	D7745	BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	BROKEN          	B			SJ3R	O				OTHER                   				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			GL	05	SJ3R	3115 						HJ1819		ON 12/14/06 REPORTED AIRCRAFT VIBRATIONS FROM STBD ENGINE. INSPECTION OF PROPELLER ON GROUND REVEALED EXCESSIVE RADIAL P	LAY OUT OF LIMIT OF NR 3 BLADE.  PROPELLER REMOVED FROM AIRCRAFT FOR FURTHER INVESTIGATION. SERVICE CENTER NOTES: BLADE 	NR 3 CAM FOLLOWER BROKEN, PRELOAD PLATE GOUGED, BLADE SIDE D-7745 BEARING CRACKED RADIALLY AND PIECE MISSING. RETAINING 	WASHER ATTACHED TO PC KNOB. BLADE NR 3 FORK SLOT WORN 0.028, OTHER 3 SLOTS WORN 0.015-0.021, CIRCUMFERENTIAL WEAR IN FOR	K SEAT. BLADE NR 3 RETENTION SHOULDER HEIGHT MEASURED 0.914 - 0.974, UNABLE TO PERFORM OPTICAL COMPARATOR INSPECTION OF 	RADIUS DUE TO SHOULDER HEIGHT DIMENSION BELOW 0.972. SEE S/B 287.	2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE	 
2007032200091	20070322	00091	GL  	2007	3	22	R022366          	3	20070316	G	6110	A20742	SEAL RING       			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550F      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROPELLER BLADE	DEBONDED        	B			SJ3R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			GL	05		81   						FP5296B		TEFLON (BLADE SEAL) DEBONDED FROM THE SHANK OF BLADE SN A0336 CAUSING GREASE LEAK.						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2007082100233	20070821	00233	GL  	2007	8	21	R0240301         	3	20070814	G	6110	B3493	BRACKET         			MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER	CRACKED         	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										FIVE B-3493 START LOCK BRACKETS WERE FOUND DURING PENETRANT INSPECTION TO BE CRACKED AT THE SAME LOCATION. CRACKS ARE LO	CATED ON THE EXTERIOR START PIN BORE NEXT TO THE SPINNER MOUNTING BOLT RELIEF CUT-OUT. THIS BRACKET IS PART OF THE 830-3	4L START LOCK UNIT INSTALLED ON 4-BLADED MU-2S.				1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
2007100200024	20071002	00024	CE  	2007	10	2	RDA092407        	1	20070924	G	2842	05235571	TRANSMITTER     			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					FUEL QTY	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	9456B	2440 				55256				WHILE CALIBRATING THE FUEL QUANTITY SYSTEM THE LT FUEL GAUGE WOULD SHOW AN INCREASE IN QUANTITY THEN START DECREASING.  	WHILE TROUBLESHOOTING THE LT TANK FUEL QUANTITY SENDER, FOUND 2 CRACKS APPROXIMATELY 1 INCH LONG IN THE BRASS FLOAT.					1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2007062700005	20070627	00005	CE  	2007	6	27	RUAGACC61007     	1	20070610	G	3210	16410077	SPRING          			CESSNA	188   	T188C       	2073012	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT MLG	FAILED          	G			RUAG	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NM	05	2535J	7163 	181  			T18803471T				AIRCRAFT ACCIDENT.  LT MLG (SPRING) FAILED DURING TAKEOFF ATTEMPT, APPROXIMATELY 6 INCHES ABOVE AXLE.  NO EVIDENCE OF PR	EVIOUS FRACTURE (CRACK) COULD BE DETECTED.  LT WING BUCKLED AND AIRCRAFT NOSED OVER.  SUBSTANTIAL DAMAGE, NO INJURIES.					1	L	7	1 	3O	3	O		A9CE    	E8CE				 
2007121300378	20071213	00378	EU  	2007	12	13	S0700432         	1	20071203	G	2435		COMMUTATOR      	BFGOODRICH  		PILATS	PC12  	PC1245      	7090551	EU  										STARTER GEN	FAILED          	B				B	A			EMER. DESCENT           	UNSCHED LANDING         			H	E		ELECT. POWER LOSS-50 PC   	VIBRATION/BUFFET          		CR	CRUISE         	1			CE	07	462PC				97102	462				DURING CRUISE FLIGHT, LOUD NOISE FROM ENGINE COMPARTMENT FOLLOWED BY VIBRATION AND LOSS OF PRIMARY ELECTRICAL POWER.  UP	ON INSPECTION, ONE SEGMENT FROM COMMUTATOR WAS MISSING AND AFT END OF GENERATOR AND BRUSHES HAD SUSTAINED HEAVY DAMAGE. 	 AFTER REPLACEMENT WITH OVERHAULED UNIT, NO ABNORMALITIES WERE NOTED.				1	L	7	1 	3T			RT	A78EU   					 
2007022700071	20070227	00071	SO  	2007	2	27	SDR0701          	1	20070123	G	5312	1159B2156227	ANGLE           			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					BS 793	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	29	254GA	11823				1032				DURING SCHEDULED 5000 LANDING FS793 BULKHEAD CAP ANGLE NDT INSPECTION, DETECTED A 1.25 INCH LONG CRACK IN RT BULKHEAD CA	P ANGLE. MANUFACTURER HAS RECOMMENDED REPLACEMENT OF LT AND RT FS793 BULKHEAD CAP ANGLES.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2007021300080	20070213	00080	CE  	2007	2	13	SO19200712477    	1	20070126	G	3297		WIRE            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					WARNING HORN	BROKEN          	C				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			SO	19	177RR					177RG0937				DURING THIRD NIGHT CURRENCY LANDING PILOT FAILED TO EXTEND GEAR AND DIDN'T HEAR THE GEAR UP WARNING HORN.  SHOWING A BRO	KEN WIRE AT THE GEAR WARNING HORN SWITCH.					1	H	7	1 	3O	3	O		A20CE   	1E10				 
2007012500157	20070125	00157	NM  	2007	1	25	SROM200700001    	1	20070105	G	2120	65544709	DUCT            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D15      	52051	NE  					A/C PACK	RUPTURED        	I			SROM	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AL	03	245US					22751				UPON TAKEOFF A POP WAS WAS HEARD FOLLOWED BY PERCEIVED SMOKE (DUST) IN THE CABIN.  PACS WERE SELECTED TO OFF AND A IMMED	IATE LANDING MADE AT THE DEPARTURE AIRPORT.  ALL COCKPIT INDICATIONS NORMAL.  FOUND LT AIR CONDITIONING PAC MIXING CHAMB	ER AND HOT AIR SUPPLY DUCT SEPARATED/ DAMAGED ALLOWING HOT CONDITIONED AIR TO ENTER CABIN THROUGH RETURN GRILLS, THUS CR	EATING DUST.  APPEARS TO HAVE EXPERIENCED INTERNAL DAMAGE RESULTING IN BACK PRESSURE WHICH CAUSED THE DUCT/FLANGE FAILUR	E.  NO OTHER DAMAGE NOTED.  REPLACED MIXING AND HOT AIR DUCTS.		2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2007061400143	20070614	00143	NM  	2007	6	14	SROM200700002    	1	20070516	G	5280		DOOR            			BOEING	737   	737205      	1384456	NM  										NLG	BINDING         	C			SROM	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AL	03	736BP					23465				LOUD VIBRATION AFTER TAKEOFF.  VIBRATION INCREASED WITH SPEED AND DECREASED AT LOWER SPEEDS.  RETURNED TO DEPARTURE AIRP	ORT.  PERFORMED VIBRATION CONDITIONAL INSPECTION.  FOUND NLG DOORS ON GRAVEL SKI EQUIPPED AIRCRAFT TO BE BINDING ON EACH	 OTHER.  ADJUSTED PER AMM 32-22-12.  AIRCRAFT RELEASED AN OPERATIONAL CHECK FLIGHT NORMAL.  NO REPORT OF VIBRATION ON SU	BSEQUENT FLIGHTS.			2	L	7	2 	4F			RT	A16WE   					 
2007061300244	20070613	00244	NM  	2007	6	13	SROM200700003    	1	20070522	G	5753		BEARING         			BOEING	737   	737205      	1384456	NM  										ROD END	LOOSE           	C			SROM	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AL	03	736BP					23465				AIRFRAME BUFFET NOTED AFTER GEAR UP ON TAKEOFF & BEFORE FLAP RETRACTION & POWER REDUCTION DURING CLIMB.  THIS IS THE 2ND	 WRITE UP OF THIS CONDITION.  PERFORMED AIRFRAME CONDITIONAL INSPECTION.  REPLACED NLG GRAVEL SKI DEFLECTOR ACTUATOR DUE	 TO LOOSE ROD END AND REPLACED BEARING IN LEFT INBOARD GROUND SPOILER OUTBOARD ACTUATOR LINKAGE DUE TO LOOSENESS.  AIRCR	AFT RELEASED FOR OPERATION CHECK FLIGHT WITH NO REPORTS OF VIBRATION ON TWO TAKEOFFS DURING CHECK FLIGHT.			2	L	7	2 	4F			RT	A16WE   					 
2007061400179	20070614	00179	NM  	2007	6	14	SROM200700004    	1	20070531	G	2120	28410	VALVE           			BOEING	737   	737205      	1384456	NM  										FLOW CONTROL	FLUTTER         	C			SROM	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AL	03	736BP		7463 			23465				AFTER TAKEOFF AT AROUND 1000 FEET VIBRATION STARTED IN FWD PART OF AIRCRAFT AND TRAVELED TO REAR OF AIRCRAFT.  AFTER SHU	TTING OFF ALL PACKS AND BLEEDS IT SLOWLY WENT AWAY.  AIRCRAFT RETURNED TO DEPARTURE AIRPORT.  AIRCRAFT INSPECTED WITH NO	 FAULTS FOUND AND RELEASED FOR FLIGHT TO MAINTENANCE BASE WITH SLIGHT VIBRATION NOTED IN FLOOR.  FURTHER INSPECTION FOUN	D CRACKED E&E BAY COOLING DUCT AND CHATTERING E&E BAY FLOW CONTROL VALVE.  REPLACED DUCTS AND VALVE.  NO REPORTS OF VIBR	ATION ON SUBSEQUENT FLIGHT.		2	L	7	2 	4F			RT	A16WE   					 
2007082400323	20070824	00323	NM  	2007	8	24	SROM200700006    	1	20070801	G	5311		FRAME           			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					BS 616	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR63-CRACK ON BODY FRAME INNER CHORD BS616 RT SIDE AT STUB BEAM LOWER CHORD ATTACH (ABOVE WING BOX BL64R). DAMAGE OF BOD	Y FRAME INNER CHORD STA 616 RT SIDE AT STUB BEAM LOWER CHORD ATTACH REMOVED IAW MFG SB 737-53-1182R1. REPAIR ANGLE INSTA	LLED IAW MFG SB 737-53-1182R1 AND MFG MSG NR: 1-508321689-2.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007090600068	20070906	00068	NM  	2007	9	6	SROM200700007    	1	20070807	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					BS 660	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR228-CRACK IN FLOORBEAM AND WEB STA 660 BL0. CRACKED FLOORBEAM AND WEB AT STA 660 BL0 REPAIRED IAW MFG SB 737-57-1210, 	REV 1, DATED AUG 27/07.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091700005	20070917	00005	NM  	2007	9	17	SROM200700008    	1	20070808	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					BS 900 S17-18L	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR247- DENT FOUND STA 900 LT BETWEEN STRINGERS 17 AND 18. REPAIRED IAW MFG SRM 53-30-3, PAGES 253-320 AND 51-30-3, PAGE 	7 AND 51-30-02.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091300062	20070913	00062	NM  	2007	9	13	SROM200700009    	1	20070808	G	3211		SUPPORT FITTING 			BOEING	737   	737205      	1384456	NM  										RT MLG	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR269 - WEAR DAMAGE RIGHT MAIN LANDING GEAR FUSE TO TRUNNION SUPPORT BEAM ATTACH FITTING.  REPAIRED IN ACCORDANCE WITH B	OEING APPROVED FAA FORM 8100-9 MESSAGE 1-515849678-6, DATED AUGUST 23, 2007.					2	L	7	2 	4F			RT	A16WE   					 
2007091300146	20070913	00146	NM  	2007	9	13	SROM200700010    	1	20070808	G	5743	65C313326	SUPPORT BEAM    			BOEING	737   	737205      	1384456	NM  										RT MLG	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR270 - PITTING RIGHT MAIN LANDING GEAR TRUNNION SUPPORT BEAM UPPER SURFACE.  REPLACED RIGHT MLG SUPPORT BEAM IN ACCORDA	NCE WITH BOEING 737 AMM 57-15-0.					2	L	7	2 	4F			RT	A16WE   					 
2007091300147	20070913	00147	NM  	2007	9	13	SROM200700011    	1	20070808	G	5743	658276415	SUPPORT BEAM    			BOEING	737   	737205      	1384456	NM  										LT MLG	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR279 - PITTING LEFT MAIN LANDING GEAR TRUNNION SUPPORT BEAM UPPER SURFACE (LIGHT).  REPLACED LEFT MLG SUPPORT BEAM IN A	CCORDANCE WITH BOEING 737 AMM 57-15-0.					2	L	7	2 	4F			RT	A16WE   					 
2007091700021	20070917	00021	NM  	2007	9	17	SROM200700012    	1	20070808	G	5343		TRUNNION        			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT MLG	WORN            	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				WEAR DAMAGE, LT MLG FUSELAGE TO TRUNNION SUPPORT BEAM ATTACH FITTING. BLEND REPAIRED IAW MFG, FORM 8100-9, MESSAGE NR 1-	515849678-6, DATED AUGUST 23, 2007.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091300063	20070913	00063	NM  	2007	9	13	SROM200700013    	1	20070808	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR291 - CORROSION ON FLOORBEAM UPPER FLANGE STA 344 LBL 48-60.  REPAIRED IN ACCORDANCE WITH BOEING SRM 53-10-9, FIGURE 1	.					2	L	7	2 	4F			RT	A16WE   					 
2007090600085	20070906	00085	NM  	2007	9	6	SROM200700014    	1	20070810	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					ZONE 100	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR296-CORROSION ON FLOORBEAM UPPER FLANGE AT STA 294 AND RBL 43 TO 53. FLOORBEAM UPPER FLANGE FROM RBL 6 (EXISTING SPLIC	E) TO RBL 60, STA 294 REMOVED AND REPLACED IAW WITH MFG SRM 53-10-9, FIG 5, SHEET 1-5.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091400101	20070914	00101	NM  	2007	9	14	SROM200700015    	1	20070810	G	5512		SKIN            			BOEING	737   	737205      	1384456	NM  										HORIZONTAL STAB	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR378 - RT STABILIZER LOWER SURFACE FOUND WITH A GOUGE IN THE SKIN ON THE RIB ATTACH LOCATION AT 138.7 DEPT IS 0.037 WHI	CH IS OVER 50 PERCENT.  DAMAGED SECTION OF SKIN ON RT STABILIZER LOWER SURFACE LOCATION 138.7 REMOVED.  REPAIR DOUBLER F	ABRICATED AND INSTALLED IN ACCORDANCE WITH DER APPROVED DRAWING NR 73R55116228.				2	L	7	2 	4F			RT	A16WE   					 
2007091300148	20070913	00148	NM  	2007	9	13	SROM200700016    	1	20070810	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR393 - FUSELAGE SKIN CRACKED AT AIRSTAIR CONTROL HANDLE CUTOUT AT BS 378 BETWEEN STRINGERS 21-L AND 22-L.  REPAIR DOUBL	ER FABRICATED AND INSTALLED IN ACCORDANCE WITH BOEING SB 737-53-1093.					2	L	7	2 	4F			RT	A16WE   					 
2007091300149	20070913	00149	NM  	2007	9	13	SROM200700017    	1	20070810	G	5343		SUPPORT BEAM    			BOEING	737   	737205      	1384456	NM  										NLG	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR419 - CRACK ON NLG ACTUATOR SUPPORT BEAM AT BS 227-0 UPPER RIGHT SIDE.  REPLACED NLG ACTUATOR UPPER RIGHT SIDE SUPPORT	 BEAM IN ACCORDANCE WITH BOEING 737 SRM 51-10-1, 53-10-2 AND 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2007090600075	20070906	00075	NM  	2007	9	6	SROM200700018    	1	20070818	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					BS 907	NICKED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NICK STA 907 STR 22 LT. NICK AT STA 907, STR 22L REPAIRED IAW SRM 53-30-3, FIG 48. NICK BEYOND LIMITS AND DAMAGE REMOVED	. HFEC IAW NDT PART 6, 53-30-00, FIG 4 OF REPAIR AT FUSELAGE SKIN STA 907 STR 22L. NO CRACKS EVIDENT.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007090600001	20070906	00001	NM  	2007	9	6	SROM200700019    	1	20070818	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					ZONE 100	NICKED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NICK STA 887 STR 24L-25L LT.  DAMAGED AREA OF SKIN REMOVED AND REPAIR PLATES FABRICATED IAW SRM 53-30-3, FIG 48. INSTALL	ED REPAIR IAW 51-30-2.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007090600071	20070906	00071	NM  	2007	9	6	SROM200700020    	1	20070818	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					ZONE 100	NICKED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NICK STA 847 STR 21 LT.  NICK AT STA 847 STR 21L FOUND TO BE BEYOND LIMITS. NICK REMOVED AND AREA AT STA 847 STR 21L REP	AIRED IAW SRM 53-30-3, FIG 48.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007090600079	20070906	00079	NM  	2007	9	6	SROM200700021    	1	20070810	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  	PWA   	PT6   	PT6A114A    	52043	NE  					BS 328	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR392-CORROSION ON UPPER CHORD OF FLOORBEAM STA 328 RBL 52. FLOORBEAM REPAIRED IAW SRM 53-10-9, FIG 5, PAGE 21.						2	L	7	2 	4F	3	T	RT	A16WE   	E4EA				 
2007090600066	20070906	00066	NM  	2007	9	6	SROM200700022    	1	20070803	G	5311		FRAME           			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					BS 783 S25R	CORRODED        	I			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR145-LIGHT CORROSION ON FRAME AT STA 783 STR 25R. REPAIRED FRAME IAW MFG MESSAGE NR 1-518342007-2, DATED AUG 1, 2007 AN	D PRODUCTION DRAWINGS FOR PN 65-47959-47 STRAP AND PN 65C31240-1 FRAME DOUBLER.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091700046	20070917	00046	NM  	2007	9	17	SROM200700023    	1	20070807	G	5524		NUT PLATE       	BOEING      		BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ELEVATOR	STRIPPED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	982  			457	23465				NR122-LT ELEVATOR TRIM TAB IB HINGE FITTING MISSING BOLT.  NEW ELEVATOR INSTALLED 12/06/06, 982 TT, 717 TC.  (2) OUT OF 	(4) HINGE ATTACH FITTING NUTPLATES STRIPPED FROM THE FACTORY. REPLACED NUTPLATES IAW SRM 51-30-2, FIGURES 3 AND 7.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091300064	20070913	00064	NM  	2007	9	13	SROM200700024    	1	20070815	G	4910		INTAKE DUCT     			BOEING	737   	737205      	1384456	NM  										APU	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	38551				23465				NR481 - CORROSION AROUND AIR INLET DUCT FLANGE APU TORQUE BOX WEB BS 1064 RIGHT HAND SIDE.  REPLACED AIR INLET DUCT FLAN	GE IN ACCORDANCE WITH BOEING SRM 51-10-1, PAGE 8, 51-30-2, FIGURES 11, 12, 13, AND 51-30-6, FIGURE 3.					2	L	7	2 	4F			RT	A16WE   					 
2007101600051	20071016	00051	NM  	2007	10	16	SROM200725       	1	20071005	G	8097		WIRE            			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					START SWITCH	BURNED          	C			SROM	A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AL	03	736BP	38641			NSN	23465				DURING CLIMB SPARKS AND SMOKE EMITTED FROM THE AREA OF THE NR 1 START SWITCH. LOW IGNITION CB POPPED AT WHICH TIME THE S	PARKS AND SMOKE CEASED. FLIGHT CREW RETURNED TO THE DEPARTURE AIRPORT FOR AN UNEVENTFUL LANDING. REPLACED SWITCH DUE TO 	ARCING ON CASE AND REPAIRED WIRING. INSPECTED OTHER AIRCRAFT IN FLEET NO OTHER CHAFED WIRES FOUND IN VICINITY OF THE STA	RT SWITCHES.			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2007091800096	20070918	00096		2007	9	18	STS001           	4	20070914	G	2564	1116FAUL33011	LIFE RAFT       																		ACTIVE          	B				K				NONE                    				L			NO TEST                   			NR	NOT REPORTED   	1			SO	15	WL7R									LIFE RAFT (APPLIANCE, CAT II) SERVICED 10/19/2005 (SMER451X) THE 406 MHZ ELT NOT TIED TO BOARDING LADDER IAW MANUAL.  EL	T WOULD NOT HAVE SELF-DEPLOYED TO ALERT SAR, AS REQUIRED BY CMM 25-60-101, REVISION E																		 
200805141    	20080514	1    	NE  	2008	5	14	SWDG20080016     	2	20070318	G	7250	310718501	GAS GENERATOR   			AIRTRC	AT802 	AT802A      	0390308	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	ERODED          	D			SWDG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	803DG	4731 	550  			802A0077	PCERD0016			BROKEN 'T' HEAD BOLT SHANK FOUND IN COWLING.  MANUFACTURER REP VISITED AND TOOK PICTURES OF ERODED GAP IN THE 'C' FLANGE	 AT THE SCAVENGE TUBE COUPLING LOCATION WHERE THE BOLT HAD BEEN SEVERED.  THE DAMAGE TO THE BOLT, FLANGE MATING SURFACES	 AND COUPLING ARE CLEARLY NOT THE RESULT OF CORROSION BECAUSE THE SURFACES IN THE AREAS OF DAMAGE ARE CLEAN AND HAVE AN 	ALMOST POLISHED APPEARANCE.  SIMILAR ENGINES HAVE A SEALING RING INCORPORATED INTO THE FLANGE APPARENTLY FOR THIS VERY R	EASON.  THE MANUFACTURER REPS HAVE STATED THAT THIS EROSION IS UNEXPLAINED AND THEREFORE IS NOT A SAFETY OF FLIGHT ISSUE	.  THE MACHINING OF THE FLANGES AND INSTALLATION OF SEALING RING WOULD BE A START FOR REPAIRS, AND THE SOLUTION WOULD BE	1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
200805141    	20080514	1    	NE  	2008	5	14	SWDG20080024     	2	20070319	G	7250	310718501	GAS GENERATOR   			AIRTRC	AT802 	AT802A      	0390308	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	ERODED          	D			SWDG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	804DG	3129 	3129 			802A0089	PCERD0024			ENGINE REMOVED FOR OVERHAUL EVALUATION. DUE TO THE FINDING OF SEVERE EROSION DAMAGE TO THE 'C' FLANGE AND NUMEROUS BROKE	N 'T' BOLTS ON 3 OTHER ENGINES, THE DISSASSEMBLED EXHAUST DUCT AND GAS GENERATOR CASE FLANGES HAVE BEEN PHOTOGRAPHED AND	 FOUND THAT THIS 4TH ENGINE SUFFERS FROM SIMILAR DAMAGE.  IT SHOULD BE NOTED THAT THE MANUFACTURER HAS BEEN NOTIFIED AND	 THAT THEIR REP HAS TAKEN PICTURES OF THE DAMAGED ENGINES AND HAS TOLD US THAT THE BROKEN BOLTS, 'C' FLANGE DAMAGE, AND 	P3 AIR LEAKAGE ONTO THE OIL TUBES ARE NOT SAFETY OF FLIGHT ISSUES.  IT IS SUGGESTED THAT THE MANUFACTURER IMPLEMENT WARR	ANTY PROVISIONS FOR THE INCORORATION OF A SEALING RING ON THE -67AG JUST LIKE SIMILAR ENGINES IN THE FAMILY.	1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
200805141    	20080514	1    	NE  	2008	5	14	SWDG20080077     	2	20070319	G	7250	310718501	GAS GENERATOR   			AIRTRC	AT802 	AT802A      	0390308	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	ERODED          	D			SWDG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	803DG	1800 	1800 			802A0077	PCERD0077			AS THE 'T' HEAD BOLTS WERE BEING REMOVED FOR HSI, ONE NUT DETACHED FROM THE BOLT SHANK WITH THE THREAD INSIDE THE NUT.  	CLOSE INSPECTION OF THE ADJACENT BOLT REVEALED SEVERE EROSION (NOT CORROSION OR STRETCH DAMAGE) TO THE BOLT SHANK.  IT W	AS FURTHER NOTED AND PHOTOGRAPHED BY THE MANUFACTURER REP THAT THE EXHAUST DUCT FLANGE AND GAS GENERATOR FLANGE IN THE B	ROKEN BOLT AREA HAD MATERIAL LOSS THAT WAS ALLOWING P3 AIR LOSS THAT MAY BE ATTRIBUTED TO THE HIGHER THAN NORMAL OIL TEM	P INDICATION ON THE GROUND.  THE AIR LEAK IS VENTING ONTO THE SCAVENGE OIL TUBE COUPLING.  MANUFACTURER REPS SAY THAT TH	IS IS AN ISOLATED CASE AND IS NOT A SAFETY OF FLIGHT ISSUE AS THAT THERE ARE MANY MORE BOLTS THAT HOLD 'C' FLANGE TOGETH	1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
200805141    	20080514	1    	NE  	2008	5	14	SWDG20080113     	2	20070319	G	7250	310718501	GAS GENERATOR   			AIRTRC	AT802 	AT802A      	0390308	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	ERODED          	D			SWDG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	804DG	346  	346  			802A0089	PCERD0113			ENGINE PARAMETERS ABNORMAL AND SUBSIQUENT INSPECTION FOUND T5 HARNESS DAMAGED AT ASSEMBLY.  IT WAS FURTHER NOTED THAT SU	BSTANTIAL MATERIAL LOSS IN THE CENTER BOLT HOLE @ THE SCAVENGE TUBE COUPLING WAS ALLOWING COMPRESSOR AIR TO ERODE THE 'T	' BOLT SHANK.  MANUFACTURER REP TOOK PICTURES OF DAMAGE AS NOTED ON NOVEMBER 22, 2006 AND HAS YET TO OFFER SUGGESTED CAU	SE OR REPAIR SCHEME.  THE "WITNESS" MARK OF SURFACE CONTACT OF THE 'C' FLANGES INDICATE NON-UNIFORM ALIGNMENT AXIALY OF 	THE FLANGE WELDED TO THE CASE.  THE MANUFACTURER REPS HAVE FURTHER COMMENTED THAT P3 AIR LEAKAGE IS NOT A SAFETY OF FLIG	HT ISSUE AND THAT FLANGE DAMAGE AND BOLT DAMAGE OR LOSS IS NOT A SAFETY OF FLIGHT ISSUE.	1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008011400042	20080114	00042	CE  	2008	1	14	T4OR4765001      	1	20071221	G	5210	5043004315	LEVER           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					CABIN DOOR	TWISTED         	B			T4OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	63	240CT	7199 				BB1063				WHILE TRYING TO RIG THE CABIN DOOR UPPER LATCH HOOKS FOR PROPER OVERCENTER, IT WAS FOUND PROPER OVERCENTER COULD NOT BE 	OBTAINED WITHOUT THE ADJUSTING ROD END WITNESS HOLES BEING EXPOSED.  CLOSER EXAMINATIONS SHOWED THE FWD AND AFT DOOR ACT	UATION LEVER ASSEMBLIES, PN 50-430043-15 (FWD) AND 50-430043-17 (AFT) WERE TWISTED, CHANGING THE RELATIVE ANGLE BETWEEN 	THE LATCH HOOK AND ROD END ATTACH POINT.  NORMALLY THE ANGLES BETWEEN THE LATCH HOOK AND LATCH ROD ATTACH POINT IS ABOUT	 90 DEGREES.  THE PARTS IN THIS DOOR WERE SOMEWHAT LESS THAT 90 DEGREES, CLOSER TO 75 DEGREES DUE TO THE TWIST.  WITH TH	IS CONDITION, THE PUSHROD FOR THE UPPER HOOK OVERCENTER ADJUSTMENT WOULD NEED TO BE EXTENDED FARTHER THAN DESIGNED, EXPO	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007120400234	20071204	00234	EU  	2007	12	4	T9NR200700001    	1	20071106	G	3246	315182	WHEEL           			AEROSP	ATR42 	ATR42*      	8680900	EU  										MLG	CRACKED         	B			TL9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										OUR SHOP REPORTS THE PRESENCE OF AN UNUSUAL CRACK ON THIS WHEEL. IT LIES BETWEEN THE WHEEL'S LIGHTING HOLES (WEB), AND I	S COMPLETELY CRACKED BETWEEN ADJACENT LIGHTING HOLES. THE WHEEL ASSEMBLY PN IS NOTED BELOW, BUT THE CRACK EXHIBITED ITSE	LF ON THE WHEEL HALF PN 300-824/10-1606				2	H	7	2 	4T			RT	A53EU   					 
2007120400235	20071204	00235	EU  	2007	12	4	T9NR200700002    	1	20071106	G	3246	315182	WHEEL           			AEROSP	ATR42 	ATR42*      	8680900	EU  										ZONE 700	CRACKED         	B			T9NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										OUR SHOP REPORTS THE PRESENCE OF AN UNUSUAL CRACK ON THIS WHEEL. IT LIES BETWEEN THE WHEEL'S LIGHTING HOLES (WEB), AND I	S COMPLETELY CRACKED BETWEEN ADJACENT LIGHTING HOLES. THE WHEEL ASSEMBLY PN IS NOTED BELOW, BUT THE CRACK EXHIBITED ITSE	LF ON THE WHEEL HALF PN 300-824/10-1606				2	H	7	2 	4T			RT	A53EU   					 
2008011100158	20080111	00158	CE  	2008	1	11	TAS07003         	1	20071116	G	3233	1FA100433	CAP             			BEECH 	1900  	1900        	1154160	CE  										MLG ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05		11943			1209B					MLG ACTUATOR WAS RECEIVED DUE TO INDICATIONS FOUND IN THE END CAP DURING ULTRASONIC TESTING.  ACTUATOR WENT THROUGH A PR	ELIMINARY INSPECTION AND A COMPLETE FUNCTIONAL TEST WITH NO EXTERNAL EVIDENCE OF LEAKING OR CRACKING.  AFTER DISASSEMBLY	, A CRACK IN THE INTERNAL RADIUS OF THE END CAP WAS CONFIRMED BY A FLUORESCENT PENETRANT INSPECTION.				2	L	7	2 	4T			RT	A24CE   					 
2007041200024	20070412	00024	EU  	2007	4	12	THMN4346176      	1	20070410	G	5340		ATTACH BRACKET  			AMD   	FALC10	FALCON10    	2730101	EU  										RT NLG DOOR	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	101HS					82				RT NOSE LANDING GEAR DOOR ATTACH POINT IN THE RT NOSE COMPARTMENT HAS 2 EA CRACKS AT FRAME C.  MADE AIRWORTHY REPAIR IAW	 SRM 51-20-02-0, 51-40-11, AND 51-40-13.					2	L	7	2 	4F				A33EU   					 
2007041200025	20070412	00025	EU  	2007	4	12	THMN4346177      	1	20070410	G	5340		ATTACH BRACKET  			AMD   	FALC10	FALCON10    	2730101	EU  										LT NLG DOOR	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	101HS					82				LT NOSE LANDING GEAR DOOR ATTACH POINT IN THE LT NOSE COMPARTMENT HAS 2 EA CRACKS AT FRAME C.  MADE AIRWORTHY REPAIR IAW	 SRM 51-20-02-0, 51-40-11, AND 51-40-13.					2	L	7	2 	4F				A33EU   					 
2007041200026	20070412	00026	EU  	2007	4	12	THMN4346179      	1	20070410	G	5320		SPLICE PLATE    			AMD   	FALC10	FALCON10    	2730101	EU  										FUSELAGE	CRACKED         	B			T0DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	101HS					82				SPLICE PLATE ON RT SIDE OF CABIN AT FRAME 13 JUST BELOW WINDOW LINE CRACKED.  MADE AIRWORTHY REPAIR IAW SRM 51-00-01 FIG	. 201 AND 51-40-11.					2	L	7	2 	4F				A33EU   					 
2007061400144	20070614	00144	CE  	2007	6	14	TIMR20070003     	1	20070521	G	3233	998201233	ACTUATOR        			BEECH 	99    	B99         	1154004	CE  										NLG DOOR	SEPARATED       	E			TIMA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	07	950AA	388  				U159				DURING CRUISE, PILOT HEARD A CLUNK AND THE -GEAR IN TRANSIT- LIGHT CAME ON.  RETURNED TO AIRPORT, PERFORMED FLY-BY WHICH	 CONFIRMED NOSE GEAR HANGING OUT BUT NOT FULLY EXTENDED.  NOSE GEAR COLLAPSED ON LANDING.  INVESTIGATION REVEALED THAT T	HE ACTUATOR SHAFT HAD SHEARED JUST ABOVE THE CLEVIS BOLT CONNECTING TO THE DRAG BRACE.				1	L	7	2 	3T				A14CE   					 
2007113000179	20071130	00179	CE  	2007	11	30	TIMR20070008     	1	20071031	G	3230		SWITCH          			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6*        	52043	EA  					POWER LEVER	INOPERATIVE     	B			TIMA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	07	899CA					U104				GEAR-IN-TRANSIT LIGHT DID NOT EXTINGUISH AFTER TAKE-OFF AND GEAR UP. PILOT CYCLED GEAR AGAIN WITH SAME RESULT.  PILOT RE	TURNED TO DEPARTURE AND LANDED.  MECHANIC FOUND THAT THE LT POWER LEVER SWITCH HAD FAILED.  REPLACING THE SWITCH RESOLVE	D THE PROBLEM.				1	L	7	2 	3T	3	T		A14CE   	E2NE				 
2007120400297	20071204	00297	CE  	2007	12	4	TIMR20070009     	1	20070928	G	3233	993880011	ACTUATOR        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG	CRACKED         	B			TIMA	A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			NM	07	4381Y		961  			U71				AFTER SELECTING GEAR DOWN ON APPROACH, THE PILOT NOTICED THAT HE DID NOT HAVE A GREEN (SAFE) INDICATION FOR THE NOSE GEA	R.  HE FOLLOWED THE EMERGENCY PROCEDURE TO PUMP THE GEAR DOWN BUT WAS UNABLE TO BUILD UP PRESSURE OR GET A GREEN LIGHT. 	PILOT THEN LANDED AND THE NOSE GEAR COLLAPSED.  INVESTIGATION FOUND THAT THE LT MAIN GEAR ACTUATOR END CAP HAD CRACKED A	ND ALLOWED THE EMERGENCY SYSTEM FLUID TO VENT OVERBOARD, PREVENTING THE NOSE ACTUATOR FROM EXTENDING FULLY.			1	L	7	2 	3T	3	T		A14CE   	E2NE				 
2007050700190	20070507	00190	EU  	2007	5	7	TL9R200700001    	1	20070501	G	3240	C200601004	BRAKE           			AIRBUS	330   	A300*       	       	EU  										MLG	MAKING METAL    	B			TL9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										BRAKE ROTORS DE-LINED (STARTED TO FALL APART) IN OPERATION.						2	L	7	2 	4F			RT	A26NM   					 
2007071200133	20070712	00133	NE  	2007	7	12	UE5R02           	2	20070705	G	7210	310825401	GEARBOX         			AIRTRC	AT602 	AT602       	0390309	SW  	PWA   	PT6   	PT6A60      	52043	NE  						CORRODED        	B			UE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61							PSRG0056			PT6A-60AG REDUCTION GEAR REAR HOUSING P/N 3106854-01 HAS SEVERE CORROSION ON OUTER SURFACE OF HOUSING. DEEP PITTING, SOM	E AREAS UP TO .125 INCH DEEP. CORRODED AREAS EXTEND THE ENTIRE CIRCUMFERENCE OF HOUSING, PRIMARILY NEXT TO MATING FLANGE	 FOR FWD HOUSING.				1	L	7	1 	3T	4	T	NC	A19SW   	E4EA				 
2007091700071	20070917	00071	EA  	2007	9	17	UE5R04           	2	20070911	G	7250	T102401100	BLADES          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					TURBINE SECTION	CRACKED         	B			UE5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	61										DURING STRETCH CHECK OF TURBINE BLADES P/N T102401-100, FLUORESCENT PENETRANT INSPECTION WAS PERFORMED.  THIS INSPECT RE	VEALED SEVERAL BLADES WITH CRACKS ALONG TRAILING EDGE. THESE CRACKS IN THE DIRECTION OF THE CHORD OF THE BLADE.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2007041600052	20070416	00052	NE  	2007	4	16	UE5R1            	2	20070402	G	7230	3023401	BLADE           	PWC         		BEECH 	100   	100BEECH    	1152916	CE  	PWC   	PT6   	PT6A67AG    	52211	NE  					COMPRESSOR DISC	CRACKED         	B			UE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61					7P070					COMPRESSOR TURBINE DISC BLADE FAILURE. SINGLE BLADE IN COMPRESSOR TURBINE DISC CRACKED IN FUR TREE AREA OF BLADE. CAUSED	 MISALIGNMENT OF CT BLADE AND SUBSEQUENT RUB ON SHROUD SEGMENTS. THE CRACK IN FIR TREE WAS NOT VISIBLE WITH ENGINE SPLIT	 IF PERFORMING A ROUTINE INSPECTION, HOWEVER BLADE MISALIGNMENT AND RUB WERE VISIBLE. THE BLADE CRACK BECAME VISIBLE WHE	N CT DISC ASSY WAS REMOVED FROM ENGINE.			1	L	7	2 	3T	4	T		A14CE   	E26NE				 
2007081700096	20070817	00096	SW  	2007	8	17	WGEA200700001    	1	20070803	G	2752	EM41165	ACTUATOR        			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										T/E FLAPS	MALFUNCTIONED   	C			WGEA	K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			EA	27	109DJ	205  	205  			000006				FLAP FAIL CAS MESSAGE IN FLIGHT.  REMOVED AND REPLACED LT AND RT INBOARD FLAP ACTUATORS PER EA 500 AM CH 27-51-11.  RIGG	ED FLAP`S AND COMPLIED WITH SATISFACTORY FUNCTIONAL/OPERATIONAL CHECKS.					1	L	7	2 	4J			RT	A00002AC					 
2008011100136	20080111	00136	CE  	2008	1	11	WSA12262007      	1	20071226	G	1400	998100611	BOLT            			BEECH 	200   	200BEECH    	1152920	CE  										MLG	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	1558					BC20				HAVE ORDERED FROM MFG THE LANDING GEAR DRAG LEG BOLTS TWICE AND HAVE RECEIVED (2) DEFECTIVE BOLTS EACH TIME. THE COTTER 	PIN HOLE WAS MISDRILLED AND WOULD COULD NOT GET THE HOLES TO LINE UP WITH THE NUT CASTELLATION. (2) OF THE BAD BOLTS WER	E DATE TAGGED 12/2/2006. THE ACTUAL BOLT MANUFACTURER IS UNKNOWN ALTHOUGH THEY WERE SOURCED FROM AC MFG. IT IS BELIEVED 	THAT AC MFG HAS PULLED THESE FROM THEIR INVENTORY AFTER OUR PROBLEM.			1	L	7	2 	4T				A24CE   					 
2007080800063	20070808	00063	EU  	2007	8	8	WTU0701          	1	20070719	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	SEIZED          	B			R8RR	A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			WP	07	5204Y	10   	10   			3101	9782			WHILE CONDUCTING A SEARCH OVER MOUNTAINOUS TERRIAN AT NIGHT UTILIZING AN SX-5 SEARCHLIGHT, TEN MINUTES INTO THE SEARCH L	IGHT QUIT WORKING.  APPROXIMATELY 30 SECONDS LATER THE GENERATOR FAIL LIGHT ILLUMINATED AND THE CREW SMELLED SMOKE IN TH	E COCKPIT.  APPROXIMATELY 30 SECONDS LATER THE FIRE LIGHT ILLUMINATED.  THE PILOT IMMEDIATELY EXCEUTED EMERGENCY PROCEDU	RES BY TURNING OFF THE GENERATOR AND LAND AS SOON AS PRACTICAL.  AFTER THE PILOT LANDED AND SHUTDOWN THE AIRCRAFT THEY E	XITED AND SAW SMOKE COMING OUT OF THE STARTER GENERATOR COOLING DUCT TUBE.  THE CREW OPENED THE ENGINE COWLING AND THERE	 WAS NO FIRE BUT EVIDENCE THAT THERE MAY HAVE BEEN ONE INSIDE THE S/G.  UPON REMOVAL THE S/G HAD A SHEARED SHAFT IT WAS 	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007090600020	20070906	00020	EU  	2007	9	6	WTU0702          	1	20070828	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	INOPERATIVE     	B			R8RR	A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			WP	07	455AE	15   	15   			3509	9576			WHILE CONDUCTING A ROUTINE PATROL AT NIGHT THE GENERATOR FAILED AND WOULD NOT RESET.  ALL NON ESSENTIAL EQUIPMENT WAS SH	UTOFF AND THE PILOT RETURNED TO BASE UTILIZING BATTERY BUSS POWER WITHOUT FURTHER INCIDENT.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2007061200149	20070612	00149	NE  	2007	6	12	Y4MR200700521    	2	20070521	G	7200	PT6A135	ENGINE          			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					RIGHT	MAKING METAL    	B			W1MA	E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	09	89CA	6546 	3399 			LA152	PCE92418			DURING CRUISE, RT ENGINE CHIP DETECTOR ILLUMINATED.  OTHER RT ENGINE INDICATIONS WERE MONITORED CLOSELY FOR ANY SIGN OF 	MECHANICAL PROBLEM.  NO OTHER INDICATIONS THAT WOULD SUGGEST MECHANICAL PROBLEMS WERE NOTED AT THAT TIME.  THE CHIP LIGH	T WENT OUT WITHIN A FEW MINUTES AND PILOT CONTINUED TO CLOSELY MONITOR RT ENGINE INDICATIONS.  PRIOR TO START OF DESCENT	 (FROM 15000) FOR DESTINATION AIRPORT (BHM) PILOT NOTED SMALL FLUCTUATION IN RT ENGINE OIL PRESSURE FOLLOWED BY TORQUE F	LUCTUATION (APPROXIMATELY 200 LBS); ITT INDICATION WAS STABLE.  DECLARED AN EMERGENCY, SECURED ENGINE AS PRECAUTIONARY M	EASURE, AND LANDED AT THE NEAREST AIRPORT WITHOUT INCIDENT.  MAINTENANCE WAS DISPATCHED TO INVESTIGATE AND UPON INSPECTI	1	L	7	2 	4T	4	T		A31CE   	E4EA				 
2007101600075	20071016	00075	NM  	2007	10	16	Y5CR200700001    	1	20071005	G	6320	369D2512311	BEVEL GEAR      			DOUG  	MD500 	MD500E      	3027372	NM  										M/R GEARBOX	BROKEN          	B			Y5CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05			687  							PART OF TOOTH ON INPUT BEVEL GEAR BROKEN OFF.						1	G	7	2 	3U			NC	        					 
2007120500058	20071205	00058	NM  	2007	12	5	Y5CR200700002    	1	20071120	G	6510		JOURNAL         			DOUG  	MD500 	MD500E      	3027372	NM  										TAIL ROTOR	BROKEN          	B			Y5CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		3149 								BEARING JOURNAL BROKEN OFF ON OUTPUT PINION.						1	G	7	2 	3U			NC	        					 
2007061400221	20070614	00221	EU  	2007	6	14	YNTA20070001     	1	20070516	G	2750		FLAP SYSTEM     			HAWKER	BAE125	BAE125700B  	7450007	EU  										TE FLAPS	INOPERATIVE     	E				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			SW	05	281B					281				ON APPROACH, THE FLAPS BECAME STUCK AT 15 DEGREES. AFTER TRYING THE FLAPS 25 DEGREE SETTING NOTICED THE FLAPS DID NOT MO	VE FROM THE 15 DEGREE POSITION. RESET THE FLAPS TO THE 15 DEGREE POSITION AND UP TO 0 DEGREE, NO MOVEMENT WAS NOTED. RES	ELECTED THE FLAPS TO 15 DEGREE EXECUTED A GO-AROUND WITH TOWER. REFERRED TO THE CHECK LIST FOR NO FLAP LANDINGS, NOTED T	HAT THERE IS NO LANDING DISTANCE DATA. DECLARED AN EMERGENCY DUE TO ABNORMAL LANDING CONFIGURATION. THE SIC BRIEFED THE 	PASSENGERS ON THE SITUATION.  AFTER LANDING, TAXIED OFF THE RUNWAY INTO A RUN-UP AREA SHUT THE AIRCRAFT DOWN. MET WITH F	IRE DEPARTMENT LOOKED AT THE TIRES AND BRAKES , NOTICED NO SMOKE OR FIRE. AIRPORT OFFICIAL SAID THEY SAW NO SMOKE ON LAN	2	L	7	2 	4F			RT	A3EU    					 
2007020500045	20070205	00045		2007	2	5	ZB0R20070001     	4	20070131	G	3197		WIRE            			CESSNA	172   	172S        	2072439	CE  										INSTRUMENT PANEL	CHAFED          	B			ZB0R	C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			SO	05	6026S					172S10206				PILOT REPORTED SMOKE ODOR AND STANDBY INSTRUMENT LIGHTS FLICKERED ON RUN-UP PRIOR TO TAKEOFF. INVESTIGATION REVEALED WIR	E BUNDLE WHICH CONTAINS THE POWER WIRE FOR THE STANDBY INSTRUMENT LIGHTS WAS CHAFING ON THE LOWER LEFT CORNER OF THE AUD	IO PANEL RACK. MAINT REPLACED A SECTION OF THE AFFECTED WIRE. OPS CK GOOD.				1	H	7	1 	3O			NT	3A12    					 
2007102300168	20071023	00168	EA  	2007	10	23	ZB0R20070002     	2	20071015	G	7322	105220	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					ENGINE	LEAKING         	B			ZB0R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	39	95300		1413 			15285871	L2379515			DURING PROGRESSIVE INSP, FOUND CARBURETOR BOWL LEAKING AT GASKET. BOLTS WOULD NOT TIGHTEN - STRIPED THREADS.  REPLACED C	ARBURETOR TO CORRECT DISCREPANCY.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007102300022	20071023	00022	SO  	2007	10	23	ZB0R20070003     	1	20071015	G	3233	9686002	ACTUATOR        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	LEAKING         	B			ZB0R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	39	15412					347350060				DURING GEAR MAINTENANCE, FOUND NLG ACTUATOR LEAKING. INSPECTION REVEALED WORN SEALS. REPLACED SEALS BUT STILL LEAKED. FU	RTHER INSPECTION WITH BORESCOPE IN BODY OF ACTUATOR REVEALED LONGITUDINAL SCORING ON INSIDE WALL OF ACTUATOR BODY. REPLA	CED ACTUATOR TO CORRECT DISCREPANCY.				1	L	7	2 	3O	3	O		A7SO    	1E10				 
2007102300174	20071023	00174	EA  	2007	10	23	ZB0R20070004     	2	20070915	G	8520	LW18840	CAM             			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	WORN            	B			ZB0R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			EA	39	41331		1216 			28R7435169	L1561051A			ON CLIMB-OUT, PILOT NOTICED LOW POWER. RETURNED TO AIRPORT. MAINTENANCE INSPECTION REVEALED BELOW MINIMUM VALVE TRAVELS 	FOR ALL INTAKE VALVES. REMOVED NR 1 CYLINDER.  FOUND CAM LOBES SEVERELY WORN AND TAPPETS CORRODED AND WORN IN A CONCAVE 	MANNER.  ENGINE REPAIRED BY SERVICE CENTER.  REINSTALLED ON ACFT.  ALL SYSTEMS OPS CK NORMAL.				1	L	7	1 	3O	3	O		2A13    	1E10				 
2007102300177	20071023	00177	EA  	2007	10	23	ZB0R20070005     	2	20071001	G	8530		CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					NR 2	LEAKING         	B			ZB0R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	39	95300					15285871	L2379515			DURING PROGRESSIVE INSP, FOUND NR 2 CYLINDER UPPER TOP THROUGH BOLT LEAKING SEVERELY.  REMOVED ENGINE FOR REPAIR.  REINS	TALLED AFTER REPAIR BY SERVICE CENTER. (CASE WAS FOUND FRETTING AND BEARING WEAR WAS EVIDENT AT BOLT LOCATION).					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2007120400072	20071204	00072	SO  	2007	12	4	ZB0R20070006     	1	20071102	G	5730	62061002	SKIN            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					RT WING	CRACKED         	B			ZB0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	15143	4617 				28R7335027				DURING PROGRESSIVE INSPECTION, DISCOVERED WING WALK ON RT WING SPONGY. INSPECTION REVEALED SUBSTRATE REINFORCEMENT CRACK	ED IN SEVERAL LOCATIONS. REPLACED WING WALK.					1	L	7	1 	3O	3	O		2A13    	1E10				 
2007120400081	20071204	00081	CE  	2007	12	4	ZB0R20070008     	1	20071102	G	2560		DETECTOR        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					CARBON MONOXIDE	INOPERATIVE     	B			ZB0R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	05	60457	85   	85   			172S10212				CARBON MONOXIDE DETECTOR FAILED. SECOND FAILURE WITHIN 6 MONTHS						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008010800375	20080108	00375	SO  	2008	1	8	ZB0R20070009     	1	20071214	G	7603	89307000	ROD END         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					FUEL CONTROL	SEPARATED       	B			ZB0R	E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			EA	39	15412	376  	39   			347350060				IN CRUISE, PILOT ATTEMPTED TO REDUCE POWER FOR MANEUVERS PRACTICE. LT ENGINE WAS UNRESPONSIVE. INSTRUCTOR IDENTIFIED LT 	ENGINE THROTTLE PROBLEM, ENGINE RPM WAS STABLE AT NEAR FULL POWER. RETURNED TO HOME BASE. PILOT FEATHERED AND SHUTDOWN L	T ENGINE ON APPROACH. MAINTENANCE DISCOVERED LT ENGINE THROTTLE CONTROL ROD END AT FUEL CONTROL HAD SEPARATED.				1	L	7	2 	3O	3	O		A7SO    	1E10